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GENERIC PICK-UP HORN FOR HIGH POWER THERMAL VACUUM TESTING OF SATELLITE PAYLOADS AT MULTIPLE FREQUENCY BANDS AND AT MULTIPLE POLARIZATIONS
GENERIC PICK-UP HORN FOR HIGH POWER THERMAL VACUUM TESTING OF SATELLITE PAYLOADS AT MULTIPLE FREQUENCY BANDS AND AT MULTIPLE POLARIZATIONS
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机译:在多个频带和多个极化条件下对卫星有效载荷进行大功率热真空测试的通用拾音器
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摘要
A system for testing one or more payload antenna feeds of a spacecraft payload, the system comprising: one or more pick-up horns (100; 200; 310; 320; 330; 401; 507; 802; 900; 1104(1)-1104(5)) for absorbing radiated power of an antenna (402; 506; 604; 1102(1)-1102(5)), each pick-up horn (100; 200; 310; 320; 330; 401; 507; 802; 900; 1104(1)-1104(5)) comprising: at least one outer metal wall (101, 102, 122; 201; 901, 902, 922) forming a metal body (103; 210; 903); at least one interior surface (104, 105; 202; 904) disposed in the metal body (103; 210; 903) and forming two or more chambers (106, 107; 209; 906) in the metal body (103; 210; 903); a front metal surface (110; 203; 311; 321; 331; 910) disposed at a front end of the metal body (103; 210; 903), and having two or more equally sized openings (108, 109; 204; 312, 313; 322, 323, 324; 332; 908) corresponding and connected to the two or more chambers (106, 107; 209; 906); at least one high-power absorbing load (114, 115; 205; 914) disposed within each of the two or more chambers (106, 107; 209; 906) and configured and arranged to conduct heat to the at least one interior surface (104, 105; 202; 904); a cooling channel disposed in the metal body (103; 210; 903) to remove heat from the body (103; 210; 903); and a plurality of thermal sensors (117; 507a; 917) configured and arranged to detect a temperature associated with the at least one high power absorbing load (114, 115; 205; 914) of the one or more pick-up horns (100; 200; 310; 320; 330; 401; 507; 802; 900; 1104(1)-1104(5)) and to produce output temperature signals indicative of the temperature associated with the at least one high power absorbing load (114, 115; 205; 914); one or more payload antenna feeds configured and arranged to receive RF drive signals and produce radiated RF power; one or more frequency synthesizers (1110, 1112) configured and arranged to produce RF output drive signals to drive the one or more payload antenna feeds; and a processor (501; 1106) configured and arranged to receive the temperature signals from the thermal sensors (117; 507a; 917) and to turn off the output signals of the control the frequency synthesizers (1110, 1112), wherein radiated RF power of the one or more antenna feeds can be reduced.
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