NASA STTR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- T9.01-5313
SUBTOPIC TITLE:
 Lander Systems Technology
PROPOSAL TITLE:
 Properties Investigation of High-MON Oxidizers for Use in Deep Space Exploration
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
Name:   Frontier Aerospace Corporation
Name:   Purdue University-Main Campus
Street:  4109A Guardian Street
Street:  155 South Grant Street
City:   Simi Valley
City:   West Lafayette
State/Zip:  CA  93063-3382
State/Zip:   IN 47907 - 2114
Phone:  (805) 577-8771
Phone:   (765) 494-6204


Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
James McKinnon
jim@frontier.us
4109A Guardian Street Simi Valley, CA 93063 - 3382
(805) 577-8771

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Kevin Schoonover
kevin@frontier.us
4109A Guardian Street Simi Valley, CA 93063 - 3382
(805) 577-8771
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract

Rocket propulsion for deep space applications typically use liquid propellants for axial stage and attitude control systems. The most common propellants are hydrazine (N2H4) and monomethylhydrazine (MMH) (CH3N2H3) for the fuels, and nitrogen tetroxide (NTO) (N2O4) for the oxidizer. The freezing points of both hydrazine and NTO approach room temperature and require on-board electrical heaters for the propellant tanks. MMH has a much lower freezing point but is used with NTO as an oxidizer so propulsion systems still require significant heater power. MON-25, an oxidizer composed of NTO mixed with 25% nitric oxide (NO), has a freezing point comparable to MMH. MMH and MON-25 propellants can allow a thruster to operate at -40°C. However, the properties of MON-25 have not been fully defined, specifically at temperatures below 5°C . This project will further characterize the properties of MON-25 and MON-30 oxidizers so they can be used with confidence at cold temperatures in space flight systems. These propellants will save considerable power required for propellant heaters, which will permit larger science payload and enhance the mission capability of deep space probes. The low-temperature oxidizers may also find use in lunar landing and ascent systems where sunlight is intermittent or absent.

Potential NASA Applications

Completion of the Phase I program will provide property data needed to reduce risk in current rocket engines under development by both NASA JPL (MON-30 hybrid motor) and Frontier Aerospace/NASA MSFC Deep Space Engines (DSE) using MON-25/MMH. The MON-30 hybrid, a possible Mars ascent motor that burns a solid with the oxidizer, is slated for possible use in the early 2020s. The DSE are ideal for use on future deep space missions for orbit insertion, transfer and landing/ascent propulsions systems.

Potential Non-NASA Applications

It is anticipated that the DSE will be used, in the 2020 timeframe, on a commercial lunar lander under development by Astrobotic. Mission success by Astrobotic will bring the DSE to a TRL 9 and provide a low-cost, high performance, high TRL engine to the space transportation market.


Form Generated on 05/25/2018 11:56:21