Analysis of state-of-the-art single-thruster attitude control techniques for spinning penetrator

Raus, Robin; Gao, Yang; Wu, Yunhua; Watt, Mark

doi:10.1016/j.actaastro.2012.02.014

Cited by 14 publications

(8 citation statements)

References 7 publications

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“…To provide the needed torque, the thruster will have to rotate (2k 1) half-revolutions, where k is a nonnegative integer representing the total number of revolution(s) the spacecraft will make. As a result, the equation has been derived to accommodate the constraint [2]:…”

Section: B Prior Concept Of Half-cone Slew Using Single Thrustermentioning

confidence: 99%

“…Specifically for this experiment, the dynamic of STRaND-1 as the proposed testbed needed to be described. However, it has been proved in [2] that the total time needed to complete the slew maneuver is small compared to the time for the disturbance due to this semirigidity to take effect. The previous assumption is for the single-thruster-based slew maneuver.…”

Section: Simulations and Analysismentioning

confidence: 99%

“…= angular momentum of spacecraft, that in reference inertial/spacecraft-fixed body coordinates, that after H t = the first actuation, that at end of the slew, and the target angular momentum, N · ms I, I z , I t = spacecraft moment of inertia matrix, moment of inertia of transverse axis/spin axis, kg · m 2 k = rotation number around spin axis of the spacecraft m = magnetic moment of the magnetorquer dipole, A · m 2 T, T magnet = control torque/ magnetic torque applied to the spacecraft, N · m t 0 , t 1f , t 2s , t 2f , t 1;2 , Δt 2 , t E XISTING research [1][2][3][4][5] on the prolate spinning spacecraft attitude maneuver has developed a series of slew algorithms using a single thruster in two categories: half-cone derived algorithms and pulse-train algorithms. Half-cone derived algorithms consist of half-cone (HC), multi-half-cone, dual-half-cone, extended half-cone, sector arc slew, and multisector arc slew, using the precession behavior of a spinning prolate spacecraft.…”

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confidence: 99%

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Slew Control of Prolate Spinners Using Single Magnetorquer

Gao

Chanik

2016

Journal of Guidance, Control, and Dynamics

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= angular momentum of spacecraft, that in reference inertial/spacecraft-fixed body coordinates, that after H t = the first actuation, that at end of the slew, and the target angular momentum, N · ms I, I z , I t = spacecraft moment of inertia matrix, moment of inertia of transverse axis/spin axis, kg · m 2 k = rotation number around spin axis of the spacecraft m = magnetic moment of the magnetorquer dipole, A · m 2 T, T magnet = control torque/ magnetic torque applied to the spacecraft, N · m t 0 , t 1f , t 2s , t 2f , t 1;2 , Δt 2 , t ⌢ 2 = time of the start, time at the end of the first actuation, time of the start of the second actuation, time at the end of second actuation, time interval between first and second actuation, the actuating duration of the second actuation and the predicted meantime of second actuation, s Z 0 , Z 1f , Z f , Z ins , Z t = spin axis of the initial/after the first actuation/after the slew/of an instant time and of the target orientation β = slew angle, deg γ = residual precession angle after the first actuation of slew, deg θ = nutation angle, deg λ = inertia ratio of spin axis and transverse axis moment of inertia ξ = the second actuation time adjustment coefficient ω, ω Z , ω XY , ω N , ω H = angular velocity of the spacecraft, that in spin axis, that in the X − Y plane, body nutation rate, and inertial nutation rate, rad∕s

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Section: B Prior Concept Of Half-cone Slew Using Single Thrustermentioning

confidence: 99%

Section: Simulations and Analysismentioning

confidence: 99%

mentioning

confidence: 99%

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Slew Control of Prolate Spinners Using Single Magnetorquer

Gao

Chanik

2016

Journal of Guidance, Control, and Dynamics

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“…For more than four decades, these actuators have been utilized in various types of satellites (Kazinczy and Leibing, 1975;Stenmark and Lang, 1997), such as spinning satellites ( Jiang et al 2008;Raus et al 2010;Ayoubi and Longuski 2009). For instance, recently, Tang et al (2011) used micro-thruster actuators in a small spinning satellite for the three-dimensional attitude control.…”

Section: Micro-thrustersmentioning

confidence: 99%

Attitude Dynamics and Control of Satellites With Fluid Ring Actuators

Nobari

Misra

2012

Journal of Guidance, Control, and Dynamics

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Successful mission of a satellite depends on maintaining a fixed orientation with respect to the Earth. However, the attitude angles of a satellite can be perturbed because of various natural disturbance sources, such as the Earth's gravity gradient, solar radiation pressure, and the Earth's magnetic field. Modeling the attitude dynamics and developing a controller to stabilize the attitude motion are quite important steps in the design of satellites. Although several actuators exist to control the attitude motion, a novel type considered in the thesis, shows promise of producing a high torque to mass ratio. This potential justifies the in-depth study reported. The novel actuator in question consists of a ring containing fluid, whose flow is regulated by a pump. The control torque is produced due to the variation of the angular velocity of the fluid.In this thesis, first, a redundant actuator system composed of four fluid rings in a pyramidal configuration is studied. The dynamical model of the system is developed for a satellite travelling either in a circular or an elliptical orbit. The dynamical analysis of this system leads to an underdetermined system of nonlinear differential equations, whose solution without considering the control input (the torque produced by the pump pressure) shows that the fluid rings can damp out the attitude disturbances of a satellite in a circular orbit and the roll-yaw disturbances in an elliptical orbit. However, this passive damping effect is fairly slow; an active controller is hence designed in the next step. The effect of the failure of one fluid ring on the performance of the attitude control subsystem (ACS) of a satellite is also studied. It is observed that even in the case of failure of one fluid ring, the satellite can be stabilized by slight modification of the active controller.Later, a sliding mode controller is designed to cope with the uncertainties existing in the fluid model and in other parameters of the system. Although the results achieved are quite satisfactory, the chattering that exists in the steady response of the system is not i desirable; hence a switching controller consisting of a sliding mode and a PID control law is designed to eliminate this chattering effect.Next, the theoretical results obtained are validated by conducting several experiments. To this end, first, a setup with one fluid ring is designed and built. Here, a single fluid ring is attached to a disk so as to verify the controllability of the system with a fluid ring and also the validity of the theoretical model. Although the experimental results confirm the theory developed in this thesis, the large torque-to-mass ratio expected is revealed to be only possible at the cost of a quite high input voltage to the pumps regulating the flow. Therefore, two novel applications of fluid rings are proposed: as an actuator for spin stabilized satellites, or as an auxiliary actuator in satellites with magnetic torquers.Using fluid rings in spin stabilized satellites is proposed in the the...

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“…Surrey Space Centre (SSC) has recently developed a testbed for a spin-stabilized spacecraft using a spherical air bearing platform. This testbed was initially targeted to be used as a real-time verification tool for the state-of-the-art slew control algorithms of prolate spinner [1][2][3]. This prolate spinner or spin-stabilized spacecraft was intended for the moon penetrator mission called MoonLITE [4].…”

Section: Introductionmentioning

confidence: 99%

Modular Testbed for Spinning Spacecraft

Chanik

Gao

2017

Journal of Spacecraft and Rockets

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Abstract-The ground verification of a spacecraft control algorithm is commonly done via air bearing facility. Air bearing testbeds are frequently developed for testing a three-axis stabilised spacecraft control algorithm but hardly for a spin stabilised spacecraft. A modular testbed for testing a spinning spacecraft has been developed in the Surrey Space Centre (SSC) initially for the real-time verification of a prolate spinner slew control algorithms. This testbed is made from commercially-offthe-shelf (COTS) components with a modular system design approach through rapid control prototyping (RCP) using Matlab xPC Target and extendable to other RCP technique. It is equipped with a novel low cost monocular vision system for attitude determination with the accuracy of 0.06 deg and angular velocity accuracy of 0.15 deg/s. For the current specification, a cold gas propulsion system is fixed to the testbed with a 2-DOF thruster set that can deliver up to 0.25N of thrust and an air bearing capability that gives 3-DOF with a maximum tilt angle of 30 deg. In this paper, the testbed implementation is described and the test platform is verified.

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Analysis of state-of-the-art single-thruster attitude control techniques for spinning penetrator

Cited by 14 publications

References 7 publications

Slew Control of Prolate Spinners Using Single Magnetorquer

Slew Control of Prolate Spinners Using Single Magnetorquer

Attitude Dynamics and Control of Satellites With Fluid Ring Actuators

Modular Testbed for Spinning Spacecraft

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