CAJ | 학술논문

重复使用运载器亚轨道再入段一般采用航天飞机应急返回发射场的飞行方案,分三个阶段:迎角恢复段、过栽保持段和过渡段.该方案的难点是抑制动压,缺点是只有开环制导.分析了动压变化的影响因素,制订了抑制下沉率的制导策略,并给出迎角和过载指令的设计方法.其次分析初始状态偏差和气动升力/阻力系数偏差对动压的影响,提出了根据初始高度调整制导指令和根据下沉率进行过载指令补偿的闭环制导方案.仿真表明设计的轨迹能够满足飞行约束,闭环制导能有效减小最大动压偏差.
중복사용운재기아궤도재입단일반채용항천비궤응급반회발사장적비행방안,분삼개계단:영각회복단、과재보지단화과도단.해방안적난점시억제동압,결점시지유개배제도.분석료동압변화적영향인소,제정료억제하침솔적제도책략,병급출영각화과재지령적설계방법.기차분석초시상태편차화기동승력/조력계수편차대동압적영향,제출료근거초시고도조정제도지령화근거하침솔진행과재지령보상적폐배제도방안.방진표명설계적궤적능구만족비행약속,폐배제도능유효감소최대동압편차.
The guidance technique of suborbital reentry for reusable launch vehicle (RLV) is based on shuttle's gliding return to launch site (GRTLS).The flight uses open-loop guidance and includes three sequential phases:Alpha Recovery,Nz Hold and Alpha Transition.The main point is to reduce dynamic pressure.The factors contributed to dynamic pressure rate are analyzed,and the guidance strategy is designed to arrest the sink rate.The methods of both alpha and Nz commands design are also given.A close-loop guidance method is proposed to adjust the alpha and Nz commands based on keeping the maximum dynamic pressure near that of the nominal when initial altitude and aerodynamic are uncertain.The simulation results show that the flight constraints are well satisfied.