Statistical Analysis of Solid Propellant Combustion.
Abstract
Studies were directed at direct measurement of the acoustic admittance of burning solid propellant with concurent pressure and optical anemometry measurements, internal ballistics of spin stabilized nozzleless rocket motors, and the application of Hilbert transforms to the computation of the imagnary part of the pressure coupled response from data for the real part. An optical anemometer based on an Argon ion laser and tracker electronics and a servo-positioned window strand burner based on Princeton window burner were constructed. The servo-positioned strand burner operated successfully and Doppler burst phenomena were observed. However, tracker lock-on was not achieved. The spin stabilized nozzleless analysis showed that gas dynamic spin effects (as contrasted with acceleration induced burning rate changes) were small for tangential Mach numbers below 0.1. The Hilbert transform study showed that the imaginary part of the response function could be computed from the real part with acceptable accuracy for frequencies below one-third of the maximum frequency of the data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1981
- Accession Number
- ADA115234
Entities
People
- R. L. Glick
Organizations
- University of Dayton