NASA SBIR 2020-II Solicitation

Proposal Summary

Proposal Information

Proposal Number:
20-2- Z7.04-5610
Phase 1 Contract #:
80NSSC20C0674
Subtopic Title:
Lander Systems Technologies
Proposal Title:
Advanced Rocket Nozzle for Planetary Landers and Reusable Space Vehicles

Small Business Concern

   
Firm:
          
STOKE Space Technologies, Inc.
          
   
Address:
          
18628 South East 180th Street, Renton, WA 98058
          
   
Phone:
          
(206) 240-7647                                                                                                                                                                                
          

Principal Investigator:

   
Name:
          
Andrew Lapsa
          
   
E-mail:
          
andy@stoke-space.com
          
   
Address:
          
18628 SE 180TH ST, WA 98058 - 0617
          
   
Phone:
          
(206) 240-7647                                                                                                                                                                                
          

Business Official:

   
Name:
          
Andrew Lapsa
          
   
E-mail:
          
andy@stoke-space.com
          
   
Address:
          
18628 SE 180TH ST, WA 98058 - 0617
          
   
Phone:
          
(206) 240-7647                                                                                                                                                                                
          

Summary Details:

   
Estimated Technology Readiness Level (TRL) :                                                                                                                                                          
Begin: 3
End: 5
          
          
     
Technical Abstract (Limit 2000 characters, approximately 200 words):

A novel rocket engine is proposed to offer major system-level advantages in planetary landers, reusable second stages, and other space vehicles that perform entry, descent, and landing maneuvers. The Phase I effort successfully developed design and performance analysis tools, and identified a design solution that meets the vehicle functional requirements. This Phase II effort is focused on designing, building, and testing engine hardware that will validate the Phase I analytical results. Successful completion of the Phase II effort will enable full engine ground- and flight-testing as part of a Phase III effort.

The engine delivers performance commensurate with today’s market-leading upper stage engines while also accommodating deep throttle operation in the presence of atmospheric pressure. When strategically integrated into the vehicle base, the engine nozzle serves as an actively cooled metallic heat shield during atmospheric entry maneuvers. The same surface creates a robust barrier that protects the rest of the vehicle from surface ejecta during terminal descent on unprepared landing sites such as the moon or Mars. The nozzle achieves high area ratio gas expansion within a form factor ten times shorter than traditional bell nozzles, alleviating plume-surface interactions by increasing the clearance between the base of a lander vehicle and the target surface, or for equivalent ground clearance, the nozzle decreases the size and mass of the requisite landing gear.

This work is in response to NASA SBIR Focus Area 12 Topic Z7.04, which seeks Lander Systems Technologies that alleviate the plume-surface interaction environment through novel propulsion cluster placements and surface ejecta damage tolerant systems, and which “improve the mass efficiency of in-space stages and landers, …reduce integration complexity, …enable reusable landing systems, …achieve multifunctional components, …and reduce operating complexity.”

          
          
     
Potential NASA Applications (Limit 1500 characters, approximately 150 words):
  • Lunar lander vehicles
  • Mars lander vehicles
  • Reusable planetary lander vehicles
  • Reusable earth return vehicles
  • In-space maneuvering system
          
          
     
Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words):
  • Reusable second stages of launch vehicles
  • On-demand launch systems
  • Compact missile systems
  • Hypersonic vehicles
  • Air-augmented rockets
          
          
     
Duration:     15
          
          

Form Generated on 05/13/2021 14:44:30