Zheng Y.-Q.,The Equipment Research Institute of PLAs Second Artillery |
Kang N.-M.,The Equipment Research Institute of PLAs Second Artillery |
Feng W.-L.,China Institute of Metrology |
Wang Y.-S.,The Equipment Research Institute of PLAs Second Artillery
Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology | Year: 2010
To solve the problem of inertial guidance initial azimuth error's influences on the missile's impact point, the vertical deflection's effects in transferring azimuth datum from ground collimation system to missile's inertial guidance device are presented. Why and how the vertical deflection induces initial azimuth error are studied. The formula for correcting the initial azimuth error are given. Simulation results indicate that vertical angle of theodolite is key to initial azimuth error, and all other factors such as azimuth angle of theodolite, azimuth angle of target, level and vertical errors between corner cube prism and hexahedron, have few effect which can be ignored. When there is a certain vertical deflection, larger vertical angle of theodolite would result larger error, while the theodolite with zero vertical angle can avoid the vertical deflection's influence on inertial guidance azimuth.
Xian Y.,PLA Second Artillery Engineering University |
Xiao L.-X.,The Equipment Research Institute of PLAs Second Artillery |
Li G.,PLA Second Artillery Engineering University
Yuhang Xuebao/Journal of Astronautics | Year: 2010
The ballistic missile with fast mobile launch capability is the important symbol of modern long-range weapon. In this paper, the positioning and orientation scheme of offhand fast launch is submitted, and the perturbation guidance method based on air online data computation is designed. The small computation load and guidance method error of the proposed method can meet the fast launch requirements for ground-based mobile ballistic missile and submarine-launched ballistic missile.
Cheng L.-R.,Tsinghua University |
Cheng L.-R.,The Equipment Research Institute of PLAs Second Artillery |
Shi H.-J.,Tsinghua University |
Chen R.,National University of Defense Technology
Gaoya Wuli Xuebao/Chinese Journal of High Pressure Physics | Year: 2013
In order to solve the difficult problem about the security of warhead in the penetration process, the relationship between damage and hot-spot formation in the charge has been researched. Based on crack friction under mechanical impact, a thermo-viscoelasticity constitutive model for explosive materials coupling the crack damage and hot spot formation is presented to analyze the formation of hot spot in warhead charge during penetration. The influence factors of hot-spot formation under different penetration conditions are discussed and compared. The numerical simulation method provided can be used to design and evaluate the security of loaded projectiles under impact.
Ren N.-L.,Tsinghua University |
Ren N.-L.,The Equipment Research Institute of PLAs Second Artillery |
Zhao X.-Q.,The Equipment Research Institute of PLAs Second Artillery |
Zhang Y.-W.,The Equipment Research Institute of PLAs Second Artillery |
Ma Y.-N.,The Equipment Research Institute of PLAs Second Artillery
Guti Huojian Jishu/Journal of Solid Rocket Technology | Year: 2010
In considering that the micro defects can not be detected with present nondestructive detection methods, PIPA(Photon Induced Positron Annihilation) is introduced. The positrons created by the PIPA process are formed throughout the solid propellant and the defects in solid propellant could be detected by examining the annihilation of the positrons in solid propellant. With this method, the changes of microstructure could be inspected before the macro defects appear. The fundamentals and effects of different factors, including temperature, strain rate and the mechanical properties of solid propellant on the nondestructive detection to solid propellant are described according to the experiment. The results of experiments are coincident with the regular tests, which proves its feasibility in nondestructive detection of solid propellant.