Ground auxiliary take-off runway and method for wheeled horizontal take-off and landing carrier
A carrier and horizontal technology, which is applied in the field of aerospace transportation, achieves the effects of reducing the complexity of the structure, high utilization rate of energy conversion, and simple structure
Active Publication Date: 2021-06-04
BEIJING AEROSPACE TECH INST
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[0011] The invention provides a ground-assisted take-off runway and a method for a wheeled horizontal take-off and landing vehicle, which can solve the problem of the structural mass ratio and the propellant mass ratio of the reusable horizontal take-off and landing aerospace shuttle vehicle in the prior art. The sharply contradictory technical issues between
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[0024] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0025] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...
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The invention provides a ground auxiliary take-off runway and method for a wheeled horizontal take-off and landing carrier, the runway comprises a parking apron, a potential energy conversion section, a horizontal acceleration take-off section and an emergency braking section which are connected in sequence, the parking apron is arranged at the upper part of the horizontal acceleration take-off section, and a set height difference exists between the parking apron and the horizontal acceleration take-off section; the potential energy conversion section and the horizontal acceleration take-off section are arranged at an included angle, the potential energy conversion section comprises a first turning section, an inclined gliding section and a second turning section which are sequentially connected, the first turning section is smoothly connected with the parking apron and the inclined gliding section, and the second turning section is smoothly connected with the inclined gliding section and the horizontal acceleration take-off section; the turning radius R1 of the first turning section is obtained, and the turning radius R2 of the second turning section is obtained. According to the ground auxiliary take-off runway, the technical problem that in the prior art, the sharp contradiction exists between the mass ratio of a repeatedly-used horizontal take-off and landing air-space back-and-forth carrier structure and the mass ratio of a propellant is solved.
Description
technical field [0001] The invention relates to the field of space vehicle technology, in particular to a ground auxiliary take-off runway for a wheeled horizontal take-off and landing vehicle. Background technique [0002] At present, space vehicles are developing in the direction of low cost, high reliability and rapid launch. Space vehicles are also developing from one-time use to partial reuse, and partial reuse to complete reuse. The space launch method is changing from vertical launch to Transition to level takeoff. Compared with rocket engines, air-breathing combined power (without carrying oxidant or carrying a small amount of oxidant) can use the oxygen in the atmosphere to organize combustion with the fuel it carries, and the specific impulse of the engine is greatly improved. Therefore, compared with launch vehicles, combined power The propellant mass ratio (the ratio of the propellant mass to the initial take-off mass of the vehicle) of the propelled space shutt...
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IPC IPC(8): B64F1/00
CPCB64F1/00
Inventor 杨铁成杨月英郭健任志伟刘冠南王书河
Owner BEIJING AEROSPACE TECH INST