In order to study the mechanical performance of the flexible inflated airship working in the stratospheric,two types of inflated saucer-shaped airbag structure,which are separate-curtain and high-pressure air-tube,are researched.A finite-element model for the airbag is established based on the membrane element and nonlinear contact algorithm.Based on this model,the deformation and stress distribution of two types of airbag under the same inflation pressure and load are analyzed and compared.The validity of the simulation analysis is verified by the comparative analysis of the experimental results.The results show that the high-pressure air-tube structure shows better rigidity and more uniform stress distribution with relatively higher inflation pressure of air-tube,which can effectively avoid the failure such as the membrane wrinkles.

With the rapid development of near space hypersonic vehicle,tracking and prediction technology of near space target has attracted wide attention.The main tracking and prediction technologies of near space target are discussed,such as the model of near space hypersonic maneuvering target,the design method of multi-model filter,the trajectory prediction method of near space hypersonic maneuvering target,etc.The main problems of existing methods are pointed out,and the main research directions are given.

Considering the characteristics of the uniform motion of the missile and target before intersection,the target image measured with infrared seeker was used to analyze the passive ranging method based on target image area and target image gray-scale.The target image model was established.Two ranging equations based on image area gradient and image gray-scale gradient were deduced without target parameter.The correctness of the two ranging methods were verified by simulations.These two methods provide references for passive infrared image ranging.

Fousing on the necessary of avoiding the detection of missile by enemy satellites,a calculation method of satellite coverage in space area was firstly discussed. Then, the evaluation index of missile trajectory safety was put forward, and the optimization model of missile trajectory safety path planning was constructed. Based on the analysis of space coverage, a missile flight planning and decision support software system with completely independent intellectual property rights was designed and developed. The architecture and function modules of the software were deeply analyzed.The simulation result proves that the system can make the missile in the monitoring range of introsystem satellite and avoid the detection of enemy satellites, which improve the probability of successful penetration.