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A novel quasi-equilibrium glide auto-adaptive guidance algorithm based on ideology of predictor-corrector is proposed for high lifting entry vehicle. The quasi-equilibrium glide condition based on constant flight path angle is adopted. The vehicle heading is adjusted to firing plane using lateral guidance logic firstly, and then the range-to-go is calculated from the terminal position constraint....
In order to implement depleted shutdown and improve guidance precision in launching process of a solid rocket, the trajectory energy management approaches should be studied. First, the rocket inserting trajectory problem is described. The real velocity and the required velocity calculating model are given. Second, under the multi-restriction conditions, the spline energy management model is given...
A guidance algorithm for spacecraft approaching a target vehicle in a quasi-halo orbit in the real earth-moon system is presented. The algorithm is based on the numerical solution of the time-variant linearized relative dynamics of RTBP in inertial coordinates. The whole trajectory is divided into several segments. The multi-impulse glideslope idea, traditionally used in the near-earth rendezvous,...
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