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....
Keywords Nozzle design · Method of characteristics · Shape optimization · Compressible flow · Surrogate-based optimization 1 Introduction The universe and the vastness of space have always been one of the greatest mysteries known to mankind. As time passed and technology evolved, ...
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 ...
(SRM) extendible exit cone(EEC) nozzle were calculated.Firstly,the nozzle was reduced to a one degree-of-freedom dynamic system,and then the dynamic equations describing the extending process of the nozzle were derived using the theory of analytical mechanics.The equivalent axial resistance was ...
a coupled fluid–solid model for thermochemical ablation on the nozzle wall is established based on the multi-component Navier–Stokes equations, SSTk-ωturbulence model, finite-rate chemical reaction model on the nozzle wall, variable transport properties of the nozzle material, and the heat conducti...
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"...
engine is the considerable change in mass during its motion because of the combustion of fuel. Single-stage rockets lose up to 90 percent of their initial (launch) mass in the process of acceleration. The laws of motion of a rocket with an operating engine are given by the equations of th...
Performance Analysis Model of Rocket Ejector Mode was established,based on quasi-1D transient flow equations.Factors such as skin friction,finite rate chemical reaction and mass injection were taken into account.A MacCormack scheme was adopted for solving the equations,which obtains by-pass ratio corr...
Side loads and aeroelastic stability of rocket nozzle were studied by solving Navier-Stokes equation coupled with structural equation of motion. The comput... GL Lü,ZY Ye - 《Science China Technological Sciences》 被引量: 16发表: 2012年 Jig-Shape Static Aeroelastic Wing Design Problem: A Decoup...