探空八號酬載冷流噴射減滾系統開發

NCUIR > Engineering College > Graduate Institute of opto-Mechatronics > Electronic Thesis & Dissertation > Item 987654321/61456

Please use this identifier to cite or link to this item: http://ir.lib.ncu.edu.tw/handle/987654321/61456

Title:	探空八號酬載冷流噴射減滾系統開發
Authors:	吳書沅;WU,SHU-YUAN
Contributors:	光機電工程研究所
Keywords:	冷流噴射推進器;探八回收艙酬載;減滾;姿態控制
Date:	2013-08-01
Issue Date:	2013-10-08 15:12:41 (UTC+8)
Publisher:	國立中央大學
Abstract:	本論文研究利用商業現成件研製冷流噴射推進系統，並量測將其搭載在太空火箭八號的回收艙上進行飛行試驗時，可以達到姿態控制的減滾效能。本系統由微控制器(MicroController Unit)控制，執行高壓氣源氣瓶穿刺、氣壓與溫度量測，以電磁閥開關控制噴氣與回收艙減滾控制。即時控制軟體建構在實驗室自主開發的LUTOS(Lookup Table Operating System)作業系統上。系統的氣路是由高壓氣瓶、調壓閥、絕對氣壓計、電磁閥、噴嘴和管件所組成。系統的推力效能是利用天秤特性和負重元來量測推力、開閥時間與推力的相對關係。調壓閥的輸出壓力預設在135psia，而實際量測二次側壓力直為145psia。在一大氣壓下，單邊噴嘴推力可達0.4N，因此可對回收艙提供0.11(Nm)的減滾力矩。利用工式推導可知在高空真空環境下，單邊推力可達2.66N，減滾力矩可達0.72(Nm)。已回收艙的吊掛旋轉測試，搭配無線電模組之數據遙傳與G&G(G-Accelerometer & Gyroscope)模組的旋轉角速度量測，確認冷流噴射系統在一大氣壓環境下對探八回收艙酬載可提供70 deg/sec^2的減滾效果，並已備便可行飛行任務。 A Cold Gas Thruster System is developed for the de-spin attitute control of the re-entry capsule in Sounding Rocket 8 Project with commercial off the shelf (COTS) components. Its thrust performance is confirmed by bench and suspended spinning tests. The system is controlled by a Micro Controller Unit (MCU) to punch open the high pressure cold gas canister, to measure the gas line pressure and system temperature, to control the thrust on and off by the solenoid valve to de-spin the re-entry capsule. The real-time control software is developed on our proprietary Lookup Table Operating System (LUTOS). And the pneumatic system consists of the high-pressure gas canister, regulator valve, absolute gas line pressure gauge, solenoid valve, gas lines, nozzles, and fittings. The magnitude and timing performance of the thrust is measured by libra balance scale and load cell. With the regulator valve set at 135psia by the manufacturer, the actual secondary side gas line pressure measured is 145psia, 0.4N thrust force can be achieved at 1 atmosphere environment (equivalently, 2.66N in high altitude vacuum), and, therefore, 0.72(N*m) de-spin torque. Hanging the re-entry capsule on a spinning bearing, the angular deceleration of 70deg/sec^2 can be achieved. In the suspended spinning test, the data telemetry is carried out by the wireless module, while the angular velocity of the spinning is measured by the G & G (G-Accelerometer & Gyroscope) module. The tests verify the effectiveness of the system for the de-spin flight test.
Appears in Collections:	[Graduate Institute of opto-Mechatronics] Electronic Thesis & Dissertation

Files in This Item:

File	Description	Size	Format
index.html		0Kb	HTML	780	View/Open

社群 sharing

Loading...