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A numerical optimization study of lifting body re-entry vehicles is presented for nominal as well as shallow entry conditions for Medium and Intermediate Range applications. Due to the stringent requirement of a high degree of accuracy for conventional vehicles, lifting re-entry can be used to attain the impact at the desired terminal flight path a...
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Context 1
... quantity is representative of the total thermal weight. The results are tabulated in Table 1-2. The two set of initial conditions would be referred as nominal entry conditions and shallow entry conditions for the rest of the document. ...
Context 2
... trajectories were obtained for the sharp as well as shallow entry conditions under the heat load and dynamic pressure constraint of the flight envelope. The numerical results for nominal entry are tabulated in Table 1. The trajectory shape for nominal entry conditions is represented in Figure 2 which clearly indicates that none of the flight path constraints is violated. ...
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Citations
... It has been shown in ref. [1] that burn-out angle is a single important parameter on which depends the overall performance, max g-load as well as the integrated heat load. Previous study performed on lifting–body vehicle has shown that for nominal shallow re-entry angle of 20 degree a cross range capability of 240-260 km can be obtained in the intermediate range [2] at re-entry speed of approximately 5 km/s. The re-entry angle was not optimal in that particular case. ...
... The re-entry angle was not optimal in that particular case. The present study is an extension of the trajectory study carried out in ref [2] and is aimed at computing best burn-out angle, which would result in optimal performance of lifting-body vehicle for the launch vehicle under consideration. The lifting-body design has a trim lift-to-drag ratio of close to 1.0 and are capable of limited cross-range capability [2].The trajectory optimization problem of a lifting-body vehicle using a boost vehicle is modeled as a four phase optimal control problem with the objective to compute the best burn-out conditions and the control deflections that would maximize the cross-range of the lifting-body glide vehicle under study. ...
... The present study is an extension of the trajectory study carried out in ref [2] and is aimed at computing best burn-out angle, which would result in optimal performance of lifting-body vehicle for the launch vehicle under consideration. The lifting-body design has a trim lift-to-drag ratio of close to 1.0 and are capable of limited cross-range capability [2].The trajectory optimization problem of a lifting-body vehicle using a boost vehicle is modeled as a four phase optimal control problem with the objective to compute the best burn-out conditions and the control deflections that would maximize the cross-range of the lifting-body glide vehicle under study. The nonlinear optimal control problem is solved using hp-adaptive Pseudospectral method implemented in Gauss Pseudospectral Optimization Software, GPOPS [3]. ...
The multiphase numerical optimization study has been carried out for a 2-stage boost vehicle and small size X-33 type lifting-body reentry vehicle with heat rate and dynamic pressure constraint. The problem has been modeled as a nonlinear, multiphase optimal control problem with the objective to compute the optimum burn-out conditions as well as the best control deflections that would maximize the cross range performance of the boost-glide vehicle under study. The study has been performed using hp-adaptive Pseudospectral method. Comparative performance of the lifting-body vehicle with conventional ballistic missile trajectory has also been carried out. It has been found that for vehicle under study, and near maximum down range, the optimum burn-out angle is 13.6 degree which results in a cross-range of more than 100 km.
