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Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof

An attitude control and aerodynamic technology, which is applied to the guidance devices of space navigation vehicles, etc., can solve the problems of short on-orbit life and large fuel consumption of aircraft, and achieve the effect of improving life and increasing propellant carrying capacity.

Inactive Publication Date: 2010-07-28
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the existing low-orbit aircraft and its attitude control method have a large amount of fuel consumption and the resulting short service life of the aircraft, and provide a low-orbit aircraft based on aerodynamic attitude control and its attitude control method

Method used

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  • Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof
  • Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof
  • Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof

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specific Embodiment approach 1

[0014] Specific implementation mode one : the low-orbit vehicle based on aerodynamic attitude control of the present embodiment, which includes aircraft body 1, pitching attitude control aerodynamic auxiliary board, yaw attitude control aerodynamic auxiliary board, first rotating mechanical arm 5, second rotating mechanical arm arm 6, the third rotating mechanical arm 7 and the fourth rotating mechanical arm 8, wherein the pitching attitude control aerodynamic auxiliary board is composed of a first aerodynamic auxiliary board 21 and a second aerodynamic auxiliary board 22, and the yaw attitude The control aerodynamic auxiliary board is composed of a third aerodynamic auxiliary board 31 and a fourth aerodynamic auxiliary board 32;

[0015] One end of the first rotating mechanical arm 5, one end of the second rotating mechanical arm 6, one end of the third rotating mechanical arm 7 and one end of the fourth rotating mechanical arm 8 are respectively connected to the tail of the...

specific Embodiment approach 2

[0018] Specific implementation mode two : Different from Embodiment 1, this embodiment also includes two wedge-shaped ailerons 4, and the cross-section of the wedge-shaped ailerons (4) is wedge-shaped, and one of the wedge-shaped ailerons 4 is located on the left side of the aircraft body 1 and It is connected with the left side surface of the aircraft body 1 , and another wedge-shaped aileron 4 is located at the right side of the aircraft body 1 and connected with the right side surface of the aircraft body 1 .

[0019] Each wedge-shaped aileron 4 is a sealed body composed of five plates, wherein the five plates include three rectangular plates of the same specification and two triangular plates, and the three rectangular plates are connected end to end in turn to form a hollow triangle For a cylinder, the two triangular plates are respectively placed on the upper bottom surface and the lower bottom surface of the triangular cylinder, and the joints of the five plates are al...

specific Embodiment approach 3

[0024] Specific implementation mode three: Different from Embodiment 1, this embodiment also includes a first aerodynamic auxiliary board aileron 9, a second aerodynamic auxiliary board aileron 10, a fifth rotating mechanical arm 11 and a sixth rotating mechanical arm 12, wherein the fifth One end of the rotating mechanical arm 11 is connected to the left side of the aircraft body 1, one end of the sixth rotating mechanical arm 12 is connected to the right side of the aircraft body 1, and the other end of the fifth rotating mechanical arm 11 is connected to the first aerodynamic auxiliary plate aileron 9, And the first aerodynamic auxiliary plate aileron 9 can be driven to rotate with the central axis of the fifth rotating mechanical arm 11 as the central axis, and the other end of the sixth rotating mechanical arm 12 is connected to the second aerodynamic auxiliary plate aileron 10, and the second aerodynamic auxiliary plate aileron 10 can be driven to rotate around the cent...

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Abstract

The invention provides a low-orbit aircraft based on aerodynamic attitude control and an attitude control method thereof, relating to the low-orbit aircraft and the attitude control method thereof and solving the problems of high fuel consumption of the current low-orbit aircraft and the attitude control method thereof and short on-orbit service life of the aircraft. The low-orbit aircraft comprises an aircraft body, a pair of pitching-direction attitude control aerodynamic auxiliary boards, a pair of yawing-direction attitude control aerodynamic auxiliary boards, a first rotating mechanical arm, a second rotating mechanical arm, a third rotating mechanical arm and a fourth rotating mechanical arm. The attitude control method of the low-orbit aircraft comprises the following steps of: acquiring the current attitude angle and the target attitude angle of the low-orbit aircraft, obtaining a member to be deflexed and an angle through combining with aircraft attitude dynamics model and a kinematics model, rotating the member, then calculating the deviation angle at the moment, and then finishing the control process when the deviation angle is in the allowed range. The invention is suitable for the attitude control field of the low-orbit aircraft in the height of 200-500 km.

Description

technical field [0001] The invention relates to a low-orbit aircraft and an attitude control method thereof. Background technique [0002] With the demand for low-cost, high-revisit frequency, and high-resolution observations for emergencies such as earthquakes, fires, and terrorism, low-Earth orbit vehicles have received more and more attention. The low-orbit vehicle is mainly affected by the aerodynamic force during its in-orbit operation, which is mainly manifested as the impact on the orbit and attitude of the vehicle. Most of the existing low-orbit aircraft and their attitude control methods are active, such as jet control, zero-momentum wheel control, bias momentum wheel control, and control moment gyro control. The rail life is short, and the control system in these control methods is relatively complicated. Contents of the invention [0003] The purpose of the present invention is to solve the problem that the existing low-orbit aircraft and its attitude control ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 张锦绣曹喜滨林晓辉杨明邢雷兰盛昌孙兆伟张志刚
Owner HARBIN INST OF TECH
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