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• W1668077980 abstract "The Canadian Space Agency's OEDIPUS sounding rocket program uses a unique payload configuration which consists of two approximately equal size subpayloads that are connected by a 1 km long conductive tether. Flight data from the first flight of this system launched in January 1989, referred to as OEDIPUS-A, indicated that one of the subpayloads experienced some unexpected attitude motions. A post-flight dynamics investigation was conducted and is briefly described in this paper. The investigation found that the likely cause of the observed dynamic behaviour is the tether interaction with the subpayload. Based on these results and on the fact that tethered space systems of this configuration (i.e., spinning with flexible end bodies) have not been previously studied, a comprehensive tether dynamics experiment has been included in the second OEDIPUS mission, referred to as OEDIPUS-C, scheduled to fly in the winter of 1994. The various elements of this experiment, which include detailed analytical investigations, ground testing, development of instruments to obtain flight dynamics data, and post-flight analyses, are discussed. The primary objectives of this experiment are to develop a comprehensive understanding of the dynamics of a momentum-stabilized, tethered, two body system with flexible end bodies which will be useful in the development of future tethered space systems. * Mechanical Systems Engineer, Space Systems Group, Member AIAA; ** Associate Professor, Department of Mechanical and Industrial Engineering; t Research Scientist, Directorate of Space Mechanics, Member AIAA; f f Professor, Department of Mechanical Engineering, Fellow AIAA; $ Professor, Department of Mechanical Engineering, Associate Fellow AIAA; $2 Associate Professor, Department of Applied Mathematics Introduction On 30 January 1989, the Canadian OEDIPUS-A tethered payload was successfully launched on a three stage Black Brant 10 sounding rocket from the Andoya launch site in northern Norway. The project was sponsored and managed by the Space Science Division of the Canadian Space Agency (CSA) and involved scientists from Canada and the United States. The primary objectives of the OEDIPUS (Observations of Electricfield Distributions in the Ionospheric Plasma a Unique Strategy) experiment were to: make passive observations of the auroral ionosphere, in particular, directly measure the weak DC electric field parallel to the Earth's magnetic field by using the payload as a large double probe; measure the response of the large double probe in the ionospheric plasma; and seek new insights into paneand sheath-wave propagations in plasmas by using a radio transmitter on the forward payload and a synchronized receiver on the aft payload. The flight successfully achieved the scientific objectives listed above and established a new record for the maximum length of a space tether (958 m)'. The OEDIPUS-A payload, developed by Bristol Aerospace Limited under contract to CSA, is depicted in Figure 1. After jettisoning the payload fairing and experiment doors, the fore and aft payloads had a mass of 84 kg and 131 kg respectively and each had its own complement of scientific instruments, control, power, and telemetry systems. The radial booms on the fore and aft payloads, used as dipoles for the plasma plane-wave propagation experiments, were 4 m and 5.5 m tip-to-tip respectively. Due to the sensitive nature of the measurements being made, active attitude control of the Copyright @ 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. 594 payloads was not permitted during experimentation as any gas expulsion or magnetic field generation could contaminate the experiments. Therefore, passive spin stabilization was used during experimentation. Prior to separation of the fore and aft payloads, the attitude control system module, located at the aft end of the aft payload, despun the complete payload to 0.7 cps after the third stage motor burn-out and aligned the spin axis to within lo of the Earth's magnetic field. Approximately 1200 m of teflon coated, stranded tin-copper tether wire, slightly less than 1 mm in diameter, was wound on a spool-type reel located on the forward payload and the free end attached to an instrument on the aft payload. Initially the payloads were separated by compression springs, and immediately thereafter an argon gas propulsion system located on the forward payload is fired for approximately 10 seconds to impart a predetermined relative velocity to the payloads. A magnetic hysteresis brake attached to the spool assembly imparts a small constant torque to the spool to smoothly decelerate the relative motion of the payloads to achieve a final separation distance of 958 m. The OEDIPUS-A Payload flight sequence is illustrated in Figure 2. During the passive spin-stabilized portion of the flight following payload separation, it was required that payload coning be minimized. The payloads, which had radial flexible booms that provide a source of internal energy dissipation, were spun about their minor axis and consequently payload coning was inevitable as each payload will naturally approach a flat spin orientation about the major axis (a dynamically stable configuration). However, considering the relatively short flight duration (approximately 15 minutes), it is possible to contain the coning angle to within a specified value by controlling the energy dissipation rate. The energy dissipation rate was predicted prior to the flight by modelling the boom dynamics resulting from the payload coning and using an experimentally measured damping factor for the boom. This analysis was conducted by the NASA Sounding Rocket Division at Wallops Island, which routinely conduct this type of analysis for all their sounding rocket flights that include flexible boom. Only the aft payload was investigated as it had longer and much more flexible ,booms than those on the forward payload. NASA's analysis predicted that with an initial coning angle as large as So, the coning angle of the aft payload should remain within 10 degrees. Since the booms located on the forward payload are much stiffer than the aft payload booms, ,the coning increase in the forward payload was expected to be significantly less than the aft payload. Magnetometer data from both the fore and aft payload was collected during the flight and was used to compute the angular deviation of each payload from the magnetic field vector which is presented in Figure 3. Since, the magnetic field vector remains relatively fixed over the trajectory (shifts approximately 5 relative to an inertial attitude control system" @default.
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• W1668077980 date "1992-08-10" @default.
• W1668077980 modified "2023-10-18" @default.
• W1668077980 title "Tether dynamics investigations for the Canadian OEDIPUS sounding rocket program" @default.
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