NASA SBIR 2016 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 16-1 S3.02-8307
SUBTOPIC TITLE: Propulsion Systems for Robotic Science Missions
PROPOSAL TITLE: Multipulse Solid Rocket Motors for MAV

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Arctic Slope Technical Services, Inc.
289 Dunlop Blvd, Bldg 300
Huntsville, AL 35824 - 1126
(256) 562-2191

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Bradford Luff
Bradford.Luff@asrcfederal.com
289 Dunlop Blvd, Bldg 300
Huntsville, AL 35824 - 1126
(410) 620-5763

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Joseph Sims
Joseph.Sims@asrcfederal.com
289 Dunlop Blvd, Bldg 300
Huntsville, AL 35824 - 1126
(256) 562-2191

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 4

Technology Available (TAV) Subtopics
Propulsion Systems for Robotic Science Missions is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
The Mars Ascent Vehicle is undergoing extensive vehicle trades to fine tune the optimal performance for a two-stage rocket motor solution to bring a payload from the Mars surface to orbit. The key is this vehicle must provide a terminal velocity of approximately 4 km/s, remain small in length and weight, and ensure the payload does not exceed 4 g's of acceleration during vehicle ascent.

Based on initial vehicle architecture optimization analysis completed by engineers at Arctic Slope Technical Services (ASTS), the acceleration limit places a significant impact on the grain profiles used on both the first and second stage rocket motors. Therefore, the use of a dual pulse rocket motor grain design enables the use of two subsequent pulses that are ignited so as to mimic a single grain along the optimal thrust profile. This solution burns down the risks associated with an end burning grain design. The dual pulse grain design leverages finocyl designs that offers significant grain stress relief because of the fins. Also this approach offers the ability for a smaller and lighter nozzle because of the shortened burn time.
Moreover, this will provide significant opportunity for the motors to get smaller in length by being able to be packaged more efficiently. This reduction in motor length will enable for a more stable vehicle in flight as well as enable the vehicle to carry either a larger volume payload or reduce the impacts on the transportation vehicle as it takes the MAV to the Mars surface.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The primary NASA application is to the Mars Ascent Vehicle (MAV). Other planetary landers and exploration vehicles could also benefit from dual pulse rocket motors.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Potential non-NASA applications include air-to-air and ground-to-air missiles, especially including missile defense interceptors.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Atmospheric Propulsion
Launch Engine/Booster
Spacecraft Main Engine

Form Generated on 04-26-16 15:14