These coupled equations are solved by using Newton's method. Both the numerical and the analytical methods are used to calculate the Jacobian matrices. Sensitivities are evaluated by using the adjoint method. The performance of the optimization method is demonstrated for rocket motor nozzle design....
burn_time=3.9,grain_number=5,grain_separation=0.005,grain_density=1815,grain_outer_radius=0.033,grain_initial_inner_radius=0.015,grain_initial_height=0.12,nozzle_radius=0.033,throat_radius=0.011,interpolation_method="linear",nozzle_position=0,coordinate_system_orientation="nozzle_to_combustion_chamber"...
However, propulsion systems which have the advantage of variable geometry nozzles operate closer to design conditions than those with fixed geometry nozzles. Generally, the propulsive force provided by a rocket nozzle is a function of many parameters such as exit to throat area ratio, type of ...
This analysis (not discussed here) enables one to optimize the engine design plus nozzle geometry such that optimal nozzle expansion is achieved during operation (or as close to it as possible). The flow of the exhaust gas through the nozzle falls under the category of compressible supersonic ...
Applications of variable property heat transfer and friction equations to rocket nozzle coolant passages and comparison with nuclear rocket test results.AIAA 70... MF Taylor 被引量: 8发表: 1970年 Investigation of the eight-stage bleed-type turbine for hydrogen-propelled nuclear rocket applications. ...
A first assumption on the grain, pre-chamber, post-chamber and nozzle converging part length was based on the previous experience acquired by the authors in previous research projects [23] in order to guarantee acceptable residence time and flow field. An initial port diameter of the grain equal...
throat of the nozzle 1. Introduction The enormous increase in interest in satellite devices and their operating techniques is one of the main factors forcing the search for a suitable, tailor-made rocket propulsion. The scope of requirements includes not only the use of rocket engines for the pr...
Rocket engine components sufficient to design most gas generator cycle cryogenic regeneratively cooled engines. 2D Node Graph for assembling components into an engine. Component Editor to view and edit component properties. Methods-Of-Characteristics Nozzle Designer ...
And the region of peak pressure occurs directly under the rocket nozzle, which is the result of the direct impact of exhaust plume. Compared with the wedge-shaped flame deflector, the cone-shaped flame deflector has great performance on guiding exhaust gas. The wedge-shaped and cone-shaped ...