Launch vehicles with ring-shaped external elements, and associated systems and methods
Technology of a ring element, aircraft, applied in the field of carrier aircraft
Active Publication Date: 2014-09-17
蓝源有限责任公司
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[0003] an ongoing challenge associated with the rocket's mission is the reusability of the system
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[0026] This document is primarily directed to launch vehicles (eg, rockets) having annular outer elements and / or fixed and detachable deceleration surfaces, and related systems and methods. For the sake of brevity, some details describing structures and processes that are well known and often associated with rocket flow surfaces and / or other structures are not set forth in the description below. Furthermore, although some embodiments are set forth below, other embodiments may exist that may have different configurations, arrangements, and / or components than those described in this section. In particular, other embodiments may have additional elements and / or lack the following Figure 1A-16 one or more of the elements described.
[0027] Many embodiments of the techniques described below may take the form of computer-executable instructions, including programs executed by a programmable computer or controller. Those skilled in the relevant art will understand that the techniq...
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Launch vehicles (1400) with ring-shaped external elements (1480), and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle (1400) having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis (V) extending between the first and second ends, and having an external, outwardly facing surface. The system further includes an annular element (1480) carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element has a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system is carried by the launch vehicle, and has at least one nozzle (1411) positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.
Description
technical field [0001] This document relates generally to launch vehicles having annular external elements and related systems and methods. Background technique [0002] Rockets have been used for many years to put human or unmanned payloads into orbit. Such rockets sent humans into space and the moon for the first time, and successively launched countless satellites into Earth orbit and beyond. The rocket is used to propel unmanned space probes and, more recently, to put structures, supplies and people into orbit to the International Space Station. [0003] An ongoing challenge associated with rocket missions is the reusability of the system. Aspects of this paper address this challenge. SUMMARY OF THE INVENTION [0004] In one embodiment of the present invention, an aerospace system is provided that includes a launch vehicle, an annular element, and a propulsion system. Wherein the vehicle may have a first end and a second end substantially opposite the first end, th...
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IPC IPC(8): B64G1/00B64G1/62
CPCB64G1/002B64G1/14B64G1/40B64G1/24F42B10/50B64G1/645F42B10/48F42B10/64F42B10/02B64G1/12B64G1/623B64G1/4021B64G1/2229B64G1/222B64G1/402B64G1/62
Inventor 马克·费瑟斯通约翰·迈克尔·桑德斯罗杰·E·南希艾瑞克·大卫·韦策尔
Owner 蓝源有限责任公司