NASA SBIR 2019-I Solicitation

Proposal Summary

 19-1- Z7.04-3492
 Lander Systems Technologies
 High Temperature Nozzle Seals for Dissimilar Materials
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Physical Sciences, Inc.
20 New England Business Center
Andover, MA 01810- 1077
(978) 689-9023

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Dr. Sean Torrez
20 New England Business Center Andover, MA 01810 - 1077
(978) 738-8176

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Dr. B. David Green
20 New England Business Center Andover, MA 01810 - 1077
(978) 689-0003
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

High-performance, lightweight nozzles and combustion chambers are a core technology need for upper-stage and planetary descent/ascent rocket engines. Future NASA missions to Moon and Mars require reduced weight in combustion chambers and nozzles so that overall mission payload fraction and cost can be improved. Ceramic Matrix Composite (CMC) nozzle extensions are a way to reduce weight and improve specific impulse because of the low density and high temperature capability of the material. CMC nozzles can help reduce component mass to 60% of current values.


This proposal addresses one of the primary outstanding challenges in using CMC nozzle extensions for flight applications: sealing the interface between metal thrust chamber and CMC nozzle extension. In traditional, heavy engines, the junction between thrust chamber and nozzle extension is welded, but this is impossible for dissimilar materials. In the Phase I effort, PSI will develop a sealing geometry based on existing couplings and incorporating similar joint methodologies from other industries. The performance of the seal will be tested at the nozzle proof pressure, tested at firing temperature, and before and after simulated launch loads have been applied.


PSI will design and manufacture surrogate nozzles to faithfully represent the nozzle geometry and the coupling. The nozzle surrogates will be machined, assembled, and tested at PSI during Phase I. PSI will deliver a manufacturing sample prototype and design data to NASA at the end of the Phase I effort, and a functional CMC nozzle extension with lightweight coupling at the end of a Phase II effort.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

PSI’s program objective is to design, build, and test a metal-to-CMC coupling suitable for in-space rocket nozzles from 1,200 pounds thrust to 35,000 pounds thrust and greater.


NASA applications include upper stage engines for Earth launch vehicles and descent and ascent for missions to Mars and Moon. The proposed technology can be used for sample return missions and rocket-based decelerators.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

In-space rocket engines and nozzles are of high interest to several of PSI’s existing customers. These customers are involved in divert and attitude control systems (DACS) for exo-atmospheric vehicles, commercial space launch, reusable launch vehicles, and other rocket nozzle applications. These needs are similar to NASA’s needs for planetary descent, but cover a broader size scales and end-uses.

Duration: 6

Form Generated on 06/16/2019 23:12:29