Demonstration sample research impulse of the propulsion system of nanosatellite

The aim of the research is to determine ways to create a pulse corrective propulsion systems of a maneuvering nanosatellite at the early stages of design when forming its design appearance on the basis of experimental and numerical studies of a demonstration sample with a multifunctional flow-through launch chamber and an micro resistojet of a transverse nozzle placement scheme. A pneumohydraulic scheme of a propulsion system with various chokes of a multifunctional flow-through starting chamber has been developed. Experimental and numerical studies of a demonstration sample of a propulsion system confirmed its operability and the possibility of achieving the specified characteristics by changing the interdependent main design parameters in terms of pressure, temperature, specific thrust pulses, duration of operation in various operating modes, and design parameters of a multifunctional flow-through launch chamber. Based on the results of experimental and numerical studies, a 3D model of an improved pulse propulsion system was developed.

[1]  Martin Sweeting,et al.  Low-cost orbit manoeuvres for minisatellites using novel resistojet thrusters , 1999 .

[2]  Xin Zhang,et al.  Design and testing of a microelectromechanical-system-based high heat flux vaporizing liquid microthruster , 2020 .

[4]  Andrea Garulli,et al.  Propulsion options for very low Earth orbit microsatellites , 2017 .

[5]  Xinguo Wei,et al.  Real-time star identification using synthetic radial pattern and its hardware implementation , 2017 .

[6]  Marco Sabatini,et al.  Centralized visual based navigation and control of a swarm of satellites for on-orbit servicing , 2020 .

[7]  Hiroyuki Koizumi,et al.  The technological and commercial expansion of electric propulsion , 2019, Acta Astronautica.

[8]  A. Grubišić,et al.  Validation of an additively manufactured resistojet through experimental and computational analysis , 2020 .

[9]  Andrea Garulli,et al.  An Adaptive Groundtrack Maintenance Scheme for Spacecraft with Electric Propulsion , 2018, ArXiv.

[11]  V. N. Blinov,et al.  Design Features and Research of Electrothermal Microthrusters with Autonomous Heating Elements for the Purposes of Small Space Vehicle Orbital Manoeuvring , 2015 .

[12]  S. Notova,et al.  Elemental Composition and Morphological Characteristics of Kidney under the Influence of Toxicants , 2015 .

[13]  Craig Underwood,et al.  Cost effective propulsion systems for small satellites using butane propellant , 2002 .

[14]  Viktor N. Blinov,et al.  Design features and experimental researches of an arcjet thruster for small satellite , 2016, 2016 Dynamics of Systems, Mechanisms and Machines (Dynamics).

[15]  C. Ryan,et al.  Development of a Low-Cost 0.1N High Test Peroxide Thruster Using Additive Manufacturing , 2019, AIAA Propulsion and Energy 2019 Forum.