A comparison of two methods of measuring particle size of Al2O3 produced by a small rocket motor

The size of aluminum oxide particles produced by small rocket motors is determined by tank collection and spectrophotometry. The size of the particulate determines loss in thrust due to particle lag, particulate radiant heat transfer, acoustic attenuation and impingement and rocket plume structure and properties

Experimental investigation and analysis of two sources of nozzle-thrust misalignment

Asymmetry of nozzle's throat produces oscillatory type net side-force axial profile. Using mean values of localized static pressure and Mach number, scaling laws for flat-plate supersonic flow over protrusion are applied to nozzle expansion cone irregularities to give approximate indication of perturbed-pressure profiles and induced side forces

Nitramine propellants

Nitramine propellants without a pressure exponent shift in the burning rate curves are prepared by matching the burning rate of a selected nitramine or combination of nitramines within 10% of burning rate of a plasticized active binder so as to smooth out the break point appearance in the burning rate curve

Recent Measurements at JPL of Particle Size of Aluminum Oxide from Small Rocket Motors

Small rocket engine test firings conducted to measure particle size distribution of aluminum oxide exhaust

Cold-flow experimental investigation and analysis of two sources of nozzle thrust misalignment

Cold flow investigation and analysis of two nozzle thrust misalignmen

Solid propellant rocket motor

The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure

Shockgas-ir: A High-temperature And High-pressure Absorption Cross-section Database

\begin{wrapfigure}{l}{0pt} \includegraphics[scale=0.28]{Illustrative_Spectra_1000K_Square.eps} \end{wrapfigure} An infrared absorption cross-section database for gas-phase molecules at high-temperatures and high-pressures is under construction to address a growing cross-disciplinary need for experimental data at these conditions. Recently developed broad-scan, rapid-tuning external-cavity quantum cascade lasers (QCL) have enabled the application of shock tube facilities, commonly used to study high-temperature chemical kinetics, to the efficient acquisition of absorption spectra under short-duration shock-heated test gas conditions. Available shock tube facilities can produce temperatures from 500 to 10,000 K and pressures from 0.1 to 1000 atm with test time durations ranging from 500 $\mu$s to 50 ms. Uncertainties in the known thermodynamic conditions as low as $\pm$1\% can be achieved. Presently available laser systems enable the rapid acquisition ($<$ 10 ms) of approximately 300 cm$^{-1}$ wide spectral regions at any location within the QCL-accessible wavelength region of 3.6 -11.7 $\mu$m (850 - 2800 cm$^{-1}$). The resulting spectra are composed of discrete data points at a spectral interval ranging from 0.3 - 0.6 cm$^{-1}$ and an instrument broadening function defined by the laser linewidth ($\leq$ 0.0033 cm$^{-1}$). Present efforts are focused on studying large polyatomic molecules (4+ atoms) dilute in a bath gas of argon under conditions for which dissociation is negligible and test time durations are favorable (T $<$ 1600K and P $<$ 5atm). The database currently includes ethylene, methanol, and ethanol with over a dozen more species measured and being prepared for inclusion soon. Database permanent URL: https://purl.stanford.edu/cy149sv568