ITU-R SA 1882-2011 Technical and operational characteristics of space research service (Earth-to-space) systems for use in the 22 55-23 15 GHz band《工作在22 55-23 15GHz频段的太空研究业务(从地球到太.pdf

1、 Recommendation ITU-R SA.1882(02/2011)Technical and operational characteristicsof space research service (Earth-to-space) systems for use in the22.55-23.15 GHz bandSA SeriesSpace applications and meteorologyii Rec. ITU-R SA.1882 Foreword The role of the Radiocommunication Sector is to ensure the rat

2、ional, equitable, efficient and economical use of the radio-frequency spectrum by all radiocommunication services, including satellite services, and carry out studies without limit of frequency range on the basis of which Recommendations are adopted. The regulatory and policy functions of the Radioc

3、ommunication Sector are performed by World and Regional Radiocommunication Conferences and Radiocommunication Assemblies supported by Study Groups. Policy on Intellectual Property Right (IPR) ITU-R policy on IPR is described in the Common Patent Policy for ITU-T/ITU-R/ISO/IEC referenced in Annex 1 o

4、f Resolution ITU-R 1. Forms to be used for the submission of patent statements and licensing declarations by patent holders are available from http:/www.itu.int/ITU-R/go/patents/en where the Guidelines for Implementation of the Common Patent Policy for ITU-T/ITU-R/ISO/IEC and the ITU-R patent inform

5、ation database can also be found. Series of ITU-R Recommendations (Also available online at http:/www.itu.int/publ/R-REC/en) Series Title BO Satellite delivery BR Recording for production, archival and play-out; film for television BS Broadcasting service (sound) BT Broadcasting service (television)

6、 F Fixed service M Mobile, radiodetermination, amateur and related satellite services P Radiowave propagation RA Radio astronomy RS Remote sensing systems S Fixed-satellite service SA Space applications and meteorology SF Frequency sharing and coordination between fixed-satellite and fixed service s

7、ystems SM Spectrum management SNG Satellite news gathering TF Time signals and frequency standards emissions V Vocabulary and related subjects Note: This ITU-R Recommendation was approved in English under the procedure detailed in Resolution ITU-R 1. Electronic Publication Geneva, 2010 ITU 2010 All

8、rights reserved. No part of this publication may be reproduced, by any means whatsoever, without written permission of ITU. Rec. ITU-R SA.1882 1 RECOMMENDATION ITU-R SA.1882 Technical and operational characteristics of space research service (Earth-to-space) systems for use in the 22.55-23.15 GHz ba

9、nd (2011) Scope This Recommendation provides system characteristics to be used in sharing studies for the space research service (Earth-to-space) in the band 22.55-23.15 GHz. The ITU Radiocommunication Assembly, considering a) that there is growing interest in space exploration, particularly around

10、the Moon, from a number of administrations; b) that space research service (Earth-to-space) transmissions will include mission data, command and control links for space exploration for lunar exploration missions; c) that space research service missions utilizing the 22.55-23.15 GHz band may also ope

11、rate in low-Earth orbit and in Sun-Earth Lagrangian (L1/L2) orbits; d) that in order to carry out sharing studies, technical and operational characteristics of space research service systems for use in 22.55-23.15 GHz are needed, recommends 1 that the technical and operational system characteristics

12、 for the space research service (Earth-to-space) in the 22.55-23.15 GHz band detailed in Annex 1 should be used in sharing studies. Annex 1 Technical and operational characteristics of space research service (Earth-to-space) systems for use in the 22.55-23.15 GHz band Characteristics of the SRS eart

13、h station emissions The characteristics of the SRS earth station emissions in the 23 GHz band are summarized in Table 1a). The SRS missions supported by these earth stations will be non-deep-space SRS missions. The SRS earth station characteristics are based on supporting three types of space resear

14、ch missions: low-Earth orbiting (LEO) missions; Lunar missions; and, Sun-Earth Lagrangian (L1/L2) missions. 2 Rec. ITU-R SA.1882 Table 1b) lists the orbital and receiving characteristics of the representative mission satellites. LEO missions Before spacecraft travel to lunar destination for explorat

15、ion, they first must be tested out in Earth orbit, especially in regard to manned exploration. The increase of computing and other technology capacity results in the need for an increased amount of mission data, command and control links to be sent to the spacecraft. Lunar missions Missions at the M

16、oon, or in transit to the Moon, will have similar data requirements to those in low-Earth orbit, but transmission will cover a greater distance, resulting in higher power transmissions and different ground station antenna. L1/L2 missions Missions at Sun-Earth Lagrangian points, are typically unmanne

17、d space observatories. These observatories have longer duration contacts with the ground stations and since they are designed to operate without much interaction from the Earth, do not require as much data to be uplinked, resulting in a lower bandwidth requirement, but a higher gain earth station an

18、tenna. TABLE 1a) Technical and operating characteristics of SRS earth stations to support representative missions Parameter Values Operating frequency (GHz) 23.1 Supported mission LEO Lunar L1/L2 SRS earth station latitude (degrees) 32.5 N 35.34 N 35.41 S 40.43 N 35.4 N SRS earth station longitude (

19、degrees) 106.6 W 116.87 W 148.98 E 4.25 W 116.9 W Transmitting antenna diameter (m) 10 18 34 Antenna gain (dBi) 65.3 70.4 75.9 Off-axis antenna gain envelope RR Appendix 7, Annex 4 Minimum elevation angle for transmission (degrees) 5 Bandwidth (MHz) 24 24 3 Power at the antenna input (dBW) 0.0 11.1

20、0.0 Power spectral density at antenna input (dBW/Hz) 70.8 59.7 61.4 e.i.r.p. (dBW) 65.3 81.5 75.9 e.i.r.p. density (dBW/Hz) 5.5 10.7 14.5 Rec. ITU-R SA.1882 3 TABLE 1b) Mission satellite characteristics Parameter Values Mission type LEO Lunar L1/L2 Orbital altitude (km) 700 384 400 1 500 000 Orbit type Circular Circular Halo Orbital inclination (degrees) 98.2 23.45 0 wrt ecliptic Antenna gain (dBi) 40.3 44.7 44.7 Noise temperature (K) 410 410 410