Analysis reentry guidance method considering restraint of multiple no-fly zones

A re-entry guidance and no-fly zone technology, applied in aerospace technology and weapons fields, can solve problems such as difficulty in re-entry guidance design for gliders

Active Publication Date: 2018-08-10
BEIHANG UNIV
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Problems solved by technology

This brings difficulties and challenges to the design of gliding vehicle reentry guidance

Method used

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  • Analysis reentry guidance method considering restraint of multiple no-fly zones

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Embodiment example

[0396] 1. Verify the accuracy of the new analytical solution

[0397] The accuracy of the new analytical solution is now verified in a rotating Earth environment. Here, five different flight directions are considered, and the following reference profiles are planned. Unlike ballistic planning and guidance, no desired end positions are given here. Therefore, in order to calculate the coefficients in formulas (14)-(17), it is necessary to call an analytical solution that does not consider the earth's rotation to roughly estimate the terminal state, and then use the analytical solution that considers the influence of the earth's rotation to accurately predict the trajectory.

[0398] L 1 / D=-0.427(E / 10 7 ) 2 -3.587 (E / 10 7 )-4.82 (72)

[0399] L 2 / D=-0.427(E / 10 7 ) 2 -3.587 (E / 10 7 )-8.62 (73)

[0400] Simulation results such as Figure 13–14 shown. For comparison, the results of ballistic simulation are also given here. The results show that the accuracy of the an...

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Abstract

The invention discloses an analysis reentry guidance method considering the restraint of multiple no-fly zones. To overcome the influences from earth rotation, conventional aerodynamic force and inertia force caused by earth rotation are combined into equivalent aerodynamic force. Then, the longitudinal range analytical solution is utilized for planning the equivalent longitudinal lift-drag ratioprofile, and accordingly, the longitudinal range and energy management requirements are met; the transverse range analytical solution is utilized for planning the equivalent transverse lift-drag ratioprofile meeting the no-fly zone restraint and transverse range requirements. An inverted point gradual increasing type analysis iteration planning strategy is designed and comprises a plurality of analysis methods which are used for solving the flight track point, closest to the no-fly zones, on the track, adjusting existing inverted points for avoiding the no-fly zones, increasing the inverted points to avoid the no-fly zones and planning the inverted points to eliminate the terminal course error. Iteration starts from two times of inversion, and then the number of inversion times is gradually increased according to the no-fly zone avoiding requirement. In addition, since the planning strategy is completely based on the analytical solutions, the planning strategy is extremely high in planning efficiency and can be executed online.

Description

technical field [0001] The invention relates to an analytical reentry guidance method considering the constraints of multiple no-fly zones, and belongs to the fields of aerospace technology and weapon technology. Background technique [0002] Hypersonic gliding vehicles are generally sent to a predetermined altitude by booster rockets, and then re-enter the atmosphere from orbit or suborbit without power. In order to obtain long-range flight capability and strong lateral maneuverability, aircraft usually adopt a lift body structure with a large lift-to-drag ratio. However, aircraft sometimes need to avoid some politically sensitive areas and military threat areas. This poses a serious challenge to the design of the reentry guidance law for two reasons. First, due to the unpowered gliding, the reentry guidance law needs to carefully manage the energy of the aircraft in the harsh mechanical and thermal environment and guide the aircraft to fly to target, which prevents the a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F41G3/22G06F17/50
CPCF41G3/22G06F30/20
Inventor 陈万春余文斌张晚晴
Owner BEIHANG UNIV
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