in this paper, by numerical simulation of gas flow, effects of divergence angles on the amplification factor, side force and thrust vector magnitude of a moveable nozzle with supersonic split line have been investigated. the study is conducted for constant exit to throat area ratio and the location of the split line is also constant. the finite volume method with second order upwind scheme for ...

In this paper, a new guidance method for surface to surface ballistic missiles without mandatory engine cut-off will be presented. The complexity of solid fuel engine cut-off demands a comprehensive method for guiding these missiles. In the method presented in this paper, a certain guidance law is applied such that by transmitting appropriate commands to the control system, by changing the miss...

The comparisons of two typical fluidic thrust vectoring exhaust nozzles including two-dimensional(2-D) nozzle and axisymmetric nozzle on aerodynamic characteristics was presented by numerical simulation. The results show: the thrust vector angles increased with the increasing secondary flow but decreased with the nozzle pressure ratio (NPR) increasing. With the same secondary flow and NPR, the ...

In this paper, a new guidance method for surface to surface ballistic missiles without mandatory engine cut-off will be presented. The complexity of solid fuel engine cut-off demands a comprehensive method for guiding these missiles. In the method presented in this paper, a certain guidance law is applied such that by transmitting appropriate commands to the control system, by changing the miss...

in this paper, a new guidance method for surface to surface ballistic missiles without mandatory engine cut-off will be presented. the complexity of solid fuel engine cut-off demands a comprehensive method for guiding these missiles. in the method presented in this paper, a certain guidance law is applied such that by transmitting appropriate commands to the control system, by changing the miss...

The thrust vector control problem for an upper-stage rocket with propellant slosh dynamics is considered. The control inputs are defined by the gimbal deflection angle of a main engine and a pitchingmoment about the center of mass of the spacecraft. The rocket acceleration due to themain engine thrust is assumed to be large enough so that surface tension forces do not significantly affect the p...

A m ultiaxis thrust-vectoring nozzle designed to have equal ow-turning capability in pitch and yaw was conceived and experimentally tested for internal static performance at Langley Research Center. The cruciform-shaped, convergent-divergent nozzle turned the ow for thrust vectoring by deeecting the divergent surfaces of the nozzle, called aps. Methods for eliminating physical interference betw...