Accession Number:

AD1173206

Title:

Long Life Monopropellant Design Criteria

Descriptive Note:

[Technical Report, Technical Report]

Corporate Author:

Bell Aerospace Company

Personal Author(s):

• Moseley, V. A.
• Fricke, H. D.
• Hinterman, T. H.

Report Date:

1975-07-01

Pagination or Media Count:

191

Abstract:

An experimental program to develop long life design criteria for 5-lbf thrust monopropellant hydrazine engines using Shell 405 catalyst is described. The test results of the effects of injector design variables, catalyst bed compositionretention, accumulated cold starts, reactor materials and thermal management on thruster life are discussed. The test matrices allowed for a variation of the superficial mass flux from 0.01 to 0.03 Ibmsec sq. in., injection velocity from one to 100 fps, orifice size from two to 20 mil and for a change in injection patterns and number of cold starts. Besides showerhead injectors, representative flight type configurations were tested. Catalyst weight loss, rate of increase of bed pressure drop with number of pulses P sub c-roughness variation and the pre and post-fired catalyst particle size spectrum were determined.

Descriptors:

• computer programs
• three dimensional
• two dimensional
• materials
• attrition
• heat transfer
• regression analysis
• test and evaluation
• databases
• rocket engines
• rocket propulsion
• computers
• contracts
• digital images
• geometric forms
• geometry
• liquid propellants

Subject Categories:

• Manufacturing and Industrial Engineering and Control of Production Systems

Distribution Statement:

[A, Approved For Public Release]