Font Size: a A A

Sensitivity Of Effected Parameters On Missile Separetion And Research Of Input Paramenters Identification

Posted on:2015-09-11Degree:MasterType:Thesis
Country:ChinaCandidate:H Y LiFull Text:PDF
GTID:2272330422992172Subject:Aerospace engineering
Abstract/Summary:PDF Full Text Request
The missile with socket form of connection is studied in this paper, the guide separation device that has long guided trip and a great chance of collision is installed in the missile characteristics. In the separation process of three-stage rocket and missile warhead, system parameters varying degrees of influence on the separation of the state, According to analyzing the relative attitude of the global sensitivity of each parameter to determine whether the separation state stability or not, identify important design parameters deviation, monitoring the change of parameters.Aiming at missile separation process, create separation kinetics model and collision detection model. Considering the separation rocket impulse is constant value, divide the design range of thrust equally, simulate the separation process under different rocket thrust, and draw the minimum separation distance and the thrust of curve fitting to get the most favorable separation impulse parameter combinations.Analysis the sensitivity of separation parameters in the state of design deviation. Take the relative attitude angle as the objective function, establish the separation system parameter sensitivity models of the relative attitude angle to calculate the degree of influence of each parameter relative attitude of the two bodies, the results show that the degree of influence of each parameter is close, separated state is stable relatively, The results also show that the lateral displacement condition of rocket thrust to the influence degree of the separation process is the largest.To identify the greatest impact on the level of thrust parameter requires acceleration noise filtering firstly. Take speed as intermediation, Based on velocity filtering of identification to achieve the noise filtering of acceleration speed, then identify the thrust and other thrust parameters with the least square method, the results show a low error parameter identification, can meet the precision requirements.
Keywords/Search Tags:Separation, Optimization, Sensitivity Analysis, Parameter Identification
PDF Full Text Request
Related items