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High-speed self-rotation guided cartridge aerial real-time alignment method

A projectile and high-speed technology, applied in the field of real-time aerial alignment of high-speed spin-guided projectiles, can solve the problems of estimation error, inability to meet requirements, slow rotation speed, etc.

Active Publication Date: 2016-01-13
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The commonly used initial alignment method uses the Kalman filter. Take the patent "A Self-alignment Method for Spin-Guided Projectiles in the Air" (Application No.: 201410712260.1) as an example, but this method is suitable for relatively slow rotating speeds. When the speed is faster, it cannot meet the requirements
For example, when the GPS external measurement value is 10 sets of observations per second, and the rotation speed of the guided projectile is greater than 4 revolutions per second, it cannot meet the requirements of signal reproduction, resulting in estimation errors

Method used

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  • High-speed self-rotation guided cartridge aerial real-time alignment method
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  • High-speed self-rotation guided cartridge aerial real-time alignment method

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Embodiment

[0067] This embodiment adopts the real-time alignment method of the high-speed spin-guided projectile in the air of the present invention to carry out the alignment solution, and the solution results are shown in Fig. 2 and image 3 shown.

[0068] Among them, in Figure 2, it includes the roll angle correction component γ, the pitch angle φ y and yaw angle φ z the convergence curve. It can be seen from Figure 2 that γ does not depend on the initial value and eventually converges to the true value. image 3 is roll angle φ x The process curve of mid-air alignment can be seen from the figure, the roll angle φ x Gradually converge to the true value, complete the air alignment of the spin-guided projectile, the convergence speed is fast and the convergence error is small.

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Abstract

The invention discloses a high-speed self-rotation guided cartridge aerial real-time alignment method. According to the method, the initial heading angle and the pitch angle are set at the initial moment according to auxiliary data of a satellite navigation system; the initial roll angle is set to be an arbitrary value; then inertial navigation attitude computation is performed when only the inertial navigation system data exist to obtain three attitude angles; when the auxiliary data of the satellite navigation system exist, the roll angle at the moment is rapidly estimated through three-dimensional Kalman filter estimation to obtain three aerial attitude angles of a self-rotation guided cartridge. Compared with existing aerial self-alignment methods, the self-rotation guided cartridge aerial alignment method is small in computation amount and high in accuracy and establishes the foundation for improving fall point accuracy of the high-speed self-rotation guided cartridge.

Description

technical field [0001] The invention relates to the technical field of dynamic initial alignment and integrated navigation, in particular to a method for real-time aerial alignment of high-speed spin-guided projectiles, which is used for aerial alignment of unmanned aerial vehicles and spin-guided projectiles. Background technique [0002] The spin-guided projectile is a high-precision weapon that is launched in the air and needs to be self-aligned. It includes an integrated navigation system of inertial navigation and GPS satellite navigation. The error of the inertial navigation system is corrected by GPS to achieve precise strikes. ability to target. Air alignment is the process of estimating the roll angle of the inertial navigation system with the assistance of navigation parameters (such as speed, attitude angle, etc.) provided by other navigation systems. [0003] The inertial navigation system is a range reckoning system based on the quadratic integration of acceler...

Claims

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Application Information

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IPC IPC(8): F42B15/01G06F19/00
Inventor 魏宗康
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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