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Record Details

Record 53 of 16814
Project ARGO: The design and analysis of an all-propulsive and an aeroassisted version of a manned space transportation vehicle
Offline Availability: Go to Request Form
Author and Affiliation:
Wang, H.(Michigan Univ., Ann Arbor, MI, United States)
Seifert, D.(Michigan Univ., Ann Arbor, MI, United States)
Waidelich, J.(Michigan Univ., Ann Arbor, MI, United States)
Mileski, M.(Michigan Univ., Ann Arbor, MI, United States)
Herr, D.(Michigan Univ., Ann Arbor, MI, United States)
Wilks, M.(Michigan Univ., Ann Arbor, MI, United States)
Law, G.(Michigan Univ., Ann Arbor, MI, United States)
Folz, A.(Michigan Univ., Ann Arbor, MI, United States)
Abstract: The Senior Aerospace System Design class at the University of Michigan undertook the design of a manned space transportation vehicle (STV) that would transport payloads between low earth orbit (LEO) and geosynchronous earth orbit (GEO). Designated ARGO after the ship of the Greek adventurer Jason, two different versions of an STV that would be based, refueled, and serviced at the Space Station Freedom were designed and analyzed by the class. With the same 2-man/7-day nominal mission of transporting a 10,000-kg payload up to GEO and bringing a 5000-kg payload back to LEO, the two versions of ARGO differ in the manner in which the delta V is applied to insert the vehicle into LEO upon return from GEO. The all-propulsive ARGO (or CSTV for chemical STV) uses thrust from its LH2/LOX rocket engines to produce the delta V during all phases of its mission. While the aeroassisted ARGO (or ASTV for aeroassisted STV) also uses the same engines for the majority of the mission, the final delta V used to insert the ASTV into LEO is produced by skimming the Earth's atmosphere and using the drag on the vehicle to apply the required delta V. This procedure allows for large propellant, and thus cost, savings, but creates many design problems such as the high heating rates and decelerations experienced by a vehicle moving through the atmosphere at hypersonic velocities. The design class, consisting of 43 senior aerospace engineering students, was divided into one managerial and eight technical groups. The technical groups consisted of spacecraft configuration and integration, mission analysis, atmospheric flight, propulsion, power and communications, life support and human factors, logistics and support, and systems analysis. Two committees were set up with members from each group to create the scale models of the STV's and to produce the final report.
Publication Date: Jan 01, 1989
Document ID:
19940004526
(Acquired Dec 28, 1995)
Accession Number: 94N71281
Subject Category: SPACE TRANSPORTATION
Document Type: Conference Paper
Publication Information: USRA, NASA(USRA University Advanced Design Program Fifth Annual Summer Conference; p 103-110; (SEE 19940004512)
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: Michigan Univ.; Senior Aerospace System Design Class.; Ann Arbor, MI, United States
Description: 8p; In English; 1 functional color page; Original contains color illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AEROASSIST; COST ANALYSIS; DESIGN ANALYSIS; HYDROGEN OXYGEN ENGINES; MANNED SPACECRAFT; PROPULSION SYSTEM CONFIGURATIONS; SPACE TRANSPORTATION; SPACECRAFT CONFIGURATIONS; TRANSFER ORBITS; HUMAN FACTORS ENGINEERING; LIFE SUPPORT SYSTEMS; LOW EARTH ORBITS; SPACE LOGISTICS; SPACECRAFT COMMUNICATION; SPACECRAFT POWER SUPPLIES; SUPPORT SYSTEMS
Imprint And Other Notes: In USRA, NASA/USRA University Advanced Design Program Fifth Annual Summer Conference p 103-110 (SEE N94-71267 09-12)
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