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At least 163 records · Page 9

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NASA NTRS1984

Proteus - An experimenter's view

The scientific experiments package to be carried by the Proteus system takes the form of an Instrument Load carried into orbit by a Space Shuttle, and there mated to a Proteus spacecraft with the Shuttle's Remote Manipulator System. The Proteus system extends to ground support equipment, development tools, and communications, as well as the orbiting satellites. It is expected that Proteus will be able to triple the number of Explorer missions while staying within the current budgetary allocation for such missions. The Proteus spacecraft encompasses a system interface assembly plug, a data handling module, remote interface units, and a power distribution module.

Hibbard, W. D.↗

NASA NTRS1982

Using computer graphics to enhance astronaut and systems safety

The Operator Station Design System (OSDS), a technique of applied computer graphics featuring a flexible interactive software package, is presented in terms of man-machine analyses, flight operations, and systems engineering. In man-machine analyses, the OSDS was used to determine if viewing from the Shuttle Remote Manipulator System was satisfactory and to identify requirements for a pallet-mounted television camera. In another study, extravehicular activity was analyzed using the example of emergency access to latches should they fail in orbit. In terms of flight operations, OSDS can be used to evaluate array monitoring of a solar array power system complex and to provide animated scenarios of mission operations. The most important application of OSDS is in relation to systems engineering, as OSDS can be used to analyze spacecraft and payload design and integration. Payload configurations are included.

Brown, J. W.↗

NASA NTRS2006

STS-121: Discovery Mission Overview Briefing

Tony Ceccacci, Lead STS-121 Space Shuttle Flight director, and Rick LaBrode, Lead STS-121 ULF 1.1 International Space Station Flight Director, are shown in this STS-121 Discovery mission overview. Ceccacci begins with an overview of the mission and gives the mission goals. He also presents various slides of the STS-121 payload that includes: 1) Orbiter Docking System; 2) Integrated Cargo Carrier (ICC); 3) Multipurpose Logistics Module (MPLM); 4) TPS Sample Box Assembly; 5) Shuttle Remote Manipulator System (SRMS); and 6) Orbiter Boom Sensor System (OBSS). He shows a video presentation on the various processes involved in the inspections of the Orbiter that include: 1) Unberthing OBSS; 2) Starboard wing leading edge survey; 3) Wing leading edge passes; 4) Nose cap surveys; 5) Port side surveys; and 6) Docking with the International Space Station. Ceccacci ends his presentation with discussing the work performed from flight day 1 to flight day 14. Rick LaBrode begins with discussing the on-orbit status of the Expedition 13 crew. He then presents a video of the MPLM installation, forward hatch of MPLM, resupply stowage platform, resupply stowage racks, and Oxygen Generator System (OGS) rack. Questions are answered from the media.

Source record↗

NASA NTRS1993

Simulation of the Attitude Determination System for Space Station berthing dynamics research

Langley has developed a simulator of the Space Station coupled to the Space Shuttle via the Remote Manipulator System for use in evaluating handling during Station assembly. To date, evaluations of this scenario had included the Station Attitude Control System (ACS), assuming that the Station Attitude Determination System (ADS) provides perfect information on the coupled configuration. Herein, the complete Station digital autopilot (DAP) is considered including both the ADS and ACS systems. The ADS, its modelling and simulation are briefly overviewed and studies concerning the closed-loop operation of the DAP during local-coordinate, orbital attitude hold are presented. Results show that the presence of a type 0 filter in the ADS angular velocity signal processing has an adverse effect on attitude estimation because of the error in steady-state tracking of the angular velocity following reaction control jet firings. This error propagates into the attitude estimate almost linearly with time and star tracker updates are required at frequent, 3-second intervals if a .001 degree accuracy is to be maintained.

Montgomery, Raymond C.↗

NASA NTRS1982

Satellite services system overview

The benefits of a satellite services system and the basic needs of the Space Transportation System to have improved satellite service capability are identified. Specific required servicing equipment are discussed in terms of their technology development status and their operative functions. Concepts include maneuverable television systems, extravehicular maneuvering unit, orbiter exterior lighting, satellite holding and positioning aid, fluid transfer equipment, end effectors for the remote manipulator system, teleoperator maneuvering system, and hand and power tools.

Rysavy, G.↗

NASA NTRS1999

The Video Guidance Sensor- A Flight Proven Technology

The Video Guidance Sensor (VGS) flew on Shuttle mission STS-95 in October of 1998 to test the VGS functional characteristics on orbit. This was the second flight of the VGS, and during these two flights, both long range and short range data were gathered under a variety of lighting conditions, orbital exposure times, and temperatures. The flight experiment sensor was designed to operate from 1.5 meter range out to 110 meter range, with a field-of-view of 16 X 21 degrees. The VGS tracked its target at a 5 Hz rate and returned 6-degree-of-freedom information on the target's position and attitude relative to the sensor. The VGS was mounted in the Shuttle cargo bay, and its target was mounted on the Spartan spacecraft being carried on this mission. The VGS is a sensor designed to allow an automated vehicle to dock with a spacecraft equipped with a passive target. The VGS is a part of an Automated Rendezvous and Capture (AR&C) system being developed and tested by NASA. The orbital testing included operations with the target on the Shuttle's Remote Manipulator System (RMS) near the start of each flight of the VGS, long-range data (on the STS-95 flight) during the Shuttle rendezvous with the Spartan two days later, and some more RMS operations later in the mission. The data returned from the orbital testing included VGS diagnostics, acquisition, and tracking data, RMS positions, hand-held laser range data, tapes of the data from the VGS video camera, and orbital positioning data from the Spartan and the Shuttle to allow correlation of the VGS data with orbital best-estimate-of-truth data. The Video Guidance Sensor performed well in all phases of the testing, and the VGS is being incorporated into the ground testing of a complete automated rendezvous and docking system. Work on the development of the next generation VGS is continuing.

Howard, Richard T.↗

NASA NTRS1990

Multiple manipulator control from orbiter for Space Station assembly

This paper discusses the assembly process of the Space Station Freedom. It is shown that the assembly of the Space Station will require 29 flights of the Space Shuttle Orbiter: six shuttle flights during the initial assembly stage when the Space Station will not have sufficient life-support capability; seven more flights before the Station will support human occupation independent of the presence of the Space Shuttle; and 16 more flights for achieving full operational capability. The shuttle systems to be used in the Space Station assembly are described together with the results of simulation and analyses. Special attention is given to the Space Shuttle Remote Manipulator System which will be available on all Shuttle flights to support the Space Station assembly.

Price, Charles R.↗

NASA NTRS1982

The Space Shuttle orbiter payload retention systems

Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.

Hardee, J. H.↗

NASA NTRS1989

Design issues in 2-port network models of bilateral remote manipulation

A two-port impedance-network model of a single-degree-of-freedom remote manipulation system in which a human operator at the master port interacts with a task object at the slave port in a remote location is presented. The design of the network involves the selection of feedback gains for the servomechanisms that transmit motion and force information from one port of the two-port to the other in both directions. The proposed methodology allows this selection to be based on both stability requirements and specifications of desired port impedances, given models of the task and the human operator. The resulting design guidelines guarantee stability for any passive task object at the slave port and any passive human impedance at the master port.

Raju, G. Jagannath↗

NASA NTRS2024

MAGIK Animation of Robotic Operations for Flight SpaceX-31 to ISS

The MAGIK Robotics analysis team provides kinematic feasibility assessments for the ISS and has produced an animation to showcase Extravehicular Robotics (EVR) activities for Flight SpaceX (SpX)-31. Shown EVR activities were developed by Flight Operations Directorate (FOD) Robotics (ROBO). The animation also displays the current ISS configuration at the time of the flight in Increment 72. Flight SpX-31 includes a SpaceX Cargo Dragon vehicle docked to Node 2 Forward (N2F) and consists of the delivery of the Coronal Observation Experiment (CODEX) payload. Robotic operations shown include utilization the Special Purpose Dexterous Manipulator (SPDM) based on the Space Station Remote Manipulator System (SSRMS), survey of the cargo trunk, extraction of CODEX from the trunk, stow of SPDM, SSRMS walkoff to the Mobile Remote Servicer (MRS) Base System (MBS), SSRMS grapple of SPDM, translate of the Mobile Transporter (MT), and install of CODEX to Express Logistics Carrier 3 (ELC-3) Site 3. There is no disposal payload for this flight.

ISS↗

NASA NTRS1991

Real Time Data System (RTDS)

Information is given in viewgraph form on the Real Time Data System (RTDS). Topics covered include applications to the Space Station Freedom, the Space Shuttle flight controllers, the Mission Control Center workstations, and the Remote Manipulator Systems (RMS). Also covered are the technology gap, pacing factors, and lessons learned during research.

Heindel, Troy A.↗

NASA NTRS2011

Dexterous Operations on ISS and Future Applications

The Mobile Servicing System (MSS) is a complex robotics system used extensively in the assembly, inspection and maintenance of the International Space Station (ISS). Its external components are comprised of the Space Station Remote Manipulator System (SSRMS), the Mobile Base System (MBS), and the Special Purpose Dexterous Manipulator (SPDM or "Dextre"). Dexterous robotic maintenance operations on the ISS are now enabled with the launch and deployment of "Dextre" in March 2008 and the recently completed commissioning to support nominal operations. These operations include allowing for maintenance of the MSS capability to be executed uniquely via robotic means. Examples are detailed inspection and the removal and replacement of On-orbit Replaceable Units (ORUs) located outside the pressurized volume of the ISS, alleviating astronauts from performing numerous risky and time-consuming extra-vehicular activities (EVAs). In light of the proposed extension of the ISS to 2020 and beyond, "Dextre" can also be seen as a resource for the support and conduct of external ISS experiments. "Dextre" can be utilized to move experiments around ISS, as test bed for more elaborate experiments outside the original design intent, and as a unique platform for external experiments. This paper summarizes the status of "Dextre", its planned use, and future potential for dexterous operations on the ISS. Lessons learned from the planning and execution of SPDM commissioning are first introduced, and significant differences between "Dextre" and SSRMS operations are discussed. The use of ground control as the predominant method for operating "Dextre" is highlighted, along with the benefits and challenges that this poses. Finally, the latest plans for dexterous operations on ISS are summarized including visiting vehicle unloading, nominal maintenance, and operations of a more experimental flavor.

Keenan, P. Andrew↗

NASA NTRS1991

Video guidance sensor for autonomous capture

A video-based sensor has been developed specifically for the close-range maneuvering required in the last phase of autonomous rendezvous and capture. The system is a combination of target and sensor, with the target being a modified version of the standard target used by the astronauts with the Remote Manipulator System (RMS). The system, as currently configured, works well for autonomous docking maneuvers from approximately forty feet in to soft-docking and capture. The sensor was developed specifically to track and calculate its position and attitude relative to a target consisting of three retro-reflective spots, equally spaced, with the center spot being on a pole. This target configuration was chosen for its sensitivity to small amounts of relative pitch and yaw and because it could be used with a small modification to the standard RMS target already in use by NASA.

Howard, Richard T.↗

NASA NTRS1992

Development of task network models of human performance in microgravity

This paper discusses the utility of task-network modeling for quantifying human performance variability in microgravity. The data are gathered for: (1) improving current methodologies for assessing human performance and workload in the operational space environment; (2) developing tools for assessing alternative system designs; and (3) developing an integrated set of methodologies for the evaluation of performance degradation during extended duration spaceflight. The evaluation entailed an analysis of the Remote Manipulator System payload-grapple task performed on many shuttle missions. Task-network modeling can be used as a tool for assessing and enhancing human performance in man-machine systems, particularly for modeling long-duration manned spaceflight. Task-network modeling can be directed toward improving system efficiency by increasing the understanding of basic capabilities of the human component in the system and the factors that influence these capabilities.

Diaz, Manuel F.↗

NASA NTRS1986

Cosmic Background Explorer (COBE) transfer orbit attitude control system

The Cosmic Background Explorer (COBE) spacecraft will be launched by the Shuttle from Vandenberg AFB into a 300 km altitude, 99 deg inclination, 6 a.m. or 6 p.m. ascending node orbit. After release from the Remote Manipulator System (RMS) arm, an on-board monopropellant hydrazine propulsion system will raise the orbit altitude to 900 km. The spacecraft continuously spins during transfer orbit operations with the spin axis nominally horizontal and in or near the orbit plane. The blowdown propulsion system consists of twelve 5 lb thrusters (3 'spin', 3 'despin', and 6 'axial') with the latter providing initially 30 lb of force parallel to the spin axis for orbit raising. The spin/despin jets provide a constant roll rate during the transfer orbit phase of the mission and the axials control pitch and yaw. The axial thrusters are pulsed on for attitude control during coast periods and are normally on- and off-modulated for control during orbit raising. Attitude sensors employed in the control loops include an array of two-axis digital sun sensors and three planar earth scanners for position measurements, as well as six gyroscopes for rate information. System redundancy is achieved by means of unique three-axes-in-a-plane geometry. This triaxial concept results in a fail-safe operational system with no performance degradation for many different component failure modes.

Placanica, Samuel J.↗

NASA NTRS1997

Applied Virtual Reality in Reusable Launch Vehicle Design, Operations Development, and Training

Application of Virtual Reality (VR) technology offers much promise to enhance and accelerate the development of Reusable Launch Vehicle (RLV) infrastructure and operations while simultaneously reducing developmental and operational costs. One of the primary cost areas in the RLV concept that is receiving special attention is maintenance and refurbishment operations. To produce and operate a cost effective RLV, turnaround cost must be minimized. Designing for maintainability is a necessary requirement in developing RLVs. VR can provide cost effective methods to design and evaluate components and systems for maintenance and refurbishment operations. The National Aeronautics and Space Administration (NASA)/Marshall Space Flight Center (MSFC) is beginning to utilize VR for design, operations development, and design analysis for RLVs. A VR applications program has been under development at NASA/MSFC since 1989. The objectives of the MSFC VR Applications Program are to develop, assess, validate, and utilize VR in hardware development, operations development and support, mission operations training and science training. The NASA/MSFC VR capability has also been utilized in several applications. These include: 1) the assessment of the design of the late Space Station Freedom Payload Control Area (PCA), the control room from which onboard payload operations are managed; 2) a viewing analysis of the Tethered Satellite System's (TSS) "end-of-reel" tether marking options; 3) development of a virtual mockup of the International Space Welding Experiment for science viewing analyses from the Shuttle Remote Manipulator System elbow camera and as a trainer for ground controllers; and 4) teleoperations using VR. This presentation will give a general overview of the MSFC VR Applications Program and describe the use of VR in design analyses, operations development, and training for RLVs.

Hale, Joseph P.↗

NASA NTRS1982

Columbia undergoes final shakedown during seven-day STS-4 mission

The launch preparations for the Space Transportation System 4 flight of the space shuttle Columbia are described. The details of the spacecraft's mission profile are given. Several experiments and payloads are described. An account of the remote manipulator system is given. Studies of long-term thermal extremes on the orbiter subsystems and a survey of orbiter induced contamination of the payload bay are identified as mission priorities.

Source record↗

NASA NTRS1979

Space transportation system options for extended duration and power

A modification kit for the Space Transportation System (STS) Orbiter is proposed to provide more power and mission duration for payloads. The power extension package (PEP) - a flexible-substrate solar array deployed on the Space Shuttle Orbiter remote manipulator system - can provide as much as 29 kW total power for durations of 10 to 48 days. The kit is installed only for those flights which require enhanced power or duration. Modifications to the Orbiter thermal control and life support systems to improve heat balance and to reduce consumables are proposed. The changes consist of repositioning the Orbiter forward radiators and replacing the lithium hydroxide scrubber with a regenerable solid amine.

Loftus, J. P., Jr.↗