標準編號:	GJB 2361-1995
中文名稱:	星地測控回路試驗方法
英文名稱:	Methods for matching test of satellite and TT&C station
行業分類:	GJB    國家軍用行業標準
發布機構:	國防科學技術工業委員會
發布日期:	1995-05-31
實施日期:	1995-12-1
標準狀態:	valid
翻譯語言:	英文
文件格式:	PDF
中文字符數:	12000 字
翻譯價格(元):	1200.0
交付時間:	付款后 1 個工作日

Codeofchina.com is in charge of this English translation. In case of any doubt about the English translation, the Chinese original shall be considered authoritative. Methods for matching test of satellite and TT&C station 1 Scope 1.1 Subject content This standard specifies the matching test contents and methods of satellite TT&C system and ground TT&C station (airship). 1.2 Application scope This standard is applicable to the matching test of satellite and TT&C system before satellite flight test. Each model may be tailored according to the actual situation. 2 Normative references There is no provision in this clause. 3 Definitions 3.1 static matching test of satellite and TT&C station joint test on system performance and working programs of satellite TT&C system and related equipment and TT&C system of TT&C station (airship) 3.2 dynamic matching test of satellite and TT&C station joint test on system performance and working programs of satellite TT&C system and related equipment on revised flight and ground TT&C station 3.3 satellite TT&C simulator equipment simulating satellite TT&C function in matching test of satellite and TT&C station 3.4 satellite attitude & orbital motion simulator equipment that receives attitude and orbit data and converts the attitude and orbit control parameters into remote control command information and control data according to dynamics and kinematics laws 3.5 satellite simulator generic terms of satellite TT&C simulator and satellite attitude & orbital motion simulator ? 4 General requirements 4.1 Test purpose a. Verify the coordination of joint work of satellite and TT&C system and related equipment; b. Verify the technical state and main TT&C technical performance of satellite and TT&C equipment; c. Rehearse the working program of satellite and TT&C system; d. Simulate satellite failures and rehearse emergency treatment methods; e. Commanders and operators performing tasks perform field drills according to working programs. 4.2 Test conditions a. The newly developed satellite system shall be subjected to matching test of satellite and TT&C station; b. Before each satellite is launched, the matching test of satellite and TT&C station shall be arranged as needed; c. Due to the needs of satellite TT&C system, when the TT&C equipment has been greatly modified, the matching test of satellite and TT&C station shall be arranged. 4.3 Test site and equipment 4.3.1 Test site The matching test is generally carried out at satellite TT&C station (airship). Personnel activities and object movements are prohibited near the antenna in test site. 4.3.2 Test equipment Satellite-borne equipment or simulation equipment and TT&C station (airship) equipment with the same electrical performance as satellite-borne equipment is adopted for matching joint test. 4.4 Test environmental conditions 4.4.1 The test environmental conditions for TT&C station (airship) equipment shall be specified according to the special technical specifications for equipment. 4.4.2 Atmospheric conditions for satellite-borne equipment, simulation equipment and test and detection equipment: a. temperature: 0~45℃; b. relative humidity: ≤80%; c. air pressure: local air pressure. 5 Detailed requirements 5.1 Static matching test of monopulse radar Place the director radar beacon, radar transponder and their antennas on the radar calibration tower, and set the uplink and downlink levels of RF signals according to the test contents. 5.1.1 Ranging accuracy test of radar Switch on director radar beacon and radar transponder. The director radar tracks the director beacon antenna, and test the performance of director radar and the stability of signals received by beacon. The director monopulse radar points to the transponder antenna. The radar sends pulse signals to trigger the radar transponder, and the monopulse radar antenna tracks the transponder antenna. At the same time, measure the fixed delay and delay stability of the transponder so as to obtain the ranging accuracy and calculate the statistical angle measurement accuracy. 5.1.2 Frequency measurement accuracy test of radar When the radar triggers the transponder, measure the RF frequency and frequency stability of the answer signal so as to obtain the frequency measurement accuracy. 5.1.3 Switch-on capture characteristic test of radar transponder Measure the time from switch-on to normal signal response of radar transponder, and measure the value of frequency and pulse delay varying with time at different time after switch-on. 5.1.4 Working frequency band test of radar transponder Change the transmitting frequency of radar, and measure the frequency band of transponder transmitting radar signal. 5.2 Static matching test of dual-frequency velocimeter Place the satellite-borne dual-frequency transmitter and antenna in the test room or calibration tower at TT&C station, and measure the frequency stability of dual-frequency transmitter through the equipment of TT&C station. Preheat the satellite-borne transmitter, and test the frequency stability after the frequency is stable. The data of continuous measurement for 20min is regarded as a group, and the data are generally processed by Allan variance. During the measurement of multiple groups of data, the time for continuous measurement of each group of data may be shortened appropriately. The high-end and low-end frequency stability, comprehensive frequency stability and dual-frequency frequency accuracy shall be measured. 5.3 Static matching test of ultrashort wave remote control Place the satellite-borne remote control equipment and antenna on the test room or calibration tower at TT&C station. Generally, the transmitting power of remote transmitter at TT&C station is limited to less than 10mW, and the modulation index is 2.5, 3.0 and 3.5 respectively. 5.3.1 In the test command channel, the remote control command is sent by hand, and the satellite-borne test equipment monitors and records the receiving result of command. 5.3.2 The computer controls the sending of remote control commands, and the satellite-borne test equipment monitors and records the receiving result of command. The computer controls the remote control command chain, and the satellite-borne test equipment monitors and records the receiving result of command. 5.4 Static matching test of ultrashort wave telemetry Place the satellite-borne telemetry equipment on the test room or calibration tower at TT&C station. Switch on the satellite-borne telemetry equipment and the TT&C station receives the data. 5.4.1 Verify the correctness of telemetry frequency, demodulation, bit error rate and data format. 5.4.2 The TT&C station processes the received telemetry data. 5.5 Static matching test of ultrashort wave ranging Place the satellite-borne ranging receiver, dual-frequency transmitter and antenna on the calibration tower at TT&C station for test, or use the simulator of satellite-borne equipment to replace satellite-borne ranging equipment for test. 5.5.1 Test with satellite-borne ranging equipment Use phase modulation/phase modulation mode for the uplink and downlink of ranging system, and carry out the test after the satellite and TT&C station equipment is stabilized after switch-on. 5.5.1.1 Measurement of distance zero value and phase matching value of each sidetone Adjust the levels of uplink and downlink signals to the receiving sensitivity level through attenuator, the modulation degree is the rated value, the carrier frequency is the used center frequency, and measure the distance zero value and the phase matching value of each sidetone in two states of "measurement" and "self-calibration” by distance measuring equipment at TT&C station. Measure ten groups of data for statistical processing so as to obtain the distance zero value and phase matching value of satellite-borne system. 5.5.1.2 Ranging accuracy of measurement system Adjust the levels of uplink and downlink signals to the receiving sensitivity level through attenuator, the modulation degree is the rated value, the carrier frequency is the used center frequency, and the distance measuring equipment of TT&C station measures the distance zero value in two states of "measurement" and "self-calibration” and carry out statistical processing for multiple groups of measured data so as to calculate the ranging accuracy value of ranging system. 5.5.1.3 Measurement of retransmitting sidetone modulation degree and frequency spectrum When the telemetry signal is modulated by the satellite-borne transmitter, measure the sidetone spectrum of the retransmitted signal by a spectrum analyzer, so as to obtain the modulation degree, sidetone spectrum structure and clutter spectrum. 5.5.1.4 Measurement of influence of various factors on ranging accuracy According to the requirements of satellite orbit measurement, change the uplink and downlink levels, carrier frequency (Doppler frequency offset) and modulation degree by 10%, and measure the change value of distance zero value caused by various changes through distance measuring equipment, so as to obtain the influence on ranging accuracy. 5.5.1.5 Measurement of stability of distance zero value Take a group of distance zero value data every 10min by the distance measuring equipment at TT&C station, with 10 groups taken in total, and the change of distance zero value shall not be out of the use range. 5.5.2 Test with simulator Test contents are the same as those in 5.5.1. Compare the measurement result with that of satellite-borne equipment, which may be used as a reference for the equipment detection of TT&C station. 5.5.3 Error propagation test of ultrashort wave ranging distance zero value Before satellite launch, the test shall be carried out at the final assembly plant, special test site or TT&C station. Use phase modulation/phase modulation mode for the uplink and downlink of test system. Carry out the test after the satellite and TT&C station equipment is stabilized after switch-on. Adjust the levels of uplink and downlink signals to the receiving sensitivity level through attenuator, the modulation degree is the rated value, and the carrier frequency is the used center frequency. 5.5.3.1 Measure the distance zero value of satellite ranging system and the phase value of each sidetone by distance measuring equipment for satellite comprehensive test. 5.5.3.2 Measure the distance zero value of simulator and the phase value of each sidetone bydistance measuring equipment for satellite comprehensive test . 5.5.3.3 Compare the distance zero value between the satellite-borne ranging system and the simulator and the difference of phase value of each sidetone, which serves as the calibration basis for the equipment of TT&C station to measure the distance zero value. 5.5.3.4 Measure the distance zero value of simulator and the phase value of each sidetone by distance measuring equipment at each ground TT&C station, compare and analyze the measured zero value and phase value with those measured by distance measuring equipment for satellite comprehensive test, complete the error propagation, and obtain the ranging value that shall be deducted when performing the flight mission.

1 Scope 2 Normative references 3 Definitions 4 General requirements 5 Detailed requirements Additional explanation

1 范圍 1.1 主題內容 本標準規定了衛星測控系統與地面測控站(船)的回路試驗內容和方法。 1.2 適用范圍 本標準適用于衛星飛行試驗前的星地測控系統回路試驗。各型號可以根據本型號實際情況適當剪裁。 2 引用文件 本章無條文。 3 定義 3.1 星地靜態對接試驗 static matching test of satellite and TT&C station 星上測控系統及有關設備與測控站(船)的測控系統進行系統性能和工作程序的聯試。 3.2 星地校飛 dynamic matching test of satellite and TT&C station 星上測控系統及有關設備在校飛飛機上與地面測控站進行系統性能和工作程序的聯試。 3.3 衛星測控模擬器 satellite TT&C simulator 星地回路試驗中模擬衛星測控功能的設備。 3.4 衛星姿態與軌道運動仿真器 satellite attitude & orbital motion simulator 接收姿態和軌道數據，根據動力學和運動學規律將姿態與軌道控制參數轉換成遙控指令信息和控制數據的設備。 3.5 衛星模擬器 satellite simulator 衛星測控模擬器和衛星姿態與軌道運動仿真器的總稱。 4 一般要求 4.1 試驗目的 a. 驗證星地測控系統及有關設備聯合工作的協調性； b. 驗證星地設備的技術狀態和主要測控技術性能； c. 演練星地測控系統的工作程序； d. 模擬衛星故障，演練應急處理方法； e. 執行任務的指揮員、操作員根據工作程序進行實地演練。 4.2 試驗時機 a. 對新研制的衛星系統應安排進行星地測控回路試驗； b. 每顆衛星發射前，根據需要安排星地測控回路試驗； c. 由于衛星測控系統本身的需要，測控設備作了重大修改時，應安排星地測控回路試驗。 4.3 試驗場地和設備 4.3.1 試驗場地 回路試驗一般在衛星測控站(船)進行。試驗場地天線附近禁止人員活動和物體移動。 4.3.2 試驗設備 利用星上設備或電氣性能與裝星設備一致的仿真設備和測控站(船)設備進行回路聯試。 4.4 試驗環境條件 4.4.1 測控站(船)設備的試驗環境條件按設備專用技術條件規定。 4.4.2 星上設備、仿真設備和試驗檢測設備的大氣條件： a. 溫度：0～45℃； b. 相對濕度：不大于80％； c. 氣壓：當地大氣壓。 5 詳細要求 5.1 單脈沖雷達靜態對接試驗 引導雷達信標機和雷達應答機及其天線置于雷達校準塔上，根據試驗內容設置射頻信號上、下行電平。 5.1.1 雷達測距精度試驗 引導雷達信標機和雷達應答機開機。引導雷達跟蹤引導信標機天線，測試引導雷達的性能和接收信標機信號的穩定性。引導單脈沖雷達天線指向應答機天線。雷達發送脈沖信號，觸發雷達應答機，單脈沖雷達天線跟蹤應答機天線，同時測量應答機的固定延時和延時穩定度，得出測距精度，計算統計測角精度。 5.1.2 雷達測頻精度試驗 雷達觸發應答機時，測出回答信號的射頻頻率及頻率穩定度，得出測頻精度。 5.1.3 雷達應答機開機捕獲特性試驗 測量雷達應答機由開機到能夠正常應答信號的時間，測量開機后不同時刻頻率和脈沖延時隨時間變化的數值。 5.1.4 雷達應答機工作頻帶測試 改變雷達的發射頻率，測量應答機轉發雷達信號的頻帶。 5.2 雙頻測速儀靜態對接試驗 星載雙頻發射機和天線置于測控站試驗室內或校準塔上，用測控站的設備測量雙頻發射機的頻率穩定度。 星上發射機預熱，待頻率穩定后開始測試頻率穩定度。連續測量20min數據為一組，一般用阿侖方差對數據進行處理。測量多組數據時，可把每組連續測量數據的時間適當縮短。要求測量高端和低端頻率穩定度、綜合頻率穩定度和雙頻的頻率精度。 5.3 超短波遙控靜態對接試驗 星載遙控設備和天線置于測控站試驗室或校準塔上。測控站遙控發射機發射功率一般限制在10mW以下，調制指數分別選2.5，3.0和3.5。 5.3.1 試驗指令通道，采用手控發送遙控指令，星上試驗設備監視、記錄指令接收結果。 5.3.2 計算機控制發送遙控指令，星上試驗設備監視、記錄指令接收結果。計算機控制發送遙控指令鏈，星上試驗設備監視、記錄指令接收結果。 5.4 超短波遙測靜態對接試驗 星載遙測設備置于測控站試驗室或校準塔上。星載遙測設備開機，測控站接收。 5.4.1 驗證遙測頻率、解調、誤碼率和數據格式的正確性。 5.4.2 測控站對接收的遙測數據進行處理。 5.5 超短波測距靜態對接試驗 星載測距接收機、雙頻發射機和天線置于測控站校準塔上進行試驗，或者使用星載設備的仿真器代替星載測距設備進行試驗。 5.5.1 使用星載測距設備試驗 測距系統上、下行采用調相/調相方式，星地設備開機達到穩定后進行試驗。 5.5.1.1 測量距離零值和每個側音的相位匹配值 利用衰減器使上、下行信號電平調到接收靈敏度電平，調制度為額定值，載波頻率為使用的中心頻率，測控站測距機分別在“測量”和“自校”兩種狀態下，測量距離零值和每個側音的相位匹配值。測量10組數據統計處理，得出星上系統的距離零值和相位匹配值。 5.5.1.2 測量系統的測距精度 利用衰減器使上、下行信號電平調到接收靈敏度電平，調制度為額定值，載波頻率為使用的中心頻率，測控站測距機分別在“測量”和“自校”兩種狀態下，測量距離零值，經多組測量數據統計處理，計算出測距系統的測距精度值。 5.5.1.3 測量轉發側音調制度和頻譜 在星載發射機調制遙測信號的情況下，利用頻譜分析儀測量轉發信號的側音頻譜，得出調制度、側音頻譜結構和雜波頻譜。 5.5.1.4 測量各因素對測距精度的影響 根據衛星軌道測量要求，改變上、下行電平、載波頻率(多卜勒頻偏)和改變調制度10％，測距機測量各項變化引入的距離零值的變化值，得出對測距精度的影響。 5.5.1.5 測量距離零值的穩定性 測控站測距機每隔10min取一組測量的距離零值數據，共取10組，距離零值的變化不應超出使用范圍。 5.5.2 使用仿真器試驗 試驗內容同5.5.1條。測量結果和星載設備的測量結果比較，作為測控站設備檢測的參考。 5.5.3 超短波測距距離零值的誤差傳遞試驗 衛星發射之前，在總裝廠、專門試驗場地或測控站進行。 試驗系統上、下行采用調相/調相方式。星地設備開機達到穩定后進行試驗。利用衰減器使上、下行信號電平調到接收靈敏度電平，調制度為額定值，載波頻率為使用的中心頻率。 5.5.3.1 利用衛星綜合測試測距機測量衛星測距系統的距離零值和每個側音的相位值。 5.5.3.2 利用衛星綜合測試測距機測量仿真器距離零值和每個側音的相位值。 5.5.3.3 比較星載測距系統與仿真器的距離零值和每個側音相位值差異，作為測控站設備測定距離零值的標定依據。 5.5.3.4 在各地面測控站用測距機測量仿真器的距離零值和各側音相位值，用所測得的零值和相位值與用衛星綜合測試測距機所測的零值相位值比較分析，完成誤差傳遞，得出執行飛行任務時測距應扣除的值。 5.6 超短波統一測控系統靜態對接試驗 參加對接試驗的星上設備，包括遙測、遙控、雙頻發射機、星載程序控制裝置(或星上計算機)和天線，在測控站試驗室中連接成試驗系統。 5.6.1 遙控、遙測回路試驗 測控站設備發送遙控指令鏈，星載試驗設備接收遙控指令，通過遙測和雙頻發射機通道向下發送遙測信號，測控站接收并處理出遙測參數，檢查遙控指令執行結果。試驗中星載設備的遙控指令執行情況應有監視手段。 5.6.2 數傳上、下行回路試驗 測控站發送數傳數據，通過遙控通道注入到星上。注入的數據通過雙頻發射機通道返回測控站，與發送的數據進行比對，數據比對正確，再由遙控發指令，把已注入到星上的數據送到星上程控裝置(或控制計算機)中。程控裝置(或控制計算機)把收到數據正確的標志，由遙測系統送到測控站檢查。 5.6.3 星地時間比對試驗 由星上程控裝置(或控制計算機)通過遙測把星上的時間碼數據傳到測控站，由測控站計算機計算出星地時間的差值及變化，確定星地時間誤差。 5.6.4 星地飛行程序試驗 按照衛星入軌段、運行段和返回段正常工作程序，并進行演練。 5.6.5 故障對策試驗 試驗正常工作程序之后，設置一些可能出現并影響衛星整個測控系統正常工作的星上設備和地面設備的軟硬件故障，運行工作程序，試驗故障對策，并進行演練。 5.6.6 仿真器和衛星測控設備一致性標定試驗 試驗內容和方法與衛星設備做法一致。 5.7 微波統一測控系統靜態對接試驗 星上測控系統TT&C硬件部分(TT&C裝星正樣產品或衛星模擬器)可以置于機房內或標校塔上。置于機房內時，測控站發射機通過電纜與TT&C硬件連接起來。置于標校塔上時，測控站發射機通過天線與TT&C硬件溝通信道。 5.7.1 應答機AGC電壓標定 5.7.1.1 AGC電壓標定 提前將應答機及地面設備加電，標定好連接電纜的衰減量，用標準信號源給應答機輸入信號，調整信號源輸出功率，使輸入到應答機的信號電平在弱信號時按每1dB一個點變化，強信號時按每5dB一個點變化，觀察并記錄應答機的AGC值。 5.7.1.2 AGC電壓特性曲線測量 上行頻率對準鑒頻零點電壓所表示的頻率，下行信號電平比額定值高20dB，按額定的調制度，改變上行載頻信號強度(弱信號時每1dB時一個點，強信號時每5dB時一個點)，從遙測相應的波道中讀出AGC電壓值，得出AGC特性曲線。 5.7.2 鑒頻特性測試 上行功率電平比額定值高20dB，上行頻率為標稱頻率，從編碼遙測相應波道中讀出并記錄鑒頻偏壓值，改變上行頻率，得出鑒頻特性曲線。 5.7.3 應答機靈敏度測量 采用上行調相體制時，測試應答機起始鎖定的最小輸入電平，即為應答機的靈敏度。 采用上行調頻體制時，在額定頻偏條件下，測試應答機能使遙控指令正常工作(一般發自檢指令50～100次)的最小輸入電平，即為應答機的靈敏度。 5.7.4 信標頻率測量 上行功率為額定電平，在應答機上行調頻和上行調相狀態下測量下行信標的頻率精度和頻率穩定度。 5.7.5 信標頻譜測試 無上行載波時，編碼遙測信號以額定調制度加到應答機下行載波上，在應答機輸出口和地面接收機第二中放輸出端用頻譜儀觀察下行頻譜，記錄各譜線的頻率和分貝數。 5.7.6 應答機轉發調制度測試 5.7.6.1 轉發特性測試 在僅有測距信號時，轉發特性是將遙測副載波斷開，上、下行電平均比額定值高20dB，地面按額定調制度發高側音測距信號，在應答機射頻輸入口和輸出口分別利用頻譜儀記錄相應的上行頻譜和下行頻譜。 在有遙測信號時，轉發特性是將遙測信號按額定調制度調到載波上，地面按額定調制度分別發高側音和全側音的測距信號，在應答機射頻輸入口和輸出口分別利用頻譜儀記錄高側音和全側音的相應上行頻譜和下行頻譜。 5.7.6.2 轉發調制度測試 在應答機上行調相、下行調相和上行調頻、下行調相兩種狀態下測試，上行為額定電平，下行信號為額定信號噪聲功率譜密度比，調整上行調制度，保證下行調制度額定值，記錄此時各機的上下行信號的調制度值。 5.7.7 載波雙捕性能測量 應答機接入測試系統，上行功率為額定電平，下行信號為額定信號噪聲功率譜密度比，按適當的頻率偏移要求，測量雙向捕獲時間，至少做10次，計算平均捕獲時間。 5.7.8 頻率突跳值測量 上行功率為額定電平，應答機處于鎖相狀態，上行載波頻率做較小的約定變化，突然斷上行或突然發上行情況下，檢測星地設備的雙捕性能。 5.7.9 應答機同步帶及捕捉帶測暈 上行功率為額定電平，應答機接入測試系統，由低至高和由高至低改變上行載頻，測量應答機調相狀態下工作的鎖定、失鎖點的頻率，換算出應答機的同步帶和捕捉帶。 5.7.10 應答機積分器零點測量 應答機處于鎖相狀態時，改變測試上行頻率，測出積分器電壓為零時的上行頻率，求出與標稱點頻率的差值。 5.7.11 應答機鑒頻器零點測量 應答機處于鑒頻狀態時，改變測試上行頻率，測出鑒頻器電壓為零時的上行頻率，求出與標稱點頻率的差值。 5.7.12 距離零值測量 5.7.12.1 測控站(船)距離零值測量 在調相/調相狀態下，按規定的上行電平、下行信號噪聲功率譜密度比、載波中心頻率和額定下行調制度，分別測量在“測量”和“自校”兩種連接方式下的系統距離零值，經計算處理得到應答機的距離零值和各側音間的相位差值(相位匹配值)。 在調頻/調相狀態下，按調頻/調相狀態的測試條件，在中頻閉環的狀態下測出“測量”(應答機、射頻閉路)和“自校”兩種連接方式下的系統距離零值，經計算處理得到應答機的距離零值。 5.7.12.2 發射場距離零值測量 測試條件同5.7.12.1條的規定。用發射星的測試設備對測控站(船)的衛星測控模擬器中的應答機測量，得到調相和調頻方式時的距離零值、測距信號間的相位匹配值。 5.7.12.3 確定傳遞關系 調相方式距離零值比對，為測控站(船)與發射場測得的距離零值的差值。 調頻方式距離零值比對，為測控站(船)與發射場測得的距離零值的差值。 相位匹配比對差值為測控站(船)與發射場在調相和調頻方式下測得的測距信號各側音的相位匹配值的差值。 5.7.12.4 測距離零值的比對校準 發射星應答機距離零值和相位匹配值的測定，用發射星測試設備分別測出調相、調頻方式時的距離零值和各側音間的相位匹配值。各測控站(船)按此測量值及傳遞關系，得到各自設備對發射星應答機的距離零值和相位匹配值。 5.7.12.5 對接試驗時距離零值有關測試 a. 星地距離零值隨上行電平的變化； b. 星地距離零值隨下行電平的變化； c. 星地距離零值隨上下行多卜勒的變化； d. 星地距離零值隨上行調制度的變化； e. 星地距離零值12h漂移測試。 5.7.12.6 發射星應答機距離零值有關測試 用發射星測試設備測量下列距離零值有關參數： a. 距離零值隨上行電平的變化； b. 距離零值隨上行多卜勒的變化； c. 距離零值隨上行調制度的變化； d. 距離零值隨溫度的變化。 5.7.13 遙控對接 5.7.13.1 主要功能測試 衛星測空模擬器與測控站(船)測控設備構成回路。按預先設計好的衛星遙控狀態調整地面系統遙控設備，調整上、下行射頻衰減器，使上、下行信號強度比額定值高20dB，選用“本控”工作方式，在各組副載頻下將所有指令發送一遍，檢查小回路比對和大回路比對是否正確。選用“遠控”工作方式，重復上述試驗。 5.7.13.2 比特誤碼率測試 星地設備加電預熱2h，上、下行調制度額定，上行功率電平額定，下行電平比額定值高20dB，遙控臺選用“遠控”工作方式，上行多卜勒頻偏為0，計算機以盡可能小的時間間隔連續發某條指令4h，由計算機統計比特誤碼率。上行多卜勒頻偏分別為±60，±120，±180kHz時，計算機統計每種頻偏下的比特誤碼率。 5.7.14 遙測對接 5.7.14.1 主要功能測試 衛星測控模擬器與測控站(船)測控設備構成回路。按預先設計好的衛星遙測狀態調整地面系統遙測設備，調整下行射頻衰減器，使下行信號強度比額定值高20dB，監視編碼遙測波形和解調是否正確，檢查副載波頻率和波道分配是否正確。 5.7.14.2 編碼遙測誤碼率測試 星地設備加電預熱2h，無上行信號，調整下行射頻衰減器，使下行信號強度為額定值，按預訂的波道信號及碼字，計算機統計2h的誤碼，得到遙測誤碼率。上行按額定電平、額定調制度發高側音，計算機再統計2h的誤碼率。上行按額定電平、額定調制度發全側音，計算機再統計2h的誤碼率。 5.7.15 星地天線極化對接 調整射頻衰減器，使上、下行信號電平均比額定值高30dB。 地面分別以左、右旋圓極化接收，記錄相應的下行信號強度。