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Multi-integrated navigation processing device under launch inertial system and navigation method of multi-integrated navigation processing device

A processing device and integrated navigation technology, which is applied in navigation, surveying device, surveying and navigation, etc., can solve the problems of complex realization, inevitable conversion and calculation errors, etc., and achieve the effect of highlighting the application value

Inactive Publication Date: 2014-09-10
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

This method is complex and requires multiple conversions of parameters, which inevitably brings conversion calculation errors and affects system accuracy.

Method used

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  • Multi-integrated navigation processing device under launch inertial system and navigation method of multi-integrated navigation processing device
  • Multi-integrated navigation processing device under launch inertial system and navigation method of multi-integrated navigation processing device
  • Multi-integrated navigation processing device under launch inertial system and navigation method of multi-integrated navigation processing device

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Embodiment Construction

[0056] The invention will be described in further detail below in conjunction with the accompanying drawings.

[0057] Such as figure 1 As shown, the principle of the navigation method of the present invention is: directly establish the integrated navigation system model of the missile under the launch inertial system, and develop the SINS / GPS / CNS integrated navigation method under the launch inertial system based on federated filtering. The specific implementation method is as follows:

[0058] 1. Modeling of the SINS / GPS / CNS integrated navigation system under the launching inertial system:

[0059] (1) Modeling of inertial navigation error state quantity equation of integrated navigation system

[0060] For the SINS / GPS / CNS multi-integrated navigation system, the calculation process of the strapdown inertial navigation system under the launch inertial system is as follows, and the speed calculation formula is:

[0061] C b f ...

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Abstract

The invention discloses a multi-integrated navigation processing device under a launch inertial system and a navigation method of the multi-integrated navigation processing device and belongs to the technical field of integrated navigation of aircraft. The device comprises a sensor module, a navigation processing device and a display module. The navigation method comprises steps of firstly, directly establishing an integrated navigation system state model and measuring model of a guided missile under the launch inertial system, developing an SINS / GPS / CNS (Strapdown Inertial Navigation System / Global Position System Central Nervous System) integrated navigation method under the launch inertial system, carrying out multi-information optimal fusion processing by adopting federal filtering, and finally directly outputting attitude, position and speed parameters of the guided missile under the launch inertial system. According to the device and the method, the SINS / GPS / CNS multi-information fusion processing can be effectively realized under the launch inertial system, a high-precision navigation result is obtained, meanwhile, an efficient support is provided for the engineering implement and application of an SINS / GPS / CNS integrated navigation system.

Description

technical field [0001] The invention discloses a multi-combined navigation processing device and a navigation method thereof under a launching inertial system, and belongs to the technical field of aircraft combined navigation. Background technique [0002] In recent years, the integrated navigation processor engineering products based on embedded operating systems have become increasingly mature, and have been widely used in airborne and missile-borne environments, but their core navigation methods are mainly limited to inertial / satellite, inertial / astronomical Combination, the multi-combination navigation system that is applied to reality has not yet been reported. In view of the characteristics of long-range missiles and high-altitude cruise missiles with long flight distances and long voyage times, the typical inertial / satellite single integrated navigation system based on inertial navigation cannot meet the requirements of missiles for navigation parameters because the ...

Claims

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Application Information

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IPC IPC(8): G01C21/00G01C21/20
CPCG01C21/165G01C21/20G01S19/49
Inventor 潘加亮熊智赵慧郁丰刘建业许建新柏青青王洁程娇娇林爱军王东升施丽娟孔雪博
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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