From Earth to Orbit An Assessment of Transportation Options (1992) / Chapter Skim
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4 Launch Vehicle Options
4 Launch Vehicle Options
Pages 26-39
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From page 26... ...
capabilities in commercial space launches is readily apparent by the trend of commercial satellites toward launches on foreign boosters, brought about by increased capability, better scheduling, and lower cost.
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From page 27... ...
27 Can ._ an: C)
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From page 28... ...
The NES Joint Program estimates development costs of $1 I.5 billion for a first launch in 2002. This estimate includes system design and integration, the Space Transportation Main Engine, development of three launch vehicles, a cargo transfer vehicle, an upper stage, and manufacturing and launch facilities.
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From page 29... ...
There will be time, however, in the NES program to permit concepts of this nature to be explored prior to committing the configurations of NES-2 or NES-l to detailed design and construction. The Committee believes that there will be future requirements for heavy lift capability to serve the Space Exploration Initiative, but that it is too early to determine the specific performance cr~tena that will dictate heavy lift design approaches.
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From page 30... ...
The various vehicles should be designed for optimal operability and reliability, and the family relationship could and should be maintained more at the subsystem and component levels. The Committee recognizes that such a course of action would represent a departure from the postulated family resemblance of the NES series and believes that the reality of producing vehicles could be considerably different from the design concepts presented.
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From page 31... ...
, which is aimed primarily at the 12,000- to 15,000-pound payload class for launch of the second block of the Global Positioning Satellite System (GPS)
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Although assessment of the specific crew return vehicle designs is not within the scope of this study, it is of concern to the Committee because of the potential impact on the Earth-to-orbit requirements necessary to place the vehicle at Space Station Freedom. The Single-Stage Rocket Technology Program Delta Clipper (DC-Y)
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From page 33... ...
Unfortunately, technical immaturity, as well as the high risk associated with the development of such an unconventional device, prompted a change to a still-undeveloped but more conventional modular bell engine.3 Although development of the bell engine is likely to take less time and cost much less than the development of the modular plug engine, it is not as neatly congruent with the DC-Y and may create some drag and heat transfer problems. The Committee also notes that instead of a new modular bell engine, it may be possible to use other engines.
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From page 34... ...
The Committee believes that the use of a lifting body for a reusable single-stage-to-orbit vehicle holds promise and may eventually lead to reduced launch costs, short turnaround time, and operational flexibility. However, the DC-Y has not yet reached the stage at which it can be considered for Earth-to-orbit transportation.
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From page 35... ...
Assured Crew Return Capability Vehicle options for crew return capabilities during the permanently manned phase of the Space Station are currently being investigated. During extended stays on Space Station Freedom, it will be necessary to provide assured crew return capability in case of medical emergencies or other difficulties that require evacuation of the Station.
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From page 36... ...
In the Committee's view, the requirement for assured crew return from the Space Station poses no launch vehicle requirements that are outside the capabilities of systems planned for other purposes. EXISTING INTERNATIONAL LAUNCH SYSTEMS International launch systems are shown in Table 3.
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1991. International Reference Guide to Space Launch Systems.
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From page 38... ...
, - C7PROPOSED INTERNATIONAL LAUNCH SYSTEMS Ariane-5/Hermes The space transportation system incorporating the Ariane-5 launch vehicle and the Hermes space vehicle is a European Space Agency (KS A) project.
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From page 39... ...
the winged reusable version designated HORUS (Hypersonic Orbiting Reusable Upper Stage) , capable of carrying two to six crew members and 4,400 to 8,820 pounds of payload into a nearEarth orbit' or (2)
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