On Stability and Control of SSTO Spaceplane in Super-and Hypersonic Ascending Phase
On Stability and Control of SSTO Spaceplane in Super-and Hypersonic Ascending Phase
复制标题
SSTO空天飞机超高超声速上升阶段稳定性与控制研究
DOI：
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发表时间：
1991
期刊：
影响因子：
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通讯作者：
松島 弘一
中科院分区：
文献类型：
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作者：
A. Diekmann;K. Matsushima;松島 弘一
在超声速至高超声速和恒动压上升轨迹上的7个参考点上，对单级入轨（SSTO）空天飞机结构的自然动态稳定性进行了评估。结果表明，在所考虑的弹道较宽的部分，在纵向和横向运动中发生动力不稳定。为了抵消这些不稳定性，引入了一个简单的输出反馈控制，以实现根据常规飞机通常使用的处理质量标准的主导模式的极点配置。评价了增广稳定性参数对反馈增益常数偏差的敏感性。通过数值模拟研究了增稳型空天飞机在标准晴空湍流中爬升时的纵向运动特性。结果表明，控制设计具有良好的性能。尽管在上升轨道的大范围内发生了严重的自然不稳定，但控制的升降舵偏转角仍然很小。
The natural dynamic stability of a single stage to orbit (SSTO) National Aerospace Laboratory Spaceplane Configuration is evaluated at seven reference points on a super-to hypersonic and constant dynamic pressure ascent trajectory. It is shown that dynamic instability occurs in the longitudinal and lateral motion during wide parts of the regarded trajectory. To counteract these instabilities a simple output feedback control is introduced to achieve a pole assignment of the dominant modes according to handling quality criteria commontly use for conventional aircraft. The sensitivity of augmented stability parameters to deviations in the feedback gain constants is evaluated. The dynamic behaviour of stability augmented Spaceplane is investigated by numerical simulation of its longitudinal motion during an ascent in standard clear air turbulence. Results indicate the sufficient performance of the control design. The controlled elevator deflection angles remain small despite the severe natural instability which occurred during wide parts of ascent trajectory.