HTV Rendezvous Technique And GN&amp;C Design Evaluation Based on 1st Flight On-Orbit Operation Result

Ueda, Shuichi; Kasai, Takeshi; Uematsu, Hirohiko

doi:10.2514/6.2010-7664

Cited by 17 publications

(7 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Space Shuttle employs a straight-line guidance law called glideslope [1]. Vehicles visiting the ISS usually employ a xed direction terminal approach, including HTV [2], ATV [3], and Cygnus [4]. In this work a constant direction guidance law is developed to rendezvous a target in circular orbit.…”

Section: Introductionmentioning

confidence: 99%

Optimal Glideslope Guidance for Spacecraft Rendezvous

Zanetti

2011

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Optimal Glideslope Guidance for Spacecraft Rendezvous

Zanetti

2011

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

“…There is an increased need for autonomous Proximity Operations (ProxOps) in such applications as rendezvous and docking for human space exploration and sample return missions, satellite servicing and on-orbit inspection, construction, and debris mitigation. Many autonomous ProxOps systems have been developed and proven in flight for large and complex systems [1][2][3] and are increasingly being used with small satellites [4][5]. Development of spacecraft Guidance, Navigation, and Control (GN&C) software architectures often involves bringing together individually developed algorithms and evaluating them using both simulation and hardware-in-the-loop testing [6].…”

mentioning

confidence: 99%

Development of an integrated spacecraft Guidance, Navigation, & Control subsystem for automated proximity operations

Schulte

Spencer

2016

Acta Astronautica

View full text Add to dashboard Cite

This paper describes the development and validation process of a highly automated Guidance, Navigation, & Control subsystem for a small satellite on-orbit inspection application, enabling proximity operations without human-in-the-loop interaction. The paper focuses on the integration and testing of Guidance, Navigation, & Control software and the development of decision logic to address the question of how such a system can be effectively implemented for full automation. This process is unique because a multitude of operational scenarios must be considered and a set of complex interactions between subsystem algorithms must be defined to achieve the automation goal. The Prox-1 mission is currently under development within the Space Systems Design Laboratory at the Georgia Institute of Technology. The mission involves the characterization of new small satellite component technologies, deployment of the LightSail 3U CubeSat, entering into a trailing orbit relative to LightSail using ground-in-the-loop commands, and demonstration of automated proximity operations through formation flight and natural motion circumnavigation maneuvers. Operations such as these may be utilized for many scenarios including on-orbit inspection, refueling, repair, construction, reconnaissance, docking, and debris mitigation activities. Prox-1 uses onboard sensors and imaging instruments to perform Guidance, Navigation, & Control operations during on-orbit inspection of LightSail. Navigation filters perform relative orbit determination based on images of the target spacecraft, and guidance algorithms conduct automated maneuver planning. A slew and tracking controller sends attitude actuation commands to a set of control moment gyroscopes, and other controllers manage desaturation, detumble, thruster firing, and target acquisition/recovery. All Guidance, Navigation, & Control algorithms are developed in a MATLAB/Simulink six degree-of-freedom simulation environment and are integrated using decision logic to autonomously determine when actions should be performed. The complexity of this decision logic is the primary challenge of the automated process, and the Stateflow tool in Simulink is used to establish logical relationships and manage data flow between each of the individual hardware and software components. Once the integrated simulation is fully developed in MATLAB/Simulink, the algorithms are autocoded to C/C++ and integrated into flight software. Hardware-in-the-loop testing provides validation of the Guidance, Navigation, & Control subsystem performance. Contents * This paper was originally presented during the 65 th International Astronautical Congress in Toronto, Canada † Corresponding author.

show abstract

“…The ISS is currently equipped with two manipulator systems, the Space Station Remote Manipulator System (Stieber et al, 1997), also known as Canadarm 2, and the Japanese Experiment Module Remote Manipulator System (Sato and Wakabayashi, 2001). The Space Station Remote Manipulator System is used to capture and berth H-II Transfer Vehicle (HTV), Dragon, and Cygnus vehicles, and to position supplies and astronauts (Dreyer, 2009;Bain, 2010;Ueda et al, 2010). With the Special Purpose Dexterous Manipulator (also called Dextre) as end-effector, the Space Station Remote Manipulator System is capable of fine manipulation (Coleshill et al, 2009).…”

Section: Introductionmentioning

confidence: 99%

Equations of Motion of Free-Floating Spacecraft-Manipulator Systems: An Engineer's Tutorial

et al. 2018

View full text Add to dashboard Cite

The paper provides a step-by-step tutorial on the Generalized Jacobian Matrix (GJM) approach for modeling and simulation of spacecraft-manipulator systems. The General Jacobian Matrix approach describes the motion of the end-effector of an underactuated manipulator system solely by the manipulator joint rotations, with the attitude and position of the base-spacecraft resulting from the manipulator motion. The coupling of the manipulator motion with the base-spacecraft are thus expressed in a generalized inertia matrix and a GJM. The focus of the paper lies on the complete analytic derivation of the generalized equations of motion of a free-floating spacecraft-manipulator system. This includes symbolic analytic expressions for all inertia property matrices of the system, including their time derivatives and joint-angle derivatives, as well as an expression for the generalized Jacobian of a generic point on any link of the spacecraft-manipulator system. The kinematics structure of the spacecraft-manipulator system is described both in terms of direction-cosine matrices and unit quaternions. An additional important contribution of this paper is to propose a new and more detailed definition for the modes of maneuvering of a spacecraft-manipulator. In particular, the two commonly used categories free-flying and free-floating are expanded by the introduction of five categories, namely floating, rotation-floating, rotation-flying, translation-flying, and flying. A fully-symbolic and a partially-symbolic option for the implementation of a numerical simulation model based on the proposed analytic approach are introduced and exemplary simulation results for a planar four-link spacecraft-manipulator system and a spatial six-link spacecraft manipulator system are presented.

show abstract

HTV Rendezvous Technique And GN&C Design Evaluation Based on 1st Flight On-Orbit Operation Result

Cited by 17 publications

References 1 publication

Optimal Glideslope Guidance for Spacecraft Rendezvous

Optimal Glideslope Guidance for Spacecraft Rendezvous

Development of an integrated spacecraft Guidance, Navigation, & Control subsystem for automated proximity operations

Equations of Motion of Free-Floating Spacecraft-Manipulator Systems: An Engineer's Tutorial

Contact Info

Product

Resources

About