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Modelling of satellite control thruster plumes

Modelling of satellite control thruster plumes
Modelling of satellite control thruster plumes
Deleterious effects such as surface heating and turning moments can arise as a consequence of the impingement of thruster plumes with spacecraft surfaces. Such thrusters are normally fired for attitude control. The prediction of such effects must be undertaken at the design stage of the vehicle.
In this study, the modelling of such plumes was undertaken. The following prediction techniques were implemented into computer programmes: (a) the Simons model, (b) the Method of Characteristics (MOC), and (c) the Direct Simulation Monte Carlo method (DSMC). The first two methods are derived from continuum equations whilst the third adopts a discrete particle approach.
Several DSMC schemes exist for treating the collisional behaviour of the gas, and it was unclear which would be best suited for the intended application. A thorough assessment of the implementation and performance of several such schemes was therefore completed.
Having determined the most suitable DSMC scheme, the three modelling techniques were then applied to the isentropic core expansion of a small hydrazine thruster plume. It was found that significant errors occur in the determination of impingement quantities through application of the continuum methods in the flow regime lying between the continuum and free molecular limits.
The DSMC technique was also used to calculate the nozzle lip and backflow expansion regions of the same hydrazine thruster. A significant degree of backflow was found with flow angles of up to 140º. The sensitivity of the calculations to the conditions initially assumed were assessed and found to be important.
Boyd, Iain D.
030c1538-5ca6-42dd-906e-94d4546d7b30
Boyd, Iain D.
030c1538-5ca6-42dd-906e-94d4546d7b30
Stark, J.
dd228bad-5d44-4cae-bc4a-00174ce035cc

Boyd, Iain D. (1988) Modelling of satellite control thruster plumes. University of Southampton, Department of Aeronautics and Astronautics, Doctoral Thesis, 215pp.

Record type: Thesis (Doctoral)

Abstract

Deleterious effects such as surface heating and turning moments can arise as a consequence of the impingement of thruster plumes with spacecraft surfaces. Such thrusters are normally fired for attitude control. The prediction of such effects must be undertaken at the design stage of the vehicle.
In this study, the modelling of such plumes was undertaken. The following prediction techniques were implemented into computer programmes: (a) the Simons model, (b) the Method of Characteristics (MOC), and (c) the Direct Simulation Monte Carlo method (DSMC). The first two methods are derived from continuum equations whilst the third adopts a discrete particle approach.
Several DSMC schemes exist for treating the collisional behaviour of the gas, and it was unclear which would be best suited for the intended application. A thorough assessment of the implementation and performance of several such schemes was therefore completed.
Having determined the most suitable DSMC scheme, the three modelling techniques were then applied to the isentropic core expansion of a small hydrazine thruster plume. It was found that significant errors occur in the determination of impingement quantities through application of the continuum methods in the flow regime lying between the continuum and free molecular limits.
The DSMC technique was also used to calculate the nozzle lip and backflow expansion regions of the same hydrazine thruster. A significant degree of backflow was found with flow angles of up to 140º. The sensitivity of the calculations to the conditions initially assumed were assessed and found to be important.

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Published date: October 1988
Organisations: University of Southampton, Aerodynamics & Flight Mechanics

Identifiers

Local EPrints ID: 52200
URI: https://eprints.soton.ac.uk/id/eprint/52200
PURE UUID: 3d3af082-bee5-492f-8d7d-3891fc0c4dfc

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Date deposited: 26 Aug 2008
Last modified: 13 Mar 2019 20:45

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