Rocket

About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.

Rotational flow in tapered slab rocket motors

Abstract: Internal flow modeling is a requisite for obtaining critical parameters in the design and fabrication of modern solid rocket motors. In this work, the analytical formulation of internal flows particular to motors with tapered sidewalls is pursued. The analysis employs the vorticity-streamfunction approach to treat this problem assuming steady, incompressible, inviscid, and nonreactive flow conditions. The resulting solution is rotational following the analyses presented by Culick for a cylindrical motor. In an extension to Culick’s work, Clayton has recently managed to incorporate the effect of tapered walls. Here, an approach similar to that of Clayton is applied to a slab motor in which the chamber is modeled as a rectangular channel with tapered sidewalls. The solutions are shown to be reducible, at leading order, to Taylor’s inviscid profile in a porous channel. The analysis also captures the generation of vorticity at the surface of the propellant and its transport along the streamlines. It is from t...

Heat Transfer and Combustion Simulation of Seven-Element O2/CH4 Rocket Combustor

Abstract: In the present Paper, the simulation of the flow inside an experimental GOX/GCH4 rocket thrust chamber is undertaken. The combustor’s injector consists of seven individual coaxial injector elements...

Rotating combustion chamber for rocket apparatus

Abstract: This invention relates to rocket apparatus adapted for use in aircraft, and relates more particularly to rocket apparatus in which the combustion chamber is rotated during the 'combustion operation. It is one important object of my invention to provide means for directly increasing the feed...

Techniques for developing approximate optimal advanced launch system guidance

Abstract: In this paper an extension to our previous technique used to develop a real-time guidance scheme for the Advanced Launch System is presented. Our approach is to construct an optimal guidance law based upon an asymptotic expansion associated with small physical parameters, ?. The problem is still to maximize the payload into orbit subject to the equations of motion of a rocket over a nonrotating spherical Earth. The trajectory of a rocket modeled as a point mass is considered with the flight restricted to an equatorial plane while reaching an orbital altitude at orbital injection speeds. The dynamics of this problem can be separated into primary effects due to thrust and gravitational forces, and perturbation effects which include the aerodynamic forces and the remaining inertial forces. An analytic solution to the reduced-order problem represented by the primary dynamics is possible. The Hamilton-Jacobi-Bellman or dynamic programming equation is expanded in an asymptotic series where the zeroth-order term (? = 0) can be obtained in closed form. The neglected perturbation terms are included in the higher-order terms of the expansion. These higher-order terms are determined from the solution of first-order linear partial differential equations requiring only integrations which are quadratures. These quadratures can be performed rapidly with the emerging computer capability so that real-time approximate optimization can be used to construct the launch guidance law. Here ? is chosen as the ratio of the atmospheric scale height to the radius of the Earth. It is important that the perturbation effects remain small.