【摘要】：火箭發(fā)動(dòng)機(jī)羽焰溫度是表征固體推進(jìn)劑燃燒特性一個(gè)重要參數(shù),對(duì)導(dǎo)彈武器研制和發(fā)射平臺(tái)設(shè)計(jì)起著關(guān)鍵的作用。由于固體火箭發(fā)動(dòng)機(jī)羽焰流場(chǎng)具有高溫、高壓和強(qiáng)沖擊的特點(diǎn),使得對(duì)其進(jìn)行溫度測(cè)量存在一定的難度。根據(jù)航天X院項(xiàng)目要求,研制出一套3目標(biāo)6波長(zhǎng)高溫計(jì),利用多光譜輻射測(cè)溫技術(shù)實(shí)現(xiàn)羽焰真溫和發(fā)射率的測(cè)量,溫度測(cè)量范圍在900-3000K,整體測(cè)溫精度優(yōu)于3%。本文主要完成了高溫計(jì)裝置的研制工作:包括高溫計(jì)的方案設(shè)計(jì),軟、硬件研制和調(diào)試,儀器的標(biāo)定和測(cè)試等。光學(xué)系統(tǒng)采用組合棱鏡分光的設(shè)計(jì)方案,增強(qiáng)了光學(xué)部分的穩(wěn)定性;利用光纖完成取樣系統(tǒng)和分光系統(tǒng)間光能量的傳輸;探測(cè)器采用硅光電二極管,實(shí)現(xiàn)近似線性的輸出;電路系統(tǒng)有針對(duì)性地設(shè)計(jì)了多級(jí)放大電路,保證高溫計(jì)在整個(gè)測(cè)溫范圍內(nèi)具有足夠的信噪比;最后采用高速數(shù)據(jù)采集卡來(lái)實(shí)現(xiàn)信號(hào)的快速獲取。軟件系統(tǒng)設(shè)計(jì)采用C#語(yǔ)言,結(jié)合ADO.NET數(shù)據(jù)庫(kù)訪問(wèn)技術(shù),實(shí)現(xiàn)數(shù)據(jù)的管理和操作。根據(jù)項(xiàng)目要求完成了標(biāo)定程序、測(cè)量和處理程序的編寫(xiě)和調(diào)試。最后利用單色儀和標(biāo)準(zhǔn)黑體爐對(duì)高溫計(jì)進(jìn)行了PWF標(biāo)定和亮溫方程標(biāo)定;并對(duì)標(biāo)定好的高溫計(jì)進(jìn)行測(cè)試實(shí)驗(yàn)。此高溫計(jì)具有3套獨(dú)立的光學(xué)取樣系統(tǒng)、光纖傳輸、棱鏡分光系統(tǒng)以及多級(jí)放大電路,可以滿足任意3個(gè)目標(biāo)點(diǎn)的同時(shí)測(cè)量。而且通過(guò)優(yōu)化結(jié)構(gòu)設(shè)計(jì),此高溫計(jì)還具有體積小,便攜式,穩(wěn)定性高的優(yōu)點(diǎn)。
[Abstract]:The plume temperature of rocket engine is an important parameter to characterize the combustion characteristics of solid propellant. It plays a key role in the development of missile weapon and the design of launch platform. Because the plume flow field of solid rocket motor has the characteristics of high temperature, high pressure and strong impact, it is difficult to measure the temperature of solid rocket motor. According to the requirements of the space X institute project, a set of 3 target 6 wavelength pyrometer is developed. The plume flame true mild emissivity is measured by multispectral radiation temperature measurement technique. The temperature measurement range is 900-3000K, and the whole temperature measurement precision is better than 3. In this paper, the development of pyrometer device is mainly completed, including the design of pyrometer scheme, the development and debugging of hardware and software, the calibration and testing of the instrument, etc. The optical system adopts the design scheme of combination prism to enhance the stability of the optical part; the optical energy is transmitted between the sampling system and the light splitting system by using optical fiber; the detector uses silicon photodiode to achieve approximately linear output. The multistage amplifier circuit is designed to ensure that the pyrometer has enough signal-to-noise ratio in the whole temperature measurement range. Finally, the high-speed data acquisition card is used to achieve the fast signal acquisition. The software system is designed with C # language and ADO.NET database access technology to realize data management and operation. According to the project requirements, the calibration program, measurement and processing procedures are written and debugged. Finally, the PWF calibration and bright temperature equation calibration of the pyrometer are carried out by using Monochromator and standard blackbody furnace, and the calibrated pyrometer is tested. The pyrometer has three sets of independent optical sampling system, optical fiber transmission, prism splitting system and multistage amplifier circuit, which can be used for simultaneous measurement of any three target points. By optimizing the structure, the pyrometer has the advantages of small volume, portable and high stability.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V435

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