This paper describes various rocket engine nozzles and additionally parametric analytical studies have been carried out for the design optimization of a toroidal aerospike nozzle for thrust vectoring at steady state condition. Numerical studies have been carried out using a two-dimensional standard k-� turbulence model. This code solves standard k-�turbulence equations with shear flow corrections using the coupled second order implicit unsteady formulation. In the numerical study, a fully implicit finite volume scheme of the compressible, Reynolds-Averaged, Navier-Stokes equations is employed. In the present paper we focus on two critical elements of the thrust vector control system. The first one pertains to weight reduction by geometrical optimization. The second refers to the accurate description of desirable flow filed in accordance with the primary and secondary flow characteristics at different altitudes, which dictates the efficient thrust vectoring for a specific mission. We concluded that the judicious optimization of a toroidal aerospike nozzle can facilitate the desirable vectoring for a precise mission with commendable improvement in payload capability to single-stage-to-orbit reusable launch vehicles.