排序方式: 共有7条查询结果,搜索用时 46 毫秒
1
1.
The relationships between path constraints such as heating rate, dynamic pressure and aerodynamic load and velocity during entry flight are analyzed in r-V plane for an entry vehicle with mediate high lift to drag ratio. Through derivation and integration, a unified formula for path constraints is obtained in r-V plane. Based on the unified formula and several characteristics an analytical solution is obtained,and an online trajectory generation method is developed. In the method, the coupled longitudinal and lateral motion is considered, and can make the best use of flight capability and satisfy path constraints. Trajectory generation cases with different flight mission and downranges are tested. Simulation results demonstrate the capability and efficiency of the trajectory planning method in dealing with path constraints. 相似文献
2.
3.
4.
5.
研究高超声速再入飞行器制导/总体参数一体化设计问题.论述飞行器总体设计中气动特性、姿控能力、防隔热水平、伺服能力、质量、结构强度、战标等总体参数对制导的影响,指出高超声速再入飞行器外形及制导的特点决定了在概念设计、方案设计阶段就需要考虑制导需求.以某飞行试验为背景,开展制导总体方案论证,协调飞行器总体参数与制导方案,给出高超声速再入飞行器制导/总体参数一体化设计的途径,为再入飞行器的工程研制提供思路. 相似文献
6.
考虑气动加热和变截面惯性矩的高超声速飞行器建模与分析 总被引:1,自引:0,他引:1
由于高超声速飞行器弹性机体/发动机的高度一体化设计,使得此类飞行器的动力学建模与控制较为复杂,而作为控制的基础以及面向控制的总体优化设计都需要建立高精度的动力学模型。首先,建立了考虑气动加热和变截面惯性矩影响的高超声速飞行器自由梁结构弹性模型,分析了气动加热和变截面惯性矩对飞行器振型的影响,得出了气动加热对振型影响非常小且振型引起的攻角变化很小,变截面惯性矩对飞行器的振型影响较大且振型引起的攻角变化较大的结论。然后,建立了考虑气动加热和变截面惯性矩影响的自由梁高超声速飞行器动力学模型,对考虑气动加热和忽略气动加热、恒截面惯性矩和变截面惯性矩对应的动力学模型进行了零极点分布对比分析,得出了气动加热对飞行器的纵向动态特性影响很小,变截面惯性矩自由梁对应的高超声速飞行器在特征点处开环不稳定性更大和非最小相位行为约束变弱的结论。 相似文献
7.
1