Company
Portfolio Data
Back to Company SearchL'GARDE, INC.
UEI: LEUWTPVHDXA8
Number of Employees: 19
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
SBIR/STTR Involvement
Year of first award: 1983
47
Phase I Awards
24
Phase II Awards
51.06%
Conversion Rate
$4,462,988
Phase I Dollars
$19,377,804
Phase II Dollars
$23,840,792
Total Awarded
Awards
SOLSTICE Test Program
Amount: $174,976 Topic: 9.5
L.Garde proposes the SOLSTICE test program to advance the Technology and Manufacturing Readiness Level (TRL & MRL) of its vectored solar sailcraft from 4 to 6 to provide a commercially viable solution to NOAA’s unmet requirements for solar wind data from 0.98AU to enable advanced solar storm warning. This test program advances the current NOAA/Aerospace Space Weather study with L.Garde to design the SOLSTICE vehicle and mission to sub-L1. During the proposed 6-month period of performance the L.Garde led team will build a full scale engineering test unit of the SOLSTICE vehicle based on the current study design for ground deployment testing and to serve as a manufacturing pathfinder for the subsequent commercial flight program. The SOLSTICE vehicle is capable of achieving and maintaining this duty station for a minimum 5-year mission. As a cost-effective platform, SOLSTICE expands upon NOAA’s Uncrewed Systems Strategy of collecting critical and time sensitive data from terrestrial aircraft and maritime systems by placing a UxS able to provide a new commercial solar wind data source at the edge of cislunar space.
Tagged as:
SBIR
Phase I
2024
DOC
NOAA
Design Tool for Highly Accurate Shape and Structural Evaluation of Space Antennas and Structures made with Tailorable Composites - SMART
Amount: $149,864 Topic: T12
For structures used in space communications (e.g., antennas) and structural support (e.g., booms and trusses for solar arrays), it is extremely important to have the ability to predict their deployed shape and structural behavior after they have been stowed for weeks or even months prior to launch.nbsp; For the STTR proposal to NASA, Lrsquo;Garde and the University of North Texas (UNT) will develop a design tool for the prediction of the material properties of tailorable composites used in space structural systems, as well as the accurate prediction of their structural and shape behavior, initially focusing on antennas made from membrane surfaces of revolution, e.g., membrane paraboloid with stiffening radial ribs and outer perimeter toroidal ring support. The design tool proposed will enable prediction of the materials properties from the percentage constituents of its elements.nbsp;For the Phase I STTR, Lrsquo;Garde and UNT will collaborate in developing the framework of a design tool that will accurately predict the structural properties and resulting on-orbit surface shape of a ldquo;design referencerdquo; hybrid antenna that consists of shape memory alloy (SMA) or shape memory composite (SMC) material and membranous RF reflective surface.nbsp; For a non-inflated antenna configuration, the radial antenna ribs made of SMA dictate the final surface shape accuracy and hence, it is very critical to have a design tool that can be used to determine the material stiffness, geometric and other structural characteristics ndash; before and after stowage.nbsp; The design tool developed will also be applicable to other hybrid geometries including space frames and hinge deployers for solar arrays.nbsp; Both one-way and two-way SMAs will be investigated.nbsp;
Tagged as:
STTR
Phase I
2022
NASA
Deployable Capture Device for Orbit Debris
Amount: $250,000 Topic: AF21S-TCSO1
L.Garde, Inc. is proposing to develop DeCaDe (Deployable Capture Device) in response the Air Force solicitation for active debris removal. DeCaDe is designed to be a compact sub-assembly which can be attached to a spacecraft, and when in close proximity deploy a net to capture the targeted orbiting debris. DeCaDe can provide permanent engagements for de-orbiting missions or reversible engagements for collecting or gathering of materials for recycle/reuse. The proposed Phase I effort will demonstrate feasibility through model based simulation, as well as component level prototype fabrication and testing. Test results will be used to update models and develop scaling laws for capturing orbiting debris of various sizes.
Tagged as:
STTR
Phase I
2022
DOD
USAF
Lightweight and Low Stow Volume Solar Concentrator for Lunar Based In-Situ Resource Utilization
Amount: $749,941 Topic: Z12
The objective of the proposed Phase II effort is to further develop a lightweight and low stow volume solar concentrator for use in lunarnbsp;in-situ resource utilization (ISRU) applications, specifically for oxygen extraction from lunar regolith. In the Phase I effort, anbsp;design of a full scale solar concentrator was created, and analysis showed the solar concentrator meeting NASA performance requirements. Also small scale prototypes were fabricated and deployment test successfully demonstrated the stowage andnbsp;deployment concept. In the Phase II effort, we will optimize the design of the solar concentrator as well develop the overall ISRU system, fabricate a demonstration-level prototype, characterize the solar concentration performance, and perform environmental test to understand how performance is affected.nbsp;nbsp;nbsp;
Tagged as:
SBIR
Phase II
2022
NASA
Lightweight and Low Stow Volume Solar Concentrator for Lunar Based In-Situ Resource Utilization
Amount: $124,965 Topic: Z12
The objective of the proposed Phase I effort is to develop a lightweight (and ultimately high W/kg) and low stow mirror solar concentrator that can concentrate sunlight light at the lunar surface for use in situ resource utilization (ISRU), specifically for oxygen extraction from lunar regolith. In Phase I, L.Garde, Inc. will (1) design a full scale solar concentrator capable of meeting NASA performance requirements, (2) build a small-scale proof-of-concept prototype, (3) demonstrate the design capabilities through experimental testing. In Phase II, L.Garde, Inc. willnbsp; develop the full scale system design and build a relevant scale prototype for ground testing and further demonstration of capabilities.
Tagged as:
SBIR
Phase I
2021
NASA
ShaMAn - Shape Memory Alloy Antenna
Amount: $124,900 Topic: S1
In the proposed effort a design for a 1 square meter aperture V-band antenna will be carried out.nbsp; It is based on shape memory alloy and antenna surface measurements on similar antenna nbsp;showed that surface accuracies on the order of (1/20)th of the wavelength at V-band are possible.nbsp; The antenna ribs are made of deployable shape memory alloy material enveloped by gold-plated molybdenum mesh.nbsp; The SMA antenna ribs are trained to seek a memorized parabolic shape when brought to its trigger temperature.nbsp; Based on design and analytical modeling with data taken from measurements and tests in the laboratory, a 1 square meter aperture, F/D=1 antenna can be packaged to fit within a 1.5U stowed volume.nbsp;nbsp; The power required to bring the antenna shape memory alloy ribs range between 5 Watts to 24 watts depending on whether the entire rib lengths are SMA or only those sections of the ribs that are folded for stowage are SMA and heated.
Tagged as:
SBIR
Phase I
2021
NASA
Lightweight Illuminating Towers
Amount: $124,970 Topic: H5
L.Garde, Inc. proposes to design and develop a modular range of freestanding Lightweight Illuminating Towers (LiT) in response to NASA#39;s need fornbsp;quot;lightweight reflectors to redirect sunlight onto solar arrays or into dark cratersquot;. The LiT will consist of two subassemblies, (1) reflector with attendant mast, tilt drive, azimuth drive, and leveler, and (2) mass and volume efficient truss structure with stabilizing legs.nbsp;The two main LiT-specific challenges are tower height and robotic deployment of wide-base legs, using a lightweight and compact structure. In Phase I, L.Garde will prove the feasibility of the proposed LiT innovations using design, analysis, and test.nbsp;In Phase II, L.Garde will aim to develop a system design that will allow for the ground testing and demonstration of a LiT reflector tower (including stabilizing legs, slew, leveling, etc.).nbsp;
Tagged as:
SBIR
Phase I
2020
NASA
Parametric VLF Loop Antenna
Amount: $149,858 Topic: AF193-006
The objective of the proposed effort is to carryout the design to the PDR level of a large diameter thermally insensitive lightweight, compactable, deployable VLF loop space antenna in the 20m diameter aperture range. The key to achieving highly accurate, large antenna diameter with low mass, low stowed volume operating at high RF frequency is the use of the L.Garde elastomeric shape-memory composite (SMC) material for the loop antenna and the Opterus Deployable Retractable Boom (DRB). The prototype parametric VLF antenna will be developed through PDR level and after CDR during Phase II, it should be ready for an in-space flight experiments.
Tagged as:
SBIR
Phase I
2020
DOD
USAF
Compact, Lightweight Bolt-on Deorbit Device for Spacecraft
Amount: $749,752 Topic: Z8
Two simple bolt-on de-orbit device configurations developed during Phase I will be carried to the CDR level for Phase II culminating in a ready-to-fly de-orbiter at the end of the project.nbsp; The first is a passive de-orbiter suitable for use at altitudes up to 1200 km where no vane sail articulation is needed. For altitudes above 1200 km our analysis showed that in order to decay within the 25-year quot;requirementquot; an articulating vane sail type de-orbiter is needed for rough-pointing against solar pressure.nbsp; Even if the vane sail of the de-orbiter is mis-pointed by 45 degrees, it will still see about 70 percent solar pressure drag. For these higher altitudes anbsp;passively articulating bolt-on de-orbit device based on two-way shape memory alloy is used. The two-way shape memory alloy unfurls to a large area against solar pressure during the sun-side of the orbit when it is warmed, and when its quot;back is turned against the sunquot; on its way to the eclipse side of the orbit, it cools down and folds back to a low area device decreasing the solar pressure on it as it exits the sun side.nbsp; The de-orbiter area can be tailored such that after it crosses the 1200 km limit on its way down, the active area against the atmosphere is still sufficient for de-orbiting within 25 years.nbsp; The SMA based de-orbiter has no need for motors or sources of power and the mass and stowed volume gained can be used for an increase in the amount of material to package making it suitable for both altitude regimes.
Tagged as:
SBIR
Phase II
2020
NASA
Novel Lightweight, Low-Cost Heliostat for Concentrating Solar Power
Amount: $199,921 Topic: 12f
Heliostats in use today are comprised mainly of many mirror facets which are mosaiced onto a structure with a reflective area of typically over 100 m2, and centrally controlled with long, wired connections. They are heavy and require large concrete slabs to support them. More recently, some companies have changed strategy and are investigating smaller area monolithic heliostats, nominally a few square meters with a single facet. These heliostats track and point with local controls, use a mounted small-area photovoltaic array for electrical power, and require just a rigid post for mounting, due to the much-reduced weight. Our proposed mirror facets address this new strategy well; the weight of our 4 m2 mirror facets are estimated to weigh 7 kg/m2 as opposed to existing facets using ~4 mm thick mirrors and metallic substrates and weighing upwards of 12 kg/m2. This competitive advantage allows not only for less support structure, but reduces shipping and labor costs, since our 4 m2 facet will weigh less than 30 kg. In addition, our facet cost per unit area is much less than conventional facets. At large volumes typical of utility-level concentrated solar power (CSP) facilities, the nominal cost of our facets is under $30/m2, in large volumes, possibly as low as $25/m2. The technical objectives of this proposed Phase I research and development effort are: (1) demonstration of L.Garde heliostat mirror fabrication scalability to large area mirrors, (2) development of the mirror support structure, (3) qualification of large area mirrors through field testing, and (4) development of path towards secure integration into nation’s electricity grid and cost models to determine cost of electricity to consumers. Although it is not possible for us to accurately calculate this effect on the LCOE of the system at this time, the weight reduction will impact the costs of shipping, handling, storage, labor and ancillary equipment. A 4 m2, 28 kg facet (~62 lbs) is easily transported and installed by two handlers, will require less structural support and a smaller motor for sun tracking. Therefore, it’s possible that this may translate to a total reduction in levelized cost of electricity (LCOE) of 20% or more.
Tagged as:
SBIR
Phase I
2019
DOE