Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Control method for realizing overload autopilot by using accelerometer

A technology of accelerometer and control method, applied in projectiles, self-propelled projectiles, offensive equipment, etc., can solve the problems of immaturity, limited anti-overload capability, low performance, etc.

Active Publication Date: 2012-04-25
BEIJING INSTITUTE OF TECHNOLOGYGY
View PDF4 Cites 16 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the complex process, low performance and limited overload resistance of MEMS gyro devices, the technology of using gyro-sensitive angular motion is not mature for gun-launched missiles.

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Control method for realizing overload autopilot by using accelerometer
  • Control method for realizing overload autopilot by using accelerometer
  • Control method for realizing overload autopilot by using accelerometer

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0027] Step 1: Carry out formula calculation, rational simplification and analysis in the inertial coordinate system to obtain the functional relationship between angular rate and overload. The attitude angular rate signal is calculated from the missile overload solution to construct the damping loop, which serves as the theoretical basis for the design and implementation of this scheme.

[0028] When the angle of attack α is small, ignoring the lift of the rudder surface, the longitudinal overload of the missile is:

[0029] a yb * = Y / m ≈ V · b α · α - - - ( 0.7 )

[0030] Substituting the third formula of formula (0.14) and the second formula of formula (0.15) into formula (0.7), we can get:

[0031] ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to a control method for realizing an overload autopilot by using an accelerometer. The control method comprises the following steps of: firstly, calculating a functional relation between the attitude angular rate and the overload of a missile body under an inertial coordinate system; secondly, obtaining a damping circuit grain Kg and a stable circuit gain KA of the overload autopilot at a characteristic point of a missile track by adopting a root locus method of a classical control theory; and finally, constructing a damping circuit by using an accelerometer signal under the missile body coordinate system according to the result obtained in the first step and realizing the overload autopilot by using the accelerometer. According to the control method disclosed by the invention, aiming at the dynamic characteristic of a guide missile, by using the function relation between the overload and the angular rate and using a method of constructing the damping circuit by repeatedly using the accelerometer through the overload autopilot, the mathematical simulation validation can be carried out and a corresponding engineering realization scheme is provided.

Description

technical field [0001] The invention relates to a control method capable of resisting high overload, in particular to a control method for realizing an overload pilot by using an accelerometer. Background technique [0002] In 1967, Alfred proposed to use multiple accelerometers to measure the linear acceleration and angular acceleration of the carrier, and imagined five accelerometer configurations and corresponding angular rate calculation algorithms; the designed 9 accelerometer configuration schemes were widely recognized. The gyro-free inertial navigation system prototype developed on this basis has an attitude accuracy of 0.082° / h. The system is equipped with nine accelerometers, which is costly and takes up a large volume, making it difficult to implement on artillery-launched missiles. In addition, the position accuracy of the system is not high, and it is only suitable for the angular rate measurement of the long-time working navigation system. [0003] Currently,...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): F42B15/01
Inventor 林德福范世鹏王江路宇龙段鑫尧
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com