The proportional integral differential (PID) controller is improved to meet control system requirements for the boost-glide rocket with difficulty in manual adjusting parameters. A method is proposed that directly takes the simulated results with the nonlinear six-degree-freedom model of the rocket as the objective function value, the genetic algorithm is adopted to adjust parameters adaptively for the global optimal control effect with a given range, and the convergence of the algorithm to search the global optimal value under given conditions is analyzed. This method introduces the measured angular velocity into the differential term of the PID controller, which is convenient to establish the system model and adjust control parameters. Parameter adjustment based on the nonlinear dynamic model can avoid deviations caused by model linearization and facilitate parallel search by genetic algorithm, then reasonable parameters can be quickly obtained with the specified value range. The proposed method is compared with the classical test method in time domain simulation. The simulated results indicate that the proposed method can adjust the parameters adaptively, the maximum deviation of attitude angle is less than 2°, the mean of deviation and the standard deviation of attitude angle deviation are less than 1°, and the control precision is obviously better than that of the classical test method. The experiments from the hardware-in-the-loop simulation show that the attitude control of the selected control parameters is stable, the deviation converges to 0°, and the control effect is good.

The boost-glide rocket needs to maneuver in the atmosphere with complex flight conditions, which is a big challenge for the attitude control system. In this paper, the design process of the control system is analyzed. With specific points of the flight trajectory, the design of an improved proportional-integrative-derivative (PID) controller based on the small perturbation theory is carried out. Design approach of the attitude control system is verified by the six-degree-freedom model simulation. The rocket flight control program is written to the onboard computer so that hardware-in-the-loop simulation experiment is completed. Experimental results show that the mean and standard deviation of the error between simulation value and experiment value are below 0.5°, so the control parameters and design method are reasonable with a great attitude tracking effect. This paper proposes the design and verification method of a boost-glide rocket attitude control system, which can provide a reference for design of the boost-glide rocket around the world.

Based on the missile-target three-dimensional relative motion model, a multi-missile coordinated three-dimensional guidance law with attack time constraints is designed for attacking stationary targets. The sliding mode variable structure control is adopted in the pitch channel, and the dynamic inverse control is adopted in the yaw channel. By maneuvering in the yaw channel, adjusting the missile's attack time and comparing with the results of using augmented proportional guidance, the simulation results show that the algorithm designed in this article can achieve coordinated attack and high hitting accuracy, which verifies the correctness and superiority of the algorithm.

Aiming at the navigation system of small solid rockets, a navigation algorithm test platform with real time simulator and flight control computer is designed. The inertial navigation algorithm is taken as an example to test the effectiveness of the platform. The flight dynamic model of a small solid rocket is established in a real time simulator, and the test is carried out in the working environment of a small test rocket to simplify the model. The acceleration and angular velocity data generated by the simulation is sent to the onboard computer to calculate the attitude of the rocket in real time, which verifies the correctness of the data communication link, real time solution and navigation algorithm between the onboard computer and the real time simulator. The test results show that the test platform is easy to use and can test the rocket navigation algorithm quickly and effectively.