Dynamic ground testing of the Skipper Attitude Control System

Fullmer, R. Rees

doi:10.2514/6.1996-103

Cited by 10 publications

(7 citation statements)

References 1 publication

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“…To minimize this disturbance torque, the distance between the center of mass and the center of rotation needs to be minimized. A standard procedure for manually balancing a spacecraft simulator is described in [4], where, by inspecting the spacecraft simulator pendulum motion, the balance masses are moved to increase the period of the pendulum motion. This method requires multiple trials and is limited in real applications because of the rotational travel constraints of the spherical air bearing.…”

Section: E Rmentioning

confidence: 99%

Automatic Mass Balancing of a Spacecraft Three-Axis Simulator: Analysis and Experimentation

Chesi¹,

Gong²,

Pellegrini³

et al. 2014

Journal of Guidance, Control, and Dynamics

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Spacecraft three-axis simulators provide frictionless and, ideally, torque-free hardware simulation platforms that are crucial for validating spacecraft attitude determination and control strategies. To reduce the gravitational torque, the distance between the simulator center of mass and the center of rotation needs to be minimized. This work proposes an automatic mass balancing system for spacecraft simulators, which uses only the three sliding masses during the balancing process, without need of further actuators. The proposed method is based on an adaptive nonlinear feedback control that aims to move, in real time, the center of mass toward the spacecraft simulator's center of rotation. The stability of the feedback system and the convergence of the estimated unknown parameter (the distance between the center of mass and the center of rotation) are analyzed through Lyapunov stability theory. The proposed method is experimentally validated using the CubeSat Three-Axis Simulator at the Spacecraft Robotics Laboratory of the Naval Postgraduate School. = theoretical control torque, N ω = angular velocity vector, rad∕s ω g = angular velocity vector parallel to the gravity field, rad∕s ω p = angular velocity vector perpendicular to the gravity field, rad∕s

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Section: E Rmentioning

confidence: 99%

Automatic Mass Balancing of a Spacecraft Three-Axis Simulator: Analysis and Experimentation

Chesi¹,

Gong²,

Pellegrini³

et al. 2014

Journal of Guidance, Control, and Dynamics

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“…Through the use of this testbed, "a signi cant number of integration problems [between spacecraft subsystems] were identi ed and resolved easily." 33 The Tele-Educationin Aerospaceand Mechatronics(TEAM) laboratory is an international project that makes use of modern multimedia and telecommunications technologies to host a virtual laboratory among the seven member universities: three in Canada, the Université de Sherbrooke, the University of Victoria, the University of Toronto, and four in Europe, the University FH RavensburgWeingarten, the Università di Bologna, the Aalborg University, and the University of Siegen. One of the laboratory facilities located at the Université de Sherbrooke is TEAMSAT.…”

Section: ¡20mentioning

confidence: 99%

Historical Review of Air-Bearing Spacecraft Simulators

Schwartz

Peck

Hall

2003

Journal of Guidance, Control, and Dynamics

275

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An overview of air-bearing spacecraft simulators is provided. Air bearings have been used for satellite attitude determination and control hardware veri cation and software development for nearly 45 years. It is interesting to consider the history of this technology: how early systems were rst devised and what diverse capabilities current systems provide. First a survey is given of planar systems that give a payload freedom to translate and spin. Then several classes of rotational air bearings are discussed: those which simulate three-axis satellite attitude dynamics. The subsequent section discusses perhaps the most interesting facilities: those that provide both translational and three-dimensional rotational freedom. The diverse capabilities each style of air-bearing testbed provides, the many settings they can be found in, and ways to improve facility performance are described.

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“…Driving applications for external, continuum, hypersonic aeow simulation in the period 1991 to the present included closeouts or continuations of several of the programs noted above as well as X-33 1 घa technology demonstrator for a fully Reusable Launch V ehicle घRLVङङ, X34 घMach 8 test vehicleङ, 12 Assured Crew Return Vehicle घACRVङ, 13 Hyper X, 14 Commercial Experiment Transporter घCOMETङ 15 घlater renamed घMultiple Experiment T ransporter to Earth Orbit and Return घMETEORङङ, Mars Exploration Program, 16 Stardust, Skipper, 17 and Pegasus XL Wing-Glove Experiment. 18 Recent advances in computational aerothermodynamics in Europe have been summarized by Kordulla and Morice.…”

Section: Historical Perspective and Technology Driversmentioning

confidence: 99%

Computational aerothermodynamic design issues for hypersonic vehicles

Olynick

Venkatapathy

1997

32nd Thermophysics Conference

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A brief review of the evolutionary progress in computational aerothermodynamics is presented. The current status of computational aerothermodynamics is then discussed, with emphasis on its capabilities and limitations for contributions to the design process of hypersonic vehicles. Some topics to be highlighted include: घ1ङ aerodynamic coeaecient predictions with emphasis on high temperature gas eaeects; घ2ङ surface heating and temperature predictions for thermal protection system घTPSङ design in a high temperature, thermochemical nonequilibrium environment; घ3ङ methods for extracting and extending computational aeuid dynamic घCFDङ solutions for eaecient utilization by all members of a multidisciplinary design team; घ4ङ physical models; घ5ङ validation process and error estimation; and घ6ङ gridding and solution generation strategies. Recent experiences in the design of X-33 will be featured. Computational aerothermodynamic contributions to Mars Pathaender, METEOR, and Stardust घComet Sample returnङ will also provide context for this discussion. Some of the barriers that currently limit computational aerothermodynamics to a predominantly reactive mode in the design process will also be discussed, with the goal of providing focus for future research.

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Dynamic ground testing of the Skipper Attitude Control System

Cited by 10 publications

References 1 publication

Automatic Mass Balancing of a Spacecraft Three-Axis Simulator: Analysis and Experimentation

Automatic Mass Balancing of a Spacecraft Three-Axis Simulator: Analysis and Experimentation

Historical Review of Air-Bearing Spacecraft Simulators

Computational aerothermodynamic design issues for hypersonic vehicles

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