Engineering reentry guidance method oriented to moving mass aircraft

Abstract

The invention discloses an engineering reentry guidance method oriented to a moving mass aircraft. The engineering reentry guidance method is used for solving the technical problem of poor engineeringapplicability of an existing moving mass aircraft reentry guidance method. According to the engineering reentry guidance method, on the basis of the most common proportional guidance law in the engineering, the landing velocity and the landing angle constraint of the moving mass aircraft is converted into an augmented item, the augmented item parameter is further subjected to robustness expandingdesign, so that the guidance parameter is a function of the flight state deviation of the moving mass aircraft, the guidance precision is ensured when the moving mass aircraft is interfered, and finally the guidance instruction, namely the roll angle instruction size, is determined on the basis of the required overload and the available overload relation. According to the method, on the basis ofa proportional guidance law, the augmented item of the landing angle and the landing speed constraint is added, trajectory lifting and reduction are achieved, meanwhile, the landing angle and the landing velocity constraint are met, and meanwhile, the robustness expanding design is carried out on the augmented term coefficient on the basis, and the method is a moving mass aircraft strong robust guidance method which is simple in form and good in engineering application performance.

Description

Technical field

[0001] The invention relates to a re-entry guidance method for a variable-cent-of-mass aircraft, in particular to an engineered re-entry guidance method for a variable-cent-of-mass aircraft. Background technique

[0002] One-dimensional variable-cent-of-mass aircraft usually adopts a fixed trim design, which is a simple and easy-to-implement reentry aircraft configuration. The fixed-trim aircraft uses its own static stability to achieve self-stabilization of pitch and yaw motions, and maneuvering can be achieved only by controlling the roll channel. However, in the roll single-channel control mode, the aircraft overload is only controllable in direction and uncontrollable in magnitude, which brings challenges to the robust guidance of fixed-trim variable-cent-of-mass aircraft restricted by falling velocity and landing angle.

[0003] Aiming at the guidance of fixed-trim variable-center-of-mass aircraft with falling corner speed terminal constraints, Ge Zhenzhen wro...

Examples

Embodiment Construction

[0041] Reference Figure 1-2 . The specific steps of the engineered reentry guidance method for the variable center of mass aircraft of the present invention are as follows:

[0042] 1. Enhancement of proportional guidance law.

[0043] Define the ground coordinate system as ex e y e z e (Abbreviated as e): the origin e is the projection point of the aircraft centroid o on the ground at the initial moment; ey e In the center of the earth O E On the line with the center of mass o of the aircraft, pointing to the center of mass o of the aircraft is positive; and ex e Perpendicular to ey at point e e In the plane of, point to the target point; ex e y e z e Form a right-handed rectangular coordinate system.

[0044] Define the line of sight coordinate system oξ o η o ζ o (Abbreviated as S): the origin is at the centroid o of the aircraft; oξ o Point from the center of mass of the aircraft to the target point; oζ o In the horizontal plane, that is, in the e-xz plane, and with oξ o The axi...

Technical field

[0001] The invention relates to a re-entry guidance method for a variable-cent-of-mass aircraft, in particular to an engineered re-entry guidance method for a variable-cent-of-mass aircraft. Background technique

[0002] One-dimensional variable-cent-of-mass aircraft usually adopts a fixed trim design, which is a simple and easy-to-implement reentry aircraft configuration. The fixed-trim aircraft uses its own static stability to achieve self-stabilization of pitch and yaw motions, and maneuvering can be achieved only by controlling the roll channel. However, in the roll single-channel control mode, the aircraft overload is only controllable in direction and uncontrollable in magnitude, which brings challenges to the robust guidance of fixed-trim variable-cent-of-mass aircraft restricted by falling velocity and landing angle.

[0003] Aiming at the guidance of fixed-trim variable-center-of-mass aircraft with falling corner speed terminal constraints, Ge Zhenzhen wro...

Examples

Embodiment Construction

[0041] Reference Figure 1-2 . The specific steps of the engineered reentry guidance method for the variable center of mass aircraft of the present invention are as follows:

[0042] 1. Enhancement of proportional guidance law.

[0043] Define the ground coordinate system as ex e y e z e (Abbreviated as e): the origin e is the projection point of the aircraft centroid o on the ground at the initial moment; ey e In the center of the earth O E On the line with the center of mass o of the aircraft, pointing to the center of mass o of the aircraft is positive; and ex e Perpendicular to ey at point e e In the plane of, point to the target point; ex e y e z e Form a right-handed rectangular coordinate system.

[0044] Define the line of sight coordinate system oξ o η o ζ o (Abbreviated as S): the origin is at the centroid o of the aircraft; oξ o Point from the center of mass of the aircraft to the target point; oζ o In the horizontal plane, that is, in the e-xz plane, and with oξ o The axi...

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