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Collaborative analysis reentry guidance method considering multiple no-fly zone constraint

A re-entry guidance and no-fly zone technology, applied in the fields of guidance and control, weapon technology, and aerospace technology

Active Publication Date: 2019-03-22
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the problem that there is no effective response to the cooperative formation flight of hypersonic glide vehicles at present, and propose a cooperative analytical reentry guidance method considering the constraints of multiple no-fly zones to solve the problem of guidance in multiple no-fly zone environments. Coordinated flight problem of multiple hypersonic glide vehicles arriving at the target at the same time

Method used

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  • Collaborative analysis reentry guidance method considering multiple no-fly zone constraint
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  • Collaborative analysis reentry guidance method considering multiple no-fly zone constraint

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Embodiment 1

[0366] In this embodiment, the time-of-flight analytical solution of the present invention is compared with traditional methods and numerical ballistic simulation results to verify the prediction accuracy of the time-of-flight analytical solution of the present invention.

[0367] The flight time formula under the condition of constant longitudinal lift-to-drag ratio in Document 2 is

[0368]

[0369] Set the initial longitude λ of the aircraft 0 =0deg, initial latitude φ 0 =50deg, initial energy E 0 =-3.8602×10 4 kJ / kg and terminal energy E f =-5.5×10 4 kJ / kg. Consider 5 different flight directions: ψ 0 =100deg, 180deg, -100deg, 20deg, -20deg. Set the vertical lift-to-drag ratio in Document 2 as The lateral lift-to-drag ratio is

[0370] The simulation results are shown in Table 1. It can be seen from the simulation results that due to the influence of the earth's rotation, the flight time of the aircraft in different directions is not the same, but the analyt...

Embodiment 2

[0374] This embodiment is an ideal non-interference situation, and solves the coordinated flight problem of guiding multiple hypersonic glide vehicles (V1, V2, V3) to launch from different locations but arrive at the same target at the same time in a multi-no-fly zone environment. 64 circular no-fly zones with a radius of 200km are arranged in the flight area. The initial conditions of the aircraft are shown in Table 1, and the position of the target point is the longitude λ T =130deg, latitude φ T =-20 deg. Using the multi-aircraft arrival time coordination scheme in step 7, t can be selected TAEM =2900s, and determine the re-entry starting time of each aircraft, which are 109.29s, 358.69s and 751.62s respectively.

[0375]

[0376] Table 2

[0377] In the reentry stage, the horizontal distance from the aircraft to the target is S TAEM = Terminate at 50km. At this point the desired terminal height is H TAEM =25km, the terminal speed is V TAEM =2000m / s, terminal head...

Embodiment 3

[0380] In this embodiment, Monte Carlo simulation is used to verify the robustness of the guidance method of the present invention under the condition that the aircraft model is deflected. Among them, the aerodynamic coefficient adopts the following linear pull-off model

[0381]

[0382]

[0383] Among them, δ CL and δ CD are the pull-off percentages of the lift coefficient and drag coefficient, respectively, which vary with the angle of attack α and the Mach number Ma. δ CL0 , is the associated zero-mean normally distributed random parameter. The wind and atmospheric density perturbation model is as follows

[0384]

[0385]

[0386] δ ρ =k ρ δ ρ(max) (130)

[0387] in, is the wind speed in the east-west direction, is the wind speed along the north-south direction, δ ρ is the percentage of atmospheric density pull. V wind(max) It is the maximum possible wind speed, which varies with height and can reach 170m / s at high altitude. δ ρ(max) It is ...

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Abstract

The invention relates to a collaborative analysis reentry guidance method considering multiple no-fly zone constraint, which comprises the steps of 1, describing a reentry guidance problem; 2, providing an analytic solution of flight time based on a rotational globe model; 3, carrying out an analytic reentry guidance process considering multiple no-fly zone and arrival time constraint; 4, providing a multi-aircraft arrival time collaboration scheme. The method herein has the advantages that an exact analytic solution of hypersonic gliding trajectory flight time based on the rotational globe model, and a prediction error is kept less than 3% to adapt to conditions with non-constant vertical lift-drag ratio profile; the problem with collaborative flight allowing multiple hypersonic gliding aircrafts to be guided to arrive at a target at the same time in a multiple no-fly zone environment is solved on the basis of the analytic solution of three-dimensional reentry trajectory and the analytic solution of flight time; a multi-target numeric iteration plan based on online trajectory simulation considering terminal time, speed and height requirements is designed. A directional derivativeis sued to modify the quasi-newton method, and the quantity of trajectory simulations is decreased.

Description

technical field [0001] The invention relates to a collaborative analytical reentry guidance method considering the constraints of multiple no-fly zones, and belongs to the fields of aerospace technology, weapon technology, and guidance control. Background technique [0002] Coordinated formation flight technology is of great significance for improving the combat effectiveness of the system and has broad application prospects. It has been extensively and in-depth researched in the field of unmanned aerial vehicles. However, for hypersonic glide vehicles, formation flight is very difficult. Because such vehicles have high initial velocities but are unpowered, flight energy needs to be precisely managed through appropriate lateral maneuvers. However, for aircraft with different take-off states and different degrees of interference, their speed decay curves and lateral maneuvering ranges are different, so it is difficult to form a relatively stable flight formation. [0003] I...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/104G05D1/105
Inventor 陈万春余文斌赵鹏雷
Owner BEIHANG UNIV
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