Launch window planning method for near-earth target interception

A launch window and target technology, applied in the aerospace field, can solve the problems of the plane model being too simple and unable to meet the window planning requirements, and achieve the effect of emergency and rapidity.

Active Publication Date: 2021-02-12
BEIJING INSTITUTE OF TECHNOLOGYGY
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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 C

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Embodiment 1

[0050] The target orbit height is H=500km, the longitude of the launch point on the ground is 102°, the latitude is 28.5°, and the mission time interval T is selected S =[2021 / 01 / 01~2021 / 01 / 03], record the number of orbital elements, the semi-major axis is a, the eccentricity is e, the orbital inclination is i, the right ascension of the ascending node is Ω, the argument of perigee is ω, true near The point angle is f, and the number of target orbital elements is selected as shown in Table 1.

[0051] Table 1 Number of target orbits at 500km altitude

[0052]

[0053] The present invention provides a launch window planning method for near-earth target interception, such as figure 1 As shown, the specific implementation steps are as follows:

[0054] Step 1: Determine the flight duration range of the interceptor according to the altitude of the intercepted target.

[0055] The dynamic model of the ascent segment of the aircraft is

[0056]

[0057] Among them, state q...

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Abstract

The invention relates to a launch window planning method for near-earth target interception, and belongs to the technical field of aerospace. The method is particularly suitable for calculation of a launch window for intercepting a low-mid-orbit near-earth target by an aircraft taking off on the ground. The method comprises the steps of firstly determining a total flight duration range of an interceptor from taking off on the ground to interception according to an orbit height of an intercepted target; secondly determining an outer boundary of a range which the interceptor can reach accordingto a maximum flight duration of the interceptor; thirdly determining a quasi launch window based on the outer boundary of the range which the interceptor can reach and the flight duration range; fourthly dividing the flight duration range, and solving an annular range which the interceptor can reach and corresponds to each flight duration point; and finally obtaining an accurate launch window according to a crossing relationship between a target sub-satellite point and each annular range.

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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Application Information

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IPC IPC(8): F41H11/02
CPCF41H11/02
Inventor 温昶煊贾飞达庞博韩宏伟
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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