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High-Performance, High Thrust, “Green” Orbital Maneuvering Vehicle for Lunar and Deep Space Missions

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC22CA228
Agency Tracking Number: 22101
Amount: $4,999,071.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: S3
Solicitation Number: SEQ_22_P2S_C1
Timeline
Solicitation Year: 2022
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-09-29
Award End Date (Contract End Date): 2024-09-28
Small Business Information
17905 Sky Park Circle, Suite F
Irvine, CA 92614-6707
United States
DUNS: 806727439
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Eric Besnard
 (949) 387-9552
 eric.besnard@flightworksinc.com
Business Contact
 Eric Besnard
Phone: (949) 387-9552
Email: eric.besnard@flightworksinc.com
Research Institution
N/A
Abstract

Flight Works is proposing to continue the development and demonstration of a high-performance Orbital Maneuvering Vehicle (OMV) which enables dedicated missions to cislunar and deep space (such as Mars rendezvous) with small launchers like Virgin Orbitrsquo;s Launcher One and ABLrsquo;s RS-1. It features a full set of avionics flight-proven in LEO. These are to be modified for deep space missions with radiation tolerant components, additional redundancy, and upgraded communication system. The high performance is enabled by Flight Worksrsquo; micropump-fed propulsion technology combined with the high density-specific impulse (Isp) provided by the green monopropellant ASCENT, with long life thrusters based on the technology developed for the NASA Lunar Flashlight CubeSat. For deep space missions, the green propellant can be stored cold to minimize heating power and a low-power pumped loop can be used to slightly warm the propellant prior to use. The result is a simple, versatile, cost-effective OMV with performance capabilities similar to that of a traditional bipropellant pressure-fed stage and which can be configured for dedicated cislunar and Mars missions. The OMV has approximately twice the capability of Rocket Labrsquo; upgraded Photon to be used on NASA CAPSTONE and ten times that of Momentus Vigoride.nbsp;The system is scalable by decreasing or increasing tank size. Also, the use of a green propellant and low-pressure tanks minimizes range safety operations and costs. The medium thrust allows for rapid, efficient transfer compared with electric propulsion systems which have to be launched at higher orbits to avoid low altitude drag and require months to reach the targeted orbit while exposing the system to the damaging radiation of the Van Allen belts. Finally, the pump in the propulsion system enables an extension to servicing missions (with the addition of proximity operations and docking features), with the OMV acting either as client or servicer.

* Information listed above is at the time of submission. *

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