Pose correction method for powered phase of aircraft

An aircraft and active segment technology, applied in attitude control, three-dimensional position/course control, etc., can solve the problems of poor inertial navigation accuracy, complex interference of active segment, low precision, etc., achieve effective correction of position and attitude, and improve landing point accuracy , the effect of long recapture time

Active Publication Date: 2015-12-23
BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
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AI Technical Summary

Problems solved by technology

However, the interference situation in the active segment is complicated, and low-cost aircraft often use low-precision MEMS inertial groups, resulting in poor inertial navigation accuracy

Method used

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  • Pose correction method for powered phase of aircraft

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Embodiment Construction

[0015] Such as figure 1 Shown, be the flowchart of the inventive method, main process is as follows:

[0016] When the aircraft is ready to launch, the GNSS and inertial group are activated, and the position, speed and attitude of the aircraft are corrected in real time by means of integrated navigation.

[0017] The method of integrated navigation using GNSS and inertial groups can be found in "GNSS_INS Integrated Navigation System Superiority Research and Simulation", Electronic Measurement Technology, No. 3, 2008.

[0018] In order to avoid multi-path interference in the initial stage, GNSS information is not used, and the total overload is judged at the same time. When the total overload is less than the rated design overload of the receiver, the GNSS position and velocity information is used to directly correct the inertial navigation information. When the overload is greater than the receiver When the rated design is overloaded, turn off the GNSS information and use the...

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Abstract

Provided is a pose correction method for a powered phase of an aircraft. The method is designed according to flight characteristics of a powered phase, and through comprehensive determination of overload and other information, effective use of pure inertial navigation, integrated navigation, and GNSS information is determined, so that effective information of GNSS is fully used, navigation precision of the powered phase of an aircraft is improved, GNSS mistaken correction caused by complex interference is prevented, and a problem of high-precision navigation of low-cost aircraft is solved. Control cost is reduced, and the method provides conditions for popularized use of the aircraft pose correction method.

Description

technical field [0001] The invention relates to a control method for an aircraft during active flight. Background technique [0002] A guided aircraft uses engine separation technology. When the main engine runs out of fuel and shuts down, throw it away in time, which can avoid the impact of the engine on the range, and ensure the maneuverability of the main-stage aircraft in the guidance flight section, improving the ability to strike moving targets. [0003] After the main engine is separated, the aircraft will be in an uncontrolled inertial ballistic state. In order to ensure the accuracy of its landing point, its speed and position must be precisely controlled before the main engine is shut down and separated. Since the active section adopts perturbation guidance, in order to ensure the guidance accuracy, it is necessary to precisely control the speed and direction of the active section. However, the interference situation in the active segment is complicated, and low-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
Inventor 秦雪方岳吴学森孙月光田源黄朝东赵春明李涛宋蔚阳方海红孙忠旭庄凌王磊张欣
Owner BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE
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