Numerical Study of Effects of injection pressure and location of secondary injection inside low-thrust satellite nozzle

摘要

Convergent-Divergent Nozzle is normally used for thrust generation. A useable control force can be generated at the expanse of some thrust loss as soon as the secondary jet interacts with the flow through the nozzle. Secondary injection in the divergent section of the nozzle diverts the mainstream flow and causes a static pressure change on the nozzle wall. This jet interaction produces an asymmetric static pressure distribution on the opposite walls of the nozzle with respect to the centre line of the nozzle. The pressure distribution depends upon the location of injection and injection pressure. Computational results are obtained as non-dimensional static pressure on the divergent section of the nozzle and depth of jet penetration (Y/D) for variation in secondary injection pressure (Pinj/P_i) and injection location (X/L). These computations are done using the Navier-Stokes Equations and control volume techniques.