Model error compensation method for ultra-high-velocity aircraft autonomous navigation system

An autonomous navigation system and model error technology, applied to integrated navigators, navigation calculation tools, instruments, etc., can solve problems such as GNSS signal interruptions and inaccurate dynamic models

Active Publication Date: 2018-04-10
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0006] Aiming at the deficiencies of the prior art, the present invention provides a method capable of compensating for the model error of the autonomous navigation system of an ultra-high-speed aircraft, so that the ultra-high-speed ai

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  • Model error compensation method for ultra-high-velocity aircraft autonomous navigation system

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[0087] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. This embodiment is carried out on the premise of the technical solution of the present invention, and detailed implementation and specific operation process are given, but the protection scope of the present invention is not limited to the following embodiments.

[0088] The simulation parameters are given as follows:

[0089] 1) The sensitivity error matrix of the geomagnetic sensor is: The non-orthogonal error matrix is: The bias error vector (unit: nT) is: b o =[900 850 750]; hard magnetic error vector (unit: nT) is: b n =[700 750 800]; The soft magnetic error matrix is: The standard deviation of the measurement random error is: 10nT; the initial estimated value of the geomagnetic sensor system error is taken as: [0,0,0];

[0090] 2) The GNSS positioning error is 10 meters, and the speed error is 0.1 meters per second;

[0091]3) Th...

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Abstract

The invention provides a model error compensation method for an ultra-high-velocity aircraft autonomous navigation system. The model error compensation method belongs to the field of autonomous navigation and is especially suitable for an ultra-high-speed aircraft autonomous navigation system. The method comprises building an autonomous navigation system measurement model through considering the measurement error of a geomagnetic sensor and constructing an autonomous navigation system dynamical model with power compensation and a unscented Kalman filter (EKF)-based autonomous navigation algorithm. The method simplifies the model and calculation, solves the problem that the ultra-high-velocity aircraft in high dynamic flight causes flashing of GNSS signals, no accelerometer information anddynamic model inaccuracy and guarantees stable work of the autonomous navigation system.

Description

technical field [0001] The invention is suitable for the field of autonomous navigation, especially for the autonomous navigation system of ultra-high-speed aircraft. Background technique [0002] Ultra-high-speed aircraft usually refers to an aircraft with a flight Mach number greater than 2. Its autonomous navigation does not rely on ground measurement and control information, but only relies on onboard sensor measurement and control data and its own motion model to determine the flight state and complete the process of determining the trajectory in real time. For the actual aircraft Engineering applications are of great value. With the continuous development of aerospace science and technology, future ultra-high-speed aircraft will present the characteristics of ultra-high speed of sound, large lift-to-drag ratio, and high maneuverability. These flight characteristics of ultra-high-speed aircraft will bring severe challenges to autonomous navigation: During the process, ...

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Application Information

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IPC IPC(8): G01C21/20G01C25/00G01C21/24
CPCG01C21/20G01C21/24G01C25/00
Inventor 矫媛媛潘晓刚孙晓民蔡伟伟梁卓涂海峰吕瑞刘靖
Owner NAT UNIV OF DEFENSE TECH
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