Determination of thrust from pitot pressure measurements

Hiers, Robert S.; Pruitt, D. W.

doi:10.2514/6.2001-3314

Cited by 15 publications

(6 citation statements)

References 2 publications

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“…For instance, for complex experimental installations which are too large or heavy to be mounted as one item on the thrust stand, for mini-or microthrusters where the thrust is extremely small and any connecting tubes or wires might cause large errors, or in cases where the use of inexpensive and easy-to-operate devices is preferred over the elaborate and expensive thrust stands, other ways need to be employed. Indirect methods of measuring thrust have been used, mostly by measuring the impulse of the jet [1][2][3][4][5][6][7], or by using pitot tubes [8]. In many recent cases, the impulse method has been applied to minior micro-thrusters [5,9,10] for its convenience and relative simplicity.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamics of indirect thrust measurement by the impulse method

Wang

Meng

et al. 2011

Acta Mech Sin

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The aerodynamic aspects of indirect thrust measurement by the impulse method have been studied both experimentally and numerically. The underlying basic aerodynamic principle is outlined, the phenomena in subsonic, supersonic and arc-heated jets are explored, and factors affecting the accuracy of the method are studied and discussed. Results show that the impulse method is reliable for indirect thrust measurement if certain basic requirements are met, and a simple guideline for its proper application is given.

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Section: Introductionmentioning

confidence: 99%

Aerodynamics of indirect thrust measurement by the impulse method

Wang

Meng

et al. 2011

Acta Mech Sin

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“…When testing the probe model discussed in Hiers et al 1,2,3 in CFD simulations, a consistent difference of around one percent was noticed between inviscid-flow predictions and the experimental data. To explain this difference, two main factors were examined.…”

Section: Second-order Boundary Layer Theorymentioning

confidence: 99%

“…To explain this difference, two main factors were examined. The preliminary CFD predictions and the theory developed by Hiers et al 1,2 assumed the flow was inviscid, which precluded the existence of a boundary layer. However, real flow (such as the experimental data) has a boundary layer and viscous effects.…”

Section: Second-order Boundary Layer Theorymentioning

confidence: 99%

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

Pasman

Cummings

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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Determining the local stream thrust (a vector quantity) from a measured pitot pressure (a scalar quantity) requires either knowledge of the flow direction, or a probe shape that compensates for flow direction. This compensation would ideally make the measured pressure directly proportional to the component of momentum along the probe axis. The flow angle sensitivity required to resolve this component of momentum was determined theoretically previously. A proposed probe nose shape was analyzed using CFD and found to produce flow angle sensitivity close to the required sensitivity. The proposed nose shape was also tested in a wind tunnel at Mach 1.67, 2.45, and 3.48 at angles of attack from 0 to 15 degrees. The test results indicate that the flow angle sensitivity of the proposed nose shape agrees with the required sensitivity to within 1% up to a flow angle of 15°. The current work extends the original theoretical development for the optimum nose shape to include viscous affects and surface curvature. The new second-order theory agrees well with experimental results for both the stream thrust probe as well as other, independent data. Further work can be done to refine the theory.

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“…The ratio of speci¦c heats κ is a function of temperature. It was shown by Laure [18] and Hiers and Pruitt [19] that a deviation has only little in §uence on the result of Mach number from Eq. (3).…”

Section: Methodsmentioning

confidence: 99%

Velocity and total pressure measurements in the two-stage hybrid thruster tihtus

Böhrk¹,

Auweter‐Kurtz²

2009

Progress in Propulsion Physics

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A novel two-stage thermal-inductive hybrid thruster of the Universitat Stuttgart (TIHTUS) is under development at the Institut fur Raumfahrtsysteme (IRS). It provides the possibility to supply power and mass- §ow through either stage into the plasma. A variation of power-and mass§ow-staging was investigated with a Pitot probe and an electric timeof- §ight probe. The present paper discloses the radially resolved measurement results of total pressure and plasma velocity at a downstream position of 200 mm. Furthermore, a method is presented to access radially resolved §ow temperature from the combined pressure and velocity measurement. The temperature data are also presented. For a sum of powers of 50 kW at 300 mg/s, the Pitot pressure maximum is at 85 Pa while maximum velocity is measured as 9,224 and 10,350 m/s for two respective conditions. On the plume axis, the temperatures reach up to 9000 K.

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Determination of thrust from pitot pressure measurements

Cited by 15 publications

References 2 publications

Aerodynamics of indirect thrust measurement by the impulse method

Aerodynamics of indirect thrust measurement by the impulse method

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

Velocity and total pressure measurements in the two-stage hybrid thruster tihtus

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