Launch Vehicles

Moss, J.B.; Dorrington, G. E.

doi:10.1002/9781119971009.ch7

Cited by 1 publication

(8 citation statements)

References 9 publications

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“…Although this type of TPS is much lighter than heat sinks and mass transfer, and reusable in contrast to ablative coating, it still represents a substantial proportion of the vehicle's mass. Space Shuttle is equipped with such a TPS, in the shape of ceramic tiles and blankets, and it represents 9.2 per cent of its landing mass (Moss, 1991).…”

Section: Re-entry Heatingmentioning

confidence: 99%

“…The evaluation of the configuration is succeeded by the mass, wing loading and thrust estimation based on the velocity increment, Dv, required for a 360 km equatorial LEO. Using the equations for spacecraft emplacement (Moss, 1991), a velocity of 7,910 m/s is needed for a 360 km LEO. To this, 1,800 m/s gravity and drag losses are added (Moss, 1991).…”

Section: Design Evaluationmentioning

confidence: 99%

“…Using the equations for spacecraft emplacement (Moss, 1991), a velocity of 7,910 m/s is needed for a 360 km LEO. To this, 1,800 m/s gravity and drag losses are added (Moss, 1991). Subtracting calculated gravity and drag losses of up to 9,000 m which are 1,270 m/s, because of the aircraft mode of operation of the aerospaceplane, and 480 and 460 m/s because of the initial velocity and because of westwards launch, the velocity increment, Dv, of 7,500 m/s is obtained as shown in Table III.…”

Section: Design Evaluationmentioning

confidence: 99%

“…The principle behind an aerospaceplane in relation to the objective requirement of LEOARTE is its aircraft-like configuration. In contrast to other concepts such as the rocket booster-orbiter, it offers the advantage of much lower drag and gravity losses (Moss, 1991). With an aerospaceplane taking-off from a runway, flying with the efficiency of an aircraft and reaching an altitude, speed and launch angle of 9,000 m Mach 1.6 and 25°, nearly two thirds of the gravity and drag losses are avoided.…”

Section: Leoarte Aerospaceplanementioning

confidence: 99%

“…The first and second phases of the mission profile of all aerospaceplane concepts aim to a vehicle design which would take-off from a runway like a conventional aircraft and then reach an altitude and speed to reduce gravity and drag losses and achieve an initial velocity for its subsequent rocket flight to orbit (Moss, 1991). This aim is approached either by a subsonic, a subsonic and a short supersonic, or a mainly hypersonic flight.…”

Section: Mission Profilementioning

confidence: 99%

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Earth-to-space and high-speed “air” transportation: an aerospaceplane design

Kehayas

2019

AEAT

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Purpose The purpose of this paper is to attempt an aerospaceplane design with the objective of Low-Earth-Orbit-and-Return-to-Earth (LEOARTE) under the constraints of safety, low cost, reliability, low maintenance, aircraft-like operation and environmental compatibility. Along the same lines, a “sister” point-to-point flight on Earth Suborbital Aerospaceplane is proposed. Design/methodology/approach The LEOARTE aerospaceplane is based on a simple design, proven low risk technology, a small payload, an aerodynamic solution to re-entry heating, the high-speed phase of the outgoing flight taking place outside the atmosphere, a propulsion system comprising turbojet and rocket engines, an Air Collection and Enrichment System (ACES) and an appropriate mission profile. Findings It was found that a LEOARTE aerospaceplane design subject to the specified constraints with a cost as low as 950 United States Dollars (US$) per kilogram into Low Earth Orbit (LEO) might be feasible. As indicated by a case study, a LEOARTE aerospaceplane could lead, among other activities in space, to economically viable Space-Based Solar Power (SBSP). Its “sister” Suborbital aerospaceplane design could provide high-speed, point-to-point flights on the Earth. Practical implications The proposed LEOARTE aerospaceplane design renders space exploitation affordable and is much safer than ever before. Originality/value This paper provides an alternative approach to aerospaceplane design as a result of a new aerodynamically oriented Thermal Protection System (TPS) and a, perhaps, improved ACES. This approach might initiate widespread exploitation of space and offer a solution to the high-speed “air” transportation issue.

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Section: Re-entry Heatingmentioning

confidence: 99%

Section: Design Evaluationmentioning

confidence: 99%