A Pulse-Jet Control Method of Electromagnetic Projectiles Based on Impact Point Prediction

2021 ◽  
pp. 2037-2047
Author(s):  
Kang Youwei ◽  
Wang Feng ◽  
Liao Xin
2013 ◽  
Vol 401-403 ◽  
pp. 1628-1631
Author(s):  
Zai Ke Tian ◽  
Suo Chang Yang ◽  
De Long Feng ◽  
Yun Zhi Yao

To determine the action angle of is the important topics on Trajectory Correction technology.The pulse force action angle and residual impact point deviation were theoretically analyzed on the basis of traditional control strategy of pulse jets. It has been found that there may be a large residual impact point deviation when the correction ability is different. An optimization strategy for the pulse force action angle control was presented, and the method was verified by the 6-degrees of freedom trajectory simulation.


2020 ◽  
pp. 136943322097179
Author(s):  
Wen-Li Chen ◽  
Yan-Jiao Guo ◽  
Xiang-Wei Min ◽  
Hui Li

Two tandem cables are frequently employed as one group of hangers in a long-span suspension bridge; however, if they are close to each other, the mutual interaction between their flow fields is prone to produce large wind/wake-induced vibrations. In the present study, initially, a numerical simulation was conducted to investigate the interaction between two static tandem cable models with different spacing ratios, SR (center-to-center longitudinal spacing divided by the cable diameter, i.e. L/D). Concurrently, the passive-suction-jet control method was employed to eliminate the interaction of these two tandem cables. Aerodynamic coefficients and time-averaged and instantaneous flow fields were used to evaluate the effectiveness of the passive-suction-jet control. Subsequently, the passive-suction-jet control method was employed in a wind tunnel experiment to manipulate the wind-induced vibrations of two elastically mounted cable models. The flow patterns of the controlled tandem cables were subdivided into three basic regimes in the present study. Furthermore, the aerodynamics force suppression mechanism was explained based on the flow patterns. Both the aerodynamic forces and vibration responses of the tandem cable models reduced significantly when SR >  SRc (critical spacing ratio). Particularly for SR = 4.0, the lift fluctuation reduction of both the cable models was remarkable, the fluctuating lifts of the upstream and downstream cable models decreased by 93.3% and 72.1%, respectively, and the vortex-induced vibration responses decreased by 31.4% and 54.0% respectively. Furthermore, the wake-induced vibration responses of the tandem cable models could be completely suppressed when both were controlled using passive-suction-jet pipes.


2014 ◽  
Vol 513-517 ◽  
pp. 3900-3906
Author(s):  
Guo Wei Zhao ◽  
Bin Tang ◽  
Liang Sun ◽  
Xing Min Zhang

As a kind of typical on-orbit capture and aberrance technology, space tether de-orbit system has broad application prospect in terms of cleaning space debris and abandoned satellites. In the paper, the attitude dynamics equations of the tether de-orbit system is established based on law of moment of momentum; Against the background of de-orbiting under a constant thrust in the tangential direction, the optimized PD control law with limited attitude feedback on jet control and momentum wheel control is designed for the mission satellite; The oscillation characteristics of the attitude of abandoned satellite are studied, and the effect of the oscillation on the tethered system and based satellite are analyzed; According to the demand for maintaining the position and suppressing the oscillation of the abandoned satellite, a kind of tension control method is put forward. Numerical simulation results indicate that the abandoned satellite oscillates at a specific angular frequency, and the large amplitude threatens the stabilization of tethered system; the designed tension control method effectively eliminate the oscillation of the abandoned satellite and ensure the flight safety of the tether de-orbit system, with economic energy consumption for the control of the based satellite.


1999 ◽  
Author(s):  
S. Raghunathan ◽  
J. Watterson ◽  
R. Cooper ◽  
S. Lee
Keyword(s):  

2015 ◽  
Vol 119 (1213) ◽  
pp. 389-405 ◽  
Author(s):  
M. Pavic ◽  
B. Pavkovic ◽  
S. Mandic ◽  
S. Zivkovic ◽  
D. Cuk

AbstractThe impact point dispersion of mortar missiles can be drastically reduced with a control ring of lateral pulse jets located around the centre of gravity and a homing head to measure or to derive estimates of appropriate missile-target states, e.g. the line-of-sight rates. A simulation model including a missile as a six-degree-of-freedom vehicle, a jet pulse flight control system, and a relative missile-to-target motion was used for the comparison of four guidance laws i.e. proportional navigation guidance, augmented proportional navigation, augmented proportional navigation with rendezvous, and adaptive sliding-mode guidance. This paper focuses on the efficiency of pulse jet control on miss distance, and thus makes the assumption that sensor measurements and the guidance states required to apply each of the guidance laws are perfectly known. Proportional navigation and the adaptive sliding mode guidance exhibit a large miss distance due to limited control authority. Augmented proportional navigation is slightly better than augmented proportional navigation with rendezvous for the same design parameters and they both give small miss distances with limited control authority, but they both require a free gyro. A proper selection of the design parameters — the number of pulse jets and the magnitude of the individual pulse jet thrust for a particular dispersion of flight parameters and the instant of the guidance start — is required to achieve optimum dispersion reduction. The minimum intensity of the individual pulse jet impulse required for the ‘pin point’ accuracy (the circular error probable smaller than 1m) of the mortar missile was determined for all presented guidance laws considering dispersion from the nominal trajectory.


2012 ◽  
Vol 49 (2) ◽  
pp. 286-294 ◽  
Author(s):  
Bojan Pavkovic ◽  
Milos Pavic ◽  
Danilo Cuk
Keyword(s):  

2021 ◽  
Author(s):  
Zhen Yang ◽  
Jian Fu ◽  
Liangming Wang ◽  
Zhi Chen
Keyword(s):  

2012 ◽  
Vol 591-593 ◽  
pp. 1285-1288
Author(s):  
Yue Yue Ma ◽  
Sheng Jing Tang

This paper focuses on agile turn control for air-to-air missile flying in the horizontal plane. The attitude dynamics is discussed and variable structure control (VSC) method for attitude control is analyzed. After analysis of the dynamic function about velocity angle, a staged control method using VSC based on reaction jet control system (RCS) is proposed to achieve fast change of velocity direction and attitude in a short time. The simplex method is used for trajectory optimization. The simulation results show the feasibility of the staged control method which makes the missile turn faster than the situation of attitude control method. The new method demonstrates that RCS is able to control the missile to realize 180°change both for the velocity angle and attitude angle.


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