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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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NASA NTRS2023

Magik Animation of Robotic Operations for Flight SpaceX-29 to ISS

The MAGIK Robotic analysis team provides kinematic feasibility assessments for the ISS and has produced an animation to evaluate Extravehicular Robotics (EVR) activities for the SpaceX (SpX)-29 flight. The animation also displays the current ISS configuration at the time of the flight. Flight SpX-29 includes a SpaceX Cargo Dragon vehicle docked to Node 2 Forward (N2F) International Docking Adapter (IDA) and consists of the delivery of AWE (Atmospheric Waves Experiment) and Integrated LCRD LEO User Modem Amplifier optical communications Terminal (ILLUMA-T). Robotic operations shown include the Special Purpose Dexterous Manipulator (SPDM) Trunk extraction of ILLUMA-T and maneuvering to the JEM RMS Handoff position, the SPDM Trunk extraction of AWE, maneuvering to Express Logistics Carrier (ELC) 1 Site 3 to remove Space Test Program - Houston 5 (STP-H5), and the installation of AWE to ELC-1 Site 3. There is no disposal payload for this flight.

EVR↗

NASA NTRSDate not supplied

Performance Evaluation of a Cartesian Move Algorithm for the LSMS Family of Cable-Driven Cranes

The Lightweight Surface Manipulation System, or LSMS, is a family of cable-actuated cranes, designed for surface operations on the Moon and Mars. Its structural design focuses on three fundamental traits for space environments: a high payload-to-mass ratio to reduce launch costs, compactness for space travel in reduced cargo bays, and self-erecting capabilities for operations before astronauts arrive. The resulting design confers nonlinear and switched dynamics to the LSMS, making these cranes an interesting challenge for autonomous and teleoperated applications. One of the protocols required for these applications is a Cartesian move algorithm. This algorithm is responsible for placing the end effector of the crane at a desired location, specified in Cartesian coordinates. This paper evaluates the performance of a Cartesian move algorithm developed for the LSMS at the NASA Langley Research Center. To this end, several payload manipulation tasks were performed with LSMS-L35, the smallest version within the LSMS family. The evaluated algorithm can place the end effector with accuracy, as shown in the hardware and simulation tests.

cable-actuated↗

NASA NTRS1999

On Orbit Testing of the Video Guidance Sensor

The Video Guidance Sensor (VGS), part of NASA's Automated Rendezvous and Capture program, was flown on Shuttle mission STS-95 in October of 1998 to orbitally test the functional characteristics of the VGS. This was the second flight of the VGS (the first flight was in 1997 on STS-87), and this time long-range tracking data was gathered during the experiment. 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 orbital testing of the VGS included operations with the target on the Shuttle's Remote Manipulator System (RMS) at the start of the 10-day mission, long-range data 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.↗

DOE OSTI2023

Liquid crystal defect structures with Möbius strip topology

Topological solitons commonly appear as energy-minimizing field configurations, but examples of stable, spatially localized objects with coexisting solitonic structures and singular defects are rare. Here we use a nonpolar chiral liquid crystal system to show how twist domain walls can co-self-assemble with vortices to form spatially localized topological objects with spontaneous folding. These soliton–vortex assemblies, which we call ‘möbiusons’, have a topology of the molecular alignment field resembling that of the Möbius strip’s surface and package localized field excitations into folded structures within a confinement-frustrated uniform far-field background. Upon supplying energy in the form of electric pulses, möbiusons with different overall symmetries of structure exhibit folding-dependent rotational and translational motions, as well as topological cargo-carrying abilities that can be controlled by tuning the amplitude and frequency of the applied fields. We demonstrate on-demand transformations between various möbiusons and show examples of encoding information by manipulating folds in such structures. A model based on the energetics of solitons and vortices provides insights into the origins of the folding instability, whereas minimization of the Landau–de Gennes free energy closely reproduces details of their internal structure. Our findings may provide a route towards topology-enabled light-steering designs.

71 CLASSICAL AND QUANTUM MECHANICS, GENERAL PHYSIC↗

NASA NTRS2020

MAGIK Animation of Robotic Operations for Flight SpaceX-22 to ISS

The MAGIK Robotic analysis team provides kinematic feasibility assessments for the ISS and has produced an animation to evaluate Extravehicular Robotics (EVR) activities for the SpaceX (SpX)-22 flight. The animation also displays the current ISS configuration at the time of the flight. Flight SpX-22 includes a SpaceX Cargo Dragon vehicle docked to Node 2 Zenith (N2Z) International Docking Adapter (IDA) and consists of the delivery of the ISS Power Augmentation (IPA) Carrier. Robotic operations shown include the Space Station Remote Manipulator System (SSRMS) Trunk extraction of the IPA Carrier and maneuvering to the install position on the Payload ORU (Orbital Replacement Unit) Accommodation (POA). There is no disposal payload for this flight.

Alexander Radford Fryer↗

NASA NTRS2024

MAGIK Animation of Robotic Operations for Flight SpaceX-30 to ISS

The MAGIK Robotic analysis team provides kinematic feasibility assessments for the ISS and has produced an animation to evaluate Extravehicular Robotics (EVR) activities for the SpaceX (SpX)-30 flight. Shown EVR activities are preliminary and final operations will be developed by Flight Operations Directorate (FOD) Robotics (ROBO). The animation also displays the current ISS configuration at the time of the flight. Flight SpX-30 includes a SpaceX Cargo Dragon vehicle docked to Node 2 Zenith (N2Z) International Docking Adapter (IDA) and consists of the delivery of the Pump Module (PM) Integrated Assembly (IA). Robotic operations shown include the Special Purpose Dexterous Manipulator (SPDM) based on the Space Station Remote Manipulator System (SSRMS) for Trunk extraction of the PM IA, maneuvering to the External Stowage Platform 3 (ESP-3), temporary removal of the Control Moment Gyro (CMG) from ESP-3 Site 4, install of the PM IA at ESP-3 Site 3 and re-install of the CMG to ESP-3 Site4. There is no disposal payload for this flight.

ISS↗

DOE OSTI2023

Ultrasound Manipulation and Extrusion of Active Nanorods

Abstract Synthetic self‐propelled nano and microparticles have a growing appeal for targeted drug delivery, collective functionality, and manipulation at the nanoscale. However, it is challenging to control their positions and orientations under confinement, e.g., in microchannels, nozzles, and microcapillaries. This study reports on the synergistic effect of acoustic and flow‐induced focusing in microfluidic nozzles. In a microchannel with a nozzle, the balance between the acoustophoretic forces and the fluid drag due to streaming flows generated by the acoustic field controls the microparticle's dynamics. This study manipulates the positions and orientations of dispersed particles and dense clusters inside the channel at a fixed frequency by tuning the acoustic intensity. The main findings are: first, this study successfully manipulates the positions and orientations of individual particles and dense clusters inside the channel at a fixed frequency by tuning the acoustic intensity. Second, when an external flow is applied, the acoustic field separates and selectively extrudes shape‐anisotropic passive particles and self‐propelled active nanorods. Finally, the observed phenomena are explained by multiphysics finite‐element modeling. The results shed light on the control and extrusion of active particles in confined geometries and enable applications for acoustic cargo (e.g., drug) delivery, particle injection, and additive manufacturing via printed self‐propelled active particles.

36 MATERIALS SCIENCE↗

NASA NTRS1979

Power Extension Package (PEP) system definition extension, orbital service module systems analysis study. Volume 3: PEP analysis and tradeoffs

The objectives, conclusions, and approaches for accomplishing 19 specific design and analysis activities related to the installation of the power extension package (PEP) into the Orbiter cargo bay are described as well as those related to its deployment, extension, and retraction. The proposed cable handling system designed to transmit power from PEP to the Orbiter by way of the shuttle remote manipulator system is described and a preliminary specification for the gimbal assembly, solar array drive is included.

Source record↗

NASA NTRSDate not supplied

Surface Transportation of the Common Habitat from Lander to Habitation Zone

The Common Habitat Architecture is a feasibility study surrounding the use of an SLS core stage liquid oxygen tank as the pressure vessel for a long-duration habitat intended for use in multiple gravity environments. The Common Habitat is used within this study as the primary habitation element in both Moon and Mars surface base camps. The Common Habitat Architecture offloads the Common Habitat from its lander and transports it to a Habitation Zone instead of leaving the habitat integrated with the lander. In this study, the Landing Zone is assumed to be approximately 3.5 kilometers from the Habitation Zone. Given the physical size and estimated 90-ton mass of the Common Habitat, a four-week trade study encompassing Moon and Mars lander identification, offloading, surface transport, and emplacement was conducted in February 2021 to assess whether there are any credible options for landing the Common Habitat on the Moon or Mars and deliver it to its intended point of use. Constrained to use only public data, the study applied subject matter expert opinion to each component of the study. The surface transportation component of the trade study assumes the habitat has been successfully offloaded from its lander and is at a point of handover to the surface transportation system. It is assumed that there are no crew present, and all human operations are performed remotely by Mission Control personnel. Three core cargo handling elements from prior NASA studies were used as the basis from which to derive surface transportation options – the Chariot, the All-Terrain Hex-Limbed Extra-Terrestrial Explorer, and the Lightweight Surface Manipulator System. Variations and hybrid combinations of these elements were used to develop transportation options for the Moon and Mars, given different habitat masses. Ultimately, several potentially feasible solutions were identified, and a solution was recommended that is common to both the Moon and Mars, with the potential to use a dissimilar system as a backup during lunar Common Habitat delivery. Next steps for sizing and additional development and analysis of the recommended surface transportation system are included as forward work.

Surface Mobility↗

NASA NTRS1987

Design, construction, and utilization of a space station assembled from 5-meter erectable struts

The primary characteristics of the 5-meter erectable truss is presented, which was baselined for the Space Station. The relatively large 5-meter truss dimension was chosen to provide a deep beam for high bending stiffness yet provide convenient mounting locations for space shuttle cargo bay size payloads which are approx. 14.5 ft (4.4 m) in diameter. Truss nodes and quick attachment erectable joints are described which provide for evolutionary three dimensional growth and for simple maintenance and repair. A mobile remote manipulator system is described which is provided to assist in station construction and maintenance. A discussion is also presented of the construction of the Space Station and the associated extravehicular active (EVA) time.

Mikulas, Martin M., Jr.↗

NASA NTRS1986

Design, construction and utilization of a space station assembled from 5-meter erectable struts

Presented are the primary characteristics of the 5-meter erectable truss designated for the space station. The relatively large 5-meter truss dimension was chosen to provide a deep beam for high bending stiffness yet provide convenient mounting locations for space shuttle cargo bay size payloads which are 14.5 ft. (4.4 m) in diameter. Truss nodes and quick-attachment erectable joints are described which provide for evolutionary three-dimensional growth and for simple maintenance and repair. A mobile remote manipulator system is described which is provided to assist in station construction and maintenance. A discussion is also presented of the construction of the space station and the associated EVA time.

Mikulas, M. M., Jr.↗

NASA NTRS1977

Analytical formulation of selected activities of the remote manipulator system

Existing analysis of Orbiter-RMS-Payload kinematics were surveyed, including equations dealing with the two body kinematics in the presence of a massless RMS and compares analytical explicit solutions with numerical solutions. For the following operational phases of the RMS numerical demonstration, problems are provided: (1) payload capture; (2) payload stowage and removal from cargo bay; and (3) payload deployment. The equation of motion provided accounted for RMS control forces and torque moments and could be extended to RMS flexibility and control loop simulation without increasing the degrees of freedom of the two body system.

K J Zimmerman↗

NASA NTRS2022

SpaceX-26 Animation - Operations from MAGIK AI-4177: SpX-26 (Launch-6)

The MAGIK Robotic analysis team provides kinematic feasibility assessments for the ISS and has produced an animation to evaluate Extravehicular Robotics (EVR) activities for the SpaceX (SpX)-26 flight. The animation also displays the current ISS configuration at the time of the flight. Flight SpX-26 includes a SpaceX Cargo Dragon vehicle docked to Node 2 Zenith (N2Z) International Docking Adapter (IDA) and consists of the delivery of the ISS Roll Out Solar Array (IROSA) mounted to an ISS Power Augmentation (IPA) Carrier. Robotic operations shown include the Space Station Remote Manipulator System (SSRMS) Trunk extraction of the IPA Carrier and maneuvering to the install position on the Payload ORU (Orbital Replacement Unit) Accommodation (POA). There is no disposal payload for this flight.

ISS↗

NASA NTRS1972

Space tools and support equipment - Current technology and future requirements.

Space tools and supporting equipment developed for past and current missions are summarized, along with projected tool and powered maneuvering aid requirements for future earth orbital missions. These tools, designed for functions such as general maintenance, replacement and repair, are reviewed and classified according to their intended application. A synopsis of the Skylab on-orbit maintenance requirements is presented, and the tools necessary for accomplishing the maintenance functions are listed. The proposed missions for future Earth Orbital Systems are summarized, and the potential functions (e.g., Remove/Replace, Cargo Transfer, etc.) are outlined. The current tool and support technology status is compared with future requirements for crew equipment to determine if these future requirements can be adequately satisfied. Of particular interest is a discussion of the augmentation of the astronaut with teleoperators (remote manipulator systems).

Brown, N. E.↗

NASA NTRS1982

Working in space

The capabilities of the NASA Neutral Buoyancy Simulator (NBS) water tank test facility are described, with reference to the proving of crew-operated mechanisms incorporated by the Space Telescope (ST). There are 24 Orbital Replaceable Units which are subject to handling in space by suited crewmen of the Space Shuttle, the largest of which is comparable to a telephone booth and weighs over 700 lb. The water volume of the simulator is sufficient to accept a full-size mockup of the Space Shuttle cargo bay, in which all ST operations will be conducted. Early ST simulations tested the mechanisms which astronauts would operate during contingency operations. More recently, the simulation tasks have reflected maintenance objectives of ST orbital life prolongation. With the recent addition of a fully functional Remote Manipulator System and the Manned Maneuvering Unit, the simulator constitutes the most complete training ground for extravehicular activities extant.

Sanders, F. G.↗

NASA NTRS1985

ACCESS (Assembly Concept for Construction of Erectable Space Structure) - A Shuttle flight experiment

ACCESS is a planned Shuttle flight experiment to assess the potential of an on-orbit construction concept designed for efficient manual assembly of a space truss. The experiment, which is scheduled for launch November 27, 1985, on the Space Transportation System (STS) flight 61-B, uses two astronauts secured in fixed foot restraints located in the Shuttle cargo bay to assemble a 45-foot long aluminum truss beam from 93 tubular struts and 33 nodal joints. Neutral buoyancy simulations of the flight experiment indicate the truss can be assembled in less than thirty minutes. Structural assembly, structural repair, flexible cable attachment and manual manipulation of the truss is also planned for the experiment using an astronaut secured in the Manipulator Foot Restraint attached to the Remote Manipulator System arm. Flight assembly data will be generated for correlation of the neutral buoyancy ground test data. This paper describes the ACCESS flight experiment and presents results of the neutral buoyancy development and training tests.

Heard, W. L., Jr.↗

NASA NTRS2007

A Wheel-On-Limb Rover for Lunar Operations

The All-Terrain Hex-Limbed Extra-Terrestrial Explorer (ATHLETE) is a new mobility platform developed for potential lunar operations. This six limbed rover is designed to traverse quickly over benign terrain by rolling, traverse rough and steep terrain by walking, as well as perform general manipulation of tools and payloads. This flexible robotic platform will provide a mobile base for pressurized lunar habitats allowing for long range surface exploration and crew transport. It will also enable in-situ construction of lunar assets providing astronauts with the ability to assemble, maintain, and service a wide range of cargo. This paper presents the design details and capabilities of this wheel-on-limb platform.

ATHLETE↗

NASA NTRS2001

Thermal Analysis for Orbiter and ISS Plume Impingement on International Space Station

The NASA Reaction Control System (RCS) Plume Model (RPM) is an exhaust plume flow field and impingement heating code that has been updated and applied to components of the International Space Station (ISS). The objective of this study was to use this code to determine if plume environments from either Orbiter PRCS jets or ISS reboost and Attitude Control System (ACS) jets cause thermal issues on ISS component surfaces. This impingement analysis becomes increasingly important as the ISS is being assembled with its first permanent crew scheduled to arrive by the end of fall 2000. By early summer 2001 , the ISS will have a number of major components installed such as the Unity (Node 1), Destiny (Lab Module), Zarya (Functional Cargo Block), and Zvezda (Service Module) along with the P6 solar arrays and radiators and the Z-1 truss. Plume heating to these components has been analyzed with the RPM code as well as additional components for missions beyond Flight 6A such as the Propulsion Module (PM), Mobile Servicing System, Space Station Remote Manipulator System, Node 2, and the Cupola. For the past several years NASA/JSC has been developing the methodology to predict plume heating on ISS components. The RPM code is a modified source flow code with capabilities for scarfed nozzles and intersecting plumes that was developed for the 44 Orbiter RCS jets. This code has been validated by comparison with Shuttle Plume Impingement Flight Experiment (SPIFEX) heat flux and pressure data and with CFD and Method of Characteristics solutions. Previous analyses of plume heating predictions to the ISS using RPM have been reported, but did not consider thermal analysis for the components nor jet-firing histories as the Orbiter approaches the ISS docking ports. The RPM code has since been modified to analyze surface temperatures with a lumped mass approach and also uses jet-firing histories to produce pulsed heating rates. In addition, RPM was modified to include plume heating from ISS jets to ISS components where the jet coordinates are specified, together with the engine cant angle. These latter studies have been focused on the PM with plumes from its reboost and ACS jets impinging on various ISS components and also focused on the Japanese H2 Transfer Vehicle (HTV) with the plumes from its reboost engines impinging on the Cupola window. This paper will present plume heating and surface temperature results on a number of ISS components with and without jet-firing histories, evaluate post-flight data, and describe any potential thermal issues

Rochelle, William C.↗