共查询到19条相似文献,搜索用时 782 毫秒
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在航空发动机试车过程中,针对数字电子控制器采集低压涡轮出口燃气温度(T6)高于试车台数采系统采集值的现象,进行了多轮测温试验,并结合T6测温原理、热电偶及补偿导线电气特性等,提出了从数字电子控制器电路板终端进行温度标定的方法,以确保在发动机实际试车过程中控制器测量的T6值更接近真实温度.试验结果表明:在航空发动机试车中采用在数字电子控制器T6采集电路板的补偿导线终端进行标定的方法后,由数字电子控制器与试车台数采系统采集的T6值相差1℃以内,证明该标定方法准确可行. 相似文献
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针对某型发动机高压转子转速摆动故障,详细分析了油门杆稳定时地面和空中多次出现高压转子转速无规则摆动、其
他参数随动的故障现象,阐述了高压转子转速受综合电子调节器、燃油系统、转速调节系统等控制的控制原理,剖析故障机理,制
定了故障树。结合故障树,列举了进口温度感受附件、综合电子调节器、燃油系统、转速调节系统等4种故障。采用故障树分析法
找出故障原因,分析薄弱环节。经对4种故障原因逐条分析,排除了进口温度感受附件、综合电子调节器、燃油系统等因素,确定
转速调节系统中加速控制器未完全退出工作是转速摆动的原因。针对波动量较大的发动机,调整加速性至合理范围,进行地面试
车和飞行等外场排故验证。结果表明:发动机工作参数正常,高压转子转速摆动现象消失,发动机推力稳定。故障得以排除。 相似文献
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系统功能 控制器的基本功能有:(1)按发动机加速供油曲线要求能自动起动、加速、速发动机,并按大气温度修正供油量,以保证发动机在起动和加速过各中不喘振、不起温。)保持发动机燃气发生器转速恒定,使输出功率稳定。 相似文献
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载人飞船返回舱六自由度再入弹道仿真研究 总被引:1,自引:0,他引:1
为了综合研究和分析载人飞船返回舱制导导航控制(GNC)系统的性能,验证系统设计的正确性、合理性和可行性,提出了返回舱六自由度再入弹道仿真研究问题。根据返回舱GNC系统的任务,建立了适用于包括风在内的各种干扰作用下六自由度再入弹道仿真数学模型,为半实物仿真奠定了基础。提出了基于标准轨道的再入制导律,严格推导了再入段总升力方向控制中滚动通道姿态控制信号的形成,并给出了工程应用中简化的方法,开发了综合仿 相似文献
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一、引言 直升机的旋翼不仅是直升机的操纵面,还是直升机的升力面。因此,直升机的性能品质及安全性等等无不与旋翼桨叶及其操纵系统相互作用的耦合动力特性有关。且不难明白在飞行条件下,它即取决于操纵系统中随频率或时间而变化的刚度特性也即动刚度特 相似文献
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The Applications Technology Satellite-6 (ATS-6) RF interferometer is utilized primarily as a precision 3-axis attitude sensor having an unambiguous field of view of 350°. This function requires two separated ground transmitters, each using one of the two available frequency channels or sharing a single channel by time multiplexing. For 3-axis control, one uplink transmitter can provide 2-axis attitude (pitch and roll) with other sensors (e.g., a Polaris tracker) providing yaw attitude. By utilizing two uplink transmitters and the Earth sensor or three time multiplexed uplink transmitters, the interferometer can also provide measurements of ATS-6 spacecraft orbit position. Uplink frequencies are 6.150 and 6.155 GHz. The receiving antennas are spaced at 19.95 wavelengths (?) for the vernier baseline and 1.66 ? for the coarse baseline. Spacecraft system weight is 8.39 kg (18.5 lb) and power requirement is 15.5 W. Flight evaluation results are given for the interferometer including R F link budgets, modulation of uplink carrier, signal-to-noise ratio, and dropout behavior. A hardware calibration model is described, containing major biases in the phase measurements. Techniques for flight calibration as both an attitude and spacecraft position sensor are outlined . Flight testing has shown that on-line calibration of receiver/converter biases must be performed on a short term routine basis. Interferometer resolution was found to be 0.00140 space angle with negligible noise (jitter) at transmitted power levels above 72 dBW. As an attitude sensor, the interferometer has demonstrated the ability to provide stabilization to better than 0. 相似文献
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The Applications Technology Satellite-6 (ATS-6) uses a 9l1-r parabolic antenna with high gain to enable communications with simple, low-cost ground stations with 3-m-diameter antennas. The structural system met all of its requirements, deployed properly, and preserved sensor alignment within 0.1 degree. The thermal control system has kept all temperatures within specified limits. The communications subsystem in-orbit performance has also exceeded specifications with high receiver gain-to-temperature ratios and high transmitter El RP. The spacecraft propulsion system performance has been within specifications. The near-perfect geosynchronous orbit achieved by the Titan IIIC resulted in a 8-kg fuel saving which should extend mission life. The attitude and control subsystem is providing the necessary stabilization and accurate slewing control. The electrical power subsystem provided 40 W more than the specified value at the last summer solstice. The telemetry and command subsystem performance has also been nominal. 相似文献
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The primary objective of the Spacecraft Attitude Precision Pointing and Slewing Adaptive Control (SAPPSAC) Experiment is to establish feasibility and evaluate capabilities of a ground-based spacecraft attitude control system, wherein RF command and telemetry links, together with a ground station on-line minicomputer, perform closed loop attitude control of the Applications Technology Satellite -6 (ATS-6). The ground processor is described, including operational characteristics and the controller software. Attitude maneuvers include precision pointing to fixed targets, slewing between targets, and generation of prescribed ground tracks. Test results show high performance and reliability for over 30 h of on-line control with no serious anomalies. Attitude stabilization relative to a prescribed target has been achieved to better than 0.007° in pitch and roll and 0.020° in yaw for a period of 43 min. Ground tracks were generated which had maximum latitude/longitude deviations less than 0.150 from reference. 相似文献
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The Applications Technology Satellite (ATS-6), the most powerful, most sophisticated, most versatile communications satellite flown to date, is the last of NASA's experimental satellites intended to demonstrate major advances in communications and spacecraft technology. It is a multipurpose, multidisciplinary spacecraft whose principal objectives were to demonstrate a large, unfurlable antenna structure and precise pointing and attitude control in the synchronous orbit The spacecraft carries 27 different experiments, 3 of which demonstrate users' applications of satellite communications. Significant advances in antenna technology, precise attitude control, materials technology, spacecraft structures, and thermal control have been successfully demonstrated. The most significant accomplishments of the ATS-6 mission are the demonstration of the practicality of satellite broadcasting to small, simple, inexpensive ground stations and the uses of this potential service in the solution of social problems involving education and health care. The success of these initial demonstrations has led ATS-6 experimenters and potential users to incorporate a Public Service Satellite Consortium dedicated to the provision of satellite broadcasting services for educational and health-care applications. 相似文献