On-line parameter identification method for jumping type reentry of lunar spacecraft

A parameter identification and jumping technology, which is applied to the system of the spacecraft returning to the earth's atmosphere, the guidance device of the spacecraft, the landing device of the spacecraft, etc., can solve the problems such as unsatisfactory results

Active Publication Date: 2014-04-09
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

Atmospheric density errors vary with parameters such as solar activity, season, latitude, and day and night. The empiric...

Method used

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  • On-line parameter identification method for jumping type reentry of lunar spacecraft
  • On-line parameter identification method for jumping type reentry of lunar spacecraft
  • On-line parameter identification method for jumping type reentry of lunar spacecraft

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Embodiment Construction

[0053] Assume that a lunar exploration spacecraft obtains lift during reentry through the center of mass offset configuration, the lift-to-drag ratio is 0.3-0.4, and the control amount of the guidance system is the roll angle ν. The re-entry process starts at an altitude of 120km, at this time the speed of the spacecraft is 11km / s, and the local velocity inclination is -5.8.

[0054] The spacecraft adopts an inertial navigation system, which can measure the apparent acceleration in the spacecraft body coordinate system and the attitude angular velocity of the spacecraft relative to the inertial coordinate system After calculation by the navigation system, the position and speed of the spacecraft in the return coordinate system can be obtained, and at the same time information such as the geographic latitude, longitude, altitude, angle of attack, sideslip angle, and velocity inclination of the spacecraft can be obtained.

[0055] Such as figure 2 As shown, for the spacecraf...

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Abstract

The invention discloses an on-line parameter identification method for jumping type reentry of a lunar spacecraft. The on-line parameter identification method comprises the steps of obtaining on-line estimation values of an atmospheric density scaling factor and a lift-drag ratio scaling factor through a low-pass filter at a primary reentry descending branch, executing track forecasting, correcting the deflection of a drop point, and constructing a fitting function relation between the atmospheric density scaling factor and the height; obtaining an atmospheric density scaling factor at a primary reentry ascending branch and in the initial stage of a secondary reentry branch via a constructed fitting function, estimating a lift-drag ratio scaling factor of the lunar spacecraft on line, executing track forecasting, and correcting the deflection of the drop point; estimating an atmospheric density scaling factor and a lift-drag ratio scaling factor in the later stage of the secondary reentry branch, executing track forecasting, and correcting the deflection of the drop point. According to the on-line parameter identification method, the robustness and the precision of a guidance algorithm are improved; the adaptability to a real atmosphere model is high.

Description

technical field [0001] The invention relates to the technical field of guidance and control, and can be applied to the guidance of a jumping reentry of a lunar exploration spacecraft, in particular to an online parameter identification method for a jumping reentry of a lunar exploration spacecraft. Background technique [0002] When the lunar exploration spacecraft returns and re-enters the earth, the initial state of reaching the boundary of the atmosphere is very different from that of the near-Earth spacecraft. The most obvious feature is that the re-entry speed of the lunar exploration spacecraft is higher, reaching 11km / s, while the near-Earth spaceflight The reentry speed of the vehicle is generally about 7.8km / s. This high-speed re-entry condition makes the re-entry trajectory more sensitive to atmospheric and aerodynamic parameter errors, the dynamic coupling during the re-entry process is more serious, and the dynamic pressure, heat flow, and overload of the spacecr...

Claims

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Application Information

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IPC IPC(8): B64G1/62B64G1/24
Inventor 张洪波罗宗富曾亮汤国建
Owner NAT UNIV OF DEFENSE TECH
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