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Method for confirming inclination angle of powerless hypersonic flight vehicle

A technology of hypersonic speed and aircraft, which is applied in directions such as navigation through speed/acceleration measurement, which can solve problems such as inability to apply large-turn flight, and achieve the effect of accurate control requirements

Inactive Publication Date: 2015-06-24
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

[0003] As for the gliding aircraft, because it has the capability of turning flight and adopts the bank to turn (BTT, bank to turn) flight mode, if it is guided by the roll angle relative to the launch inertial coordinate system, it cannot be applied to the state of large turn flight

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  • Method for confirming inclination angle of powerless hypersonic flight vehicle
  • Method for confirming inclination angle of powerless hypersonic flight vehicle
  • Method for confirming inclination angle of powerless hypersonic flight vehicle

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Embodiment Construction

[0035] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.

[0036] This embodiment provides a method for determining the tilt angle of an aircraft.

[0037] figure 1 It is a schematic flowchart of a method for determining the tilt angle of an unpowered hypersonic vehicle in an embodiment of the present invention. Such as figure 1 As shown, the method for determining the tilt angle of the unpowered hypersonic vehicle in the embodiment of the present invention mainly includes the following steps:

[0038] Step 101, setting a track coordinate system.

[0039] In the technical solution of the present invention, firstly, a track coordinate system can be set (that is, defined). The orientation of the horizontal axis of the track coordinate system is related to the track of the aircraft, so it is called the track c...

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Abstract

The invention discloses a method for confirming the inclination angle of a powerless hypersonic flight vehicle. The method comprises the following steps: setting a flight track coordinate system; calculating a transformation matrix from a launching inertial system to the flight track coordinate system according to inertial navigation parameters; calculating a transformation matrix from the flight track coordinate system to an elastic body system according to a transformation matrix from the launching inertial system to the elastic body system and the transformation matrix from the launching inertial system to the flight track coordinate system; calculating an inclination angle of an aircraft relative to the flight track coordinate system according to the transformation matrix from the flight track coordinate system to the elastic body system. By adopting the method for confirming the inclination angle of the powerless hypersonic flight vehicle, logic inclination angles of the powerless hypersonic flight vehicle for turning left or turning right can be relatively visibly and accurately obtained.

Description

technical field [0001] The invention relates to the navigation, guidance and control technology of a hypersonic vehicle, in particular to a method for determining the tilt angle of an unpowered hypersonic vehicle. Background technique [0002] In the prior art, traditional ballistic missiles generally use the launch inertial system as the navigation reference. Because the maneuverability of traditional ballistic missiles is not strong, its flight trajectory is always within the shooting surface, and the side to turn (STT, side to turn) method is adopted, so the attack angle and sideslip angle characteristic parameters based on the velocity coordinate system can be used Realize turning or maneuvering flight. [0003] As for the gliding aircraft, because it has the capability of turning flight and adopts the bank to turn (BTT, bank to turn) flight mode, if it is guided by the roll angle relative to the launch inertial coordinate system, it cannot be applied to the state of la...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/16
CPCG01C21/16
Inventor 杨业包为民黄万伟马卫华祁振强禹春梅唐海红田海涛
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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