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At least 343 records · Page 19
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NASA NTRSDate not supplied

TriTruss Packaging and Deployment Trade Study

A trade study was conducted that evaluated viable concepts of operation for the packaging and deployment (P&D) of novel deployable modular truss modules, called TriTruss modules, that can be assembled to form a large aperture In-Space Assembled Telescopes (iSAT). In this first phase of an ongoing more comprehensive trade study, concepts were proposed and then evaluated based on initial metrics representing features of an ideal P&D concept. The ideal TriTruss P&D concept is defined as one that: allows for efficient packaging, has sufficient geometric versatility to be launch vehicle independent, provides a stiff and lightweight structure, has low mechanical complexity, and has component modularity. The P&D concept should allow for prelaunch subsystem or utility integration if required. The concept should be kinematically simple and be robotically deployed using a minimum number of specialized tools. The P&D concepts evaluated are categorized as: core collapse, face collapse, and erectable structures. Sub-scale models were constructed to help understand the kinematics and mechanical complexity required to enable P&D. Based on a weighting scale, the most promising candidate P&D concepts have been selected and will undergo more rigorous structural design, analysis, and testing in the study’s next phase. The ultimate goal of the comprehensive trade study will be to recommend a single TriTruss design and associated P&D concept that will be built and evaluated at NASA Langley Research Center’s In-Space Assembly Laboratory.

in-space assembly (ISA)↗
NASA NTRS2019

Deployment mechanisms for high packing efficiency One-MEter Reflectarray Antenna (OMERA)

While the capabilities of CubeSats have greatly increased in the past years, large, deployable high frequency apertures remain a limitation. The goal of this work is to develop a large 1 meter antenna operating at 35.75 GHz for RADAR applications. A reflectarray design was selected, as the flat panels are compatible with the CubeSat form factor. A center-fed, Cassegrain configuration was selected for the feed, to minimize deployed height. The flat panel configuration and Cassegrain feed allowed the entire 1 meter antenna to be compatible with a 6U bus, leaving a little under 4U of volume for remaining instrument and spacecraft components. Several iterations of the design have been built and tested, with an RF test of a fully deployed assembly being completed most recently. Prior to constructing the flight model, another iteration will need to be built and tested. The goal is to have the antenna flight ready before 2020.

Cwik, Tom↗
NASA NTRS2019

Deployment Mechanisms for High Packing Efficiency OneMeter Reflectarray Antenna (OMERA)

While the capabilities of CubeSats have greatly increased in the past years, large, deployable high frequency apertures remain a limitation. The goal of this work was to develop a large 1 meter antenna operating at 35.75 Ghz for RADAR applications. A reflectarray design was selected, as the flat panels were compatible with the CubeSat form factor. A center-fed, Cassegrain configuration was selected for the feed, to minimize deployed height. The flat panel configuration and Cassegrain feed allowed the entire 1 meter antenna to be compatible with a 6U bus, leaving a little under 4U of volume for remaining instrument and spacecraft components. Several iterations of the design have been built and tested, with an RF test of a fully deployed assembly being completed most recently. The goal is to have the antenna flight ready before 2020.

Cwik, Tom↗
NASA NTRS2021

An Operational Overview of the EXport Processes in the Ocean from RemoTe Sensing (EXPORTS) Northeast Pacific Field Deployment

The goal of the EXport Processes in the Ocean from RemoTe Sensing (EXPORTS) field campaign is to develop a predictive understanding of the export, fate, and carbon cycle impacts of global ocean net primary production. To accomplish this goal, observations of export flux pathways, plankton community composition, food web processes, and optical, physical, and biogeochemical (BGC) properties are needed over a range of ecosystem states. Here we introduce the first EXPORTS field deployment to Ocean Station Papa in the Northeast Pacific Ocean during summer of 2018, providing context for other papers in this special collection. The experiment was conducted with two ships: a Process Ship, focused on ecological rates, BGC fluxes, temporal changes in food web, and BGC and optical properties, that followed an instrumented Lagrangian float; and a Survey Ship that sampled BGC and optical properties in spatial patterns around the Process Ship. An array of autonomous underwater assets provided measurements over a range of spatial and temporal scales, and partnering programs and remote sensing observations provided additional observational context. The oceanographic setting was typical of late-summer conditions at Ocean Station Papa: a shallow mixed layer, strong vertical and weak horizontal gradients in hydrographic properties, sluggish sub-inertial currents, elevated macronutrient concentrations and low phytoplankton abundances. Although nutrient concentrations were consistent with previous observations, mixed layer chlorophyll was lower than typically observed, resulting in a deeper euphotic zone. Analyses of surface layer temperature and salinity found three distinct surface water types, allowing for diagnosis of whether observed changes were spatial or temporal.The 2018 EXPORTS field deployment is among the most comprehensive biological pump studies ever conducted. A second deployment to the North Atlantic Ocean occurred in spring 2021, which will be followed by focused work on data synthesis and modeling using the entire EXPORTS data set.

Biological pump↗
NASA NTRSDate not supplied

Cubesat Deployment from a Near Rectilinear Halo Orbit

Satellites deployed from the Gateway in a Near Rectilinear Halo Orbit (NRHO) must be safely delivered their desired destinations in cislunar space and beyond. The presence of simultaneously significant gravitational forces from the Moon, the Earth, and the Sun, along with the absence of atmospheric drag, complicates the mission design problem for cubesats deployed from the Gateway. The current investigation defines candidate green zones for safe satellite deployment, allowing a passive departing spacecraft to avoid recontact with the Gateway as it departs the NRHO vicinity.

NRHO↗
NASA NTRS2021

Robotics Instrument Deployment System Surface Operations for the InSight Mars Lander

This paper describes NASA’s first successful precision robotics instrument placement and release on another astronomical body since Apollo. This operations breakthrough enabled NASA’s InSight lander to detect the first known ‘marsquake’, a faint trembling of Mars’s surface on 6th April 2019, 128 Martian days after landing on Mars on the 26th November 2018. This is the first quake detected on an astronomical body other than Earth or the Moon. This paper describes the operations of the Robotics Instrument Deployment Systems (IDS) that successfully deployed the InSight science payload to the surface of Mars. The payload includes a seismometer (SEIS), Wind and Thermal Shield (WTS) and Heat Flow and Physical Properties Package (HP3), enabling scientists to perform the first comprehensive surface-based geophysical investigation of Mars’ interior structure. In addition, the paper describes the IDS planning and command sequence generation process used for the successful deployment of SEIS, WTS and HP3 on the surface of Mars. The paper concludes with recommendations based on the experience gained from InSight IDS operations. This includes identified technology gaps in the operations of in-situ manipulators for planetary exploration.

Yen, Jeng↗
NASA NTRSDate not supplied

Artemis Internal Science Team Update: Deployed Payloads

Artemis will reestablish human presence on the Moon and lead to a new era of scientific discovery and exploration. Led by the National Aeronautics and Space Administration (NASA), the Artemis effort includes a collaboration of space agencies and companies from around the world [1]. In support of Artemis, a cross-disciplinary effort of science, engineering, operations, and human factors personnel is currently developing the best methods, facilities, and field locations to test hardware, train astronauts, and evaluate concepts of operations. This abstract, as part of the Artemis Internal Science Team (AIST) [2], provides an update to NASA’s plans for the solicitation, development, and operations of deployed surface payloads. In calendar year 2023, NASA’s Science Mission Directorate will solicit proposals for instruments to be deployed by crew on the surface of the Moon (Fig. 1), beginning with Artemis III [3]. The Artemis III mission will land in the south polar region of the Moon, within 6º of latitude from the south pole, in the vicinity of both persistently illuminated and permanently shadowed areas of the Moon, with potential access to surface-accessible volatile deposits [4]. Several of the proposed landing regions are located among some of the oldest parts of the Moon, and together with the permanently shadowed regions, provide the opportunity to learn about the history of the Moon through previously unexplored lunar regions [5]. Deployed payloads will be a critical part of a notional program that captures the highest-priority science for Artemis III and provides the greatest feedforward to follow-on missions and the build-up to the Artemis Base Camp

R. C. Weber↗
NASA NTRSDate not supplied

Artemis Internal Science Team Update: Deployed Payloads

Artemis will reestablish human presence on the Moon and lead to a new era of scientific discovery and exploration. Led by the National Aeronautics and Space Administration (NASA), the Artemis effort includes a collaboration of space agencies and companies from around the world. In support of Artemis, a cross-disciplinary effort of science, engineering, operations, and human factors personnel is currently developing the best methods, facilities, and field locations to test hardware, train astronauts, and evaluate concepts of operations. This poster, as part of the Artemis Internal Science Team (AIST), provides an update to NASA’s plans for the solicitation, development, and operations of deployed surface payloads. In calendar year 2023, NASA’s Science Mission Directorate will solicit proposals for instruments to be deployed by crew on the surface of the Moon (Fig. 1), beginning with Artemis III. The Artemis III mission will land in the south polar region of the Moon, within 6º of latitude from the south pole, in the vicinity of both persistently illuminated and permanently shadowed areas of the Moon, with potential access to surface-accessible volatile deposits. Several of the proposed landing regions are located among some of the oldest parts of the Moon, and together with the permanently shadowed regions, provide the opportunity to learn about the history of the Moon through previously unexplored lunar regions. Deployed payloads will be a critical part of a notional program that captures the highest-priority science for Artemis III and provides the greatest feed-forward to follow-on missions and the build-up to the Artemis Base Camp.

R. C. Weber↗
NASA NTRSDate not supplied

Preliminary Design of a Deployable Optical Space Array Based on a Thickened Origami Flasher Pattern

Performance of space-based optics could be greatly enhanced by using deployable origami-based arrays, which can offer a large aperture size relative to their stowed volume when compared to traditional technology, thus improving imaging quality. In this work, we select, develop, and adapt the origami flasher pattern to serve as the foundation for a deployable array that shows promise for meeting stringent optical requirements. We apply a novel thickness accommodation technique, outline an approach for implementing the technique, improve stability by adjusting geometric characteristics of the pattern, and create an array of frames for housing optical elements in a co-planar configuration. Problems of non-rigid foldability in the flasher pattern are addressed. A prototype is created and tested. We find that the deployable flasher shows promise as an optical array. By following the guidelines in this work, more efficient and powerful optical arrays can be developed.

Jared Hunter↗
NASA NTRS2022

Development of a Deployable Opitcal Aperature

The Deployable Optical Receive Aperture (DORA),a new technology being developed jointly between JetPropulsion Laboratory (JPL) and Arizona State University(ASU), is based on deploying arrays of fast optical detectors tocreate large receive apertures and seeks to achieve gigabitconnectivity at distances of thousands of kilometers. Smallspacecraft forming the LunaNet communications network andequipped with optical communications systems, such as theproposed DORA aperture, should be able to communicate atGigabit per second rates over long distances. This data rateenhancement can allow gigabit per second connectivitybetween lunar assets (astronauts, rovers, instruments) and thelunar gateway. Under sponsorship of NASA's Small SpacecraftTechnology Program (SSTP), JPL is deploying the DORApayload and ASU is developing a 3U CubeSat for a follow-onlow-Earth-orbit (LEO) mission to demonstrate DORA'scapabilities. The basic DORA payload consists of 5 receiverpanels, a transmitting telescope and processing units. Eachreceiver panel contains dozens of power-combined detectors tomimic a large optical aperture. The total receive aperture ofDORA is provided by the sum of the effective detecting area ofthe 5 panels. The transmit telescope includes a 200mW, 850nmlaser and a voice-coil fast steering mirror (FSM). The resultingDORA terminal should be able to provide duplex connectivityat rates up to 1 gigabit per second at the distances of interest.We have designed the entire DORA payload and plan topresent the test results of our DORA engineering model. Theseresults include angle-of-arrival, data rate and bit error ratemeasurements.

Yi, Lin↗
NASA NTRSDate not supplied

Novel Deployable Sunshade for a Formation-Flying Telescope

- Deployable sunshade is based on folding paper party decoration. - Cellular structure creates strong, rigid form. - Instead of folding flat, the cellular fan is wrapped around a central hollow core to accommodate a focusing optic. - Imbedded spring ribs deploy the cellular fan into a large disk. - Shade is constructed of thermal blanket materials and is sewn together rather than glued. - Design bears some resemblance to JPL starshade, but is a much simpler design - JPL design includes pantograph-like mechanical structure and motors to drive deployment.

Anne-Marie Novo-Gradac↗
NASA NTRS2003

Deployment study of a self-rigidizable inflatable boom

Deployment dynamic behavior of an inflatable space structure is analyzed using a combination of gas dynamic analysis and rigid body kinematics simulations. Modeling technique is presented for deployment of a simple cantilever boom that is rolled up on a cylindrical mandrel.

inflatable boom deployment dynamics vibration kina↗
NASA NTRS2015

SpRoUTS (Space Robot Universal Truss System): Reversible Robotic Assembly of Deployable Truss Structures of Reconfigurable Length

Automatic deployment of structures has been a focus of much academic and industrial work on infrastructure applications and robotics in general. This paper presents a robotic truss assembler designed for space applications - the Space Robot Universal Truss System (SpRoUTS) - that reversibly assembles a truss from a feedstock of hinged andflat-packed components, by folding the sides of each component up and locking onto the assembled structure. We describe the design and implementation of the robot and show that the assembled truss compares favorably with prior truss deployment systems.

Deployable↗
NASA NTRSDate not supplied

Venus Cloud Layer Investigation: Aeroshells for Entry, Descent and Deployment

Entry, Descent and Deployment (EDD) of aerial platforms at Venus follows similar operational approach as landers. •Limited only by the availability of mass efficient and robust aeroshell (heatshield/TPS) technology. •Heatshield for Extreme Entry Environment Technology (HEEET) at TRL 6 is an enabler of Venus in-situ missions.Lower ballistic coefficient, deployable concept, ADEPT, offers additional options•Low deceleration entry profile•Release of one or more payloads (balloons) from open back of the entry vehicle2

Venus↗
NASA NTRS1998

Inflatable Deployable Space Structures Technology Summary

There has been limited in inflatable deployable space structures since the 1950's due to their potential for low cost flight hardware, exceptionally high mechanical packaging efficiency, deployment reliability and low weight.

inflatable↗
NASA NTRSDate not supplied

Arc-jet Testing of Continuously Woven Aeroshells–Spiderweave–for Adaptable Deployable Entry Placement Technology

The Adaptable, Deployable Entry Placement Technology (ADEPT) is an entry system that, when deployed, creates a large, umbrella-like drag surface that can be used to decelerate spacecraft during atmospheric entry, resulting in lower entry loads and heating than a rigid aeroshell of equivalent mass. Until needed for entry, the system can remain stowed, enabling missions to overcome launch vehicle fairing diameter constraints. 12-inch diameter umbrella-like articles, similar to a small reentry probe using ADEPT, were tested in the Ames 20-MWAerodynamic Heating Facility. Performance of the test articles built with a novel, continuously woven aeroshell construction (called Spiderweave) is compared against those built with legacy construction styles. In addition, candidate thermal protective layer treatments applied to structurally sensitive regions of the aeroshell are assessed using data from on-board instrumentation as well as facility optical instruments.

ADEPT↗
NASA NTRSDate not supplied

Custom Space Mechanisms and Deployable Structures

MIT LL has experience in the design, analysis, building, testing, and deployment of custom mechanisms and structures for space systems. Previous work includes deployable structures and mechanisms for CubeSats and small satellites in LEO, GEO, and deep space applications.

mechanisms↗