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 car

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

Experimental program
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Example Embodiment

[0043] Example one

[0044] The H-2B carrier rocket is a two-stage semicocuted, and the core-stage liquid hydrogen hydrogen is advanced, and two LE-7 engines are configured at the primary level. The secondary is configured with a Le-5B engine, and bundled four solid boosters. ; 350km, 51 ° inclination LEO circle, solid booster quality to the correction constant of carrying capacity 1 For -0.1, the core level quality to the correction constant of carrying capacity K 2 For -0.3, the above-level quality to the carrying capacity correction constant K 3 For -1, therefore, the 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, each of the solid booster is increased by 1T, the carrying capacity will reduce 100kg; the mass of the solid booster is reduced by 1T, the carrying capacity will increase 100kg; the quality of the core level is 500kg, carry The ability will reduce 150kg; the quality of the core l...

Example Embodiment

[0047] Example 2

[0048] The Ali'an 5eca launch rocket is a two-stage semicocuted, and the core-level liquid hydrogen liquid oxygen is advanced, and a Vinger engine is configured at the second level to configure a Vinci engine, bundled two solid boosters. In Guyana launch field, 250km, 5 ° inclination LEO circular orbit, solid booster quality to the carrying capacity correction constant K 1 To -0.13, the core level quality to the correction constant of carrying capacity K 2 To -0.113, the above-level quality correction constant of carrying capacity K 3 For -1, therefore, the 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, each of the quality of the solid booster is increased by 1T, the carrying capacity will reduce 130kg; the mass of the solid booster is reduced by 1T, the carrying capacity will increase by 130kg; the quality of the core level is 100kg, carry The ability will reduce 11.3kg...

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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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