Orbital Transfer Rocket Engine Technology. Advanced Engine Study, Task D.6 Final Report

Abstract

This report documents an advanced LOX/LH2 engine study for the use of NASA and vehicle prime contractors in developing concepts for manned missions to the Moon, Mars, and Phobos. Parametric design data was obtained at five engine thrusts from 7.5K lbf to 50K lbf. Also, a separate task evaluated engine throttling over a 20: 1 range and operation at a mixture ratio of 12 + or - 1 versus the 6 + or - 1 nominal. Cost data was also generated for DDT and E, first unit production, and factors in other life cycle costs. The major limitation of the study was lack of contact with vehicle prime contractors to resolve the issues in vehicle/engine interfaces. The baseline Aerojet dual propellant expander cycle was shown capable of meeting all performance requirements with an expected long operational life due to the high terminal margins. The basic engine design readily accommodated the 20:1 throttling requirement and operation up to a mixture ratio of 10 without change. By using platinum for baffled injector construction the increased thermal margin allowed operation up to mixture ratio 13. An initial engine modeling with an Aerojet transient simulation code (named MLETS) indicates stable engine operation with the baseline control system. A throttle rate of 4 to 5 seconds from 10% to 100% thrust is also predicted. Performance predictions are 483.1 sec at 7.5K lbf, 487.3 sec at 20K lbf, and 485.2 sec at 50k lbf with a mixture ratio of 6 and an area ratio of 1200. Engine envelopes varied+++om 120 in. length/53 in. exit diameter at 7.5K lbf to 305 in. length/136 in. exit diameter at 50K lbf. Packaging will be an important consideration. Continued work is recommended to include more vehicle prime contractor/engine contractor joint assessment of the interface issues.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1992
Accession Number
ADA253786

Entities

People

  • Warren R. Hayden

Organizations

  • Aerojet Rocketdyne Holdings

Tags

Communities of Interest

  • Biomedical
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Artificial Intelligence
  • Boundary Layer
  • Carbon Carbon Composites
  • Composite Materials
  • Dc Motors
  • Energy
  • Energy Transfer
  • Geometry
  • Heat Energy
  • Heat Transfer
  • Material Degradation Processes
  • Materials
  • Materials Processing
  • Materials Science
  • Materials Testing
  • Pressurization
  • Rocket Engines

Readers

  • Electrical Engineering
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster