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search.filters.applied.f.advisor: Gunter, Brian C. × End date: 2018 × Start date: 2018 × Item Type: Publication × search.filters.applied.f.isOrgUnitOfPublicationTitle: Space Systems Design Laboratory (SSDL) ×

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Now showing 1 - 6 of 6
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Relative Positioning and Tracking of Tethered Small Spacecraft Using Optical Sensors

2018-12 , Guo, Yanjie

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Attitude Dynamics of a Tethered CubeSat-Inflatable System in Low Earth Orbi

2018-04-26 , Boisvert, Alexander J.

This paper analyzes the attitude dynamics of an inflatable tetrahedron tethered to a 3U CubeSat via a 10 meter tether. In previously flown space tether missions the primary moment on the system being considered is the gravity gradient torque. In this analysis, however, the large area to mass ratio of the target increases the impact of drag and solar radiation moments so they are also examined. The dynamics of the deployed system was analyzed using the 42 spacecraft simulator, an open source simulation software developed by NASA Goddard. Both single and 10 element tethers were analyzed at altitudes ranging from 300 kilometers to 600 kilometers. They system showed the potential to develop unstable oscillations when uncontrolled but an active damping control scheme shows potential for maintaining the stability of the system. The deployment of the tether is analyzed as a damped spring system in SIMULINK. The deployment is analyzed for three deployment speeds and three potential damping ratios. The impact of this analysis on the requirements for the attitudedetermination and control subsystem are also considered.

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A Preliminary Assessment of the RANGE Mission's Orbit Determination Capabilities

2018-08 , Claybrook, Austin W.

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Attitude Dynamics of a Tethered CubeSat-Inflatable System in Low Earth Orbit

2018-04 , Boisvert, Alexander J.

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A scalable hardware-in-the-Loop simulation for satellite constellations and other multi-agent networks

2018-05-01 , DeGraw, Christopher F.

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A Preliminary Assessment of the RANGE Mission’s Orbit Determination Capabilities

2018-03-08 , Claybrook, Austin W.

The primary mission object of the Ranging And Nanosatellite Guidance Experiment (RANGE) is the demonstration of precision position determination on the nanosatellite platform expected to launch in late 2018. RANGE consists of two 1.5U CubeSats each with a high precision GNSS receiver. The GNSS receiver on each satellite receives GPS pseudoranges and phases in the civilian L1 and L2 frequencies, which will be used for precision orbit determination. The re ceiver clocks are supplemented by high precision atomic clocks to reduce timing uncertainties. The satellites also host a near proximity laser ranging system to reduce relative in-track orbit uncertainties. A preliminary examination of the RANGE mission’s orbit capabilities suggests a 3σ position uncertainty of less than 10 cm in the radial, intrack and crosstrack direction when taking GPS measurement once per minute. During select times of higher frequency 1 second logging, the 3σ position uncertainty in the radial, intrack and cross track directions may be driven down to the 2.5 cm, 1 cm and 1.5 cm level, respectively. Hardware in the loop simu lations with a GPS signal generator have verified the performance of the CubeSat hardware against the hardware spec sheets and show increased clock stability when the atomic clock is used. Once the RANGE missios has launched, ground based laser ranging measurements provided by the NRL and ILRS will be used to independantly validate the post processed precision orbit determination solutions of the RANGE mission.

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