Accession Number : ADA115234

Title :   Statistical Analysis of Solid Propellant Combustion.

Descriptive Note : Final rept.,


Personal Author(s) : Glick,R L

PDF Url : ADA115234

Report Date : Oct 1981

Pagination or Media Count : 17

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)

Descriptors :   *Solid propellants, *Combustion, *Statistical analysis, Burning rate, Interior ballistics, Measurement, Nozzleless rocket engines, Spin stabilization, Anemometers, Pressure, Optics, Frequency, Argon lasers, Accuracy

Subject Categories : Statistics and Probability
      Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE