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Method for evaluating scale of two-stage injection recyclable aircraft

A technology of aircraft and scale, applied in the direction of instruments, calculations, special data processing applications, etc., can solve problems such as the inability to assess whether the aircraft can enter orbit, the size of the aircraft cannot be evaluated, etc.

Active Publication Date: 2018-04-03
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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AI Technical Summary

Problems solved by technology

Existing methods that can calculate the mass of an aircraft at a certain size cannot evaluate whether the aircraft can enter orbit, while methods that can calculate the total mass of an aircraft entering orbit cannot evaluate the size of an aircraft

Method used

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  • Method for evaluating scale of two-stage injection recyclable aircraft
  • Method for evaluating scale of two-stage injection recyclable aircraft
  • Method for evaluating scale of two-stage injection recyclable aircraft

Examples

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Embodiment Construction

[0014] A method for estimating the size of a reusable vehicle in two stages of orbiting, including the following:

[0015] This method firstly determines the load mass and load volume of the flight mission, and based on the requirements for entering orbit and the flight profile, starting from the second-level scale prediction, establishes the relationship between the overall parameters of the aircraft shape, fuel, power, and structural quality at all levels, and finally Obtain the evaluation method of the whole system scale of the two-stage orbit entry with practical reference significance. Specific steps include:

[0016] (1) Based on the overall parameters of the developed multi-type reusable space vehicle, the calculation formula of the structural mass based on the size of each component is formed:

[0017] Body quality:

[0018]

[0019] Wing mass:

[0020]

[0021] Vertical Tail Mass:

[0022]

[0023] Thermal protection system:

[0024]

[0025] Among th...

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Abstract

The invention discloses a method for evaluating a scale of a two-stage injection recyclable aircraft. The method comprises the following steps of step I, calculating a second-stage structure mass of the aircraft in a preset size; step II, calculating a propellant mass required by a second stage; step III, obtaining a second-stage structure size and mass scale parameter after the effective capacityof a second-stage structure is sufficient to load the second-stage propellant and an effective load; step IV, calculating a first-stage structure mass of the aircraft in the preset size; step V, calculating the propellant mass required by a first stage; and step VI, obtaining a first-stage structure size and mass scale parameter after the effective capacity of a first-stage structure is sufficient to load the first-stage propellant. With the method, the structure scale of two-stage injection recyclable aircraft in the case of satisfying the injection demand can be systematically evaluated, and the method can be used for analyzing the influence of different factors such as an engine, a fuel and a track on the overall structure size and the mass scale.

Description

technical field [0001] The invention relates to a method for estimating the scale of a two-stage orbiting reusable aircraft. Background technique [0002] In order to further reduce the cost of space transportation and improve the reliability of transportation, countries around the world are focusing on the development of reusable aircraft and have proposed a variety of single-stage and two-stage orbital entry schemes. At present, there is no scale evaluation method suitable for the complete concept of the two-stage orbiting system at home and abroad. Existing methods that can calculate the mass of an aircraft at a certain size cannot evaluate whether the aircraft can enter orbit, while methods that can calculate the total mass of an aircraft entering orbit cannot evaluate the size of the aircraft. This method uses the overall parameter regression analysis method to obtain the mass and volume scale of the structure. Through reverse analysis, considering the different modal ...

Claims

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Application Information

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IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 刘磊杨肖锋唐伟肖光明魏东刘深深冯毅杜雁霞桂业伟
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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