Air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint

A speed process, multi-terminal technology, applied in aerospace technology and weapons fields, it can solve the problems of less consideration of speed control, complicated preparation work, and inability to deal with battlefield environment.

Active Publication Date: 2014-08-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this guidance method has two shortcomings: first, it needs to calculate the reference trajectory in various situations off-line, the preparation work is complicated, and it cannot cope with the complex and changeable battlefield env

Method used

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  • Air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint
  • Air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint
  • Air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint

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Example Embodiment

[0159] Examples:

[0160] In order to verify the performance of the guidance law for the gliding section mentioned above, the Tomahawk cruise missile is selected as a model here. The missile has a mass of 1204.54Kg, a firing Mach number of 0.6 to 0.7, a height of 0.5km to 4km, a ballistic angle of 0deg, and an angle of attack of 2deg to 6deg. The maximum airspeed of the flight is limited to 0.9Ma, the launch speed is from 0.6Ma to 0.9Ma, the possible launch altitude is 1km to 13km, and the ballistic inclination during launch is 0deg. The aerodynamic data of the missile is solved by the aerodynamic estimation software Datcom, the aerodynamic reference area is 0.38m2, and the fitting of the aerodynamic coefficient is shown in the following formula.

[0161] C l =C l1 α+C l0

[0162] C d =C d2 α 2 +C d1 α+C d0

[0163] Where C l0 = -0.009, C l1 =0.259, C d0 =0.0478Ma 2 -0.0807Ma+0.1415, C d1 = 0.0001, C d2 = 0.0043. In the simulation test, the Mach number is usually 0.7; the ignition ...

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Abstract

The invention discloses an air-to-ground guided missile projection glide-section guidance method including speed process constraint and multi-terminal constraint. The method comprises the steps of dividing the resistance consumed energy into a part for overcoming the gravity and a turning maneuver part according to the characteristic that the lift-drag ratio of an aircraft is not great when a projection section nearly stays at an equilibrium gliding state, and respectively acquiring an expression; solving by utilizing the energy conservation law, and obtaining a corresponding relation of a terminal speed and longitudinal distance, so that the terminal speed constraint problem can be solved by utilizing the general guidance law; finally designing a speed control feedback by utilizing a normal control boundary and an axial control boundary, so that a guidance law which can simultaneously meet the requirements of terminal height, terminal angle, terminal speed and maximal speed constraint can be obtained. The air-to-ground guided missile projection glide-section guidance method has the advantages that the multi-constraint guidance problem of the projection glide section can be solved by adopting a closed-loop analysis guidance method, so that not only can good task adaptability be realized, but also convenience in engineering realization can be realized.

Description

technical field [0001] The invention belongs to the field of aerospace technology and weapons, and relates to a multi-constraint guidance method for launching a subsonic air-to-ground missile in the glide section. Specifically, it is a guidance method for the glide section of an air-to-ground missile that includes speed process constraints and multi-terminal constraints. Ensure that the missile is guided from the launch altitude to the ignition altitude under the minimum control index requirements, and meet the maximum airspeed constraint and terminal airspeed, angle of attack, and ballistic inclination constraints. Background technique [0002] Air-to-ground missiles are an important weapon for precision strikes in modern warfare, featuring low cost, strong defense penetration capabilities, and strong versatility. In modern warfare, air-to-ground missiles are required to have good task adaptability in order to ensure the safety of the carrier aircraft. In order to ensure t...

Claims

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Application Information

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IPC IPC(8): F41G3/00
Inventor 陈万春周浩胡锦川
Owner BEIHANG UNIV
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