Research On The Rocket Flight Process Simulation Based On Multi-body Dynamic Method

The load and the movement of the vehicle are very complicated during its fighting. The traditional design pattern of the launch vehicle is the serial mode. The design results were list in a sequence. This design pattern artificially separates the factors which affect the flight path at the same time. The factors include gravity, pneumatic, power, ballistic etc.As the current research method did not take full consideration of the interaction between the various disciplines (subsystems), the results is very likely to lose the system’s overall optimal solution, resulting in longer design cycles, higher development costs.To solve this problem, improve design quality, speed up the progress of the design, reduce development costs, it is urgently required of advanced integrated approach to the design of the integration of various disciplines.This paper put forward to a "all-digital simulation methods and model" of the flight path in order to achieve different types of rockets, based on the multi-body dynamics software ADAMS, application of secondary development function to write the rocket flight path simulation software. The main achievements of this paper are as followings:1A comprehensive and systematic analysis has been made of the all kinds of loads of the rocket at the initial phase;2Adams subroutines of mass change, mass center change and the inertia moment changes were developed by FORTRAN language.3The interaction of vibration and the internal structure of the rocket being ignored, a dynamic model of the rocket, including the gravity module, standard atmospheric module, thrust, and control module was established.4Rocket position, speed and acceleration in flying were simulated and analyzed.5The interaction between the position and orientation of the rocket during flight, speed, acceleration and rocket sub-structure with each other, analysis of force in inter-stage rocket separation.This paper firstly developed the integrated simulation methods for rocket flight of mass change, mass center change and the inertia moment change, control force change and aerodynamics. This method is helpful for the rocket design and development.