<p>The paper presents a selection of rational design solutions for payload separation devices from the last stage of the launch vehicle without using pyrotechnic elements (spring, bandage and pneumatic pin-based types). An overview and analysis of the applicability of various options for separation devices as part of existing disposable and reusable launch vehicles is presented, as a result of which the growing need for using separation devices without pyrotechnics is revealed due to the need to ensure shock-free separation and rescue of the payload in case of an emergency, as well as increased requirements for reducing the number of pyrotechnic elements due to possible risk fire or explosion during transportation, launch and separation of the payload. The methods of reducing the influence of disturbing factors leading to a deviation of the calculated parameters of the payload motion during launch into a given orbit are considered. It has been established that one of the effective methods to reduce these disturbances is to ensure a minimum time delay between the shutdown of the propulsion system of the last stage and the separation of the payload, which is selected from the after action pulse decline in order to reduce the loss of work of the separation device for its parrying. Mathematical modeling of the dynamics of separation of the payload from the last stage of the launch vehicle was carried out when the proposed separation devices were triggered, while docking rings were considered as dangerous points for collision of structural elements. An analysis of the results of mathematical modeling is presented, which shows that the angular velocity of the last stage of the launch vehicle has little effect on smooth separation of the payload, while the required work when the proposed separation devices are triggered should be determined based on the required relative velocity of the payload at the time of its separation from the last stage.</p>