Payload environment and gas release effects on sounding rocket neutral pressure measurements

Pickett, J. S.; Morgan, D. D.; Merlino, R. L.; Adrian, M. L.; Berg, G.A.; Raitt, W. J.

doi:10.2514/3.26791

Cited by 6 publications

(4 citation statements)

References 9 publications

(7 reference statements)

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“…High-flux releases alternated with low-and zero-flux emissions. Both the highand low-emission levels (as well as ACS firings) are confirmed by the neutral pressure gauge (NPG) data [Pickett et al, 1996].…”

Section: Gas Density Distributionmentioning

confidence: 60%

SPEAR 3 flight analysis: Grounding by neutral gas release, and magnetic field effects on current distribution

Mandell¹,

Jongeward²,

Cooke³

et al. 1998

J. Geophys. Res.

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Abstract. The Space Power Experiment Aboard Rockets (SPEAR) 3 experiment was launched on March 15, 1993, to test grounding devices for negative payloads. In this paper we review two aspects of the high-altitude flight data and compare them with preflight predictions. The SPEAR 3 neutral gas release experiment studied a grounding mechanism observed on previous flights during attitude control system (ACS) firings. Preflight calculations using Paschen law physics generalized to three dimensions predicted that the high rate gas release (about one order of magnitude below normal ACS) would reduce the rocket potential to within 200-300 V of plasma ground. The flight data is well fit by a value of -225 V. Orientation relative to Earth's magnetic field had no effect on the floating potential or grounding operations but had a large effect on the portion of the current collected by the boom. We compare these flight measurements with preflight calculations made with the DynaPAC computer code.

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Section: Gas Density Distributionmentioning

confidence: 60%

SPEAR 3 flight analysis: Grounding by neutral gas release, and magnetic field effects on current distribution

Mandell¹,

Jongeward²,

Cooke³

et al. 1998

J. Geophys. Res.

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“…(2-4) we find Vfl = A:Z)peak ~ ^source (4) (5) As shown by Eq. (5), the spacecraft's floating potential relative to true ground can be determined from the deflection voltage applied to pass electrons at an electron spectral peak, the deflection constant of the spectrometer, and the kinetic energy of the electrons produced by the electron source.…”

Section: Physical Basis Of the Measurementmentioning

confidence: 89%

“…3 Because charging can be a problem for spacecraft systems, 4 sounding rockets have been launched to test the effectiveness of grounding schemes. 5 Over the decades various methods have been used to determine spacecraft potential. 6 " 8 However, the determination of spacecraft potential with precision has proven very difficult.…”

mentioning

confidence: 99%

Instrument for measuring spacecraft potential

Goembel¹,

Doering

1998

Journal of Spacecraft and Rockets

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A high-resolution, low-energy electron spectrometer can be deployed on rockets or satellites to measure absolute spacecraft floating potential relative to true (Earth) ground with an accuracy of ±0.2 V. Features due to the photoionization of nitrogen and atomic oxygen by an extremely sharp solar extreme ultraviolet line (304 A, He II) appear in the electron spectra collected by the instrument. At altitudes where the photoelectron production is local (below 250 km), the peaks that appear in the spectrum are created by electrons of a known kinetic energy: the energy of the ionizing photon minus the energy needed to ionize either atomic oxygen or molecular nitrogen. The spacecraft potential is determined from the apparent shift in the energy of the photoelectron spectral peaks. The instrument is best suited for use in the daytime atmosphere at altitudes between 150 and 250 km. The spectrometer is based on an earlier design, that of the photoelectron spectrometer of the Atmosphere Explorer satellites. Enhancements of the earlier design, including a threefold greater throughput and a specialized scan mode, greatly improve the determination of spacecraft potential. The placement of the instrument on the spacecraft is critical to the success of the measurements. D P ass(peak)

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“…There have been numerous ground-based experimental investigationsof small thruster plumes. 1 ¡ 5 Space-based experiments that demonstrated the effects of thruster plumes on the induced pressure environment include the Space Shuttle, 6 rocket experiments, 7 and Mir. 8 The interpretationof data collectedonboard active spacecraft is often dif cult because of the complexity of the induced environment,as well as because of the ow into such instruments that in many cases exhibits nonequilibrium and rarefaction effects.…”

Section: Mmentioning

confidence: 99%

Simulations of Cold-Gas Nozzle and Plume Flows and Flight Data Comparisons

Gatsonis

Nanson

LeBeau

2000

Journal of Spacecraft and Rockets

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The nozzle and plume ows of small cold-gas attitude control thrusters, plume interactions with spacecraft surfaces, and the induced pressure environment are investigated numerically. The motivation for this study originates from pressure measurements that exhibited nonperiodic pulses during the rings of small cold-gas thrusters onboard a suborbital spacecraft. Pitch, yaw, and roll cold-gas thrusters were located on the 0.56-m-diam base of the spacecraft. The conical spacecraft ew at altitudes between 670 and 1200 km and carried inside a pressure sensor connected to the side surface with a tube. Predictions of the pressure inside the sensor chamber are obtained using a semi-analytical model with inputs from coupled continuum and kinetic simulations. The nozzle and plume ows for each thruster are simulated using a three-dimensional Navier-Stokes solver until breakdown. Flow eld properties inside the breakdown surface are used as inputs to the direct simulation Monte Carlo calculations in a domain that includes the spacecraft geometry. Flow eld properties at the entrance of the sensor tube are used as inputs to an analytical model to obtain the pressure inside the sensor chamber. Simulationsshow plume expansion, re ection off the spacecraft surfaces, and back ow. Pressure predictions for the pitch and yaw thruster plumes that reach the sensor after expanding on the spacecraft base are in very good agreement with measurements. Pressure induced by the roll thrusters is shown to be very sensitive to their radial position at the Environmental Monitor Package base and decreases with decreasing radial distance. Pressure overprediction of the roll thrusters is attributed to possible difference between the simulated and actual radial position.Nomenclature C m = most probable random speed at the pressure-sensor tube entrance, m/s D e = exit diameter of nozzle, mm D t = diameter of pressure-sensor tube, m D th = throat diameter of nozzle, mm Kn = Knudsen number L t = length of pressure-sensor tube, m M = Mach number P = Bird's breakdown parameter P C = pressure inside pressure-sensorchamber, Pa P E = pressure at the entrance of the pressure-sensor tube, Pa P 0 = stagnation pressure, kPa Re = Reynolds number S = ratio of mean speed to most probable random speed T C = temperature in the pressure-sensor chamber, K T E = temperature at the entrance of the pressure-sensor tube, K T w = wall temperature, K T 0 = stagnation temperature, K U E = mean speed at the entrance of the pressure-sensor tube, m/s x, y, z = coordinates used in the simulations a E = angle of attack at the entrance of the pressure-sensor tube, deg b = polar angle of the pressure-sensor tube entrance, deg k = mean-free path, m

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Payload environment and gas release effects on sounding rocket neutral pressure measurements

Cited by 6 publications

References 9 publications

SPEAR 3 flight analysis: Grounding by neutral gas release, and magnetic field effects on current distribution

SPEAR 3 flight analysis: Grounding by neutral gas release, and magnetic field effects on current distribution

Instrument for measuring spacecraft potential

Simulations of Cold-Gas Nozzle and Plume Flows and Flight Data Comparisons

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