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High-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on drag profile

A technology with high lift-to-drag ratio and reentry guidance, applied in the fields of weapons and aerospace technology, can solve the problems of tracking error and low accuracy

Active Publication Date: 2018-04-20
BEIHANG UNIV
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Problems solved by technology

However, most of the analytical solutions for the gliding distance are not accurate in the background of the rotating earth due to ignoring the inertial force caused by the earth's rotation, and there are tracking errors

Method used

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  • High-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on drag profile
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  • High-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on drag profile

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Embodiment example

[0250] In order to verify the accuracy of the algorithm, the CAV-H is used as the reentry vehicle model to carry out simulations under seven different target states. Reentry initial state is h 0 = 80km, V 0 =7000m / s, λ 0 = 0°, θ 0 = 45°, γ 0 = 0°. ψ 0 Take the value according to the target direction. Ballistic damping feedback term coefficient K γ =5. terminal bound to V f =2000m / s, h f =25km, projectile distance R tm ≤5km. Terminal heading angle error |Δψ f |≤5°. Simulation results such as Figure 7-Figure 10 .

[0251]

[0252] table 3

[0253] Figure 7 In , from left to right in the counterclockwise direction, there are seven different target positions, namely from northwest to northeast. Figure 8-Figure 10 Table 3 and Table 3 (terminal state quantities) show that the ballistic damping control technology can control the aircraft to successfully suppress the ballistic oscillation in different target states and accurately hit the target. Taking the tar...

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Abstract

The invention relates to a high-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on a drag profile. The method comprises the following steps that the first step, modeling ofa hypersonic flight vehicle is conducted; the second step, gliding distance analytic solution derivation is conducted; the third step, reentry track planning and tracking guidance are conducted; and the fourth step, a stable gliding trajectory tilt angle based on an earth rotation model is derived. The high-lift-to-drag-ratio hypersonic stable gliding reentry guidance method based on the drag profile has the advantages that a gliding distance analytic solution which is higher in accuracy and is based on energy is obtained, the form is simple, and application is convenient; the drag profile isplanned by using the energy as an independent variable, the drag profile is converted into the longitudinal lift-to-drag ratio under the rotating earth background, then a heeling angle is adjusted, tracking is conducted under the condition of the maximum lift-to-drag ratio, and transverse movement is controlled by a course error threshold; and in order to solve the reentry trajectory oscillation problem, the stable gliding trajectory tilt angle based on the earth rotation model is derived, and a trajectory damping technology using the stable gliding trajectory tilt angle as the feedback item is adopted to restrain oscillation.

Description

technical field [0001] The invention relates to a high-lift-drag ratio hyper-smooth gliding reentry guidance method based on a drag profile, belonging 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. [0003] Reentry flight is a multi-constraint problem, which has the characteristics of variable tasks, long flight time, large changes in speed and position, and severe changes in the flight environment. This brings difficulties and challenges to the design of gliding vehicle reentry guidance. The standard orbital guidance law is guided by tracking the standard trajectory, which is characterized by a small amount...

Claims

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Application Information

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IPC IPC(8): F41G3/22B64G1/24G06F17/50
CPCB64G1/242F41G3/22G06F30/15
Inventor 陈万春张晚晴余文斌
Owner BEIHANG UNIV
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