Ballistic Trajectory Planning And Guidance Research For Small Solid Launch Vehicle

The small solid launch vehicle (SSLV) was an important vehicle, which delivered the middle and small satellites into the space. This paper used the SSLV as background, analyzing the issues of ballistic trajectory planning and guidance, discussing the problems about depleted shutdown, orbit injection strategy and guidance of error correction.The method of depleted shutdown based on the energy management was analyzed on the first portion. Sight velocity was used as the independent variable of control on the attitude angles, whose bidirectional adjustment tactic had been deduced, and then the time function of the angles was deduced. The results proved that the impotent influencing factors were the maximum of the attitude angles and the length of attitude angles varying phases. As a result, both of the factors need to be considered in order to obtain the optimum results. Corresponding to the bidirectional adjustment tactic, the unidirectional adjustment tactic, which also used sight velocity as the independent variable of control on the attitude angles, was introduced. It is confirmed that the key factors of this unidirectional adjustment tactic were the sizes of the state and the end of the attitude angles. The two tactics was contrast to recognize that both of these got some kind of advantages, could be chose depending on the concrete situations.The guidance for orbit injection according on the phase plane controlment was explored on the second potion. This guidance could be used in a stated bound, in which the initial statements of the rockets were under constraint. The concept of false target was proposed in order to turn the problem of orbit injection to the issue of the relative movement between the rocket and the false target. Depending on the theory on phase plane, the relative velocity and position became zero at the end of this control tactic. For the sake of simplification, sight velocity was introduced into the analysis results solution.The third potion of the paper was based on the guidance for orbit injection. The integrated optimization design of trajectory/guidance was utilized to correct the errors of the rocket velocity, and then the algorithm of the modified parameter was deduced and proved to be right by simulation. And then, the simulink implement was used to build a flight program on depleted shutdown of the 2rd boost in SSLV and the orbit injection strategy.This paper, which could advise the construction of the SSLV, was studied by the method of theory demonstrate and simulation, possessed the engineering practicability.