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Integrated Modular Engine / Propulsion Systems Technology
The Integrated Modular Engine (IME) / Propulsion system concept is a move away from the "stand-alone" engine concept and towards a shared sub-system approach. By way of example, rather than X-quantity of turbomachinery per X number of engines, a necessity for the "stand-alone" approach where each engine is purposely kept independent of the others, the IME approach uses an N-subsystem approach. Here one set of turbomachinery feeds more than one thrust chamber. Other propulsion subsystems may be addressed similarly.

This approach is highly applicable to a Single-Stage-to-Orbit (SSTO) Reusable Launch Vehicle (RLV). Parts count on propulsion can be dramatically reduced by 30-50%. Thus, weight is also reduced. It is a concept that attempts to reverse the notion that all operability ($) concessions increase weight.

Of special relevance here is the issue of parts count as relates to affordability, reliability and certification. Consider a Tripropellant vehicle with stand alone engines and the STS with 3 standalone SSME's. Just to be as reliable as the SSME's would require individual parts on the tripropellant option to be more reliable by definition. The number of opportunities for failure has been drastically increased in any tripropellant option with standalone engines. Even integration, such as in the RD-170 (Russian/NPO Energomash, 1632K lbf (sl) from 4 thrust chambers fed with a single turbopump assembly) only begins to address subsystems and complexity reduction.

Edgar Zapata

Technology Summary

Technology Description: Fully Integrated Vehicle Propulsion System

  • System integration of entire propulsion systems, decreasing the number of parts, increasing system operability and reliability
  • Provides greater margin (fault tolerance)
  • Less hardware elements (less interfaces/ tests)
  • Greater simplicity (ease of checkout, maximizes availability, less surge)

Technology Rationale:

  • 50% reductions in major hardware requirements such as turbopumps, propellant inlet lines, gas generators
  • Increased reliability (doubling, for a given level of performance)
  • Reduces system complexity
  • Reduces cost (development and operations)
  • Increased fault tolerance
  • Interfaces minimized
  • Enhanced performance (less weight)
  • Eliminates systems when combined with other technology (ref. Large Flow Range Pumps, Differential Throttling)

State of the Art:TRL 2

  • IME study, U.S.A.F. ; Study and conceptual design
  • Operationally Efficient Propulsion System Study (OEPSS) / Rocketdyne conceptual design, upper stage application
  • AIAA ref. 92-3692, 3693, 3694 and 3695

Approach to Mature:

  • Expand on previous concept for candidate configurations
  • Develop and evaluate candidate systems
  • Identify subsystem technologies for development
  • Develop and test prototype (X-vehicle)

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Website Contact: Edgar Zapata, NASA Kennedy Space Center