Ryan Malloy
4ed92efd69
Cospas-Sarsat specification summaries moved to reference/ for internal use only. Links updated to point to official cospas-sarsat.int site. The extracted images remain in public/ for use in other pages.
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Markdown
---
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title: "T004: Cospas-Sarsat Leosar Space Segment Commissioning Standard C"
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description: "Official Cospas-Sarsat T-series document T004"
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sidebar:
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badge:
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text: "T"
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variant: "note"
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# Extended Cospas-Sarsat metadata
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documentId: "T004"
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series: "T"
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seriesName: "Technical"
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documentType: "specification"
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isLatest: true
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issue: 2
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revision: 5
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documentDate: "March 2022"
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originalTitle: "Cospas-Sarsat Leosar Space Segment"
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---
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> **📋 Document Information**
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>
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> **Series:** T-Series (Technical)
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> **Version:** Issue 2 - Revision 5
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> **Date:** March 2022
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> **Source:** [Cospas-Sarsat Official Documents](https://www.cospas-sarsat.int/en/documents-pro/system-documents)
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---
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# T004 - T004-MAR-25-2022.pdf
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**Pages:** 43
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---
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COSPAS-SARSAT LEOSAR SPACE SEGMENT
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COMMISSIONING STANDARD
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C/S T.004
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Issue 2 – Revision 5
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COSPAS-SARSAT LEOSAR SPACE SEGMENT
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COMMISSIONING STANDARD
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History
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Issue Revision
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Date
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Comments
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Nov 95
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Approved (CSC-15)
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Oct 96
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Approved (CSC-17)
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Oct 99
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Approved (CSC-23)
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Oct 01
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Approved (CSC-27)
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Oct 04
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Approved (CSC-33)
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Nov 07
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Approved (CSC-39)
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Oct 09
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Approved (CSC-43)
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Oct 10
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Approved (CSC-45)
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Oct 12
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Approved (CSC-49)
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Dec 15
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Approved (CSC-55)
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Dec 16
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Approved (CSC-57)
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Mar 22
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Approved (CSC-66)
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TABLE OF CONTENTS
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1.
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INTRODUCTION ............................................................................................................ 1–1
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1.1
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Purpose ................................................................................................................. 1–1
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1.2
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Scope ..................................................................................................................... 1–1
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1.3
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Reference Documents .......................................................................................... 1–2
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1.4
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Common System of Units .................................................................................... 1–2
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1.5
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Common List of Definitions ................................................................................ 1–3
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2.
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ON-ORBIT LEOSAR SPACE SEGMENT TESTING AND COMMISSIONING ... 2–1
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2.1
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Initial On-orbit Tests ........................................................................................... 2–1
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2.2.1
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Cospas Payload ............................................................................................... 2–2
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2.3
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Periodic Tests ....................................................................................................... 2–3
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2.4
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Routine Monitoring of the Space Segment ........................................................ 2–5
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2.5
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De-commissioning Procedure ............................................................................. 2–5
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2.5.1
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Cospas De-commissioning Procedure ............................................................ 2–5
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2.5.2
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Sarsat De-commissioning Procedure .............................................................. 2–5
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LIST OF ANNEXES
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A.
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LIST OF ACRONYMS USED IN C/S T.004 ............................................................... 2.1-1
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B.
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COSPAS-SARSAT LEOSAR SPACE SEGMENT TESTING .................................. 2.2-1
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B.1:
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Total Received Signal Power ........................................................................... 2.2-2
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B.2:
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Spectral Occupancy of the Downlink .............................................................. 2.2-2
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B.3:
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Spurious Output Levels .................................................................................... 2.2-2
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B.4:
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Received Signal Power of Test Signals in the 406.05 MHz Repeater Band . 2.2-3
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B.5:
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Location Accuracy ............................................................................................ 2.2-4
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B.6:
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AGC Dynamic Range ....................................................................................... 2.2-4
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B.7:
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Modulation Index of the Repeater .................................................................. 2.2-5
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B.8:
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Translation and Transmitter Frequencies ..................................................... 2.2-6
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B.9:
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Channel Bandwidth and Amplitude Ripple .................................................. 2.2-6
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B.10: Intermodulation and Harmonic Levels ........................................................... 2.2-7
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B.11: SARR 406 MHz Receive Antenna Patterns ................................................... 2.2-8
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B.12: SARP 406 MHz Receive Antenna Pattern ...................................................... 2.2-9
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B.13: SARP Calibration and Characteristics .......................................................... 2.2-10
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B.14: SARP Processing and Localization Performance ........................................ 2.2-12
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B.15: SARP Performance with Variable Emission Power .................................... 2.2-14
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C.
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LIST
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OF
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LEOSAR
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SPACE
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SEGMENT
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ASSESSMENT
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INDICATORS
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/
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COMPLIANCE LEVELS ....................................................................................................... 2.3-1
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D.
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SARSAT LEOSAR ASSESSMENT REPORT (SARR) ............................................. 2.4-1
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E.
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SARSAT LEOSAR ASSESSMENT REPORT (SARP_3) ......................................... 2.5-1
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F.
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SARSAT LEOSAR ASSESSMENT REPORT (ANTENNAS) .................................. 2.6-1
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G.
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LEOSAR COMMISSIONING REPORT .................................................................... 2.7-1
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H.
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COSPAS LEOSAR COMMISSIONING REPORT ................................................... 2.8-1
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LIST OF FIGURES
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Figure 1.1:
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Cospas-Sarsat LEOSAR Space Segment ............................................... 1–2
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Figure 2.1:
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Sarsat LEOSAR Payload Commissioning Procedure .......................... 2–4
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Figure 2.2: Sarsat LEOSAR Payload De-commissioning Procedure ............................. 2–7
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LIST OF TABLES
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Table C.1: Sarsat LEOSAR Space Segment Assessment Indicators/Compliance Levels
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2.3-1
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Table C.2: Cospas LEOSAR Space Segment Assessment Indicators / Compliance Levels
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2.3-3
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Table D.1: SARSAT LEOSAR Assessment Report (SARR-1) ..................................... 2.4-1
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Table D.2: SARSAT LEOSAR Assessment Report (SARR-2) ..................................... 2.4-2
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1–1
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1.
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INTRODUCTION
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1.1
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Purpose
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This document defines the recommended tests, technical measurement standards and
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procedures required for implementing on-orbit testing and commissioning of the Cospas-
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Sarsat LEOSAR Space Segment. On-orbit testing is a component of system assessment as
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defined in C/S G.006. Use of these measurement standards for testing the Cospas-Sarsat
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Space Segment will provide a standardized approach for determining the quality of space
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segment performance. Prior to launch, the Space Segment Provider will test the spacecraft to
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ensure that interoperability parameters and specifications contained in C/S T.003 are met.
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Commissioning is a formal declaration by the responsible Space Segment Provider that a
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payload is operational with or without limitations. De-commissioning is a formal declaration
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by the responsible Space Segment Provider that a payload is no longer operational.
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An additional objective of this document is to ensure that measurements of Cospas-Sarsat
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LEOSAR Space Segment parameters are in accordance with a common set of test methods
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and definitions, so that the results may be understood and compared.
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1.2
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Scope
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Three phases of on-orbit testing of the LEOSAR Space Segment are addressed: initial on-
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orbit test, periodic test, and routine monitoring. The basic responsibilities, specific tests to be
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performed, and test methodologies are defined.
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Initial on-orbit tests are performed in order to establish that the payloads can be placed in
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service to support SAR operations. The tests focus on establishing that the payload will
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properly interface and be interoperable with the ground segments as shown in Figure 1.1.
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The initial on-orbit tests also confirm that values for assessment indicators are within
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accepted thresholds and the payload can be formally commissioned. The data from the
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payload can then be exchanged operationally as described in the Data Distribution Plan,
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C/S A.001.
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Periodic tests to be performed semi-annually are defined. These tests provide measurement
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data used to confirm continued on-orbit performance of the LEOSAR payload.
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Routine monitoring of the on-orbit payloads is conducted by the spacecraft provider.
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Significant changes (loss of channel, etc.) can also be detected by LEOLUT / MCC operators.
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1–2
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COSPAS-SARSAT
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SPACECRAFT
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Out-of-limits and other abnormal conditions are reported to the Space Segment Provider for
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further tests and corrective action as required. If deemed necessary the Space Segment
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Provider may have limitations placed on the payload or it may be de-commissioned.
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The test descriptions provide sufficient detail to define the measurement method, but are not
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intended to be specific test procedures. It is the responsibility of the National Administrations
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to develop test procedures for specific tests which are traceable to the methods described in
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this document.
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* Only for Sarsat spacecraft equipped with SARR-1 Instrument
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Figure 1.1:
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Cospas-Sarsat LEOSAR Space Segment
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1.3
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Reference Documents
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• Cospas-Sarsat Glossary, C/S S.011
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• Cospas-Sarsat System Assessment, C/S G.006
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• Cospas-Sarsat Data Distribution Plan, C/S A.001
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• Cospas-Sarsat System Monitoring and Reporting, C/S A.003
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• Specification for Cospas-Sarsat 406 MHz Distress Beacons, C/S T.001
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• Description of the Payloads Used in the Cospas-Sarsat LEOSAR System, C/S T.003
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• Cospas-Sarsat LEOLUT Performance Specification and Design Guidelines, C/S T.002
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1.4
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Common System of Units
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The units of measurement for interoperability parameters and exchanged test results will be
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the System International (SI).
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LUTs
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406 MHz
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*
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1544.5
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MHz
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SARR
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RADIO
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BEACONS
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SARP
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1–3
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1.5
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Common List of Definitions
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Interpretation of technical terms in exchanged documentation will be in accordance with the
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latest edition of the "IEEE Standard Dictionary of Electrical and Electronic Terms".
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- END OF SECTION 1 -
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2–1
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2.
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ON-ORBIT LEOSAR SPACE SEGMENT TESTING AND COMMISSIONING
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2.1
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Initial On-orbit Tests
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Following the launch of each new satellite, initial on-orbit tests are conducted. These tests
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are conducted by the spacecraft provider to confirm that the LEOSAR payload meets the
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interoperability requirements and is functioning within the requirements range as specified in
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C/S T.003.
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The data from the initial on-orbit tests will be used to establish baseline values of system
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parameters, and to ensure Assessment Indicators are within previously established limits or to
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establish new limit values.
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The initial on-orbit tests of elements of the Cospas-Sarsat LEOSAR Space Segment are
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traditionally performed by the appropriate Space Segment Providers. Each Space Segment
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Provider determines the extent and level of on-orbit tests performed on the elements it
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provides to the LEOSAR Cospas-Sarsat Space Segment.
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When the initial on-orbit tests on the Cospas or Sarsat LEOSAR satellite are successfully
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completed, the appropriate Space Segment Provider completes the assessment report or the
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commissioning report and declares the payload operational. The satellite provider then
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supplies ephemeris data to all Ground Segment Operators.
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The initial on-orbit tests to be conducted and the associated test methods are listed in
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Annex B. It is the responsibility of each Space Segment Provider to develop test procedures
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for the satellite assembly and/or unit provided by that party. Such tests shall be traceable to
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the methods described in this document. In addition, other states may perform LEOSAR
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Space Segment tests. However, these tests shall conform to the methods described herein and
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the test procedures shall be provided to the party responsible for the space assembly or unit
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that will be tested. Furthermore, all participants conducting tests shall provide appropriate
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coordination and ensure that there is no negative impact on Cospas-Sarsat operations. The
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Space Segment Provider shall still be responsible for forwarding the assessment or the
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commissioning reports.
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The initial on-orbit tests shall provide a set of baseline values for various parameters, at the
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time the satellite begins operations. The baseline values can be compared with pre-launch
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data to determine if in-orbit operation is nominal and with results from subsequent on-orbit
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tests to monitor on-going performance trends.
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The Space Segment Providers should conduct on-orbit tests and submit to the Secretariat the
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results of the tests along with a description of the tests sufficient to allow interpretation of the
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data. These post-launch test reports that are submitted will then be distributed in accordance
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with section 2.6 of this document.
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2–2
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2.2
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Commissioning Procedure
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Commissioning is a formal declaration by the responsible Space Segment Provider that the
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LEOSAR payload meets its assessment indicators and is declared operational as part of the
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Cospas-Sarsat System. Commissioning may be declared with limitations placed on the
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operational use if some assessment indicators are not met and limited operation is still
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deemed essential. Commissioning procedures for the Cospas and Sarsat LEOSAR payloads
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are described below.
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In recognition of the fact that commissioning tests may be time consuming, and that valid
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operational data will normally be available from a satellite payload that is under test, a
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payload may be declared to be in an initial operational capability (IOC) state before the
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commissioning test report is completed. This may be done at the option of the spacecraft
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provider if there is sufficient confidence that use of its data by the Ground Segment will not
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cause unnecessary expenditure of SAR resources.
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Once declared, IOC status shall remain in effect until commissioning is completed, which
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shall normally be no more than 90 days after IOC status was declared.
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Payload status will be declared by the responsible Space Segment Provider with an
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appropriate system status message. Distribution of satellite ephemeris and TCAL data, which
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may precede declaration of IOC status, shall not itself be understood as a declaration of IOC
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status.
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2.2.1
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Cospas Payload
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Commissioning of the COSPAS LEOSAR payload requires collection and analysis of
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post-launch test data to verify compliance or non-compliance with the expected values
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of the assessment indicators after basic health and safety of the payload is confirmed.
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Commissioning procedure includes 406 MHz Receivers, Transmitters and antenna
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subsystems testing.
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Upon completion of all tests, Russia will evaluate assessment indicators and prepare,
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within 2.5 months of spacecraft launch, the commissioning report.
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The report shall recommend that the payload be declared at full operational status,
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limited operational status or non-operational.
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Once the COSPAS payload is declared operational, Russia will inform all Cospas-
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Sarsat Ground Segment Providers and begin transmission of ephemeris data.
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2–3
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2.2.2
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Sarsat Payload
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Commissioning of the Sarsat payload is the signed agreement of all Sarsat Space
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Segment Providers that the Sarsat payload meets its assessment indicators and is
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declared operational as part of the Cospas-Sarsat System. Commissioning requires the
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collection and analysis of post-launch test data to verify compliance or non-compliance
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with the expected values of the assessment indicators after basic health and safety of
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the payload is confirmed. The flow of the Sarsat LEOSAR payload commissioning
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procedure is shown in Figure 2.1. This includes payload testing by the responsible
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LEOSAR Space Segment Providers and submittal of assessment reports, as shown at
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Annex F, to the USA, which prepares the commissioning report.
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The purpose of generating an assessment report is to declare the Sarsat payload
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operational as soon as practical. The assessment report determines whether the Sarsat
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payload can operate nominally and provide useful data. Canada, France and the USA
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will respectively evaluate the SARR, SARP and the associated antennas according to
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the responsibilities outlined in Annex B. Upon completion of the initial on-orbit tests
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each Sarsat Space Segment Provider will prepare an assessment report and forward it to
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the USA. The assessment reports will be prepared within 2.5 months of spacecraft
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launch. The assessment reports should note any anomalies or limitations on the
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performance or operation of the Sarsat payload.
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The USA will evaluate the assessment reports for the SARR, SARP and the SAR
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antenna subsystems and prepare a commissioning report as shown at Annex G. This
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report will summarize the status of the assessment indicators and show whether they are
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within acceptable levels. The report shall then recommend that the payload be declared
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at full operational status, limited operational status or non-operational.
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When the Sarsat payload is declared commissioned or at IOC status, the USA, through
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the USMCC, will inform all Cospas-Sarsat Ground Segment Operators and transmit
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ephemeris data. At this time France through the FMCC will transmit time calibration
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data to all MCCs. Telemetry data will also be provided by the USMCC to the CMCC
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and FMCC.
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2.3
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Periodic Tests
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Periodic technical tests are performed semi-annually on each LEOSAR satellite to confirm
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that Assessment Indicator measurements remain within the accepted limits. The data will
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also be used to provide trend data for forecasting satellite operations and projecting the
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remaining lifetime of the search and rescue payloads.
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The periodic tests are a subset of the post-launch tests as listed in Annex B.
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2–4
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Figure 2.1:
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Sarsat LEOSAR Payload Commissioning Procedure
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USA
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Launch
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USA
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USA
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Canada
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SARR In-Orbit
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Verification
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Canada
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Assessment
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Report
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Antenna In-Orbit
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Verification
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Assessment
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Report
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France
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Assessment
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Report
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France
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SARP
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In-Orbit
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Verification
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USA
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Prepare
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Commissioning
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Report
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US
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Declare Sarsat
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Commissioned
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with Channels in
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Full / Limited
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Operations or
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Non-operational
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USA / USMCC
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Notify all
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MCCs
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Cospas-Sarsat
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Secretariat
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Copy of
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Commissioning
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Report
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2–5
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2.4
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Routine Monitoring of the Space Segment
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|
||
The general health of the spacecraft is routinely monitored by the spacecraft Provider, using
|
||
telemetry data. Payload providers shall notify all Ground Segment Operators when their
|
||
payload performance has degraded to the extent that there is an impact on SAR service.
|
||
|
||
Significant changes in the basic parameters of the search and rescue payload, listed in
|
||
Annex C as assessment indicators (e.g. transmitter downlink power and frequency, loss of
|
||
channel, etc.) can be detected during routine system monitoring performed by
|
||
LEOLUTs/MCCs as described in document C/S A.003. If degradation is detected, the
|
||
LEOLUT/MCC operator shall report this information to the associated payload provider.
|
||
The payload provider shall conduct tests sufficient to take corrective action or characterize
|
||
the performance degradation and provide notification to Ground Segment Operators as
|
||
described in section 2.6. The payload then can be declared operational with limitations or
|
||
de-commissioned and the appropriate status forwarded to all Ground Segment Operators and
|
||
the Cospas-Sarsat Secretariat.
|
||
|
||
|
||
2.5
|
||
De-commissioning Procedure
|
||
|
||
De-commissioning is a formal declaration by the responsible Space Segment Provider that a
|
||
LEOSAR payload is no longer operational and is no longer part of the Cospas-Sarsat System.
|
||
A de-commissioned payload can later be re-commissioned with or without limitations, if this
|
||
is deemed essential. The decision to de-commission payloads will be based on the
|
||
operational value of the SAR data versus the impact of continued operation of the payload.
|
||
|
||
2.5.1
|
||
Cospas De-commissioning Procedure
|
||
|
||
|
||
Russia will initiate an investigation as a result of unacceptable values for assessment
|
||
indicators derived from COSPAS LEOSAR payload periodic tests, spacecraft
|
||
operational anomalies or MCC anomaly reporting. If the results of the investigation
|
||
substantiate de-commissioning, Russia will prepare a de-commissioning report.
|
||
|
||
2.5.2
|
||
Sarsat De-commissioning Procedure
|
||
|
||
|
||
As shown in Figure 2.2, the USA will initiate an investigation in conjunction with
|
||
Canada and France as a result of unacceptable values for assessment indicators derived
|
||
from Sarsat LEOSAR payload periodic tests, spacecraft operational anomalies or MCC
|
||
anomaly reporting. If the results of the investigation substantiate de-commissioning,
|
||
the USA will prepare a de-commissioning report which includes rationales, test reports
|
||
and analyses to support de-commissioning.
|
||
|
||
|
||
|
||
|
||
2–6
|
||
|
||
|
||
2.6
|
||
Space Segment Status Reporting Procedures
|
||
|
||
The post-launch commissioning report on each new satellite that is prepared by the
|
||
responsible Space Segment Provider shall be distributed to all Space Segment Providers.
|
||
A copy of the test report shall also be sent to the Secretariat. Ground Segment operators may
|
||
obtain copies by request from the Secretariat.
|
||
|
||
The Cospas-Sarsat Secretariat shall update the status of the LEOSAR Space Segment on the
|
||
Cospas-Sarsat website.
|
||
|
||
The periodic test reports shall be distributed to the Cospas-Sarsat Space Segment Providers
|
||
and the Secretariat. Copies may also be obtained from the Secretariat on request.
|
||
|
||
Any LEOLUT / MCC which detects anomalies of the Space Segment during routine system
|
||
monitoring, shall in form the relevant Space Segment Provider so that special tests can be
|
||
conducted and appropriate notification can be provided. Analysis of Space Segment
|
||
anomalies shall be coordinated among the relevant Space Segment Providers and possible
|
||
corrective action (e.g., switch to backup payload) shall be taken, as appropriate.
|
||
|
||
The relevant Space Segment Provider shall provide information on any anomalies which
|
||
could significantly degrade system performance, to all Ground Segment Providers via the
|
||
MCC network, in accordance with procedures defined in document C/S A.001. If an
|
||
anomaly is confirmed by the relevant Space Segment Provider, then the relevant Space
|
||
Segment Provider shall notify the Secretariat who shall then update the status of the
|
||
LEOSAR Space Segment on the Cospas-Sarsat website.
|
||
|
||
|
||
|
||
2–7
|
||
|
||
|
||
Figure 2.2: Sarsat LEOSAR Payload De-commissioning Procedure
|
||
|
||
|
||
|
||
- END OF SECTION 2
|
||
USA
|
||
Decision to
|
||
Investigate
|
||
USA
|
||
USA
|
||
Canada
|
||
SARR
|
||
Investigation
|
||
Canada
|
||
Results and
|
||
Recommendations
|
||
Antenna
|
||
Investigation
|
||
France
|
||
France
|
||
SARP
|
||
Investigation
|
||
USA
|
||
System Assessment
|
||
and Final
|
||
Recommendation
|
||
US
|
||
Declare Sarsat
|
||
Payload
|
||
De-commissioned
|
||
or Limited
|
||
Operational
|
||
USA / USMCC
|
||
Notify all
|
||
MCCs
|
||
Results and
|
||
Recommendations
|
||
Results and
|
||
Recommendations
|
||
PROBLEM
|
||
MCC, Payload Periodic Tests,
|
||
C/S System Monitoring
|
||
Cospas-Sarsat
|
||
Secretariat
|
||
Copy of
|
||
De-commissioning
|
||
Report
|
||
|
||
|
||
|
||
|
||
ANNEXES TO DOCUMENT
|
||
C/S T.004
|
||
|
||
COSPAS-SARSAT LEOSAR SPACE SEGMENT
|
||
COMMISSIONING STANDARD
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
2.1-1
|
||
|
||
|
||
ANNEX A
|
||
|
||
|
||
2.1
|
||
LIST OF ACRONYMS USED IN C/S T.004
|
||
|
||
AGC .................. automatic gain control
|
||
AOS ................... acquisition of signal
|
||
|
||
BCH .................. Bose-Chaudhuri-Hocquenghem code
|
||
BW .................... bandwidth
|
||
|
||
C/No ................... carrier-to-noise density ratio
|
||
|
||
DA0 .................... date and time at which the Sarsat SARP time counter resets to zero
|
||
dBHz ................. decibel above one Hertz
|
||
dBm ................... decibel above one milliwatt
|
||
dBW……………decibel above one Watt
|
||
|
||
DRU .................. data recovery unit
|
||
|
||
EIRP .................. equivalent isotropically radiated power
|
||
|
||
FCal .................... frequency calibration (Sarsat SARP)
|
||
|
||
G/T .................... gain-to-temperature ratio
|
||
|
||
IF ........................ intermediate frequency
|
||
|
||
kHz .................... kilohertz
|
||
|
||
LEOLUT ........... local user terminal in the LEOSAR system
|
||
LEOSAR ........... low-altitude Earth orbit satellite system for search and rescue
|
||
LOS .................... loss of signal
|
||
|
||
MHz .................. megahertz
|
||
ms ...................... milliseconds
|
||
mW .................... milliwatt
|
||
|
||
RHCP ................ right hand circular polarization
|
||
|
||
SARP ................. search and rescue processor
|
||
SARR ................ search and rescue repeater
|
||
S/No ................... signal-to-noise density ratio
|
||
|
||
TCal ................... time calibration (Sarsat SARP)
|
||
|
||
USO ................... ultra-stable oscillator
|
||
|
||
|
||
|
||
|
||
2.1-2
|
||
|
||
|
||
VCO .................. voltage controlled oscillator
|
||
- END OF ANNEX A-
|
||
|
||
|
||
|
||
2.2-1
|
||
|
||
|
||
ANNEX B
|
||
|
||
|
||
2.2
|
||
COSPAS-SARSAT LEOSAR SPACE SEGMENT TESTING
|
||
|
||
The following tests are performed on each satellite soon after launch.
|
||
Selected tests as indicated are repeated as periodic tests.
|
||
|
||
|
||
Parameter Tested
|
||
Unit
|
||
Requiring
|
||
Test
|
||
See
|
||
Notes
|
||
B.1
|
||
Total Received Signal Power
|
||
SARR and
|
||
Antenna
|
||
1,2,3
|
||
B.2
|
||
Spectral Occupancy of the Downlink
|
||
SARR
|
||
1,2,3
|
||
B.3
|
||
Spurious Output Levels
|
||
SARR
|
||
2,3,5
|
||
B.4
|
||
Received Signal Power of Test Signals in the 406.05 MHz Repeater Band
|
||
SARR
|
||
2,3,5
|
||
B.5
|
||
Location Accuracy of 406 MHz Test Beacons
|
||
SARR
|
||
1,2,5
|
||
B.6
|
||
AGC Dynamic Range
|
||
SARR
|
||
2,3,5,6
|
||
B.7
|
||
Modulation Index of the Repeater
|
||
SARR
|
||
1,2,3,5
|
||
B.8
|
||
Translation and Transmitter Frequencies
|
||
SARR
|
||
2,3,5
|
||
B.9
|
||
Channel Bandwidth and Amplitude Ripple
|
||
SARR
|
||
2,3
|
||
B.10 Intermodulation and Harmonic Levels
|
||
SARR
|
||
2,3,5
|
||
B.11 SARR Receive Antenna Pattern
|
||
Antenna
|
||
2,3,5
|
||
B.12 SARP Receive Antenna Pattern
|
||
Antenna
|
||
3,4
|
||
B.13 SARP Calibration and Characteristics
|
||
SARP
|
||
1,2,3
|
||
B.14 SARP Processing and Localization Performance
|
||
SARP
|
||
1,2,3
|
||
B.15 SARP Performance with Variable Emission Power
|
||
SARP
|
||
1,2,3
|
||
|
||
Note 1:
|
||
This test is also performed as a periodic test.
|
||
Note 2:
|
||
The responsible parties for testing the Sarsat Spacecraft are Canada for the
|
||
SARR, France for the SARP and the USA for the antennas.
|
||
Note 3:
|
||
Commissioning tests.
|
||
Note 4:
|
||
COSPAS only.
|
||
Note 5:
|
||
Does not apply in full to Sarsat satellites equipped with SARR-2.
|
||
Note 6:
|
||
Does not apply to Cospas satellites.
|
||
|
||
|
||
|
||
|
||
2.2-2
|
||
|
||
|
||
B.1: Total Received Signal Power
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the satellite L-band downlink EIRP contour and
|
||
compute the total power emitted by the satellite transponder at 1544.5 MHz as a function of
|
||
the nadir angle, to compare the results with the level specified in the Description of the
|
||
Cospas-Sarsat LEOSAR Space Segment, C/S T.003 and to identify any degradation of
|
||
satellite performance.
|
||
|
||
Procedure
|
||
|
||
The received carrier power is a measured parameter. This is measured using the calibrated
|
||
AGC voltage of the receiver. This voltage is read by digital voltmeter and stored for
|
||
subsequent analysis. After a particular satellite pass is completed, a graph of satellite EIRP
|
||
versus nadir angle is obtained for comparison with the specified levels. An alternate
|
||
procedure is to use a calibrated spectrum analyser to measure the down link signal’s carrier
|
||
power levels. The EIRP is then calculated from these measurements, and an EIRP versus
|
||
nadir angle graph is produced.
|
||
|
||
|
||
B.2: Spectral Occupancy of the Downlink
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the spectral occupancy of the downlink in order to
|
||
identify the presence of out-of-band spurious signals or any other anomalous spectral
|
||
characteristics.
|
||
|
||
Procedure
|
||
|
||
The downlink spectra of the 1 MHz band centred on the carrier are measured several times
|
||
during a satellite pass and stored for subsequent analysis. The average of these spectra is
|
||
calculated and plotted and used to identify the signals received directly from ground based
|
||
interferers. By studying the frequencies relative to the carrier it is possible to distinguish
|
||
between spacecraft based interferers and signals originating from the ground in the 406 MHz
|
||
band and which are being retransmitted by the spacecraft transponder. The procedure is
|
||
repeated for the 5 MHz band centred on the carrier.
|
||
|
||
|
||
B.3: Spurious Output Levels
|
||
|
||
Objective
|
||
|
||
This test has two objectives:
|
||
|
||
a)
|
||
To check for any out-of-band signals from the satellite which are within the range of
|
||
frequency covered by the LEOLUT antenna feed and receiver subsystem.
|
||
|
||
|
||
|
||
|
||
2.2-3
|
||
|
||
|
||
b)
|
||
To check for any spurious signals within the repeater bandwidth. This objective does
|
||
not apply to SARR-2.
|
||
|
||
Procedure
|
||
|
||
A spectrum analyzer is used to check repeatedly for out-of-band spurious signals in an
|
||
8 MHz band centred on the downlink carrier during a satellite pass. A comparison between
|
||
spectra received from the spacecraft with reference spectra for the ground receiving system is
|
||
used to discriminate between potential spacecraft generated spurious signals and locally
|
||
generated signals. The receiving system reference spectrum must be taken with the ground
|
||
station antenna not pointing at a spacecraft.
|
||
|
||
Spurious signals within the repeater bandwidth can be detected in the LEOLUT Doppler
|
||
frequency/time "dot" plot and the frequency established. Any spurious signal originating in
|
||
the spacecraft will not have an associated Doppler frequency and will therefore be seen as a
|
||
straight line in the dot plot. The frequency can be scaled from the dot plot. Once the
|
||
spurious signal has been identified, more accurate frequency measurements may be obtained
|
||
by using a spectrum analyzer to monitor the channel baseband and make frequency
|
||
measurements
|
||
|
||
The levels of spurious signals referred to the SARR receiver input (except for SARR-2) can
|
||
be determined by making the measurements with the SARR channel tested in the fixed gain
|
||
mode. In fixed gain mode, the SARR is a linear repeater with a preset gain, Gr, and receiver
|
||
output level of -8.5 dBm for nominal modulation index. The ground receiver/demodulator is
|
||
calibrated to read Snom when receiving a signal modulated at the nominal modulation index.
|
||
The SARR receiver channel output is then given by:
|
||
|
||
|
||
|
||
|
||
Po = -8.5 dBm + (Sm - Snom)
|
||
and
|
||
|
||
|
||
|
||
Pi = Po - Gr = -8.5 dBm - Gr + (Sm - Snom)
|
||
where:
|
||
|
||
Po = SARR channel output power
|
||
|
||
Pi = SARR channel input power
|
||
|
||
Gr = SARR channel receiver gain (available from prelaunch data)
|
||
|
||
Snom = Ground receiver/demodulator output for nominal SARR channel mod index
|
||
|
||
Sm = measured value of spurious signal at ground receiver/demodulator output.
|
||
|
||
|
||
B.4: Received Signal Power of Test Signals in the 406.05 MHz Repeater Band
|
||
|
||
Objective
|
||
|
||
The objective of this test is to check the end-to-end performance of the 406.05 MHz repeater
|
||
link. This objective does not apply for SARR-2.
|
||
|
||
Procedure
|
||
|
||
The test consists of measuring the signal-to-noise density ratio (S/No) of the test signal in the
|
||
demodulated baseband and of measuring the carrier-to-beacon ratio in the predetected IF.
|
||
|
||
|
||
|
||
2.2-4
|
||
|
||
|
||
a)
|
||
The calibrated uplink facility is used to provide an unmodulated test signal to the input
|
||
of the onboard 406.05 MHz repeater at a nominal level of -120 dBm, correcting for
|
||
range and the variation of antenna gain with angle-off-nadir. The signal frequency is
|
||
compensated for the uplink Doppler frequency shift and is located 7 kHz above the
|
||
band centre. A spectrum analyzer is used to measure the signal strength (S) in the
|
||
baseband and the noise level (N) is obtained from the trace by inspection. Thus:
|
||
|
||
|
||
|
||
|
||
Noise Density, No
|
||
= N - l0 log (Resolution BW)
|
||
|
||
|
||
|
||
|
||
|
||
|
||
= N - l0 log(l00)
|
||
|
||
|
||
|
||
|
||
|
||
|
||
= N - 20 dBHz
|
||
|
||
|
||
|
||
|
||
|
||
|
||
S/No
|
||
= S - No
|
||
|
||
|
||
|
||
|
||
|
||
|
||
= S - N +20 dBHz
|
||
|
||
These measurements are taken as frequently as possible during a single pass.
|
||
|
||
b)
|
||
In a separate pass the uplink signal is set up as previously but this time the predetected
|
||
IF is used and the signal levels of the carrier and the beacon are measured using the
|
||
spectrum analyzer to obtain the carrier-to-beacon ratio. This is carried out as many
|
||
times as possible during the pass.
|
||
|
||
|
||
B.5:
|
||
Location Accuracy of Test Beacons
|
||
|
||
Objective
|
||
|
||
The objective of this test is to determine the accuracy of the location data produced by the
|
||
tracking computer from test signals and to compare it with the previous system performance
|
||
and with the specifications. This test does not apply to SARR-2.
|
||
|
||
Procedure
|
||
|
||
A 406 MHz ELT or beacon simulator is used to produce the test signal for the 406 MHz
|
||
band. The location estimates are produced by the tracking computer. All test signals are
|
||
transmitted from a predetermined position.
|
||
|
||
Only passes with durations over ten minutes are used. Shorter passes are not used in practice
|
||
and so would be unrepresentative. All such testing must be coordinated with the MCC so that
|
||
the signals will not be treated as genuine alarms and to avoid interference with any ongoing
|
||
search operation. The tests can be run unattended subject to MCC approval.
|
||
|
||
|
||
B.6: AGC Dynamic Range
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the AGC dynamic range curve of the SARR
|
||
406.05 MHz receivers. This test does not apply to SARR-2.
|
||
|
||
Procedure
|
||
|
||
|
||
|
||
2.2-5
|
||
|
||
|
||
In this test, a carrier is transmitted to the SARR 406.06 MHz receiver in the form of a power
|
||
staircase. The uplink is increased in 2 dB steps such that the input power to the receiver is
|
||
varied from -130 to -90 dBm (21 steps). The test time interval for each step is three seconds,
|
||
during which time the downlink baseband signal level at 170 kHz and the respective
|
||
baseband No level (at 3 kHz away from the signal) are measured. The duration of the test for
|
||
the 21 steps is 63 seconds, so that the run can be repeated a number of times during the pass
|
||
under dynamic background noise and interference conditions.
|
||
|
||
The test ground station receiver is calibrated in terms of phase demodulator baseband output
|
||
level versus the downlink modulation index. Therefore, the test data plots may be either
|
||
relative downlink baseband level or actual downlink modulation index versus the input to the
|
||
SARR receiver.
|
||
|
||
The equivalent noise temperature, Te, of the total discrete and noise-like interference power
|
||
in the receiver may be computed as follows. Note the spacecraft receiver test input where the
|
||
AGC curve is 3 dB below the maximum. At this point, the test uplink power (P1) and total
|
||
other power (P2) in the channel bandwidth are equal (P1/P2 = 0 dB). Therefore, the equivalent
|
||
noise temperature (Te) of the total power in the channel other than the test signal may be
|
||
computed from the following:
|
||
|
||
P1 = P2 = KTeB
|
||
where:
|
||
|
||
K =
|
||
Boltzmann's constant
|
||
|
||
Te = Equivalent noise temperature
|
||
|
||
B =
|
||
Noise bandwidth of the spacecraft receiver being tested
|
||
P2 =
|
||
Total other power in the receiver bandwidth which is equal to the receiver test
|
||
input power at the 3 dB down point of the AGC curve. The other power
|
||
consists of noise-like interference plus discrete interference plus the inherent
|
||
SARR receiving system noise, including 290 K for the earth's temperature.
|
||
It follows that:
|
||
|
||
Te (dB-K)
|
||
=
|
||
P1 / KB
|
||
or
|
||
|
||
Te (dB-K)
|
||
=
|
||
P1 (dBm) - 10 log K - 10 log B
|
||
|
||
|
||
|
||
=
|
||
P1 (dBm) + 198.6 dBm - 10 log B
|
||
|
||
|
||
B.7: Modulation Index of the Repeater
|
||
|
||
Objective
|
||
|
||
The purpose of this test is to measure the modulation index of the 406.05MHz repeater and of
|
||
the 2.4 kbps data channel. For Sarsat SARR-2, only the modulation index of the 2.4 PDS data
|
||
channel is to be measured.
|
||
|
||
|
||
Procedure
|
||
|
||
|
||
|
||
|
||
2.2-6
|
||
|
||
|
||
Under computer control, a signal generator is used to provide an unmodulated test signal to
|
||
the input of the satellite receiver at a level which will saturate the AGC in the spacecraft
|
||
receiver, in the 406 MHz uplink frequency band. (The 406 MHz receive band applies only to
|
||
Sarsat SARR-1 LEOSAR satellites, and not to the SARR-2 satellites.)
|
||
|
||
The uplink test signal frequency is compensated for the Doppler shift and is set 7 kHz above
|
||
the centre frequency of each receiver band. The amplitude is also compensated for free space
|
||
path loss and the effect of nadir angle on the Cospas-Sarsat antenna gain. A spectrum
|
||
analyzer is used to measure the carrier-to-beacon power ratio of each test signal in the 10
|
||
MHz IF signal, except for SARR-2. The data is stored and subsequently used to calculate the
|
||
RMS modulation index. SARR-2 Modulation Index will be calculated using the phase
|
||
demodulator option of the spectrum analyser.
|
||
|
||
|
||
B.8: Translation and Transmitter Frequencies
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the in-orbit SARR translation and transmitter
|
||
frequencies for SARR-1 and the transmitter frequency for SARR-2.
|
||
|
||
Procedure
|
||
|
||
For Sarsat satellites equipped with SARR-1 only a strong uplink carrier at the channel centre
|
||
frequencies is transmitted from the Test ground station to the 406.05 MHz spacecraft repeater
|
||
channel. Frequency measurements of the downlink 1544.5 MHz carrier and the downlink
|
||
baseband are performed every six seconds during the pass. For Sarsat SARR-2, only the
|
||
carrier frequency is to be measured. The frequencies are measured with a spectrum analyzer
|
||
operating in the counter mode with a 1 Hz resolution.
|
||
|
||
The nominal downlink and baseband frequencies are 1544.5 MHz for the downlink carrier,
|
||
and 170 kHz for the 406.05 MHz repeater on SARR-1.
|
||
|
||
All frequencies for the test equipment in this test are derived from the test ground station
|
||
10 MHz ultra-stable frequency standard. This includes the frequency source for the
|
||
synthesizers generating the uplink test signals, the spectrum analyzer, and all
|
||
downconversions in the test ground station receiver. Thus, the spacecraft frequencies are
|
||
being compared with the test ground station ultra-stable standard.
|
||
|
||
It is necessary to subtract the Doppler frequency shift from the frequency measurements at
|
||
the test ground station to obtain a measure of the frequencies referred to the spacecraft. The
|
||
Doppler frequency shift to be subtracted is computed from the spacecraft orbit parameters
|
||
obtained during the test pass. Quality of the current orbit parameters is monitored.
|
||
|
||
|
||
|
||
B.9: Channel Bandwidth and Amplitude Ripple
|
||
|
||
Objective
|
||
|
||
|
||
|
||
|
||
2.2-7
|
||
|
||
|
||
The objective of this test is to measure the bandwidth and the amplitude ripple in the SARR
|
||
406 MHz repeater channel.
|
||
|
||
Procedure
|
||
|
||
This measurement is performed by frequency sweeping the uplink test signal to a spacecraft
|
||
receiver and tracking the downlink baseband frequency while measuring the baseband signal
|
||
amplitude. For Sarsat SARR-2, only the PDS signal is to be measured. The desired
|
||
arrangement can be achieved using a standard spectrum analyzer tracking generator setup.
|
||
|
||
In the case of Sarsat SARR-1, it is desirable to perform the test for both the AGC and fixed
|
||
gain mode configuration.
|
||
|
||
|
||
B.10: Intermodulation and Harmonic Levels
|
||
|
||
Objective
|
||
|
||
The objectives of this test are to detect and measure any intermodulation products produced
|
||
by two large in-band test signals in the 406 MHz SARR channel and to detect and measure
|
||
any harmonic products produced by an uplink test signal in one SARR channel and falling in
|
||
another SARR channel. This test does not apply to SARR-2.
|
||
|
||
Procedure
|
||
|
||
For testing intermodulation products, two strong uplink carriers are simultaneously
|
||
transmitted from the test ground station to the 406 MHz SARR receiver. All tests are
|
||
performed with the receivers in the AGC mode. The in-band uplink frequencies are as
|
||
follows:
|
||
|
||
|
||
fl =
|
||
Nominal channel frequency - 1 kHz
|
||
|
||
f2 =
|
||
Nominal channel frequency + 1 kHz
|
||
|
||
The uplink frequencies are automatically Doppler compensated so that the frequencies at the
|
||
SARR receiver input are constant throughout the test pass. It follows that the downlink signal
|
||
baseband frequencies are constant. This enables the prediction of exactly where the
|
||
intermodulation products would occur in frequency, if present.
|
||
|
||
When intermodulation products are generated, the third order intermods are generally the
|
||
strongest and occur at 2f1-f2 and 2f2-f1. If f1 equals nominal frequency minus 1 kHz and f2
|
||
equals nominal frequency plus 1 kHz, then the third order intermodulation products would be
|
||
at the nominal frequency -3 kHz and at the nominal frequency +3 kHz. Therefore, the
|
||
baseband frequencies to search for detecting any third order intermods are as follows:
|
||
|
||
|
||
|
||
|
||
|
||
|
||
Nominal Channel
|
||
Lower Intermod
|
||
Upper Intermod
|
||
Channel
|
||
|
||
|
||
Frequency (kHz)
|
||
Frequency (kHz)
|
||
Frequency (kHz)
|
||
|
||
406.05 MHz (SARR-1)
|
||
|
||
|
||
2.2-8
|
||
|
||
|
||
The uplink EIRP of each test signal is +28 dBW. This produces the following range of test
|
||
signal strengths at the spacecraft referred to isotropic, where the minimum is at AOS and the
|
||
maximum is at overhead:
|
||
|
||
|
||
|
||
406.05 MHz Channel:
|
||
-126 to -115 dBW
|
||
|
||
In order to avoid intermodulation products from the test ground station test system itself,
|
||
separate transmitters are used for the two uplinks. One transmitter is connected to the
|
||
horizontal elements of the test ground station uplink antenna and the other to the vertical
|
||
elements.
|
||
|
||
To test for the possible generation of harmonic products, one or two Doppler compensated
|
||
uplink carriers are transmitted to the 406 MHz SARR channel. The downlink baseband is
|
||
swept with the spectrum analyzer to detect and measure any harmonic products.
|
||
|
||
|
||
B.11: SARR 406 MHz Receive Antenna Patterns
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the in-orbit antenna pattern of the SARR 406 MHz
|
||
receiver. This test does not apply to SARR-2.
|
||
|
||
Procedure
|
||
|
||
The antenna pattern of the SARR 406 MHz receiver is measured with the receiver in the
|
||
Fixed Gain Mode. In an automated test, the test uplink EIRP and the test uplink frequency are
|
||
updated every three seconds to maintain the input power and frequency at the SARR receiver
|
||
constant throughout the pass. The input power requirement is to establish a sufficient
|
||
downlink S/N ratio for the measurements, and to stay within the linear dynamic range of the
|
||
receiver in the Fixed Gain Mode.
|
||
|
||
During the test interval of 3 seconds, a power and frequency updated RHCP uplink is
|
||
transmitted to the 406 MHz SARR receiver. The downlink baseband output level (SR) at the
|
||
test ground station, and the baseband noise level (No) in a frequency slot away from the
|
||
signal frequency, are measured in each 3 second interval.
|
||
|
||
From the test ground station's EIRP and the known path loss obtained from orbit data, the
|
||
input power to the SARR receiver referred to isotropic (Pio) is computed. Also, the nadir
|
||
angle is known from orbit data. By combining the above data with the measured downlink
|
||
baseband data, the antenna pattern shape is computed throughout the pass as a function of the
|
||
nadir angle.
|
||
|
||
The actual on-orbit antenna gain is computed using the measured data and pre-launch values
|
||
for the SARR receiver gains in the Fixed Gain Mode. The specific gain values are available
|
||
from prelaunch test results.
|
||
|
||
The test ground station receiver gain is set such that the demodulated baseband output is
|
||
+13.0 dBm when the downlink is at nominal modulation index. Therefore, the SARR
|
||
receiver output (PO) to the SARR modulator is equal to
|
||
|
||
|
||
|
||
2.2-9
|
||
|
||
|
||
PO = -8.5 dBm + (SR - 13.0 dBm)
|
||
|
||
where SR is the measured test ground station's baseband output level in dBm. For example,
|
||
when SR equals 13.0 dBm, the SARR receiver is known from the prelaunch setting to be
|
||
producing an output equal to -8.5 dBm.
|
||
|
||
The receiver absolute antenna gain GA is given by:
|
||
|
||
|
||
GA = PO- Gr dB - Pio
|
||
|
||
where Pio is the input to the SARR-1 receive antenna referred to isotropic. The values of Pio
|
||
are set throughout the test pass by adjusting the uplink test signal EIRP as required to
|
||
compensate for variation in the path loss to the spacecraft.
|
||
|
||
The antenna G/T can be measured absolutely in orbit and needs no calibration parameters
|
||
from pre-launch data, which is necessary for the absolute antenna gain. However, the G/T is a
|
||
function of the instantaneous background noise, which affects the T in the denominator. One
|
||
must, therefore, monitor the channel activity during the tests and not use data from passes
|
||
which were corrupted with interference signals that impact the noise temperature
|
||
measurement.
|
||
|
||
The antenna G/T is computed from the measured downlink baseband level (SR) and the
|
||
measured downlink baseband noise level (No dBm per Hz). The data reduction formula is as
|
||
follows:
|
||
|
||
|
||
G/T = SR/No - Pio - 198.6 dBm
|
||
|
||
where for a strong downlink path it can be assumed that the baseband S/No is equal to the
|
||
uplink S/No at the spacecraft receiver input.
|
||
|
||
|
||
B.12: SARP 406 MHz Receive Antenna Pattern
|
||
|
||
Objective
|
||
|
||
The objective of this test is to measure the in-orbit SARP antenna pattern.
|
||
|
||
Procedure
|
||
|
||
The SARP instrument contains a power detector which measures Pi, the received signal level
|
||
at the input to the SARP receiver. The precision of the measurement is ±2.5 dB and must be
|
||
considered in interpretation of results. This may result in being able to determine only the
|
||
pattern shape and not the absolute gain of the antenna. The SARP received signal level, Pi,
|
||
can be obtained by decoding the SARP PDS data and processing in accordance with the
|
||
algorithms in C/S T.003.
|
||
|
||
The general approach for making the antenna pattern measurement is as follows. Test
|
||
transmissions from a 406.025 MHz beacon will be uplinked at a 3 second rate via a
|
||
programmed tracked yagi antenna. Each beacon transmission received by the SARP is
|
||
|
||
|
||
|
||
2.2-10
|
||
|
||
|
||
processed at the ground measurement station and the beacon ID, time, and value of Pi derived
|
||
from the SARP data. A point on the antenna pattern can be computed for each SARP
|
||
message correlated with the uplink transmission. Computation of the antenna gain points are
|
||
given by the following equations.
|
||
|
||
|
||
G(∏n) =
|
||
Pij + Lr - Pioj
|
||
|
||
|
||
where:
|
||
|
||
|
||
Pioj
|
||
=
|
||
EIRPuj - L(j) - Pol
|
||
|
||
|
||
|
||
Input power (dBm at SARP receiver at time j referred to isotropic)
|
||
|
||
Lr
|
||
=
|
||
1.5 dB SARP Receiver line loss.
|
||
Pol
|
||
=
|
||
0.5 dB estimated polarization loss for RHCP uplink to RHCP antenna
|
||
|
||
on spacecraft.
|
||
|
||
L(j)
|
||
=
|
||
Path loss from Test ground station to spacecraft at time j.
|
||
|
||
EIRPuj =
|
||
Pu - Lt + Ga (∏e) Equivalent Isotropically Radiated Power at time j.
|
||
|
||
Lt
|
||
=
|
||
Loss from beacon output to uplink test antenna (dB).
|
||
GA(∏e)=
|
||
Gain of uplink test antenna. GA is a fixed value (on axis gain) for case
|
||
where yagi is used in the program track mode. If a fixed antenna is
|
||
used, GA is described by the antenna pattern.
|
||
|
||
The data output will consist of tables and graphic presentations of SARP antenna gain (dB)
|
||
versus angle off spacecraft nadir in degrees. The data processing software should have the
|
||
capability of merging data from pass to pass to construct a cumulative pattern. Test passes
|
||
should be selected to include minimum angles off nadir of at least 10 degrees.
|
||
|
||
|
||
B.13: SARP Calibration and Characteristics
|
||
|
||
B.13.1: USO Mean Frequency
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the mean frequency of the on-board Ultra-Stable Oscillator,
|
||
and to compare it to the instrument specification (10.000000 MHz +/- 5 Hz for SARP-3 and
|
||
5.203205 MHz +/- 2.5 Hz for SARP-2). This test does not apply to Cospas satellites.
|
||
|
||
|
||
Procedure
|
||
|
||
The USO mean frequency is calculated as the average value of the USO frequency
|
||
measurements provided by the LEOLUT over a 2-month period.
|
||
|
||
B.13.2: USO Frequency Drift/Day
|
||
|
||
Objective
|
||
|
||
|
||
|
||
|
||
2.2-11
|
||
|
||
|
||
The objective is to characterise the drift of the USO frequency on a one-day duration. The
|
||
USO frequency drift/day, calculated with the below procedure, cannot be directly compared
|
||
to the instrument specification (Drift/day less than 1 mHz for SARP-3 and 0.5 mHz for
|
||
SARP-2) due to ground segment contribution, but is expected to be lower than 15 mHz.
|
||
|
||
Procedure
|
||
|
||
The USO frequency drift/day is calculated using the USO frequency measurements provided
|
||
by the LEOLUT over a 2-month period. It is the standard deviation of the observed drifts,
|
||
reduced to a one-day duration.
|
||
|
||
B.13.3: Time Tagging Accuracy
|
||
|
||
Objective
|
||
|
||
The objective is to characterise the time tagging accuracy, and to compare it to the system
|
||
specification (10 ms, as per document C/S T.003).
|
||
Procedure
|
||
|
||
The time tagging accuracy is calculated using the dates of the Toulouse orbitography beacon
|
||
bursts provided by the LEOLUT. It is the standard deviation of the time tagging error
|
||
observed for all the bursts of the Toulouse beacon over a 2- month period.
|
||
|
||
B.13.4: Instrument Sensitivity
|
||
|
||
Objective
|
||
|
||
The objective is to characterise the sensitivity of the instrument, and to compare it to the
|
||
instrument specification (-134 dBm for SARP-3 and -131 dBm for SARP-2).
|
||
|
||
Procedure
|
||
|
||
The sensitivity of the instrument is derived from the histogram of the levels (in dBm)
|
||
received on-board the instrument for all the beacons (operational + test beacons) over a 5-day
|
||
period. The sensitivity is the lower level plotted on the histogram.
|
||
B.13.5: Dynamic Range
|
||
|
||
Objective
|
||
The objective is to characterise the dynamic range of the instrument, and to compare it to the
|
||
instrument specification (29 dB for SARP-3 and 23 dB for SARP-2).
|
||
|
||
Procedure
|
||
|
||
The dynamic range is derived from the histogram of the levels (in dBm) received on-board
|
||
the instrument for all the beacons (operational + test beacons) over a 5-day period. The
|
||
dynamic range is the difference between the higher and the lower levels plotted on the
|
||
histogram.
|
||
|
||
B.13.6: Frequency Bandwidth
|
||
|
||
|
||
|
||
|
||
2.2-12
|
||
|
||
|
||
Objective
|
||
|
||
The objective is to characterise the frequency bandwidth of the instrument, and to compare it
|
||
to the specification (80 kHz [406.010 – 406.090 MHz] for SARP-3 and Cospas satellites, and
|
||
40 kHz [406.010 – 406.050 MHz] (Mode 2) for SARSAT SARP-2).
|
||
|
||
Procedure
|
||
|
||
The frequency bandwidth is derived from the histogram of the frequencies measured for all
|
||
beacons (operational + test beacons) over a 5-day period.
|
||
|
||
|
||
B.14: SARP Processing and Localization Performance
|
||
|
||
B.14.1: Probability to provide a valid solution
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to provide a valid solution, and to compare it
|
||
to the specification (probability better than 95% to provide a valid solution (15 hexa
|
||
identification provided) for a beacon transmitting with a 37 dBm output power (with a whip
|
||
antenna) and for satellites passes with elevation above 5°).
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
over a 5-day period (the Toulouse beacon simulator is used for Sarsat satellites).
|
||
|
||
B.14.2: Access probability or throughput
|
||
|
||
Objective
|
||
The objective is to characterize the access probability or throughput, i.e. the probability to
|
||
retrieve a valid message for each single transmitted message in the same conditions as above.
|
||
The specification is 75 % at 37 dBm and the target is a value higher than 90%.
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
over a 5-day period (the Toulouse beacon simulator is used for Sarsat satellites).
|
||
|
||
B.14.3: Probability to retrieve a complete message
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to retrieve a complete message for each
|
||
transmitted message in the same conditions as above. There are no specifications for this
|
||
parameter.
|
||
|
||
Procedure
|
||
|
||
|
||
|
||
|
||
2.2-13
|
||
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
over a 5-day period (the Toulouse beacon simulator is used for Sarsat satellites).
|
||
|
||
B.14.4: Probability of Doppler processing
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to retrieve at least 4 beacon bursts per pass, in
|
||
the same conditions as above. The specification is 95 % at 37 dBm.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
over a 5-day period (the Toulouse beacon simulator is used for Sarsat satellites).
|
||
|
||
B.14.5: Probability of Doppler location better than 5 km
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to provide a Doppler location with an
|
||
accuracy better than 5 km. The specification is a probability better than 95% to provide a
|
||
Doppler location with an accuracy better than 5 km for a beacon transmitting with a 37 dBm
|
||
output power (with a whip antenna) and for satellites passes with elevation above 5°.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
over a 5-day period (the Toulouse beacon simulator is used for Sarsat satellites).
|
||
|
||
|
||
|
||
|
||
|
||
|
||
B.14.6: Accuracy of Doppler location
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the accuracy of Doppler location, i.e. the average value of the
|
||
error made when processing the location. There is no specification for this parameter.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
(the Toulouse beacon simulator is used for Sarsat satellites), and also for the Toulouse
|
||
orbitography beacon over a 5-day period.
|
||
|
||
B.14.7: Ellipse error mean radius
|
||
|
||
|
||
|
||
|
||
2.2-14
|
||
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the average value of the ellipse error radius parameter
|
||
provided by the LEOLUT. There are no specifications for this parameter. This test does not
|
||
apply to Cospas satellites.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with the Toulouse
|
||
beacon simulator over a 5-day period.
|
||
|
||
|
||
B.15: SARP Performance with Variable Emission Power
|
||
|
||
For assessing these performances, the power will be varied from 20 dBm to 37 dBm with a
|
||
2 dBm or 3 dBm step.
|
||
|
||
B.15.1: Probability to provide a valid solution
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to provide a valid solution (15 hexa
|
||
identification provided) as a function of beacon emission power .
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
B.15.2: Access probability or throughput
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the access probability or throughput, i.e. the probability to
|
||
retrieve a valid message for each single transmitted message, as a function of beacon
|
||
emission power.
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
B.15.3: Probability to retrieve a complete message
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability to retrieve a complete message as a function
|
||
of beacon emission power.
|
||
|
||
|
||
|
||
|
||
2.2-15
|
||
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
B.15.4: Probability of Doppler processing
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the probability of Doppler processing, i.e. the probability to
|
||
retrieve at least 4 beacon bursts per pass, as a function of beacon emission power.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
B.15.5: Accuracy of Doppler processing
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the accuracy of Doppler location, i.e. the average value of the
|
||
error made when processing the location, as a function of beacon emission power.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
B.15.6: Threshold for a 75% access probability
|
||
|
||
Objective
|
||
|
||
The objective is to characterize the threshold for a 75% access probability, i.e. the value of
|
||
beacon power for which the LEOLUT is able to provide a valid message for each beacon
|
||
event 75% of the time. The target is a value about 23 dBm.
|
||
|
||
Procedure
|
||
|
||
The statistical analysis is done through beacon messages transmitted with a beacon simulator
|
||
with variable power over a 3-day period (the Toulouse beacon simulator is used for Sarsat
|
||
satellites).
|
||
|
||
|
||
- END OF ANNEX B -
|
||
|
||
|
||
|
||
|
||
|
||
2.3-1
|
||
|
||
|
||
ANNEX C
|
||
|
||
|
||
2.3
|
||
LIST OF LEOSAR SPACE SEGMENT ASSESSMENT INDICATORS /
|
||
COMPLIANCE LEVELS
|
||
|
||
|
||
Table C.1: Sarsat LEOSAR Space Segment Assessment Indicators/Compliance Levels
|
||
|
||
Assessment Indicator
|
||
Compliance Level
|
||
L-band EIRP
|
||
As per Section 5 of C/S T.003, the EIRP is calculated by
|
||
combining the transmitter output power 8.6 dBW (7.2 W) for
|
||
SARR-1 and 6 dBW (4.0 W) for SARR-2 with the SLA
|
||
Gain Pattern for the corresponding antenna used on the
|
||
specific spacecraft. EIRP values vary over the range of nadir
|
||
angles depicted in document C/S T.003.
|
||
Spectral occupancy (of downlink)
|
||
As per C/S T.003 Figure 3.9 “Typical Sarsat SARR-1
|
||
1544.5 MHz Observed Downlink Signal” and Figure 3.14
|
||
“Typical Sarsat SARR-2 1544.5 MHz Observed Downlink
|
||
Signal”.
|
||
Signal levels (out-of-band)
|
||
As per C/S T.003 Figure 3.10 “Sarsat SARR Transmitter
|
||
Spurious Emission Limits”
|
||
Signal levels (spacecraft generated)
|
||
-145 dBm referred to SARR receiver input
|
||
Signal-to-noise density ratio
|
||
As per C/S T.004 test B.4
|
||
Carrier-to-beacon ratio
|
||
As per C/S T.004 test B.4
|
||
Location accuracy (test signals)
|
||
406 MHz
|
||
5 km
|
||
2.4 kb/s
|
||
5 km
|
||
AGC dynamic range
|
||
As per C/S T.003 Table 3.2 “Sarsat SARR-1 Receiver
|
||
Parameters”.
|
||
|
||
406 MHz
|
||
> 50dB
|
||
Modulation index
|
||
As per C/S T.003 Table 2.4 “Cospas and Sarsat Output
|
||
Parameters”
|
||
|
||
For SARR-1:
|
||
406 MHz
|
||
[.58] ± 10% radians rms
|
||
2.4 kb/s
|
||
[.39] ± 10% radians rms
|
||
overall
|
||
[.70] ± 10% radians rms
|
||
|
||
For SARR-2:
|
||
2.4 kb/s
|
||
0.347 to 0.476 radians rms
|
||
|
||
SARR
|
||
translation
|
||
and
|
||
transmitter
|
||
frequencies
|
||
|
||
As per C/S T.003 Table 3.2 “Sarsat SARR-1 Receiver
|
||
Parameters”, Table 3.3 “Sarsat SARR-1 1544.5 MHz
|
||
Transmitter Parameters” and Table 3.4 Sarsat SARR-2
|
||
1544.5 MHz Transmitter Parameters”.
|
||
|
||
406 MHz
|
||
± 406 Hz
|
||
1544.5 MHz
|
||
± 3.2 kHz
|
||
|
||
|
||
|
||
2.3-2
|
||
|
||
|
||
Assessment Indicator
|
||
Compliance Level
|
||
SARR Channel bandwidth (1 dB)
|
||
As per C/S T.003 Figure 3.8 “Sarsat SARR-1 Baseband
|
||
Frequency Spectrum”, Figure 3.13 “Sarsat SARR-2
|
||
Baseband Frequency Spectrum”, and Table 2.3, “Cospas and
|
||
Sarsat Input Parameters”.
|
||
|
||
406 MHz
|
||
80 kHz
|
||
2.4 kb/s 4.8 kHz
|
||
Amplitude ripple of passbands
|
||
As per C/S T.003 Table 3.3 “Sarsat SARR-1 1544.5 MHz
|
||
Transmitter Parameters” and Table 3.4 “Sarsat SARR-2
|
||
1544.5 MHz Transmitter Parameters”.
|
||
|
||
406 MHz < 2.5 dB
|
||
2.4 kb/s < 2.5 dB
|
||
Intermodulation products (2 test signals)
|
||
As per C/S T.003 Table 3.2 “Sarsat SARR-
|
||
1 Receiver Parameters”.
|
||
|
||
406 MHz
|
||
< 170 dBW
|
||
|
||
Harmonic products in downlink baseband
|
||
(from Doppler compensated uplink carriers)
|
||
As per C/S T.003 Table 3.2 “Sarsat SARR-1 Receiver
|
||
Parameters”.
|
||
|
||
406 MHz
|
||
< 170 dBW
|
||
|
||
As per C/S T.003 Table 3.4 “Sarsat SARR-2 Receiver
|
||
Parameters” [TBD].
|
||
Antenna patterns of SARP receivers
|
||
As per C/S T.003 Figure 5.6 “Sarsat-TIROS SARP
|
||
Receive Antenna (UDA) Gain Pattern”.
|
||
Antenna patterns of SARR receivers
|
||
As per C/S T.003 Figure 5.5 “Sarsat-TIROS 406 MHz
|
||
Receive Antenna (SRA) Gain Pattern”.
|
||
Antenna pattern of SARP/SARR receivers
|
||
(SARSAT-METOP)
|
||
As per C/S T.003 Section 5.3 “SARSAT-MetOp 406 MHz
|
||
SARR and SARP Receive antenna (CRA)”, Figure 5. 9.
|
||
|
||
|
||
|
||
2.3-3
|
||
|
||
|
||
Table C.2: Cospas LEOSAR Space Segment Assessment Indicators / Compliance Levels
|
||
|
||
Assessment Indicator
|
||
Compliance Level
|
||
L-band EIRP
|
||
EIRP values vary from approx 4 dBW to 6 dBW over the
|
||
range of nadir angles depicted in document C/S T.003
|
||
Spectral occupancy (of downlink)
|
||
As per C/S T.003 Figure 3.3 “Typical Cospas 1544.5
|
||
MHz Observed Downlink Signal”
|
||
Signal levels (out-of-band)
|
||
As per C/S T.003 Table 3.1 “Cospas 1544.5 MHz
|
||
Transmitter Parameters”
|
||
Spurious Output Level ≤-60 dBW
|
||
Signal levels (spacecraft generated)
|
||
- 150 dBm referred to Cospas Repeater input
|
||
Location accuracy (test signals)
|
||
2.4 kb/s 5 km
|
||
Modulation index
|
||
As per C/S T.003 Table 2.4 “Cospas and Sarsat Output
|
||
Parameters”
|
||
SARR
|
||
translation
|
||
and
|
||
transmitter
|
||
frequencies
|
||
406 MHz ± 100 Hz
|
||
1544.5 MHz ± 1.5 kHz
|
||
SARR Channel bandwidth (3 dB)
|
||
> 80 and <100 kHz
|
||
Amplitude ripple of 406 MHz passband
|
||
≤ 2.5 dB at minus 1 dB level
|
||
Intermodulation and harmonic products
|
||
≤ 30 dBc
|
||
Antenna pattern of SARP receiver
|
||
As per C/S T.003 Figure 5.2 “Cospas (SARP-2) 406
|
||
MHz Receive Antenna (SPA) Gain Pattern”
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
- END OF ANNEX C -
|
||
|
||
|
||
|
||
2.4-1
|
||
|
||
|
||
ANNEX D
|
||
|
||
|
||
2.4
|
||
SARSAT LEOSAR ASSESSMENT REPORT (SARR)
|
||
|
||
Table D.1: SARSAT LEOSAR Assessment Report (SARR-1)
|
||
SARSAT - _______
|
||
Test
|
||
Result
|
||
Pass / Fail
|
||
Comments
|
||
B.1 Total Received Signal Power
|
||
|
||
|
||
|
||
B.2 Spectral Occupancy of the
|
||
Downlink
|
||
|
||
|
||
|
||
B.3 Spurious Output Levels
|
||
|
||
|
||
|
||
B.4 Received Signal Power of
|
||
Test Signals in the 406 MHz
|
||
Repeater Band
|
||
|
||
|
||
|
||
B.5 Location Accuracy of 406
|
||
MHz Test Beacons
|
||
|
||
|
||
|
||
B. 6 AGC Dynamic Range
|
||
|
||
|
||
|
||
B. 7 Modulation Index of the
|
||
Repeater
|
||
|
||
|
||
|
||
B. 8 Translation and Transmitter
|
||
Frequencies
|
||
|
||
|
||
|
||
B. 9 Channel Bandwidth and
|
||
Amplitude Ripple
|
||
|
||
|
||
|
||
B.10
|
||
Intermodulation
|
||
and
|
||
Harmonic Levels
|
||
|
||
|
||
|
||
|
||
Note: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
|
||
SARR: Operational _______ Not Operational _______
|
||
|
||
Limitations:
|
||
|
||
|
||
|
||
|
||
Remarks:
|
||
|
||
|
||
|
||
2.4-2
|
||
|
||
|
||
Table D.2: SARSAT LEOSAR Assessment Report (SARR-2)
|
||
SARSAT - _______
|
||
|
||
Test
|
||
Result
|
||
Pass / Fail
|
||
Comments
|
||
B.1 Total Received Signal Power
|
||
B.2 Spectral Occupancy of the
|
||
Downlink
|
||
B.3 Spurious Output Levels
|
||
B. 7 Modulation Index of the
|
||
Repeater
|
||
B. 8 Translation and Transmitter
|
||
Frequencies
|
||
B. 9 Channel Bandwidth and
|
||
Amplitude Ripple
|
||
|
||
Note: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
SARR: Operational
|
||
Not Operational
|
||
|
||
|
||
Limitations:
|
||
|
||
|
||
Remarks:
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
- END OF ANNEX D -
|
||
|
||
|
||
|
||
2.5-1
|
||
|
||
|
||
ANNEX E
|
||
|
||
|
||
2.5
|
||
SARSAT LEOSAR Assessment Report (SARP_3)
|
||
|
||
|
||
SARSAT - _______
|
||
Test
|
||
Result
|
||
Pass/Fail
|
||
Comments
|
||
B.13 SARP Calibration
|
||
USO Mean Frequency
|
||
|
||
10 MHz +/-5Hz
|
||
|
||
|
||
B.13 SARP Calibration
|
||
Dating Accuracy
|
||
|
||
≤ 10 ms
|
||
|
||
B.13 SARP
|
||
Calibration
|
||
Sensitivity/Dynamic Range
|
||
|
||
-134dBm/29dB
|
||
|
||
B.13 SARP
|
||
Calibration
|
||
Frequency Bandwidth
|
||
|
||
[406.01-406.09MHz]
|
||
|
||
B.14 SARP
|
||
Performance
|
||
Throughput
|
||
|
||
≥ 75%
|
||
Expected value
|
||
≥ 90%
|
||
B.14 SARP Performance
|
||
Prob. of Location ≥ 5 km
|
||
|
||
|
||
≥ 95%
|
||
|
||
|
||
B.15 SARP Variable Power
|
||
Threshold for a 75% Access
|
||
Probability
|
||
|
||
≤ 37 dBm
|
||
Expected
|
||
value
|
||
about 23 dBm
|
||
|
||
Note: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
|
||
SARP: Operational _______ Not Operational _______
|
||
|
||
|
||
Limitations:
|
||
|
||
|
||
|
||
|
||
Remarks:
|
||
|
||
|
||
|
||
|
||
2.5-2
|
||
|
||
|
||
- END OF ANNEX E -
|
||
|
||
|
||
|
||
2.6-1
|
||
|
||
|
||
ANNEX F
|
||
|
||
|
||
2.6
|
||
SARSAT LEOSAR ASSESSMENT REPORT (ANTENNAS)
|
||
|
||
SARSAT - _______
|
||
Test
|
||
Result
|
||
Pass/Fail
|
||
Comments
|
||
B.1 Total Received Signal Power
|
||
|
||
|
||
|
||
B.12 SARP 406 MHz Antenna
|
||
Receive Pattern
|
||
|
||
|
||
|
||
B.11 SARR-1 406 MHz Receive
|
||
Antenna Pattern
|
||
|
||
|
||
|
||
|
||
Note: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
Antennas: Operational _______
|
||
Not Operational _______
|
||
|
||
Limitations:
|
||
|
||
|
||
|
||
|
||
|
||
|
||
Remarks:
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
- END OF ANNEX F -
|
||
|
||
|
||
|
||
2.7-1
|
||
|
||
|
||
ANNEX G
|
||
|
||
|
||
2.7
|
||
LEOSAR COMMISSIONING REPORT
|
||
|
||
Satellite: __________
|
||
|
||
Unit
|
||
|
||
Pass/Fail
|
||
Operational,
|
||
Limited Operation,
|
||
Not Operational
|
||
|
||
Comments
|
||
SRA Antenna(1)
|
||
|
||
|
||
|
||
SPA Antenna(2)
|
||
|
||
|
||
|
||
UDA Antenna(3)
|
||
|
||
|
||
|
||
SLA Antenna
|
||
|
||
|
||
|
||
406 MHz SARR(3)
|
||
|
||
MHz
|
||
Global
|
||
|
||
|
||
|
||
SARP
|
||
Local
|
||
|
||
|
||
|
||
|
||
(1)
|
||
Not applicable to Sarsat SARR-2
|
||
(2)
|
||
Cospas payloads only
|
||
(3)
|
||
Sarsat SARR-1 payloads only
|
||
|
||
Notes: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
|
||
SARR - Search and Rescue Repeater
|
||
|
||
|
||
SARP - Search and Rescue Processor
|
||
|
||
|
||
SRA - SARR Receive Antenna
|
||
|
||
|
||
SPA - SARP Receive Antenna
|
||
|
||
|
||
UDA - UHF data collection system antenna
|
||
|
||
|
||
SLA - SARR L-band transmit antenna
|
||
|
||
Limitations:
|
||
|
||
|
||
|
||
|
||
Remarks:
|
||
- END OF ANNEX G -
|
||
|
||
|
||
|
||
|
||
2.8-1
|
||
|
||
|
||
ANNEX H
|
||
|
||
2.8
|
||
COSPAS LEOSAR COMMISSIONING REPORT
|
||
|
||
Table
|
||
H.1:
|
||
COSPAS
|
||
LEOSAR
|
||
COMMISSIONING
|
||
REPORT
|
||
COSPAS -
|
||
|
||
Test
|
||
Result
|
||
Pass / Fail
|
||
Comments
|
||
B.1 Total Received Signal Power
|
||
B.2 Spectral Occupancy of the Downlink
|
||
B.3 Spurious Output Levels
|
||
B.4 Received Signal Power of Test Signals in the 406
|
||
MHz Repeater Band
|
||
B.5 Location Accuracy of 406 MHz Test Beacons
|
||
B. 7 Modulation Index of the Repeater
|
||
B. 8 Translation and Transmitter Frequencies
|
||
B. 9 Channel Bandwidth and Amplitude Ripple
|
||
B.10 Intermodulation and Harmonic levels
|
||
B.12 SARP 406 MHz Antenna Receive
|
||
Pattern
|
||
B.13 SARP Calibration and Characteristics
|
||
B.14 SARP Processing and Localization Performance
|
||
B.15 SARP Performance with Variable Emission Power
|
||
|
||
Note: Required graphics and/or data should be provided as attachments to this report.
|
||
|
||
SARR: Operational
|
||
Not Operational
|
||
|
||
|
||
Limitations:
|
||
|
||
Remarks:
|
||
|
||
- END OF ANNEX H -
|
||
|
||
- END OF DOCUMENT -
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
|
||
Cospas-Sarsat Secretariat
|
||
1250 René-Lévesque Blvd. West, Suite 4215, Montreal (Quebec) H3B 4W8 Canada
|
||
Telephone: +1 514 500-7999 / Fax: +1 514 500 7996
|
||
Email: mail@cospas-sarsat.int
|
||
Website: www.cospas-sarsat.int |