Numerical Analysis Of Internal Ballistic Of Solid Fuel Micro-Thruster For Use In Space Applications

Document Type : Original Article

Authors

1 Aerospace engineering ,amirkabir university of technology

2 Director of Aviation Department, Shahid Sattari University of Aviation Sciences and Technologies

10.22034/jfnc.2024.444281.1374

Abstract

In the present study, an attempt was made to numerically simulate the internal ballistics of a solid fuel micro-thruster. The simulation is performed by a one-dimensional code that includes the equations of mass, energy (heat transfer), species and state. The results are validated by one experimental work that show good compliance. The grain used in Micro thruster is of Finocyl type, which is designed in three modes of 4, 8 and infinite fin. The angles of the fins are 90,45, 0 (circle) degrees, respectively. The mentioned equations form a set of equations from which the values of pressure P, temperature T and mass m are obtained and by obtaining these three parameters, the amount of grain's burning time t ,grain's burning rate r0,pressure and mach at the exit of convergent-divergent nozzle Pe and Me can be determined. At the end calculated thrust and total impulse. The results show that the use of Finocyl grain due to the increased level of burning causes the chamber pressure to increase and more thrust to be generated. The results also show that in the presence of heat transfer, the chamber pressure is reduced by approximately 0.5 bar and the total impulse is reduced by 15%.

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Main Subjects

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  • Receive Date: 16 February 2024
  • Revise Date: 16 March 2024
  • Accept Date: 03 April 2024

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