The Multi-Stage-Q System and the Inverse-Q System for Possible Application in Satellite-Launch Vehicle (SLV)

Steering a Sa tellite-Launch Vehicle (SLV) to strictly follow a predefined trajectory imposes unnecessary load on the control loop, and may, possibly, saturate servos. This If may introduce a permanent error in the vehicle-destination position and velocity vectors. Consequently, the payload (the satellite) would be deployed in a wrong orbit. The orbital- error correction utilizes onboard energy, which reduces the operational life of the satellite. Therefore, it is desirable that SLV is capable of altering its trajectory according to the new operating conditions, in order to achieve the required destination position and velocity vectors. In this paper, an innovative adaptive scheme is presented, which is based on " the Multi-Stage-Q System ". Using the control laws expressed in the elliptic-astrodynamical- coordinate mesh (the normal-component-cross-product steering and the normal-component- dot-product steering) this scheme proposes a design of autopilot, which achieves the pre- decided destination position and velocity vectors for a multi-stage rocket, when each stage is detached from the main vehicle after it burns out, completely. In " the Inverse-Q System", one applies the extended-cross-product steering to the vector sum of velocity vectors of spacecraft and interceptor.