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检索条件"机构=Astrodynamics and Control Laboratory"

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Author Correction: Orbital Averaging Advancement for Low-Thrust Trajectory Design

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The Journal of the Astronautical Sciences 2025年第3期72卷 1-3页

作者： Shannon, Jackson Astrodynamics & Control Systems Group Johns Hopkins University Applied Physics Laboratory Laurel USA

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The VISION - Concept of Laser Crosslink Systems Using Nanosatellites in Formation Flying 73

The VISION - Concept of Laser Crosslink Systems Using Nanosa...

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73rd International Astronautical Congress, IAC 2022

作者： Kim, Geuk-Nam Park, Sang-Young Seong, Sehyun Choi, Jae-Young Ryu, Han-Gyeol Kim, Young-Eon Choi, Suyong Lee, Joohee Lee, Sungmoon Astrodynamics and Control Laboratory Yonsei University Seoul03722 Korea Republic of Telepix Co. Ltd. Busan48058 Korea Republic of Broadband Transmission Network Laboratory Yonsei University Seoul03722 Korea Republic of

The recent growth in spaceborne data volume can be handled using a laser-communication system that enables super-high-speed data transfers, faster than 1 Gbps, and provides size, weight, and power (SWaP) efficiencies at low costs. Compared to traditional radio frequency (RF) systems, the laser-communication systems have garnered attention by enhancing the SWaP efficiencies. In this study, we propose a novel system for space-to-space laser communication called very-high-speed inter-satellite link system using infrared optical terminal and nanosatellite (VISION). This study aims to establish and validate laser-crosslink systems and several space technologies using two 6U nanosatellites in formation flying. The payload is a laser-communication terminal (LCT) containing a deployable space telescope. The LCT shares beam paths for communication and pointing, acquisition, and tracking (PAT) with a single aperture, providing feedback control for the PAT without steady-state beam pointing errors. The nanosatellites include a precise formation-flying guidance, navigation, and control system with an S-band RF crosslink and propulsion system. Particularly, each nanosatellite is equipped with a propulsion system and can change their inter-satellite ranges rapidly and accurately based on the mission operation scenarios. The proposed laser-crosslink systems are expected to contribute to the establishment of high-speed space-to-space network at low costs in the future. Copyright © 2022 by the International Astronautical Federation (IAF). All rights reserved.

关键词： Nanosatellites

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A Transport Theorem for the Inertia Tensor for Simplified Spacecraft Dynamics Development 73

A Transport Theorem for the Inertia Tensor for Simplified Sp...

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73rd International Astronautical Congress, IAC 2022

作者： Allard, Cody Maxwell, Jordan Schaub, Hanspeter Guidance Navigation and Control Engineer Laboratory for Atmospheric and Space Physics 1234 Innovation Dr BoulderCO80303 United States Sr. Guidance Navigation and Control Engineer Hedron United States Ann and H.J. Smead Department of Aerospace Engineering Sciences University of Colorado Boulder Colorado Center for Astrodynamics Research 431 UCB BoulderCO80309 United States

Dynamics development for free floating bodies in space involves describing how the body moves and can be complex for multi-body systems. If the body is assumed rigid, the change in mass properties is trivial because they do not change with respect to the body. However, if this is assumption cannot be made, describing the change in mass properties is critical. A key aspect of this variation is the change in the inertia tensor of the composite spacecraft. The transport theorem of vectors is widely utilized for dynamics development but is not well suited for simplification of the expression for the time rate of change of the inertia tensor. In this paper, the transport theorem of the inertia tensor is derived. A dynamics derivation is included and highlights the simplifications and time savings gained by the application of this tool. Copyright © 2022 by the International Astronautical Federation. All rights reserved.

关键词： Dynamics

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DESIGNING TRAJECTORIES RESILIENT TO MISSED THRUST EVENTS USING EXPECTED THRUST FRACTION

DESIGNING TRAJECTORIES RESILIENT TO MISSED THRUST EVENTS USI...

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AAS/AIAA astrodynamics Specialist Conference, 2020

作者： Rubinsztejn, Ari Sandel, Carrie Grace Sood, Rohan Laipert, Frank E. Astrodynamics and Space Research Laboratory Department of Aerospace Engineering and Mechanics The University of Alabama TuscaloosaAL35487 United States Flight Path Control Group Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States

ISBN: (纸本)9780877036753

With the adoption of efficient low-thrust propulsion methods, the probability of a missed thrust event occurring has become a significant concern for short and long-duration missions. If the missed thrust events take place during a critical portion of the trajectory, the mission can be compromised. Therefore, it is essential to develop trajectories that are resilient to missed thrust events. This paper investigates the use of expected thrust fraction, which embeds the stochastic nature of missed thrust events into a deterministic optimal control problem. The performance of trajectories designed using expected thrust fraction is compared with traditionally designed trajectories to measure changes in resiliency to missed thrust events. In this investigation, trajectories designed using expected thrust fraction arrive with a median lateness half that of traditionally designed trajectories. Using expected thrust fraction can help astrodynamicists mitigate risks posed by the use of low-thrust propulsion. © 2021, Univelt Inc. All rights reserved.

关键词： Trajectories

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USING REINFORCEMENT LEARNING TO DESIGN MISSED THRUST RESILIENT TRAJECTORIES

USING REINFORCEMENT LEARNING TO DESIGN MISSED THRUST RESILIE...

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AAS/AIAA astrodynamics Specialist Conference, 2020

作者： Rubinsztejn, Ari Bryan, Kyra Sood, Rohan Laipert, Frank E. Astrodynamics and Space Research Laboratory Department of Aerospace Engineering and Mechanics The University of Alabama TuscaloosaAL35487 United States Flight Path Control Group Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States

ISBN: (纸本)9780877036753

From ion thrusters to solar sails, spacecraft continue to adopt new and more efficient forms of propulsion. As these low-thrust propulsion methods have become more prevalent, new challenges have arisen. Depending on the mission, low-thrust propulsion elements may need to thrust continuously for days/months. During these thrusting periods, external factors, such as a micro-meteoroid impact or a software glitch, may cause the spacecraft to prematurely cease its thrust stage. Half of all deep space missions enter a safe mode where they cannot thrust every four months. These missed thrust events can result in the complete loss of a spacecraft for time-dependent trajectories like planetary rendezvous. This paper demonstrates how neural networks, trained using reinforcement learning, can autonomously correct for missed thrust events during an interplanetary trajectory. © 2021, Univelt Inc. All rights reserved.

关键词： Trajectories

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Evaluation of Magnet Configurations for Magnetohydrodynamic Trajectory control during Planetary Entry

Evaluation of Magnet Configurations for Magnetohydrodynamic ...

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AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025

作者： Fawley, Destiny M. Eggl, Siegfried Putnam, Zachary R. D’souza, Sarah Borner, Arnaud University of Illinois at Urbana-Champaign Department of Aerospace Engineering 104 S. Wright St. UrbanaIL61801 United States Johns Hopkins Applied Physics Laboratory Astrodynamics and Control Group LaurelMD20723 United States NASA Ames Research Center Entry Systems and Vehicle Development Branch Moffett FieldCA94035 United States AMA Inc. NASA Ames Research Center Thermal Protection Materials and Systems Branch MS 234-1 Moffett FieldCA94035 United States

ISBN: (纸本)9781624107238

Magnetohydrodynamics is a phenomenon that can be harnessed during planetary entry to augment aerodynamic drag and may enable higher mass payloads to safely reach the surface. The magnetohydrodynamic force is quantified over a wide range of freestream conditions using computational fluid dynamics results from a previous study. The force is calculated for an array of small electromagnets, a large non-superconducting magnet, a large superconducting magnet, and a uniform field. The superconducting magnet produces a magnetohydrodynamic force within an order of magnitude of aerodynamic drag for velocities higher than 10 km/s, indicating that it may have a reasonable impact on the trajectory for some cases. The array of small magnets and non-superconducting magnet produced a magnetohydrodynamic force that is less than 1% of the aerodynamic drag, so their magnetic fields are not strong enough to affect an entry trajectory. Additionally, the magnet placement plays an important role in magnetohydrodynamic force magnitude, with a magnet located near the shoulder producing approximately eight times more force than a magnet placed on the axis of symmetry. A mass and power budget for each magnet configuration is given assuming current state-of-the-art magnet technology. This study also discusses implementation challenges for each type of magnet on a spacecraft. © 2025, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Aerodynamic drag

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Neural network based optimal control: Resilience to missed thrust events for long duration transfers

Neural network based optimal control: Resilience to missed t...

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AAS/AIAA astrodynamics Specialist Conference, 2019

作者： Rubinsztejn, Ari Sood, Rohan Laipert, Frank E. Astrodynamics and Space Research Laboratory Department of Aerospace Engineering and Mechanics The University of Alabama TuscaloosaAL35487 United States Flight Path Control Group Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States

ISBN: (纸本)9780877036654

A growing number of spacecraft are adopting new and more efficient forms of in-space propulsion. One shared characteristic of these high efficiency propulsion techniques is their limited thrust capabilities. This requires the spacecraft to thrust continuously for long periods of time, making them susceptible to potential missed thrust events. This work demonstrates how neural networks can autonomously correct for missed thrust events during a long duration low-thrust transfer trajectory. The research applies and tests the developed method to autonomously correct a Mars return trajectory. Additionally, methods for improving the response of neural networks to missed thrust events are presented and further investigated. © 2020, Univelt Inc. All rights reserved.

关键词： Space flight

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Constant Thrust control Based on Double Threshold for Hovering at Asteroid Equilibrium Points

Constant Thrust Control Based on Double Threshold for Hoveri...

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第32届中国控制与决策会议

作者： SUI Zhihui FENG Junhua LI Maodeng ZHU Shengying School of Aerospace Engineering Beijing Institute of Technology Key Laboratory of Autonomous Navigation and Control for Deep Space Exploration National Key Laboratory of astrodynamics Key Laboratory of Science and Technology on Space Intelligent Control Beijing Institute of Control Engineering

This paper proposes a dual-threshold control method for constant thrust of hovering orbit at the unstable equilibrium point of an ***,according to the orbital dynamics model of the probe,the nominal hover ing orbit of the probe near the equilibrium point is ***,according to the basic idea of threshold control,not only set the threshold at the current moment,but also predict the state of the future moment and set the threshold at that *** when both thresholds are triggered at the same time does the constant thrust engine come into operation,which keeps the detector on the hovering ***,simulation was performed with Eros433 as the target *** simulation results show that the method can effectively reduce the number of engines switching and operating time while maintaining a certain accuracy.

关键词： Equilibrium points Constant thrust Dual-threshold control Nominal hover orbit

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Rapid Design and Exploration of High-Fidelity Low-Thrust Transfers to the Moon

Rapid Design and Exploration of High-Fidelity Low-Thrust Tra...

引用

IEEE Aerospace Conference

作者： Jackson Shannon Martin Ozimek Justin Atchison Christine Hartzell University of Maryland College Park Md Astrodynamics and Control Systems Group Johns Hopkins Applied Physics Laboratory 11101 Johns Hopkins Rd Laurel MD

ISBN: (数字)9781728127347

ISBN: (纸本)9781728127354

Spiral trajectories to the Moon present a difficult trajectory design problem. In this paper we show that the well-known Q-Law guidance algorithm can be leveraged to rapidly produce near optimal, high fidelity trajectories. By combining forward and backward propagated Q-Law, continuous trajectories are generated from an Earth parking orbit to a target Lunar orbit. The Q-Law result can then be refined using direct collocation. To demonstrate this process, we solve a problem inspired by the SMART-1 mission and compare to literature results. Then, an ESPA-class mission scenario is analyzed. We demonstrate that this technique can be used to efficiently explore the trajectory trade space and provide suitable initial guesses for direct optimization.

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PRELIMINARY TRAJECTORY DESIGN FOR NASA’S SOLAR CRUISER: A TECHNOLOGY DEMONSTRATION MISSION

PRELIMINARY TRAJECTORY DESIGN FOR NASA’S SOLAR CRUISER: A T...

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AAS/AIAA astrodynamics Specialist Conference, 2020

作者： Pezent, James B. Sood, Rohan Heaton, Andrew Miller, Kyle Johnson, Les Astrodynamics and Space Research Laboratory The University of Alabama 245 7thAve TuscaloosaAL35401 United States EV/42 NASA Marshall Space Flight Center NASA Marshall Space Flight Center HuntsvilleAL35812 United States Guidance Navigation and Control Systems NASA Marshall Space Flight Center NASA Marshall Space Flight Center HuntsvilleAL35812 United States Solar Cruiser PI Science Technology Office NASA Marshall Space Flight Center NASA Marshall Space Flight Center HuntsvilleAL35812 United States

ISBN: (纸本)9780877036753

This work outlines preliminary trajectory design for NASA’s proposed sail-based Solar Cruiser spacecraft, which is a finalist to be a secondary payload launched with the Interstellar Mapping and Acceleration Probe (IMAP) in October 2024. Trajectory optimization is carried out to ensure that Solar Cruiser can successfully reach a halo orbit about a Sun-Earth sub-L1 Lagrange point in under one year using only solar sail propulsion. Trade studies are performed to identify optimal trajectories subject to restrictions on sail-incidence angles and deployment times, and off nominal initial-conditions are examined to determine the feasibility of the baseline mission profile. Results, thus far, show that Solar Cruiser can be incorporated as a secondary payload on IMAP while satisfying tight operational restrictions. However, additional work must be done to mitigate risks from large launch vehicle injection errors. © 2021, Univelt Inc. All rights reserved.

关键词： NASA

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