PLUME EFFECTS DATA STUDY PROGRAM.
Abstract
This report has two major objectives: To prepare charts predicting full scale heating patterns from the impingement of typical storable propellant rocket plumes on adjacent spacecraft surfaces, and to study the subscale testing techniques and instrumentation covering areas such as subscale model plume temperature and profile, thermal modeling of spacecraft surfaces, instrumentation for surface contamination and pressure effects testing. Results of the study showed that subscale model plume stagnation temperatures close to full scale unit values are achievable. Unavailability of a computer program to predict the profile from a microthrust engine with a converging approach sonic orifice left this area of consideration open. Parametric groupings for thermal modeling of a spacecraft skin were established, permitting prediction of full scale transient effects from subscale test data. Design concepts were established for simple 'plug-in' modules for the measurement of surface contamination effects on several types of functional spacecraft surfaces. Consideration of pressure loading instrumentation revealed no unusual problem for static pressure measurements, but did reveal a potential response and miniaturization requirement for acoustic loadings measurements. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1965
- Accession Number
- AD0475794
Entities
People
- Charles E. Upper
- Stanley Lehrer