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Small deviation rapid correction method for carrying capacity of solid binding carrier rocket

A technology of carrying capacity and launch vehicle, which is applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve the problems of high computational complexity and large amount of calculation of carrying capacity, achieve considerable technical application prospects, and fully exploit , the effect of full carrying capacity potential

Pending Publication Date: 2021-06-15
NO 63921 UNIT OF PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in the prior art, whenever the mass of the rocket module changes, it is necessary to recalculate the carrying capacity of the rocket, resulting in high computational complexity and a large amount of calculation for the carrying capacity in the overall design process
Therefore, even when the mass of the rocket module changes slightly, there is still the problem of high computational complexity and large amount of calculation for the carrying capacity

Method used

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  • Small deviation rapid correction method for carrying capacity of solid binding carrier rocket
  • Small deviation rapid correction method for carrying capacity of solid binding carrier rocket
  • Small deviation rapid correction method for carrying capacity of solid binding carrier rocket

Examples

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Effect test

Embodiment 1

[0044] The H-2B carrier rocket has a two-and-a-half-stage configuration. The core stage is propelled by liquid hydrogen and liquid oxygen. The first stage is equipped with two LE-7 engines, the second stage is equipped with an LE-5B engine, and four solid boosters are bundled. ; launch a 350km, 51° inclination LEO circular orbit at the Tanegashima launch site, and the correction constant K of the mass of the solid booster to the carrying capacity 1 is -0.1, the correction constant K of the primary mass of the core to the carrying capacity 2 is -0.3, the correction constant K of the mass of the upper stage to the carrying capacity 3 is -1, therefore, the change value of carrying capacity ΔM E The expression is:

[0045] Δm E =-0.1ΔM 1 -0.3ΔM 2 -ΔM 3 ;

[0046] According to the above expression, it can be seen that for every 1t increase in the mass of the solid booster, the carrying capacity will decrease by 100kg; for every 1t decrease in the mass of the solid booster, t...

Embodiment 2

[0048] The Ariane 5ECA carrier rocket has a two-and-a-half-stage configuration. The core stage is propelled by liquid hydrogen and liquid oxygen. The first stage is equipped with a Vulcan engine, the second stage is equipped with a Vinci engine, and two solid boosters are bundled. Launching a 250km, 5° inclination LEO circular orbit at the Guyana launch site, the correction constant K of the mass of the solid booster to the carrying capacity 1 is -0.13, the correction constant K of the primary mass of the core to the carrying capacity 2 is -0.113, the correction constant K of the mass of the upper stage to the carrying capacity 3 is -1, therefore, the change value of carrying capacity ΔM E The expression is:

[0049] Δm E =-0.13ΔM 1 -0.113ΔM 2 -ΔM 3 ;

[0050] According to the above expression, it can be seen that for every 1t increase in the mass of the solid booster, the carrying capacity will decrease by 130kg; for every 1t decrease in the mass of the solid booster, ...

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Abstract

The invention discloses a small deviation rapid correction method for the carrying capacity of a solid binding carrier rocket, and the method comprises the following steps: giving the mass, thrust, specific impulse and working time of each module of a reference scheme of the solid binding carrier rocket, and calculating the carrying capacity of the solid binding carrier rocket in a designated target orbit; calculating the change rate of the carrying capacity relative to the mass of each module; and correcting the carrying capacity by using the mass change of each module and the change rate of the carrying capacity relative to the mass of the module. According to the small deviation rapid correction method, the rocket carrying capacity deviation can be rapidly corrected under the condition that the mass deviation is given, and the method has the advantages that the carrying capacity calculation complexity is simplified, the calculation amount is reduced, and the rocket design efficiency is improved.

Description

technical field [0001] The invention belongs to the technical field of overall design of launch vehicles, and in particular relates to a method for quickly correcting small deviations in the carrying capacity of solid-bound launch vehicles. Background technique [0002] At present, the propulsion power of launch vehicles is divided into solid power and liquid power. Solid motors have the characteristics of simple testing, convenient transfer, and easy launch guarantee; liquid engines have high propulsion specific impulse, can be finely controlled, and are easy to scale; through solid-liquid combination means , the booster uses solid power, the rocket core stage uses liquid power, and the solid bundled launch vehicle configuration relies on solid engines to provide most of the take-off thrust during the boost stage, and relies on liquid engines to provide orbital thrust during the high-altitude stage. On the one hand, it can greatly simplify the rocket. Launch guarantee is di...

Claims

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Application Information

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IPC IPC(8): G06F30/17G06F30/20
CPCG06F30/17G06F30/20
Inventor 周城宏程洪玮刘阳谭云涛雍子豪谷建光刘鹰朱雄峰王一杉韩秋龙
Owner NO 63921 UNIT OF PLA
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