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NASA NTRS1991

Research and technology 1991 annual report

As the NASA Center responsible for assembly, checkout, servicing, launch, recovery, and operational support of Space Transportation System elements and payloads, NASA Kennedy is placing increasing emphasis on the center's research and technology program. In addition to strengthening those areas of engineering and operations technology that contribute to safer, more efficient, and more economical execution of the current mission, the technical tools are being developed which are needed to execute the center's mission relative to future programs. The Engineering Development Directorate encompasses most of the labs and other center resources that are key elements of research and technology program implementation and is responsible for implementation of the majority of the projects in this Kennedy Space Center 1991 annual report.

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NASA NTRS1992

Combustion of LOX with H2(sub g) under subcritical, critical, and supercritical conditions (Task 1) and experimental observation of dense spray and mixing of impinging jets (Task 2)

The objective was to achieve a better understanding of the combustion processes of liquid oxygen and gaseous hydrogen under broad range of pressure covering subcritical, critical, and supercritical conditions. The scope of the experimental work falls into the following areas: (1) design of the overall experimental setup; (2) modification of an existing windowed high pressure chamber; (3) design of the LOX feeding system; (4) provision of the safety features in the test rig design; (5) LOX cleanliness requirements; (6) cold shock testing; (7) implementation of data acquisition systems; (8) preliminary tests for system checkout; (9) modification of LOX feeding system; and (10) evaporation tests. Progress in each area is discussed.

Kuo, K. K.↗

NASA NTRS1992

Description of a Pressure Measurement Technique for Obtaining Surface Static Pressures of a Radial Turbine

The aerodynamic performance of a solid uncooled version of a cooled radial turbine was evaluated in the Small Engine Components Test Facility Turbine rig at the NASA Lewis Research Center. Specifically, an experiment was conducted to rotor surface static pressures. This was the first time surface static pressures had been measured on a radial turbine at NASA Lewis. These pressures were measured by a modified Rotating Data Package (RDP), a standard product manufactured by Scanivalve, Inc. Described here are the RDP, and the modifications that were made, as well as the checkout, installation, and testing procedures. The data presented are compared to analytical results obtained from NASA's MERIDL TSONIC BLAYER (MTSB) code.

Dicicco, L. Danielle↗

NASA NTRS1991

Orbit transfer rocket engine technology program: Automated preflight methods concept definition

The possibility of automating preflight engine checkouts on orbit transfer engines is discussed. The minimum requirements in terms of information and processing necessary to assess the engine'e integrity and readiness to perform its mission were first defined. A variety of ways for remotely obtaining that information were generated. The sophistication of these approaches varied from a simple preliminary power up, where the engine is fired up for the first time, to the most advanced approach where the sensor and operational history data system alone indicates engine integrity. The critical issues and benefits of these methods were identified, outlined, and prioritized. The technology readiness of each of these automated preflight methods were then rated on a NASA Office of Exploration scale used for comparing technology options for future mission choices. Finally, estimates were made of the remaining cost to advance the technology for each method to a level where the system validation models have been demonstrated in a simulated environment.

Erickson, C. M.↗

NASA NTRS1991

Dual frequency along-track interferometry

In recent months, the JPL Airborne Synthetic Aperture Radar (AIRSAR) System has had a C-band Along-Track Interferometer installed. This, in addition to the L-band interferometer already operating in the system, makes it possible to simultaneously acquire two frequency interferometer data. Also, another upgrade involving the radar digital system allows each interferometer to be operated in such a way as to obtain two along-track interferometric baselines differing by a factor of 2 in length. An engineering checkout flight has demonstrated the ability to acquire and process both frequencies to high-resolution velocity maps of the ocean surface. The status of these interferometers and some initial data are presented.

Carande, R. E.↗

NASA NTRS1992

Anthropomorphic teleoperation: Controlling remote manipulators with the DataGlove

A two phase effort was conducted to assess the capabilities and limitations of the DataGlove, a lightweight glove input device that can output signals in real-time based on hand shape, orientation, and movement. The first phase was a period for system integration, checkout, and familiarization in a virtual environment. The second phase was a formal experiment using the DataGlove as input device to control the protoflight manipulator arm (PFMA) - a large telerobotic arm with an 8-ft reach. The first phase was used to explore and understand how the DataGlove functions in a virtual environment, build a virtual PFMA, and consider and select a reasonable teleoperation control methodology. Twelve volunteers (six males and six females) participated in a 2 x 3 (x 2) full-factorial formal experiment using the DataGlove to control the PFMA in a simple retraction, slewing, and insertion task. Two within-subjects variables, time delay (0, 1, and 2 seconds) and PFMA wrist flexibility (rigid/flexible), were manipulated. Gender served as a blocking variable. A main effect of time delay was found for slewing and total task times. Correlations among questionnaire responses, and between questionnaire responses and session mean scores and gender were computed. The experimental data were also compared with data collected in another study that used a six degree-of-freedom handcontroller to control the PFMA in the same task. It was concluded that the DataGlove is a legitimate teleoperations input device that provides a natural, intuitive user interface. From an operational point of view, it compares favorably with other 'standard' telerobotic input devices and should be considered in future trades in teleoperation systems' designs.

Hale, J. P., II↗

NASA NTRS1992

A conceptual design of a large aperture microwave radiometer geostationary platform

A conceptual design of a Large Aperture Microwave Radiometer (LAMR) Platform has been developed and technology areas essential to the design and on-orbit viability of the platform have been defined. Those technologies that must be developed to the requirement stated here for the LAMR mission to be viable include: advanced radiation resistant solar cells, integrated complex structures, large segmented reflector panels, sub 3 kg/m(exp 2) areal density large antennas, and electric propulsion systems. Technology areas that require further development to enhance the capabilities of the LAMR platform (but are not essential for viability) include: electrical power storage, on-orbit assembly, and on-orbit systems checkout and correction.

Garn, Paul A.↗

NASA NTRS1992

Ulysses mission operations

The Ulysses mission is described in terms of in-Shuttle operations, initial in-orbit operations, routine operations, operational organization, and data gathering and production. The configuration of the Ulysses payload is illustrated, and the flight to orbit is described including a three-hour on-orbit checkout. The first contact was reported at the Deep Space Network station followed by an adjustment of the spacecraft solar-aspect angle and the acquisition of ranging and Doppler data. In-orbit operations include the earth acquisition maneuver, a trajectory correction maneuver, and a payload switch. Continuous data gathering is discussed with reference to the Jupiter encounter and the first and second oppositions and conjunctions. The data-gathering components comprise ground stations, a data-processing computer, and a data-records system. Data production is performed in an off-line mode that does not interfere with the real-time operations.

Beech, P.↗

NASA NTRS1991

EMU processing - A myth dispelled

The refurbishment-and-checkout 'processing' activities entailed by the Space Shuttle Extravehicular Mobility Units (EMUs) are currently significantly more modest, at 1050 man-hours, than when Space Shuttle services began (involving about 4000 man-hours). This great improvement in hardware efficiency is due to the design or modification of test rigs for simplification of procedures, as well as those procedures' standardization, in conjunction with an increase in hardware confidence which has allowed the extension of inspection, service, and testing intervals. Recent simplification of the hardware-processing sequence could reduce EMU processing requirements to 600 man-hours in the near future.

Peacock, Paul R.↗

NASA NTRS1992

In-space assembly-servicing requirements

A method for developing the requirements for in-space assembly, servicing, and checkout of proposed Mars space transfer vehicles is discussed. Required in-space operations and functions are identified in relation to various Earth to Orbit (ETO) vehicles by looking at the manifesting options of baseline Mars Space Transfer Vehicles (STV). Each operation is then reduced to a minimum complexity state resulting in a set of operational primitive functions. These primitive functions are used to assess the trade-offs between robotic, telerobotic, and EVA operations. The study demonstrates that the complexity of the in-space operations remains stable with ETO vehicle size, and therefore the functions, and ultimately the infrastructure required to support proposed missions, are relatively unaffected by varying the ETO vehicle size within the range considered for this study.

Cockrell, Charles E.↗

NASA NTRS1989

Design the support rather than support the design

Recommendations are presented for reducing the operational cost of the Space Shuttle. Operational cost drivers at the launch site are identified by examining Shuttle operational data collected over the past two and a half years, and arguments are presented for incorporating support and maintainability criteria in the design process. It is also shown that the increased application of automation to evaluate systems and conduct operations will provide ways to reduce launch operations costs in addition to other benefits, such as increasing the speed of the total checkout, reducing manpower requirements, reducing the possibility of human error, and minimizing documentation changes.

Scholz, Arthur L.↗

NASA NTRS1990

Space Station Freedom accommodation of the Human Exploration Initiative

The design requirements of the Space Station Freedom (SSF) are proposed based on the requirements and assumptions of the Human Exploration Initiative. In this summary of a NASA study consideration is given to the mission-supporting capabilities needed to sustain support of a continuous human presence in earth orbit for scientific activities. The initial SSF configuration (called Assembly Complete) is found to be insufficient in terms of the optimal provisions for crew size, power, pressurized volume, and truss structure. Specific design requirements are also given for the Lunar Transfer Vehicle, and the checkout of this vehicle creates additional demands on the SSF facilities. General specifications are given for the SSF modules, vehicle processing, remote manipulator, and mobile transporter within the context of a continuous human presence in orbit.

Meredith, Barry D.↗

NASA NTRS1992

National Launch System KSC facilities and operations

The current planning for the launch site ground operations and facilities required at the Kennedy Space Center to accommodate the National Launch System (NLS) are described. Special consideration is given to the program activities associated with reducing costs for ground operations and with the ground operations vehicle processing scenarios for launching the NLS vehicles from KSC. The KSC facilities described include the Payload Encapsulation Facility, the Mobile Launcher Platform, and the Cargo Transfer Vehicle Checkout Facility. Attention is also given to the modifications of existing facilities required to accommodate the NLS facilities and the transportation and handling equipment.

Evans, R. T., Jr.↗

NASA NTRS1992

Vehicle health management technology needs

Background material on vehicle health management (VHM) and health monitoring/control is presented. VHM benefits are described and a list of VHM technology needs that should be pursued is presented. The NASA funding process as it impacts VHM technology funding is touched upon, and the VHM architecture guidelines for generic launch vehicles are described. An example of a good VHM architecture, design, and operational philosophy as it was conceptualized for the National Launch System program is presented. Consideration is given to the Strategic Avionics Technology Working Group's role in VHM, earth-to-orbit, and space vehicle avionics technology development considerations, and some actual examples of VHM benefits for checkout are given.

Hammond, Walter E.↗

NASA NTRS1992

Description of a pressure measurement technique for obtaining surface static pressures of a radial turbine

Dicicco, L. D.↗

NASA NTRS1992

Requirements for on-orbit operations

Consideration is given to the impact of on-orbit operations during the assembly and checkout of potential piloted Mars spacecraft, and the development of the requirements for those operations. An operational scenario is developed based on assumed earth-to-orbit capability, a ground based support capability, and a baseline Mars Space Transfer Vehicle. The scenarios developed define each of the operations that must transpire at the system level, thus expanding the planning horizon for the SEI.

Cockrell, Charles E.↗

NASA NTRS1989

Large Deployable Reflector (LDR) system concept and technology definition study. Analysis of space station requirements for LDR

A study was conducted to determine how the Large Deployable Reflector (LDR) might benefit from the use of the space station for assembly, checkout, deployment, servicing, refurbishment, and technology development. Requirements that must be met by the space station to supply benefits for a selected scenario are summarized. Quantitative and qualitative data are supplied. Space station requirements for LDR which may be utilized by other missions are identified. A technology development mission for LDR is outlined and requirements summarized. A preliminary experiment plan is included. Space Station Data Base SAA 0020 and TDM 2411 are updated.

Agnew, Donald L.↗

NASA NTRS1991

Vehicle/payload interface specification for the reusable reentry satellite

This document describes the common interface requirements between the Vehicle Segment and the Payload Segment of the Reusable Reentry Satellite (RRS) system. The system consists of a single transport vehicle design that provides a uniform, unidirectional payload gravitational environment which is selectable during on-orbit operations over the range of 10(exp -5) (microgravity) to 1.5 g's. The initial Reusable Reentry Vehicle/Payload Module (RRV/PM) integration and checkout will occur at the launch base unless otherwise agreed to in a mission-unique addendum to this specification. Pre-integration interface qualification shall be done using emulators as described.

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