Method for rapidly generating finite time track of hypersonic aircraft

A hypersonic, finite-time technology, applied in the direction of instruments, adaptive control, control/regulation systems, etc., can solve the optimal control problem unsuitable for solving path constraints, trajectory optimization speed and real-time re-entry environment interference , Non-linear programming solutions and other problems cannot be guaranteed, to achieve the effect of solving closed-loop guidance problems, easy to use, and less memory occupation

Inactive Publication Date: 2014-08-20
HARBIN INST OF TECH
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Problems solved by technology

[0009] The purpose of the present invention is to solve the rapid optimization problem of the trajectory of a hypersonic vehicle. The process of deriving the optimal solution of the indirect method is relatively complicated and cumbersome and is not suitable for solving the optimal control problem with path constraints. The direct method cannot guarantee the obtained nonlinearity. The planning solution is the original optimal control problem and the dynamic programming method cannot satisfy the rapidity and real-time performance of trajectory optimization, resulting in complex re-entry environment interference and environmental uncertainty. generation method

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  • Method for rapidly generating finite time track of hypersonic aircraft
  • Method for rapidly generating finite time track of hypersonic aircraft
  • Method for rapidly generating finite time track of hypersonic aircraft

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specific Embodiment approach 1

[0027] Specific Embodiment 1: The method for quickly generating a finite-time trajectory of a hypersonic vehicle according to this embodiment is specifically prepared according to the following steps:

[0028] Step 1: Analyze and model the motion of the hypersonic vehicle at the end of re-entry to obtain the motion model of the hypersonic vehicle as follows: Figure 5 ;

[0029] Step 2, describe the motion model of the obtained hypersonic vehicle re-entry terminal trajectory for optimization problem, and form a nonlinear optimization problem;

[0030] Step 3. Convex processing (discrete linearization) of the hypersonic vehicle re-entry terminal nonlinear optimization problem, describing the optimization index of the optimization problem and the constraints of the optimization problem as a quadratic convex problem;

[0031] Step 4: Describe the quadratic convex optimization problem according to the CVXGEN code writing specification, and use the online compiler to compile the cod...

specific Embodiment approach 2

[0039] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the process of selecting the site of the borrow pit described in step 1 is as follows: in step 1, the motion of the hypersonic vehicle at the end of re-entry is modeled to obtain the hypersonic vehicle The specific process of the motion model is:

[0040] (1) The engine of the hypersonic vehicle re-entry process is stopped, no longer subject to thrust and control force, mainly subject to the effects of gravity and aerodynamic force, and carry out long-distance gliding; in addition, the present invention does not consider the movement of the aircraft around the center of mass, and considers that the orbiting The motion of the center of mass is in the state of instantaneous balance or trimming, and the aircraft is regarded as a mass point to study only the motion of its center of mass; simplified into the dynamic equation of the center of mass:

[0041] m ...

specific Embodiment approach 3

[0079] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that: the process of selecting the site of the borrow pit described in step one is: the motion model of the hypersonic vehicle re-entry terminal trajectory obtained in step two The specific process of describing the optimization problem and forming the nonlinear optimization problem is as follows:

[0080] (1) Express the hypersonic vehicle re-entry final stage motion model shown in (2) in the form of a differential equation:

[0081]

[0082] Among them, (3) is a nonlinear equation, that is, a state equation constraint, x=[r,γ,V,λ,φ,ψ] T is the state variable, u=[α,σ] T is the control quantity; this is the state equation constraint that must be satisfied during the optimization process; Indicates the real number field to which both the state variable and the control quantity belong; m represents the dimension of the control quantity, and n represents the dimens...

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Abstract

The invention relates to finite time tracks of aircrafts, in particular to a method for rapidly generating a finite time track of a hypersonic aircraft. The method aims to solve the problems that the process of deriving an optimal solution according to a traditional method is complex, nonlinear programming problems with complex constraints cannot be effectively solved, the rapidity and real-time performance of track optimization cannot be met, and complex reentry environmental disturbance and environmental uncertainty cannot be handled. The method includes the steps that 1, the motion model of the hypersonic aircraft is obtained; 2, the nonlinear programming problem is formed; 3, the nonlinear programming problem is described to be a quadric form convex problem; 4, a high-speed resolver is generated; 5, the quadric form convex optimization problem is solved, and the solution is analyzed. The method is applied to the field of the finite time tracks of the aircrafts.

Description

technical field [0001] The invention relates to a method for quickly generating a finite-time trajectory of a hypersonic vehicle. Background technique [0002] At present, hypersonic technology is a new technology field integrating the advantages of aerospace and aviation technology, and is the strategic commanding height in the field of aerospace technology in the 21st century. Its development will have a great impact on future military development strategy, space technology, weapon system construction and even the entire scientific and technological progress. Significant impact. Vigorously carrying out hypersonic technology research has important strategic significance for consolidating and improving my country's comprehensive strength and international status. my country has included major projects of hypersonic vehicle science and technology projects in its medium and long-term development plan. The rapid progress in high technology in the past ten years has led to the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/10G05B13/04
Inventor 段广仁谭峰路钊侯明哲
Owner HARBIN INST OF TECH
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