The analysis and development of the development of a group of small spacecraft in accordance with their tasks in outer space was carried out. It is found that the use of space tugboat with electric ohmic propulsion system in modern space exploration is a promising task, which includes compliance with the requirements of changing the orbital position, relative to the support, with the permissible mismatch of the angular position of the thrust vector, the time of operation and the restriction on weight according to the purpose. The basic requirement for the formation is the creation of orbital positions of satellites in the group without propulsion systems, with the corresponding Keplerian elements and orbital time. The analysis is based on consideration of the use and application of basic space platforms, which represent the finite set of service subsystems required to perform a specific task in outer space. The most popular among them is the platform under the general term "CubeSat". Formation conditions involve the orbital maneuvering of a space tugboat by means of a propulsion device until reaching a predetermined position and the separation of individual satellites when forming a group. It has been found that when preparing for the start-up and shut-down of the electric propulsion system, it is important that the start-up and shut-down times are related to the thermal dynamics of the preparation of the working fluid with the power supply from the on-board power plant. Thus, the scientific and practical task of reducing the duration of preparation for the launch of the electric heating propulsion system when used on a space tug is relevant.
A glance was made over the capacities of rocket engines during stagnation on a tug boat. It’s explained that shifting is possible with a single-stage commercially available tug with a chemical missile thruster, a one-stage commercially available tug with an electric rocket thruster.
An analysis was made of the electric rocket engine and the same vibration during a stowed tug boat, as well as an analysis of the possibility of electric rocket propulsion systems were always on a small spacecraft, so on a tug boat.
The working parameters of the orbit were calculated with the determination of the space of the tugboat by rotation, which made it possible to set the maneuver points, as well as the energy characteristics of the tugboat, which characterize the dependence of the change of altitude and inclination of the orbit on the mass of the space boat and the value of the initial orbital position, which allowed to develop the concept electric ohmic propulsion system in space tugboat.
A mathematical model of the electronic heating installation of a space tug has been scattered, which is a system of differentiation and transmission functions with cob and boundary minds. A numerical model was carried out at the middle of MathLab and a clear decision was made to show the possibility of a forward estimate of the hour the unit was put into operation for an immediate launch before the weekend maneuver. We can see the possibility of realizing the model for the on-board controller of the thrusterinstallation on the Arduino application, using the method introduced by the author of the engine-start-up engine shut-off algorithm.
The adequacy of the model of the electric propulsion plant according to the results of the physical experiment was conducted, which was carried out on the experimental model of concept electric ohmic propulsion system using the bench base SV-10K of the Inter-branch Scientific and Technical Center of Space Energy and Engines of the Department 402 of the National Aerospace University. Zhukovsky M. E. "KhAI".
The methods and experimental means of experimental research of spacecraft electric motors have been improved, namely the method of measuring thrust, the method of measuring the flow of the working fluid, the method of measuring the power supplied to the engine of the engine, the steam generator and the tank, and the method of measuring the vacuum in the chamber.
The analysis of limiting factors in the control of a rocket engine is carried out. An algorithm for controlling a rocket motor is developed based on the simulation of the first start-up of the plant with minimization of preparation time and reduction of the working fluid and energy costs.
Recommendations for the further development and use of the electric propulsion system have been developed.
