Abstract Deterred-coating DIANP gun propellant was prepared by the two-step process called “polymer composite materials deterring and energetic coating”. The performance of energy static combustion deterred-coating investigated explosive heat closed-bomb test. results show that compared with propellant, decreased only about 3.2%, but it had better progressivity low temperature sensitivity effec...

An investigation of the conversion from anode electrical energy to jet kinetic energy in a laboratory model Hall thruster yielded an experimentally determined thrust efficiency that was analytically decomposed into the product of propellant, voltage, and current utilization efficiency. This method accounts for loss of propellant utilization from plume divergence, unionized propellant, and multi...

In missile propulsion technology it is conventional to employ solid rocket boosters. These boosters are loaded with solid propellants, which are energetic compositions where raw materials are comprised of solid particulates, such as fuel, and oxidizer particles, in which are dispersed and immobilized throughout a binder (polymeric) matrix. The processability of these compositions is not simple ...

In this work we report on progress in the development of models for a Micro-Pulsed Plasma Thruster (μPPT) and its exhaust plume. As a working example we consider a μPPT developed at the Air Force Research Laboratory. This is a miniaturized design of the axisymmetric PPT with a thrust in the 10 μN range that utilizes Teflon as a propellant. The plasma plume is simulated using a hybrid fluid-PIC-...

An ion thruster discharge cathode assembly (DCA) erosion theory is presented based on near-DCA NSTAR plasma potential measurements and experimental results for propellant flow rate effects on ion number density. The plasma potential structures are utilized in an ion trajectory algorithm to determine the location and angle at the DCA keeper of bombarding ions. These results suggest that the plas...

Mission proposals that land spacecraft on asteroids are becoming increasingly popular. However, in order to have a successful mission the spacecraft must reliably and softly land at the intended landing site with pinpoint precision. The problem under investigation is how to design a propellant optimal powered descent trajectory that can be quickly computed onboard the spacecraft, without intera...

In the combustion stability assessment of solid propellant rocket motors, several new destabilizing terms are introduced when rotational-flow effects are properly accounted for. Such effects must be included when the wave motion is parallel to the burning surface. A normal fluctuating velocity component then appears in a careful resolution of intrinsic fluid dynamics, including acoustico–vortic...

T study demonstrates the advantages of using a real coded genetic algorithm (GA) for aerospace engineering design applications. The GA developed for this study runs steady state, meaning that after every function evaluation the worst performer is determined and that worst performer is then thrown out and replaced by a new member that has been evaluated. The new member is produced by mating two ...