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Switching method for building aircraft motion model

A motion model and aircraft technology, applied in navigation calculation tools and other directions, can solve the problem of large output error of rigid body motion model

Active Publication Date: 2012-07-18
XIAN FEISIDA AUTOMATION ENG
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Problems solved by technology

[0004] In order to overcome the problems such as the large output error of the existing rigid body motion model, the present invention provides a switching method for establishing the aircraft motion model. The method obtains the expression of the motion attitude of the aircraft by defining two switching state variables, and avoids the singular problem of the attitude differential equation , according to the two switching state variables and the pitch angle state equation, the aircraft attitude solution switching model described by Euler angles is obtained

Method used

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  • Switching method for building aircraft motion model
  • Switching method for building aircraft motion model
  • Switching method for building aircraft motion model

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Embodiment Construction

[0019] 1. Establish the switching model of the aircraft movement:

[0020]

[0021] in: along the axis of the aircraft body the velocity component of the shaft; , , respectively along Shaft overload; are roll, pitch, and yaw angular velocities; Euler angles Respectively refer to roll, pitch, yaw angle; is the height; is the acceleration of gravity, when exist near, take

[0022]

[0023] when exist near, take

[0024]

[0025] when when, take

[0026]

[0027] when when, take

[0028] ;

[0029] 2. Assumption , , can export , .

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Abstract

The invention provides a switching method for building an aircraft motion model, which obtains expression of aircraft motion gestures by defining two switched state variable quantities and avoiding singular problems of a gesture differential equation. An aircraft gesture resolving and switching model described by an euler angle is obtained according to the two switched state variable quantities and a pitch angle state equation.

Description

technical field [0001] The invention relates to a space motion rigid body model, in particular to the problem of the output model of the large maneuvering flight state of an aircraft. Background technique [0002] The differential equation of rigid body motion of the body shaft system is the basic equation describing the space motion of aircraft, torpedo, and spacecraft. Usually, in applications such as data processing, the state variables of the body axis system mainly include three velocity components, three Euler angles, and the ground coordinate system's wait, because is defined as the vertical ground pointing towards the center of the earth, so The actual negative flight altitude; Usually mainly rely on GPS, GNSS, Beidou, etc. to give directly; the Euler angle represents the attitude of the rigid body in space, and the differential equation describing the attitude of the rigid body is the core. Usually, the three Euler angles are pitch, roll and yaw. angle to de...

Claims

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Application Information

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IPC IPC(8): G01C21/20
Inventor 史忠科
Owner XIAN FEISIDA AUTOMATION ENG
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