Compared with traditional design optimization method,MDO method can gain the optimum design for flight vehicle as well as the optimum thrust-time curves of booster.

For it's excellent performance, Rocket-Based-Combined-Cycle (RBCC) should be the most competitive propulsion system of Hypersonic Flight Vehicle for martial and civil purpose.

The flowfield around a hemisp here and a flatnosed cylinder in the shock tube is simulated numerically by using nonequilibrium NavierStokes equations with a n air chemical model of 5 species 17 reactions, and the catalytic rate constant of surface materials such as Pt, SiO2, Ni and a flight vehicle materials is de termined by using the heat transfer rate of testing in the shock tube and the di stribution of heat transfer rate along with the catalytic rate constants.

The asymptotic technical stability conditions for the nonlinear controllable motion of an elongated elastic flight vehicle are formulated.

Asymptotic Technical Stability in Measure of the Nonlinear Controllable Motion of an Elastic Flight Vehicle

Influence of vibrocavitation on physicochemical properties of fuel in flight vehicle systems

Most of these demand a high-fidelity aerodynamic database representing the flight vehicle.

Numerical and experimental techniques are used to model the flow and pressure distribution around the forebody of the HYFLEX hypersonic flight vehicle.

Since the action of actuators on flexible flight vehicles is an important exciting source to elastic vibration, it is of practical significance to choose appropriate positions for actuators as well as for sensors. We shall in this paper study optimal positions of rate gyros and elevators that are modelled as lumped operating elements, Through the feedback control, a term (B1 GH1)q is introduced to the system to count for the damping force, where B1 is a control matrix, relying on the actuator locations,...

Since the action of actuators on flexible flight vehicles is an important exciting source to elastic vibration, it is of practical significance to choose appropriate positions for actuators as well as for sensors. We shall in this paper study optimal positions of rate gyros and elevators that are modelled as lumped operating elements, Through the feedback control, a term (B1 GH1)q is introduced to the system to count for the damping force, where B1 is a control matrix, relying on the actuator locations, and H1 is a measurment matrix depending on the gyro locations. An effective damping matrix Da is defined in ( 5 ),and then Rayleigh' s dissipation function can be obtained as F=1/2qrDcq.In order to make the system having most damping effect to vibration, the actuators and sensors are so positioned that the effective damping force (aF/eq) could be maximized.Because of its real symmetry, Dc can always be diagonalized. In accor-dance, suppose that , the elastic motion willbe decelerated by force bkqk, if bk< 0 , the motion will be decelerated by force bkqk, if bk< 0 , the motion will be accelerated. That is, the forcesderived from F may be either dissipating or accelerating. Whenit is thought that the dissipating force is leading to the accelerating one.Since the trace of a matrix will not be changed by a normal transfor-mation, we have . Then a new performance index is defined by (12). The problem under consideration is to determine the positions of actuators and sensors so that index (12) is maximized.In general, the same results can be obtained from Lagrange's dynamic equations.A simple condition has been studied. Through analysis, we have derived a set of simple and practical formulae (7) and (8) that give the very positions at which the effective damping force is always dissipating. By applying formulae ( 7 ) and ( 8 ) to a given missile, it is shown that the present position of the elevator is suboptimal and is 0.06m away from the optimal position.

Dryden model is Usually used in studying the response of flight vehicle to atmospheric turbulence. For a modern flight simulator, it is necessary to generate random winds(in Dryden model or sometimes others) with a digital computer. In this paper, a theoretically stricted new method to meet this purpose is proposed. By this method, we can acquire a three-dimensional atmospheric turbulence which contains three components of wind velocity and three components of wind velocity gradient. The reliability...

Dryden model is Usually used in studying the response of flight vehicle to atmospheric turbulence. For a modern flight simulator, it is necessary to generate random winds(in Dryden model or sometimes others) with a digital computer. In this paper, a theoretically stricted new method to meet this purpose is proposed. By this method, we can acquire a three-dimensional atmospheric turbulence which contains three components of wind velocity and three components of wind velocity gradient. The reliability of this method is checked by comparing with the autocorrelation value obtained from the theoretical autocorrelation value. A numerical example has shown a satifactpry result. Finally, some proposals about how to use this mathematical model in flight simulator are given.

The present paper reviewed briefly some developmest courses of solid mechanics and showed the close relationship between the development of . solid mechanics and its applications to engineerings. The Flight Vehicle Strength, as an application of solid mechanics to aeronautical and mis sile structures, is discussed. Particularly, discussions on some important aspects of the Flight Vehicle Strength much as the Mechanics of Composite Materials, Computational Mechanics, Active Suppression on Flutter,...

The present paper reviewed briefly some developmest courses of solid mechanics and showed the close relationship between the development of . solid mechanics and its applications to engineerings. The Flight Vehicle Strength, as an application of solid mechanics to aeronautical and mis sile structures, is discussed. Particularly, discussions on some important aspects of the Flight Vehicle Strength much as the Mechanics of Composite Materials, Computational Mechanics, Active Suppression on Flutter, Safety and Reliability of Structures, and Fatigue and Fracture, are given. The present paper aims at the investigation and study of the state-of-the-art of branches described about and trying to predict the possible research trends.