Most of the current launchers and spacecraft employs pyro technic devices to separate sub structures as well as to deploy appendages. The pyrotechnic devices are short duration, single shot devices which produces a high energy shock which travels through the structure damaging the avionic and electronic components positioned near it leading to mission failures of several systems in the past. There is a requirement to reduce this shock in space craft systems, especially during stage separation events. Several experimental studies have been taken up to understand different mechanisms to reduce the shock. This presentation focuses on the experimental works carried out and the logical conclusion of shock reduction and proposal for a unique Gas Generator based Stage Separation system. This Gas Generator based system utilizes a propellant for creating the required actuation pressure than use of explosives as used in pyro technic devices.