Designing the terminal guidance algorithm of a typical air-launched launch vehicle

Generally, the guidance and the control are designed as separate modules, which are suitable for many common and normal applications, but in order to achieve less error in deploying the satellite into the orbit increase the accuracy in performing the mission, we need to develop integrated Guidance and Control algorithms (IGC). By using such algorithms, it is possible to design the closed loop guidance for the last stage of the launch vehicle in vacuum condition. Examples of this are iterative guidance mode (IGM) and power explicit guidance (PEG). In this paper, the guidance of the final phase along with the guidance of the first and second stages of a typical solid rocket launch vehicle is modeled and simulated. The results of this article show that the IGM guidance can be well compatible with the Pitch Program guidance of the previous steps and successfully complete the deployment in the orbit.