Pitot pressure and heat transfer measurements in hydrazine thruster plumes

Legge, H.; Dettleff, G.

doi:10.2514/6.1985-934

Cited by 2 publications

(3 citation statements)

References 3 publications

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“…2), and regarding u as the mean velocity over the plume cross section, u can be taken in front of the integral in Eq. (23) if we use /c hy = 1.37 (determined previously), JR«638 J/kg-K, and T 0 ~ 1200 K deduced from heat transfer measurements in the same hydrazine thruster plume 7 for Re E ~ 3600. Similar results for the gas velocity are obtained in a more accurate estimate.…”

Section: Experiments With Hydrazine Thruster Plumesmentioning

confidence: 99%

Attitude control thruster plume flow modeling and experiments

Dettleff¹,

Boettcher²,

Dankert³

et al. 1986

Journal of Spacecraft and Rockets

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A plume flow model has been developed to calculate the impingement forces and heat transfer caused by the firing of attitude control thrusters on satellites. Its validity for the inviscid core flow was tested and verified by an experimental study including pitot pressure and velocity measurements in plumes with different pure test gases. Measurements in real hydrazine thruster plumes allowed the determination of essential data (especially an effective ratio of specific heats) necessary for the description of this flowfield.x,y y b Nomenclature = cross section of nozzle exit = plume constant 1 = plume constant, determined by experiment = factor of proportionality in Eq. (12) = specific heats at constant pressure and volume, respectively = surface element = diameter of pitot probe = distance from nozzle throat to nozzle exit = mass flow = molecular mass = Mach number = surface normal vector = stagnation pressure = pitot pressure = pitot pressure on centerline = (specific) gas constant = nozzle Reynolds number, = radius, polar coordinate = nozzle throat radius = nozzle exit radius = stagnation temperature = velocity = velocity at nozzle throat = velocity at nozzle exit (isentropic flow) = velocity determined by experiment = maximum gas velocity V2/c/(/c-1) -R-T Q = virtual source point of streamlines = coordinates = plume boundary coordinate = boundary-layer thickness at nozzle exit angle, polar coordinate = angle between plume axis and streamline, which separates the isentropic core and the boundary-layer expansion region = maximum expansion angle = angle between surface normal and streamline ( Fig. 9) = ratio of specific heats -viscosity Presented as Paper 85-0933 at

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Section: Experiments With Hydrazine Thruster Plumesmentioning

confidence: 99%

Attitude control thruster plume flow modeling and experiments

Dettleff¹,

Boettcher²,

Dankert³

et al. 1986

Journal of Spacecraft and Rockets

Self Cite

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“…The conditions of hydrazine catalytic combustion product gases, together with the plume gas properties, are determined by the following overall decomposition reaction process of N 2 H 4 , which occurred in the combustion chamber through the procedures stated in reference [28]:…”

Section: Nozzle¯ow®eld Predictionmentioning

confidence: 99%

“…In addition, measurements of pitot pressure and aerodynamic heat¯ux in the vacuum condition were conducted to explore plumes and plume interactions of M BB/ER N O 0.5 N (conical nozzle), 2 N and 5 N (contoured nozzles) hydrazine thrusters. The development process from the shock waves in a nozzle to plume¯ow expansion was well elucidated [27,28]. The aforementioned measured results have established an extensive database on plume ®eld properties as well as impingement pressure and heat¯ux giving increasing con®dence in the plume¯ow predictions.…”

Section: Introductionmentioning

confidence: 99%

Determination of plume impingement disturbance characteristics for the ROCSAT-1 satellite

Yang

Kuo

2002

Proceedings of the Institution of Mechanical Engineers, Part G:

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The impingement disturbance characteristics of the hydrazine thruster plumes have been examined comprehensively for the R OCSAT-1 satellite. In this study, the velocity and temperature distrib utions at the nozzle exit are obtained from the nozzle¯ow®eld analysis. The axial velocity, transverse velocity and temperature pro®les are further correlated with the curve-®tting procedure for resolving in¯ow properties of molecules ejected into a vacuum. The free-molecular direct simulation M onte Carlo technique is used to describe the particle nature of the distant plume¯ow behaviour near the impingement surface. The in¯ow molecular motions as well as the collisio n interactions between the molecules and the solid surface are treated on a probabilistic basis. On the other hand, the intercollision s among molecules are considered to be relatively unimportant in the far-®eld plume region. A reasonable number of simulated molecules is also employed to reproduce the¯uid behaviour in the macroscopic level. The predicted disturbance torques and thrust loss are found to be much less than the design control torques and the nominal thrust force for R OCSAT-1 satellite, indicating that the plume impingement effect will not cause any performance deterioration of the propulsive function.

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Pitot pressure and heat transfer measurements in hydrazine thruster plumes

Cited by 2 publications

References 3 publications

Attitude control thruster plume flow modeling and experiments

Attitude control thruster plume flow modeling and experiments

Determination of plume impingement disturbance characteristics for the ROCSAT-1 satellite

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