Study Of Maneuvering Technology For Hypersonic Gliding Vehicle

Hypersonic gliding vehicle has the capability of large downrange and cross range, it can land precisely with a prescribed position, reach a long-range quickly and deliver a load precisely with a large scope of height and velocity, which make it the reasearch focus about the hypersonic vehicle at present.This paper focuses on hypersonic gliding vehicle. The technology that influences the manuverability of hypersonic gliding vehicle is studied and discussed, such as the aerodynamic design, dynamic characteristic, bank-to-turn control, the design of control face, trajectory optimization and etc. The elementary concept model of a new hypersonic gliding vehicle is established.In the aerodynamic design and analysis, the generation method of waverider is studied. The cone derived waverider is chosen as the reference configuration for gliding vehicle. A new generation method based on reshaping of boundary layer is put forward, which is verified through CFD techniques. The reshaped configuration has a higher lift-to-drag ratio than the original configuration. Consiedeing the engineering consideration such as lift-to-drag ratio, volume, volume efficiency and the position of pressure, the waverider is optimized with improved differential evolutionary algorithm. For the purpose of pratical use, the blunting the leading edge's influence on the aerodynamic/aerothermodynamic performance of waverider is studied. When designing the waverider, one should consider both the aerodynamic and aerothermodynamic factors to select an appropriate blunt radius.The dynamic characteristic of hypersonic gliding vehicle is studied. The generation mechanism of dynamic derivatives is analyzed and a calculation method is put forward. The phugoid dynamics of the hypersonic gliding vehicle is studied, which show that the equilibrium gliding is the fixed state of the renerty trajectory, when the initial states do not satisfy equilibrium glide condition or perturbation occurs, a damped oscillation along the equilibrium glide trajectory, viz. skip trajectory, could be observed. The characteristic parameters such as the damping and the number of oscillations are analyzed. The dynamics of angle-of-attack is studied based on a typical reentry trajectory; the damping, period of the oscillation is studied. To improve the damping characteristic, a pitch damper is designed. The damper's influence on aerodynamic parameter and dynamic characteristic are studied. The damper provides an effective way to improve the damping characteristics of the waverider, which can be referenced in similar designs.A collectivity aerodynamic configuration with embed control faces, all-moving wing and reaction control system was designed. The trim characteristic of the designed configuration is analyzed, due to its unique aerodynamic characteristic, the centroid of the whole vehicle could be placed at the rear part of the vehicle, and the stability is achieved through the trim contral faces, which improve the usage of the volume. The aerodynamic analysis shows that the vehicle retains the good aerodynamic efficiency after the control faces are introduced. The parameters of the all-moving wing and the embed control faces' influence to the aerodynamic characteristic is analyzed. The main contributions of the introduced wings are the control ability and trim efficiency.An Bank-to-Turn control system for hypersonic gliding vehicle is designed. The control model is established, the control system is based on trajectory linearization control method. Considering the characteristic of multi-control-faces, a control allocation method based on optimized minimum deflection angle is studied. The bank-to-turn parameters are analyzed. A nonlinear disturbance observer is used to estimate the uncertainties and integrated with the TLC method, which improve the efficiency of the controller. A state observer based on trajectory linearization method is introduced and integrated with TLC. The observer error is found to be exponentially stable and simulation results verify the excellent performance and robustness of the proposed method, the method also reduces the requirement of the actuator of the controller.The maneuver trajectory optimization method for hypersonic gliding vehicle is studied; the flight dynamic model was set up, considering the rotation of the earth, reentry path constraints and terminal constraints. A direct method based on Akima spline interpolation is proposed and simulation results verify the validity of the method. A multiresolution technique that based on the grid self adapting was applied to trajectory optimization; the corresponding tactic deal with the waypoint constraint is suggested. A practical trajectory optimization application that including waypoint, no-fly zones and terminal constraints is presented. Finally, the optimized trajectory and designed control system is integrated and simulatied. The uncertainty of the aerodynamic parameter and the measurement error are introduced respectively to study the efficiency of the control system. The simulation results show trajectory optimization method is effective and the control scheme is reasonable.This dissertation focuses on the key technology relative to the manuverability of hypersonic gliding vehicle. The theoretical researches in this dissertation sustain the aerodynamic design, trajectory optimization and the control design for hypersonic gliding vehicle, which is a good reference to the development of the new type of hypersonic glide-reentry vehicle in the future.