A novel fluidic thrust-vectoring (FTV) control method based on dual synthetic jets actuator (DSJA) is proposed and evaluated. Numerical simulations are governed by the compressible Unsteady Reynolds-Averaged Navier–Stokes (URANS) equations. According to results, DSJA capable of deflecting a primary jet with velocity 100 m/s height 50 mm approximately 18 degrees momentum coefficient 1.96%. It pr...

BACKGROUND Jaw-thrust is a noxious stimulus that might induce sympathetic responses. The purpose of this study, was to evaluate the effects of jaw-thrust on sympathetic responses. METHODS We investigated seventy three patients. Patients who received general anesthesia were randomly divided into a control group (maintenance of combined airway maneuver with head tilt, open mouth by mouthpiece, ...

Numerical studies have been carried out using a validated two-dimensional RNG k-epsilon turbulence model for the design optimization of a thrust vector control system using shock induced supersonic secondary jet. Parametric analytical studies have been carried out with various secondary jets at different divergent locations, jet interaction angles, jet pressures. The results from the parametric...

In impulsive orbital maneuvers, a large disturbance torque is generated by the thrust vector misalignment from the center of mass (C.M). The purpose of this paper is to reject the mentioned disturbance and stabilize the spacecraft attitude, based on the combination of a one degree of freedom (1DoF) gimbaled-thruster, two reaction wheels (RWs) and spin-stabilization. In this paper, the disturban...

Clearance of Thrust Vector Control (TVC) laws for launchers demands the capability to provide analytical certificates for the system’s robust stability. During exo-atmospheric flight, a key role is played by the ability to deal with non rigid-body effects such as fuel sloshing. Depending on its frequency and magnitude, sloshing can easily deteriorate the performance of the TVC laws to the point...

Linear electro-mechanical actuators are finding increased use in the field of thrust vectoring of launch vehicles. Earlier, linear electro-hydraulic actuators were used especially in the lower stages of the launch vehicles where there is a requirement for large actuation forces. However, electro-mechanical actuators are being scrutinized for this purpose in an effort to provide lighter, cleaner...

The lecture is given in four parts, each being a step in the process of nozzle design, and within each part the methods and techniques preferred by the lecturer are presented. We begin with a reminder concerning control volumes and the separation of aerodynamic and propulsive forces and moments. Then it is demonstrated how an appropriate control volume can help define the propulsive force vecto...

which clearly reduces to the vacuum case deŽ ned by Eq. (3) as ̄ ! 0. The velocity- ight-path-angle proŽ le is shown in Fig. 2 for a range of drag parameters ̄ . It can be seen that as the effect of air drag increases, the trajectory curves more quickly toward the local vertical.Because the effect of drag is to increasethe effectivethrustweight ratio of the vehicle, the descentmaneuvermay be com...