标题： 带有姿态运动学约束的最小辐射热与推进剂气动捕获制导 显示英文标题

标题： Minimum Radiative Heat and Propellant Aerocapture Guidance with Attitude Kinematics Constraints

摘要： 气动捕获利用大气阻力将航天器的双曲线轨道转化为受束缚的轨道。 对于某些气动捕获任务，由于激波层高温气体辐射产生的加热可能远大于对流导致的加热。 本文提供了分析证明和数值验证，表明辐射热负荷通过最小化最终{\Delta }V 的同一轨迹达到最小值：一种从抬升开始的单切换bang-bang轨迹。该证明非常通用，并且适用于多种辐射热流公式；此外，相同的证明可以用来得出结论，根据许多可用的公式计算的对流热负荷反而由该轨迹最大化。 此外，引入了一种新的制导方法，计划具有姿态动力学约束的bang-bang轨迹。虽然性能与当前最先进的方法相当，但姿态动力学中的约束包含允许更少的调整。 最后，引入了一种横向制导，利用预测轨迹的最终倾角信息。这种制导通过要求调整单一参数，能够在倾角需求方面实现非常高的精度，只需两次反转即可。 显示英文摘要

摘要： Aerocapture leverages atmospheric drag to convert a spacecraft's hyperbolic trajectory into a bound orbit. For some aerocapture missions, heating due to the radiation of high temperature gases in the shock-layer can be much larger than the heat due to convection. This paper provides analytical proof and numerical validation that radiative heat load is minimized by the same trajectory that minimizes the final {\Delta} V: a single switch bang-bang trajectory, starting with lift up. The proof is very general and is valid for several formulations of radiative heat flux; further, the same proof can be used to conclude that convective heat load, computed according to many of the available formulations, is instead maximized by that trajectory. Further, a novel guidance that plans a bang-bang trajectory with constraints in the attitude kinematics is introduced. While achieving performance similar to that of the current state-of-the-art, the inclusion of constraints in attitude kinematics allows for much less tuning. Finally, a lateral guidance that makes use of information on the final inclination of the predicted trajectory is introduced. Such guidance allows for very high accuracy in the inclination requirements with only two reversals, by requiring a single parameter to be tuned.