Three-stage orbit injection space launch vehicle

A carrier and track technology, applied in the direction of aerospace vehicle propulsion system devices, etc., can solve the problems of high technical difficulty, large flight Mach number Ma span, and large take-off mass of the carrier, so as to improve engine thrust and reduce design difficulty Effect

Active Publication Date: 2017-10-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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  • Claims
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AI Technical Summary

Problems solved by technology

However, the new carrier schemes powered by these engines all use two stages to enter orbit, and the take-off mass of the entire carrier is very large
Since the flight Mach number Ma span of each stage of the two-stage launch vehicle is relatively large (the maximum span exceeds 10Ma), its technical difficulty is also relatively high

Method used

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  • Three-stage orbit injection space launch vehicle
  • Three-stage orbit injection space launch vehicle
  • Three-stage orbit injection space launch vehicle

Examples

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Embodiment

[0053] Taking 200km circular orbit and 500kg payload as an example, the overall parameters and trajectory of the three-stage orbital space vehicle in the present invention have been calculated, as figure 2 and image 3 .

[0054] figure 2 and image 3 In the OA section, the engines of the first-stage RBCC-powered aircraft and the second-stage RBCC-powered aircraft work together; in the AB section, the engines of the first-stage RBCC-powered aircraft work independently; in the BC section, the engines of the second-stage RBCC-powered aircraft work; CD The segment works for the engines of the third-stage rocket-powered vehicle. When point A is Ma=2.5 Mach, the engine shutdown point of the second-stage RBCC powered aircraft, point B is the separation point of the first-stage RBCC-powered aircraft and the second RBCC-powered aircraft and the third-stage rocket-powered aircraft, and point C is the first-stage RBCC-powered aircraft. The point where the second-stage RBCC-powered...

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Abstract

The invention discloses a three-stage orbit injection space launch vehicle. The three-stage orbit injection space launch vehicle comprises a first-stage RBCC power aircraft, a second-stage RBCC power aircraft and a third-stage rocket power aircraft, wherein the second-stage RBCC power aircraft is arranged at the back of the first-stage RBCC power aircraft, and the third-stage rocket power aircraft is arranged in the second-stage RBCC power aircraft. According to the three-stage orbit injection space launch vehicle, the requirement for takeoff thrust is low, and the performance of engines and the whole efficiency are enhanced.

Description

technical field [0001] The invention belongs to the technical field of space vehicle launch, and in particular relates to a three-stage orbit space vehicle. Background technique [0002] At present, space launch vehicles are powered by rocket engines during the entire flight process, and adopt a vertical take-off scheme. Since the rocket engine needs its own oxidant and fuel, its specific impulse performance is relatively low, and the economy of the vehicle is poor. At present, technical personnel at home and abroad are studying a variety of air-breathing engines, such as rocket-based combined cycle (abbreviated as RBCC) engines, turbine-based combined cycle (abbreviated as TBCC) engines and air-breathing rocket engines, etc., fully absorb air when flying in the atmosphere. The oxygen in the engine reduces the carrying amount of the oxidant, improves the specific impulse performance of the engine and the economy of the vehicle. However, the new carrier schemes powered by t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40
Inventor 吕翔李俊闫晓东秦飞何国强
Owner NORTHWESTERN POLYTECHNICAL UNIV
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