Orion Handling Qualities During International Space Station Proximity Operations and Docking

Stephens, John-Paul; Vos, Gordon A.; Bilimoria, Karl D.; Mueller, Eric R.; Brazzel, Jack; Spehar, Pete

doi:10.2514/1.a32253

Cited by 9 publications

(4 citation statements)

References 10 publications

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“…Early forms of the capability have been shown on the Japanese ETS-VII, European ATV, Russian Soyuz, US XSS-11, and US DART demonstrators. Most recently, the human-rated SpaceX Crew Dragon performed autonomous docking with the ISS, and the Orion Spacecraft is set to also feature this ability (Stephens et al, 2013;D'Souza et al, 2007). Further development in autonomous spacecraft rendezvous calls for smaller and cheaper sensors as well as a reduction in the degree of cooperation by the target spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Advances in Trajectory Optimization for Space Vehicle Control

Malyuta¹,

Yu²,

Elango³

et al. 2021

Preprint

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Space mission design places a premium on cost and operational efficiency. The search for new science and life beyond Earth calls for spacecraft that can deliver scientific payloads to geologically rich yet hazardous landing sites. At the same time, the last four decades of optimization research have put a suite of powerful optimization tools at the fingertips of the controls engineer. As we enter the new decade, optimization theory, algorithms, and software tooling have reached a critical mass to start seeing serious application in space vehicle guidance and control systems. This survey paper provides a detailed overview of recent advances, successes, and promising directions for optimization-based space vehicle control. The considered applications include planetary landing, rendezvous and proximity operations, small body landing, constrained attitude reorientation, endo-atmospheric flight including ascent and reentry, and orbit transfer and injection. The primary focus is on the last ten years of progress, which have seen a veritable rise in the number of applications using three core technologies: lossless convexification, sequential convex programming, and model predictive control. The reader will come away with a well-rounded understanding of the state-of-the-art in each space vehicle control application, and will be well positioned to tackle important current open problems using convex optimization as a core technology.

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Section: Introductionmentioning

confidence: 99%

Advances in Trajectory Optimization for Space Vehicle Control

Malyuta¹,

Yu²,

Elango³

et al. 2021

Preprint

View full text Add to dashboard Cite

show abstract

“…Scenarios similar to structural deployment are found in applications ranging from the operation of space systems to robotics . For example, in the final phase of space rendezvous and docking, a quasi‐static approach is ideal to ensure soft docking . During the last 60 m before contact, the relative speed between the docking spacecraft is only 2‐3 m/min and angular velocities and accelerations are practically zero .…”

Section: Introductionmentioning

confidence: 99%

Close tracking of equilibrium paths

Sultan

2018

Intl J Robust & Nonlinear

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Summary A method to control a generic system of nonlinear ordinary differential equations between equilibrium states is analyzed. The objective is to ensure that the system's state space trajectory closely tracks an equilibrium path. The control law is obtained via time parameterization of the corresponding equilibrium control path. Conditions which guarantee that the system's state space trajectory closely tracks the equilibrium path are proved using two approaches. One approach uses the mean value theorem, and the other uses the slowly time‐varying systems theory. Importantly, both methods provide relationships between the control rate norm and the tracking error norm. These allow computation of upper bounds on the control rate norm which guarantee a desired upper bound on the tracking error norm. They also enable computation of upper bounds on the tracking error norm for a given upper bound on the control rate norm. Examples illustrate the theoretical results.

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“…The modeling and analysis methods of man-in-loop dynamics system can be classified into the analytical method [3][4][5][6] and the experimental method [7][8][9][10][11][12]. Due to the safety concerns of astronauts, the fault experiment cannot be conducted in the real environment.…”

Section: Introductionmentioning

confidence: 99%

Failure effect analysis and reconfiguration of thrusters based on inverse simulation of manually controlled RVD

Zhou

Wang

Thomson

et al. 2018

Aerospace Science and Technology

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Fault analysis of man-in-loop systems is a valuable issue worthy of being studied, especially in projects including high risk and high investment like manned space missions. Spacecraft sometimes must have the fault tolerance to complete their task even after errors occurring. Inverse simulation was previously proved to achieve manually rendezvous and docking (RVD) successfully. The aim of this paper is to demonstrate the potential applications of inverse simulation to undertake the thruster fault analysis and reconfigurations in manned RVD mission. Firstly, the inverse simulation system is established in a model predicted control structure. Then, the astronauts' operational strategy is analyzed through the thruster fault simulation, and an operational rate factor is proposed to assess the failure risk. In addition, the original configuration is transformed to strengthen the resistance under consideration of the fault tolerance. The comparative results indicate that the modified configuration can improve the performance effectively and then guarantee the success of the mission.

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Orion Handling Qualities During International Space Station Proximity Operations and Docking

Cited by 9 publications

References 10 publications

Advances in Trajectory Optimization for Space Vehicle Control

Advances in Trajectory Optimization for Space Vehicle Control

Close tracking of equilibrium paths

Failure effect analysis and reconfiguration of thrusters based on inverse simulation of manually controlled RVD

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