【摘要】：某型地面電源是某型火箭地面測(cè)發(fā)控系統(tǒng)中的一個(gè)部分,用于某型運(yùn)載火箭在地面測(cè)試期間給箭上電氣系統(tǒng)和地面測(cè)試單機(jī)設(shè)備供電和在發(fā)射期間給電爆管供電點(diǎn)火。地面電源的工作情況直接關(guān)系到火箭在整個(gè)測(cè)試流程中的測(cè)試狀態(tài),所以在地面電源恢復(fù)期間對(duì)電源的單機(jī)測(cè)試就顯得尤為重要。同時(shí),目前所使用傳統(tǒng)的人工測(cè)試方法已經(jīng)越來(lái)越不能滿足運(yùn)載火箭測(cè)試高可靠性、周期短、自動(dòng)化程度高的要求,設(shè)計(jì)自動(dòng)測(cè)試設(shè)備已成為現(xiàn)代航天技術(shù)的發(fā)展趨勢(shì),在測(cè)試過(guò)程中引入自動(dòng)測(cè)試系統(tǒng)也成為設(shè)計(jì)新設(shè)備的標(biāo)準(zhǔn)之一。本文設(shè)計(jì)了一種某型地面電源的自動(dòng)測(cè)試系統(tǒng),用以在地面電源恢復(fù)階段對(duì)其進(jìn)行功能性考核,確認(rèn)其是否滿足能夠完成后續(xù)發(fā)射任務(wù)的要求。硬件部分設(shè)計(jì)以STM32F103芯片作為測(cè)試系統(tǒng)的控制部分,設(shè)計(jì)了測(cè)試系統(tǒng)硬件部分的指令模塊、采樣模塊、人機(jī)交互模塊、存儲(chǔ)部分、報(bào)警部分和電源模塊等功能模塊,軟件部分編寫(xiě)了主程序、測(cè)試流程、A/D轉(zhuǎn)換程序、通信程序、LCD顯示程序、SD讀寫(xiě)程序、報(bào)警程序、中斷程序等軟件模塊,對(duì)采樣數(shù)據(jù)可以在硬件和軟件利用算法進(jìn)行優(yōu)化,減小了信號(hào)非線性、溫漂和電磁干擾,滿足完成地面電源的整個(gè)測(cè)試流程,對(duì)測(cè)試過(guò)程中的采樣數(shù)據(jù)進(jìn)行判讀記錄,最后形成測(cè)試報(bào)告的基本要求。通過(guò)測(cè)試系統(tǒng)初樣設(shè)備在地面電源上的實(shí)機(jī)測(cè)試,系統(tǒng)運(yùn)行穩(wěn)定、各功能模塊工作正常,各項(xiàng)測(cè)試指標(biāo)均達(dá)到了預(yù)期設(shè)計(jì)要求,在現(xiàn)有測(cè)試數(shù)據(jù)證明測(cè)試系統(tǒng)硬件設(shè)計(jì)合理、軟件功能正常,全面快速地完成測(cè)試流程,能夠充分滿足對(duì)地面電源的自動(dòng)化測(cè)試工作的要求。
[Abstract]:A certain type of ground power supply is a part of the ground test and launch control system of a certain rocket. It is used for a certain type of carrier rocket to supply electricity to the onboard electrical system and the single equipment of the ground test during the ground test and to supply the electric detonator to ignite the fire during the launching period. The working condition of the ground power supply is directly related to the test state of the rocket in the whole testing process, so it is very important to test the power source on a single machine during the recovery of the ground power supply. At the same time, the traditional manual test methods used at present have been unable to meet the requirements of high reliability, short period and high degree of automation of carrier rocket testing, so the design of automatic test equipment has become the development trend of modern space technology. The introduction of automatic test system in the testing process has also become one of the standards for designing new equipment. In this paper, an automatic test system for ground power supply is designed, which is used to check the function of ground power supply during the recovery stage, and to confirm whether it meets the requirements of the subsequent launch task. In the hardware part, the STM32F103 chip is used as the control part of the test system. The command module, the sampling module, the man-machine interaction module, the storage module, the alarm part and the power module of the hardware part of the test system are designed. The main program, test flow, A / D conversion program, communication program, LCD display program, SD read and write program, alarm program, interrupt program and other software modules are written in the software part. The sampling data can be optimized in hardware and software to reduce the signal nonlinearity, temperature drift and electromagnetic interference, satisfy the whole test flow of ground power supply, and read and record the sampling data in the testing process. Finally, the basic requirements of the test report are formed. Through the test of the initial equipment of the test system on the ground power supply, the system runs stably, each functional module works normally, and all the test indexes meet the expected design requirements. The existing test data prove that the hardware design of the test system is reasonable. The function of the software is normal and the testing process is completed completely and quickly, which can fully meet the requirements of the automatic testing of the ground power supply.
【學(xué)位授予單位】：華東理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V556

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