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A Perturbed Gravitational Approach to the Space Envelope of Large-Scale Maneuvering Ballistics along Nearby Space

A near-space, perturbed gravitational technology, applied in the field of perturbed gravitational fast computing

Active Publication Date: 2018-12-11
GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, there is no mature method that can meet the requirements of fast calculation of the disturbance gravitational force along the spatial envelope of large-scale maneuvering ballistics in any adjacent space

Method used

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  • A Perturbed Gravitational Approach to the Space Envelope of Large-Scale Maneuvering Ballistics along Nearby Space
  • A Perturbed Gravitational Approach to the Space Envelope of Large-Scale Maneuvering Ballistics along Nearby Space
  • A Perturbed Gravitational Approach to the Space Envelope of Large-Scale Maneuvering Ballistics along Nearby Space

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Experimental program
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Embodiment

[0131] Simulation based on the CAV-H aircraft model, the basic simulation conditions are set as follows: ① mass m = 908kg, reference area Sm = 0.48375m2; ② re-entry point state parameters: speed V I =6500m / s, velocity inclination θ I = 0°, height H I =80km; ③Terminal state parameter of gliding section: speed V k =2500m / s, velocity inclination θ k = 0°, height H k =30km, the terminal track yaw angle deviation is not more than ±5°; ④ Flight constraints: maximum heat flux density Maximum dynamic pressure q max =100kPa, maximum overload n max =3g; ⑤ The waiting distance from the target point at the end of the terminal: S togo = 100 km.

[0132] The simulation computer configuration is: Intel(R) Core(TM) i5-3470CPU@3.20GHz, memory 3.46GB. The software environment is WindowXP operating system, and the calculation program is developed based on VC++6.0.

[0133] The method for approaching the disturbance gravitational force approaching the space envelope of the large-scale m...

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Abstract

The invention discloses a disturbing gravity approximation method for a large-range maneuvering trajectory space envelope along a near space. The method comprises the following steps of establishing mathematic models of the lateral width and longitudinal range of a trajectory envelope; establishing a pole-changing coordinate system; establishing an aircraft dynamic model in the pole-changing coordinate system; calculating a three-dimensional trajectory envelope of the pole-changing coordinate system; dividing the whole airspace of the pole-changing coordinate system; establishing a general coordinate system space envelope disturbing gravity reconstruction model; judging a grid where a current trajectory position is; establishing a local area coordinate system in the computational grid; and performing approximation calculation on a disturbing gravity net function in the grid. The trajectory space envelope calculation method disclosed by the invention can cover the large-range maneuvering trajectory along the near space in any condition; the disturbing gravity along the trajectory is calculated according to the method provided by the invention; and the method has the characteristics of small calculation scale, high calculation speed and high calculation precision, and can meet the requirements of trajectory planning, guidance calculation and the like on calculation amount and calculation speed.

Description

technical field [0001] The invention relates to a method for quickly calculating the disturbance gravitational force of the large-scale maneuvering trajectory space envelope along the adjacent space in the field of aircraft dynamics modeling, in particular to a disturbance gravitational approximation method along the large-scale maneuvering trajectory space envelope of the adjacent space. Background technique [0002] The large-scale maneuvering trajectory in the near space specifically refers to the trajectory of the hypersonic glide vehicle, including the initial descent trajectory and the glide trajectory. The starting point is the re-entry point and the end point is the end of the glide trajectory. This kind of ballistic trajectory stays in the adjacent space for a long time, has the characteristics of lateral large-scale maneuvering, and is significantly affected by the gravitational force of the earth's outer space disturbance. Disturbing gravity affects the determinat...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 周欢丁智坚郑伟汤国建
Owner GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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