Micro Satellite Orbital Boost by Electrodynamic Tethers

Yao, Peter; Sands, Timothy

doi:10.3390/mi12080916

Cited by 7 publications

(4 citation statements)

References 24 publications

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“…The manuscript will examine systems design and analysis of the Alpha mission developed at the Cornell Space Systems Studio. The mission aims to be a proof of the concept of interstellar travel, furthering the maturity of (1) a CubeSat satellite deployer, (2) an autonomous picosatellite [3], and (3) light sail technology [4]. These technologies would parallel techniques proposed by the Breakthrough Starshot initiative.…”

Section: Background Of the Alpha Missionmentioning

confidence: 99%

Micro-Satellite Systems Design, Integration, and Flight

Naumann,

Sands

2024

Micromachines

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Within the past decade, the aerospace engineering industry has evolved beyond the constraints of using single, large, custom satellites. Due to the increased reliability and robustness of commercial, off-the-shelf printed circuit board components, missions have instead transitioned towards deploying swarms of smaller satellites. Such an approach significantly decreases the mission cost by reducing custom engineering and deployment expenses. Nanosatellites can be quickly developed with a more modular design at lower risk. The Alpha mission at the Cornell University Space Systems Studio is fabricated in this manner. However, for the purpose of development, the initial proof of concept included a two-satellite system. The manuscript will discuss system engineering approaches used to model and mature the design of the pilot satellite. The two systems that will be primarily focused on are the attitude control system of the carrier nanosatellite and the radio frequency communications on the excreted femto-satellites. Milestones achieved include ChipSat to ChipSat communication, ChipSat to ground station communication, packet creation, error correction, appending a preamble, and filtering the signal. Other achievements include controller traceability/verification and validation, software rigidity tests, hardware endurance testing, Kane damper, and inertial measurement unit tuning. These developments matured the technological readiness level (TRL) of systems in preparation for satellite deployment.

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Section: Background Of the Alpha Missionmentioning

confidence: 99%

Micro-Satellite Systems Design, Integration, and Flight

Naumann,

Sands

2024

Micromachines

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“…Their long working hours and high efficiency can greatly save the cost of space exploration and perform more complex tasks [1][2][3][4]. Therefore, it is of great significance to do research on space robots [5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Space Robot On-Orbit Operation of Insertion and Extraction Impedance Control Based on Adaptive Neural Network

Liu

Chen

2023

Aerospace

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The on-orbit operation of insertion and extraction of space robots is a technology essential to the assembly and maintenance in orbit, satellite fuel filling, failed satellite recovery, especially modular in-orbit assembly of micro-spacecraft. Therefore, the force/posture impedance control for the on-orbit operation of insertion and extraction is studied. Firstly, the dynamic model of space robots’ system in the form of uncontrolled carrier position and controlled attitude is derived by using the momentum conservation principle. Through the kinematic constraints of the replacement component plug, the Jacobi relationship of the plug motion in the base coordinate system is established. Secondly, to achieve the output force control of the plug during the on-orbit operation of insertion and extraction, a second-order linear impedance model is established based on the dynamic relationship between the plug posture and its output force and the impedance control principle. Then, in order to improve the stability, robustness, and adaptability of the controller, an adaptive Radial Basis Function Neural Network (RBFNN) is used to approximate the uncertainties in the dynamic model for the force/posture control of the plug. Finally, the stability of the system is verified by the Lyapunov principle. The simulation results show that the designed neural network impedance control strategy can achieve a control accuracy of less than 10−3 rad for the plug’s attitude tracking error, less than 10−3 m for its position tracking error, and less than 0.5 N for its output force tracking error.

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“…In recent years, green technologies are raising interest with electrodynamic tethers generating control forces by interacting with the ionosphere (Bechasnov, 2021; Sarego et al, 2021). An electrodynamic tether can be manipulated indefinitely but only for very low Earth orbits and under many other limitations (Lu et al, 2019; Xie et al, 2021; Yao and Sands, 2021).…”

Section: Introductionmentioning

confidence: 99%

Mathematical modeling and partial feedback linearization control of a constrained and underactuated space tether

Fenili

2022

Journal of Vibration and Control

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This paper investigates the application of the nonlinear control technique called collocated partial feedback linearization to the position and stretching control of a planar underactuated mechanical system. This system is designed to emulate under certain conditions the behavior of a space tether connected to one mass (representing a satellite) at each of its extremities. The flexible cable is approximated by two rigid bodies (thin rods) with springs and dampers attached to represent the cable stiffness and structural damping. The control objective is to move both satellites to its desired positions and to guarantee that on the final configuration the tether is completely stretched. The stability of the closed-loop system is verified and it is proved that the system has global asymptotic stability. The performance of the proposed nonlinear control technique is analyzed via numerical simulations for two cases: one case considering three different values for the damping coefficients and one case considering three different values for the stiffness coefficients. The simulation results show that the collocated partial feedback linearization plus a proportional-derivative control is able to move the satellites to the desired positions and to keep the cable stretched.

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Micro Satellite Orbital Boost by Electrodynamic Tethers

Cited by 7 publications

References 24 publications

Micro-Satellite Systems Design, Integration, and Flight

Micro-Satellite Systems Design, Integration, and Flight

Space Robot On-Orbit Operation of Insertion and Extraction Impedance Control Based on Adaptive Neural Network

Mathematical modeling and partial feedback linearization control of a constrained and underactuated space tether

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