Pre-flight testing and flight performance of the OEDIPUS-C tether force sensor

Jablonski, Alexander M.; Vigneron, F. R.; Rhew, Ray D.; Bergmans, John L.; Whitehead, William; Tyc, George

doi:10.2514/6.1996-3572

Cited by 3 publications

(4 citation statements)

References 2 publications

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“…Figure 6 shows the OEDIPUS ight data for tension vs time. 9 The data show an initial spike of up to 7.4 N and then a relaxation to near zero. Then the thrusterson phase begins at 174 s and lasts for 14.7 s to time 188.7 s. The tension data uctuate, likely due to the reel bearings and exibility in the tether.…”

Section: Initiation Of Deployment By Thrustersmentioning

confidence: 91%

“…This choice leads to equations that are compatible with a model of the reel deployer and also with ight data from subpayload-mounted star trackers 7,8 and the tether force sensor. 9 The subpayloads [c] basis is de ned relative to the inertial [i] basis by 1) a rotation about i 3 by angle a , leading to the [i 0 ] basis, where…”

Section: Separation Vector In Right Ascension and Declination Variablesmentioning

confidence: 99%

“…5¡ 7 This paper relates to the rst of these two categories; it describes model formulation and design laws and compares modeling results with OEDIPUS-C ight data. 8,9…”

mentioning

confidence: 99%

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Tether Deployment and Trajectory Modeling for Space Plasma Science Missions

Vigneron

Schultz

Jablonski

et al. 2000

Journal of Spacecraft and Rockets

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Certain space plasma science missions employ a research payload that comprises two subpayloads that are connected by an electrically conductive tether of up to 1200 m in length. The missions are conducted in suborbital trajectory attained with a small multistage launch vehicle. A reel-type deployer is used, and subpayload separation is achieved mainly by thrusters on one of the subpayloads. The focus is on modeling the deployment phases and the orientation of the con guration in space. The subpayloads are modeled as mass points in inertial space in the Earth's gravity eld. Approximate solutions are derived that provide functional relationships that are useful for mission design. Results from simulation and the approximate formulas are shown to compare well with ight dynamics measurements made with a tether force sensor and star cameras during a mission in November 1995.

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Section: Initiation Of Deployment By Thrustersmentioning

confidence: 91%

Section: Separation Vector In Right Ascension and Declination Variablesmentioning

confidence: 99%

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Tether Deployment and Trajectory Modeling for Space Plasma Science Missions

Vigneron

Schultz

Jablonski

et al. 2000

Journal of Spacecraft and Rockets

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“…The fact that the two-subpayload configuration and the individual spin states were gracefully maintained throughout the flight suggests that the separation magnitude did not change radically after cutting. At that time, the tether force sensor[Jablonski et al, 1997] detected negligible tension in the tether. Separation was achieved smoothly.…”

mentioning

confidence: 99%

Interference fringes detected by OEDIPUS C

James¹,

Calvert²

1998

Radio Science

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Abstract. An HF transmitter was operated at one end of the tethered sounding rocket payload OEDIPUS C, and a synchronized receiver was operated at the other end. Both the transmitter and the receiver were connected to dipoles. On the flight downleg after the tether had been cut, direct bistatic propagation experiments were carried out with the transmitter-receiver pair. During the flight, sharp minima which can be attributed to interference fringes were detected in the directly transmitted signal. Fringe frequencies observed on OEDIPUS C ionograms for four different interference schemes have been examined using the cold-plasma theory. First, fringes were observed which can be attributed to the Faraday rotation of the plane of linear electric field polarization for the

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