3 results about "Separation scheme" patented technology

The present application relates to a kind of launch vehicle star rocket separation timing taskless design method.The present application is automatically designed rocket separation timing according to star rocket separation mode, the position and speed of rocket before first star rocket separation, separation speed, the mass of satellite and the total mass of rocket, satellite installation position in rocket, satellite quantity, can avoid using STK software to call rocket orbit UTC time and orbit six root numbers, rocket navigation coordinate system attitude angle such as trajectory parameter for far-field safety analysis, can effectively reduce operation amount and artificial design process, improve work efficiency.Meanwhile, the present method can design the timing of star rocket separation section for different launch tasks, so as to realize the taskless design of star rocket separation scheme.

The present application belongs to the field of aerospace separation technology, and particularly relates to a rocket fairing rotating separation evaluation method. It aims to solve the problem of long cycle and high cost caused by the dependence of traditional fairing rotating separation scheme on high-fidelity simulation and physical test. By simplifying the half fairing as an analysis object of rigid body planar motion, the mass center kinematics and dynamics equations of the half fairing rotating around a fixed point are established. Then, the Runge-Kutta method is used to solve the mathematical model by cyclic iteration to obtain the motion trajectory parameters in the separation process. Finally, the separation motion trajectory is visualized based on the trajectory parameters, and the collision risk is evaluated by analyzing the relative position relationship between the trajectory and the rocket body. Based on the physical simplified model and numerical calculation method, the rapid and safe evaluation of the fairing separation process is realized, which greatly shortens the design verification cycle, and significantly reduces the evaluation cost due to the pure numerical calculation.

This invention provides a direct-thrust missile hood separation method and structure, primarily addressing the problems of added counterweights and complex timing control in existing hood separation schemes. In this invention, the lateral separation velocity is provided by the lateral aerodynamic force generated during hood separation by adjusting the missile's attitude. While ensuring load-bearing and heat protection requirements, the same specifications of separation actuators are used, resulting in a simpler separation structure. The hood separation scheme only requires the separation actuators to provide the specified axial separation velocity, reducing the synchronicity and speed requirements of each actuator during operation, lowering the timing control requirements of the system, and improving the reliability of the separation system.