Space Shuttle separate-surface control-system study
Space Shuttle separate-surface control-system study
复制标题
航天飞机分离表面控制系统研究
DOI：
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发表时间：
1984
期刊：
影响因子：
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通讯作者：
R. Montgomery
中科院分区：
文献类型：
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作者：
L. W. Brown;R. Montgomery
本文提出了一种控制系统的概念，它只需要对航天飞机进行软件修改，就能对航天飞机从早期进入到马赫数2的偏航力矩进行比例控制。它使用了内侧和外侧升降副翼表面的单独偏转，并通过考虑升降副翼表面的偏转极限来确定可用的最大静态偏航力矩来进行评估。可以获得比最有效的反作用控制系统（RCS）喷气偏航控制所产生的力矩稍大的比例力矩。除了静力矩研究外，还设计了一种控制律，其目的是产生所需的飞行品质。
A control system concept is presented that produces proportional control of yaw moment for the space shuttle from early entry to Mach 2 with only software modifications of the vehicle. It uses separate deflections of the inboard and outboard elevon surfaces and is evaluated, by determining the maximum static yawing moment available by considering the deflection limits of the elevon surfaces. A proportional moment slightly in excess of that produced by the most effective reaction control system (RCS) jet for yaw control can be obtained. In addition to the static moment study, a control law is designed which is intended to produce desired flying qualities.