Optimization method of smooth and steady gliding trajectory of hypersonic flight vehicle

A technology of gliding trajectory and optimization method, which is applied in the field of aerospace flight, can solve problems such as difficult to realize the optimization of smooth gliding trajectory in all states, achieve the effects of suppressing trajectory jumping, improving optimization efficiency, and reducing the difficulty of numerical solution

Inactive Publication Date: 2016-12-14
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a method for optimizing the smooth glide trajectory of a hypersonic vehicle, which

Method used

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  • Optimization method of smooth and steady gliding trajectory of hypersonic flight vehicle
  • Optimization method of smooth and steady gliding trajectory of hypersonic flight vehicle
  • Optimization method of smooth and steady gliding trajectory of hypersonic flight vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0111] Example 1 verifies the effectiveness of the expanded ballistic damping technology

[0112] CAV-H is selected as the re-entry vehicle model, the aerodynamic parameters and performance parameters are as described above, the angle of attack is selected to be 10 degrees close to the maximum lift-to-drag ratio, and the roll angle is also selected to be 10 degrees. In equation (10), it is necessary to suppress the formation of the trajectory Angle of attack α 2 and roll angle σ 2 It can be calculated according to the following formula:

[0113]

[0114]

[0115] In finding the angle of attack α 2 When , choose to use the first formula in equation (10) for calculation because the roll angle range of the aircraft is [-60°, 60°]; There will be strange phenomena in the corners, which can be avoided by using the first formula.

[0116] The initial state quantity of the aircraft is: h 0 =60000m; θ 0 = 0deg; V 0 =7100m / s; γ 0 = 0deg; ψ 0 =90 deg. All simulations ar...

Embodiment 2

[0118] Embodiment 2 does not consider the smooth gliding ballistic optimization of roll reversal

[0119] Use the hp adaptive Radau pseudospectral method to optimize the trajectory of the hypersonic reentry vehicle using ballistic suppression technology. During the optimization process, some related parameters are set as mentioned above, and the dynamic constraints are formed by Equation (11) For the smooth glide reentry dynamics model, the derivatives of the angle of attack and the roll angle with respect to time are used as control variables, and in order to obtain a smooth enough smooth glide trajectory, the following performance indicators (15) are selected.

[0120]

[0121] Among them, K 1 and K 2 are the weighting coefficients of the elements in the performance index, and the constraint relationship between the actual attack angle and roll angle is shown in equations (16) and (17).

[0122]

[0123]

[0124] Different process constraints and terminal constrai...

Embodiment 3

[0133] Example 3. Optimization of smooth glide trajectory considering roll reversal

[0134] Generally speaking, the goal of smooth glide trajectory optimization is to provide practical reference trajectory information for traditional tracking guidance laws (such as LQR linear quadratic regulation tracking), in fact, these guidance laws eliminate the lateral presence of The error of , only tracks the state on the longitudinal profile. In order to provide a feasible reference trajectory, this embodiment will study the optimization of a smooth glide trajectory considering one roll reversal. When adding roll reversal to the optimization process, it greatly increases the feasibility of reentry flight trajectories. All simulation settings are the same as in Example 2, and the initial condition is: h 0 =70000m, θ 0 = 0deg, v 0 =7100m / s, γ 0 = 0deg, ψ 0 =70deg. In addition, different target positions will be used to verify the adaptability of the smooth glide trajectory opti...

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Abstract

The invention discloses an optimization method of a smooth and steady gliding trajectory of a hypersonic flight vehicle. The optimization method specifically comprises the steps that 1, a reentry dynamics equation and a trajectory process constraint are established; 2, a trajectory damping control technology is extended; 3, the trajectory damping control technology is utilized to improve the dynamics equation; 4, a hp self-adaptive Radau pseudo-spectral method is utilized to solve an optimal control problem. The optimization method effectively inhibits trajectory jumping by changing the dynamic characteristics of a reentry trajectory and establishes the optimal control problem having smooth and steady state characteristics by changing the dynamic characteristics of the reentry trajectory, the difficulty of numerical solution is greatly reduced, the high-precision smooth and steady gliding trajectory meeting multiple constraint requirements can be obtained within short time, the optimization efficiency of the smooth and steady gliding trajectory is improved, and the regularity of the trajectory optimization is greatly strengthened.

Description

technical field [0001] The invention relates to the field of spaceflight technology, in particular to an optimization method for a smooth glide trajectory of a hypersonic vehicle. Background technique [0002] Smooth gliding is an important flight mode for reentry. It has the advantages of gentle altitude change, small heat flux and dynamic pressure peaks, and smooth curves of angle of attack and roll angle. It is widely used in reentry guidance. [0003] The re-entry guidance law is very important to generate the guidance instructions to guide the aircraft from the initial position to the target position accurately and safely. Generally speaking, the traditional guidance law is divided into two parts, one part is to generate a feasible reference trajectory, and the other part is the design of the tracking guidance law. Scott used the Legendre pseudospectral method for reentry trajectory planning, and used the co-state mapping principle of the Legendre pseudospectral method...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/367Y02T90/00
Inventor 陈万春杨良杜文豪周浩
Owner BEIHANG UNIV
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