Spacecraft mass property identification with torque-generating control

Bergmann, E.; Dzielski, John

doi:10.2514/3.20522

Cited by 61 publications

(27 citation statements)

References 3 publications

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“…However, these methods require a great quantity of valuable fuel to be consumed in order to obtain the data which is needed in identification algorithm. Bergmann et al [9] develops an algorithm for estimation of the mass and mass center of a rigid spacecraft using only torque-producing actuators, such as controlmoment gyros or reaction wheels, and commonly available sensors, e.g., rate gyros and accelerometers. The use of torqueproducing control for estimation prevents fuel usage, disturbances, and contamination problems.…”

Section: Introductionmentioning

confidence: 99%

Docked spacecraft mass property identification using space manipulator

Wang

Huang

Chang

et al. 2014

2014 IEEE International Conference on Information and Automation (ICIA)

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This paper presents an approach for identification of mass properties of the docked spacecraft only by the motion of space manipulator. The approach makes use of the conservation of momentum, and the corresponding identification algorithm that does not require torque or acceleration measurement is developed based the recursive least square, and can be solved in two steps. The first step is to identify the mass and mass center of the docked spacecraft based on the principle of linear momentum conservation; and the second step is to identify the inertia tensor of the docked spacecraft based on the principle of angular momentum conservation. The significant advantage of the approach is to decouple the mass, mass center and inertia tensor, without consuming valuable jet fuel, and requires only a wide range of motion of space manipulator. Validity of the identified result is confirmed by the simulation.

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Section: Introductionmentioning

confidence: 99%

Docked spacecraft mass property identification using space manipulator

Wang

Huang

Chang

et al. 2014

2014 IEEE International Conference on Information and Automation (ICIA)

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“…Although they are different in details, most of them (i.e., [7][8][9][10][11][12]) use the same fundamental approach, which is based on the Newton-Euler equation of motion, namely,…”

Section: Literature Surveymentioning

confidence: 99%

“…The procedure can be roughly illustrated in Fig Precisely measuring the time history of the magnitude and direction of each thrust force is difficult. References [7][8][9][10] basically followed the above outlined approach. References [11] and [12] smartly improved the above-mentioned force-based approach by eliminating the nonlinear term t x Io from the regression equation by pre-multiplying to x to each term of eq.(2).…”

Section: Literature Surveymentioning

confidence: 99%

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On-Orbit Identification of Inertia Properties of Spacecraft Using Robotics Technology

2007

AIAA Guidance, Navigation and Control Conference and Exhibit

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“…Bergman et al [2] developed an algorithm for the estimation of spacecraft mass characteristics using only torque-producing actuators. This capability enhances the usefulness of an autopilot function that is capable of adapting to changes in the spacecraft's mass characteristics.…”

Section: Introductionmentioning

confidence: 99%

Novel Measurement Method for Determining Mass Characteristics of Pico-Satellites

2018

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Abstract:The centroid and moment of inertia directly affect the dynamic characteristics of aircraft, and accurate mass characteristic measurements are crucial to adequately control aircraft attitude. This paper proposes a new measurement method for determining aircraft mass characteristics that can improve measurement precision when used in regard to pico-satellites. The measurement system is designed according to the principles of three-point measure and constant torque. The feasibility of the test method of this study for determining the mass characteristics is proved by using a dynamic simulation and an experimental analysis method. Through a number of standard workpiece tests, the deviation of the measurement system and effective compensation methods of the mass characteristics are obtained. The measurement system and compensation methods are applied to measure the mass characteristics of a pico-satellite, which can be detected by only one time clamping. The measurement system proposed herein can effectively improve measurement precision, as it was found that the accuracy of the centroid and the moment of inertia of the pico-satellite are less than 1 mm and 1.5 × 10 −2 kgm 2 , respectively. The proposed measurement system also has many advantages, such as a simple operation, high efficiency, small volume, and low cost.

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Spacecraft mass property identification with torque-generating control

Cited by 61 publications

References 3 publications

Docked spacecraft mass property identification using space manipulator

Docked spacecraft mass property identification using space manipulator

On-Orbit Identification of Inertia Properties of Spacecraft Using Robotics Technology

Novel Measurement Method for Determining Mass Characteristics of Pico-Satellites

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