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Optimization of projectile state and trajectory of reentry body considering attainment of carrying aircraft 被引量:2
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作者 Changsheng Gao Chunwang Jiang Wuxing Jing 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2017年第1期137-144,共8页
As an improvement of traditional maximum range trajectory optimization, both the projectile state and control sequence of reentry body are optimized to achieve the maximum range. To ensure the optimal projectile state... As an improvement of traditional maximum range trajectory optimization, both the projectile state and control sequence of reentry body are optimized to achieve the maximum range. To ensure the optimal projectile state is in the reachable domain of the carrying aircraft, the climb of the carrying aircraft and the flight of reentry body are optimized as a whole based on the hp-adaptive pseudospectral method. Meanwhile, the path constraints, control constraints and initial/terminal states constraints are considered in the optimization as well. In face of the fact that the range of the optimal control solution resulted from the pseudospectral method may be unsmooth, virtual control variables (second derivatives of the angle of attack and bank angle) are proposed in the optimization, while the angle of attack and bank angle are treated as the virtual state variables to guarantee the smoothness of the optimal control solution. The validity of the virtual control variables in smoothing the optimal control solution is verified by simulation, and the optimality of the resulting projectile state and control sequence for reaching the maximum range is confirmed using the indirect approach. © 1990-2011 Beijing Institute of Aerospace Information. 展开更多
关键词 Aerodynamics angle of attack Optimal control systems PROJECTILES
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BTT autopilot design for agile missiles with aerodynamic uncertainty
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作者 Yueyue Ma Jie Guo Shengjing Tang 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 2015年第4期802-812,共11页
The approach to the synthesis of autopilot with aerody- namic uncertainty is investigated in order to achieve large maneu- verability of agile missiles. The dynamics of the agile missile with reaction-jet control syst... The approach to the synthesis of autopilot with aerody- namic uncertainty is investigated in order to achieve large maneu- verability of agile missiles. The dynamics of the agile missile with reaction-jet control system (RCS) are presented. Subsequently, the cascade control scheme based on the bank-to-turn (B-I-T) steering technique is described. To address the aerodynamic un- certainties encountered by the control system, the active distur- bance rejection control (ADRC) method is introduced in the autopi- lot design. Furthermore, a compound controller, using extended state observer (ESO) to online estimate system uncertainties and calculate derivative of command signals, is designed based on dynamic surface control (DSC). Nonlinear simulation results show the feasibility of the proposed approach and validate the robust- ness of the controller with severe unmodeled dynamics. 展开更多
关键词 agile missile AUTOPILOT high angle of attack active dis-turbance rejection control (ADRC) dynamic surface control (DSC) extended state observer (ESO).
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