A Launch Window Planning Method for Intercepting Near-Earth Targets

Abstract

The invention relates to a launch window planning method aimed at intercepting near-earth targets, and is especially suitable for calculation of launch windows for an aircraft taking off from the ground to intercept mid-low orbit near-earth targets, and belongs to the technical field of aerospace. The present invention firstly determines the total flight time range of the interceptor from ground take-off to interception according to the orbit height of the interception target; then determines the outer boundary of the reachable range according to the maximum flight time of the interceptor; then based on the outer boundary of the reachable range and the flight duration range Determine the quasi-launch window; then divide the range of flight duration, and solve the reachable ring range of the interceptor corresponding to each flight duration point; finally, obtain the precise launch window according to the crossing relationship between the target sub-satellite point and each ring.

Description

technical field [0001] The invention relates to a launch window planning method aimed at intercepting near-earth targets, and is especially suitable for calculation of launch windows for an aircraft taking off from the ground to intercept mid-low orbit near-earth targets, and belongs to the technical field of aerospace. Background technique [0002] Near-Earth space is an important place for human beings to carry out activities such as communication, monitoring, and navigation. It has always been the resource object that various countries strive for. Accurate interception of targets in near-Earth space is an effective means to ensure the safety of near-Earth space. There are a large number of aircraft in the near-Earth space all the time. When there are space objects that have been abandoned or threaten their own safety, they need to be intercepted and cleared in time. The key technology is the rapid planning and interception of the target, and the determination of the launc...

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Problems solved by technology

[0003] Prior art [1] (see Hu W, Yang J J. Modeling and Simulation of the TBM Post-boost Interception Time Window [J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010,30 (3): 181-184.) have studied the influence of factors such as the flight speed of the interceptor bomb and the interception height boundary on the interception time window, but the plane model it uses is too simple; the prior art [ 2] (See Jing Wuxing, Li Luogang, Gao Changsheng. Anti-missile interception flight plan and time window fast search algorithm [J]. Systems Engineering and Electronic Technology, 2013, 35(6): 1256-1261.) proposed a method based on iteration The least squares flight plan and the fast search design algorithm of the launch time window, but the initial state needs to be guessed, and the obtained window is a discrete point at a specific time, which cannot meet the window planning requirements

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