Proceedings - Space Transportation System Propulsion Technology Conference. Volume 4 - Cryogens
Insulation for propellant tanks of space shuttle
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The space transportation system and its payloads
The STS and its three major elements - the Space Shuttle, Spacelab, and a propulsive Upper Stage - are discussed. Attention is given to other NASA programs which have a bearing on STS, including Skylab, Landsat, and ATS.
Naugle, J.↗
Space adaptation syndrome: Incidence and operational implications for the space transportation system program
Better methods for the prediction, prevention, and treatment of the space adaptation syndome (SAS) were developed. A systematic, long range program of operationally oriented data collection on all individuals flying space shuttle missions was initiated. Preflight activities include the use of a motion experience questionnaire, laboratory tests of susceptibility to motion sickness induced by Coriolis stimuli and determinations of antimotion sickness drug efficacy and side effects. During flight, each crewmember is required to provide a daily report of symptom status, use of medications, and other vestibular related sensations. Additional data are obtained postflight. During the first nine shuttle missions, the reported incidence of SAS has been48%. Self-induced head motions and unusual visual orientation attitudes appear to be the principal triggering stimuli. Antimotion sickness medication, was of limited therapeutic value. Complete recovery from symptoms occurred by mission day three or four. Also of relevance is the lack of a statistically significant correlation between the ground based Coriolis test and SAS. The episodes of SAS have resulted in no impact to shuttle mission objectives and, no significant impact to mission timelines.
Homick, J. L.↗
Space Transportation System Liftoff Debris Mitigation Process Overview
Liftoff debris is a top risk to the Space Shuttle Vehicle. To manage the Liftoff debris risk, the Space Shuttle Program created a team with in the Propulsion Systems Engineering & Integration Office. The Shutt le Liftoff Debris Team harnesses the Systems Engineering process to i dentify, assess, mitigate, and communicate the Liftoff debris risk. T he Liftoff Debris Team leverages off the technical knowledge and expe rtise of engineering groups across multiple NASA centers to integrate total system solutions. These solutions connect the hardware and ana lyses to identify and characterize debris sources and zones contribut ing to the Liftoff debris risk. The solutions incorporate analyses sp anning: the definition and modeling of natural and induced environmen ts; material characterizations; statistical trending analyses, imager y based trajectory analyses; debris transport analyses, and risk asse ssments. The verification and validation of these analyses are bound by conservative assumptions and anchored by testing and flight data. The Liftoff debris risk mitigation is managed through vigilant collab orative work between the Liftoff Debris Team and Launch Pad Operation s personnel and through the management of requirements, interfaces, r isk documentation, configurations, and technical data. Furthermore, o n day of launch, decision analysis is used to apply the wealth of ana lyses to case specific identified risks. This presentation describes how the Liftoff Debris Team applies Systems Engineering in their proce sses to mitigate risk and improve the safety of the Space Shuttle Veh icle.
Mitchell, Michael↗
Space Transportation System Cargo projects: inertial stage/spacecraft integration plan. Volume 1: Management plan
The Kennedy Space Center (KSC) Management System for the Inertial Upper Stage (IUS) - spacecraft processing from KSC arrival through launch is described. The roles and responsibilities of the agencies and test team organizations involved in IUS-S/C processing at KSC for non-Department of Defense missions are described. Working relationships are defined with respect to documentation preparation, coordination and approval, schedule development and maintenance, test conduct and control, configuration management, quality control and safety. The policy regarding the use of spacecraft contractor test procedures, IUS contractor detailed operating procedures and KSC operations and maintenance instructions is defined. Review and approval requirements for each documentation system are described.
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National Launch System Space Transportation Main Engine
The present liquid-oxygen/liquid-hydrogen engine is described as meeting the specific requirements of the National Launch System (NLS) Program including cost-effectiveness and robustness. An overview of the NLS and its objectives is given which indicates that the program aims to develop a flexible launch system to meet security, civil, and commercial needs. The Space Transportation Main Engine (STME) provides core and boost propulsion for the 1.5-stage vehicle and core propulsion for the solid booster vehicle. The design incorporates step-throttling, order-of-magnitude reductions in welds, and configuration targets designed to optimize robustness. The STME is designed to provide adaptable and dependable propulsion while minimizing recurring costs and is designed to meet the needs of NLS and other typical space-transportation programs currently being planned.
Hoodless, Ralph M., Jr.↗
Highly Reusable Space Transportation System Concept Evaluation (The Argus Launch Vehicle)
This paper summarizes the results of a conceptual design study that was performed in support of NASA's recent Highly Reusable Space Transportation study. The Argus concept uses a Maglifter magnetic-levitation sled launch assist system to accelerate it to a takeoff ground speed of 800 fps on its way to delivering a payload of 20,000 lb. to low earth orbit. Main propulsion is provided by two supercharged ejector rocket engines. The vehicle is autonomous and is fully reusable. A conceptual design exercise determined the vehicle gross weight to be approximately 597,250 lb. and the dry weight to be 75,500 lb. Aggressive weight and operations cost assumptions were used throughout the design process consistent with a second-generation reusable system that might be deployed in 10-15 years. Drawings, geometry, and weight of the concept are included. Preliminary development, production, and operations costs along with a business scenario assuming a price-elastic payload market are also included. A fleet of three Argus launch vehicles flying a total of 149 flights per year is shown to have a financial internal rate of return of 28%. At $169/lb., the recurring cost of Argus is shown to meet the study goal of $100/lb.-$200/lb., but optimum market price results in only a factor of two to five reduction compared to today's launch systems.
Olds, John R.↗
Space transportation system as seen by an astronaut
Discussion of the astronaut's role in the Space Shuttle and its associated payload operations. It is shown that there will be a shift in the astronaut's tasks as the Shuttle system matures. The Shuttle is designed for automatic guidance, navigation, and control, and the need for active piloting will accordingly decrease. With the shift to onboard autonomous operation, the system management role will expand. Direct tasks with delivery/recovery and laboratory/observatory payloads will continue to expand throughout the Shuttle program duration through the 1980s.
Haise, F. W., Jr.↗
Development of an experiment of opportunity test payload for the space transportation system
This paper describes a means for flying existing Sounding Rocket payloads aboard the Space Shuttle by developing small experiment carriers which become detached from the Orbiter and are later retrieved and reused. An effort is underway at the Goddard Space Flight Center to develop such a carrier which would be flown as an Experiment of Opportunity Payload (EOP). The activity is viewed as a feasibility test, and success will encourage the construction of similar packages for additional sounding rocket experiments, for eventual evolution of p
Shrewsberry, D. J.↗
Satellite services - An added benefit of the space transportation system
It is argued that the greatest economic benefit can be achieved by the Space Shuttle Orbiter's use as a satellite servicing platform if the following conditions are fulfilled: (1) the international user community must build serviceability features into its satellite and orbital platform designs, based on a common set of guidelines; (2) the various tools required for satellite servicing must be developed in a timely manner; and (3) servicing costs must be kept as low as possible, in order to appeal to the greatest number and variety of satellite operators. A three-part program development schedule is proposed, beginning with near-Orbiter servicing in low earth orbit, continuing with servicing at orbital heights between the low and geosynchronous at greater distances from the Orbiter, and culminating in the early 1990's with the use of the Space Operations Center (SOC) platform for servicing at all orbital heights.
Herardian, M. M.↗
Proceedings - Space Transportation System Propulsion Technology Conference. Volume 1 - Main Propulsion
Design, fabrication, testing, and materials selection for space shuttle propulsion systems
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Space Processing Applications - Designing the initial space transportation system payloads capability
A review is presented of the broad objectives identified by the U.S. Space Processing Applications program. A description is given of the types of materials to be considered, taking into account aspects of crystal growth, questions of purification and separation, mixing, solidification, and processes in fluids. The program requirements are discussed, giving attention to time in space, energy, research and development payload equipment design efforts, design payloads, early mission automated payloads, and early mission manned payloads.
Hammel, R. L.↗
Space Transportation System Technology Symposium. Volume 1 - Aerothermodynamics and configurations
Aerodynamics and configurations, atmospheric performance, and aerodynamic heating of space shuttle systems
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Space Transportation System Technology Symposium. Volume 6 - Integrated Electronics /including Electric Power/
Research and development of electronic equipment for space shuttle vehicles
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Proceedings - Space Transportation System Propulsion Technology Conference. Volume 2 - Auxiliary propulsion system
Conference on auxiliary propulsion system performance and configurations for space shuttle applications - Vol. 2
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The Consolidated Planning and Scheduling System for Space Transportation and Space Station operations - Successful development experience
In 1992, NASA made the decision to evolve a Consolidated Planning System (CPS) by adding the Space Transportation System (STS) requirements to the Space Station Freedom (SSF) planning software. This paper describes this evolutionary process, which began with a series of six-month design-build-test cycles, using a domain-independent architecture and a set of developmental tools known as the Advanced Scheduling Environment. It is shown that, during these tests, the CPS could be used at multiple organizational levels of planning and for integrating schedules from geographically distributed (including international) planning environments. The potential for using the CPS for other planning and scheduling tasks in the SSF program is being currently examined.
Hornstein, Rhoda S.↗
Linear rocket engines for advanced space transportation systems
The linear rocket engine is shown to be a viable candidate propulsion system for post-Space Shuttle single-stage-to-orbit systems. The linear engine system has been developed and fired demonstrating high performance and long life with firing durations exceeding 500 seconds. The application of the split or dual combustor to the linear engine permits the uses of two different propellant combinations in a single engine system. The split combustor possesses the advantages of the two position extendible bell nozzle in a fixed nozzle configuration. Engine power cycles and applications to typical vehicles are discussed.
Sobin, A. J.↗
Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study, volume 2, addendum 2
The feasibility of developing and producing a launch vehicle from an external tank (ET) and an engine module that mounts inline to the tankage at the aft end and contains six space transportation main engines (STME), was assessed. The primary mission of this launch vehicle would be to place a PLS (personnel launch vehicle) into a low earth orbit (LEO). The vehicle tankage and the assembly of the engine module, was evaluated to determine what, if any, manufacturing/production impacts would be incurred if this vehicle were built along side the current ET at Michoud Assembly Facility. It was determined that there would be no significant impacts to produce seven of these vehicles per year while concurrently producing 12 ETs per year. Preliminary estimates of both nonrecurring and recurring costs for this vehicle concept were made.
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