Investigation of Periodic-Disturbance Identification and Rejection in Spacecraft

Lau, Jimmy; Joshi, Sanjay S.; Agrawal, Brij N.; Kim, Jong-Woo

doi:10.2514/1.17341

Cited by 24 publications

(12 citation statements)

References 12 publications

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“…In the present paper, disturbance-rejection filters are studied further to explicitly employ the periodic-disturbance frequency into a filter embedded in the feedback control loop. The DRF is based on linear theory and internal model principle [9], it has superiorities to implement in space application because of simplicity and computational efficacy [10], and its effectiveness has been shown experimentally on the realistic nonlinear rigid-body spacecraft model [6]. However, the rejection filter is not robust to disturbance frequency uncertainty.…”

Section: Chuzystar@gmailcommentioning

confidence: 98%

“…The traditional disturbance rejection filter is based on the internal mode principle, which places periodic-disturbance poles inside the compensator loop so that the unstable disturbance poles are canceled during loop closure between the output signal and input disturbance [6]. The disturbance rejection filter is designed with the quosi-periodic disturbance frequency ω p :…”

Section: B Adaptive Disturbance Rejection Filtermentioning

confidence: 99%

“…Considering the properties of robustness and duration synthetically, optimal input shaping is the optional selection to implement [4]. It can suppress the residual vibration of the moving flexible appendage to noticeable improve the performance of the platform [5], but the existence of coupling between the spacecraft motion and manipulator vibration motion is inevitable, so another challenge in high-performance spacecraft control is the mitigation of quasi-periodic disturbances caused by the excitation of flexible appendages and so on [6].…”

Section: Chuzystar@gmailcommentioning

confidence: 99%

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Vibration Control of Maneuvering Spacecraft with Flexible Manipulator Using Adaptive Disturbance Rejection Filter and Command Shaping Technology

Chu

Cui

2012

2012 Sixth International Conference on Internet Computing for Science and Engineering

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In order to satisfy the requirement of agile and precise performance of flexible spacecraft during an orientating maneuver with a large angle of rotation, an Adaptive Disturbance Rejection Filter (ADRF) combined with Optimal Input Shaping (OIS) control law is developed for a rigid space platform with flexible manipulator. OIS based smoothing method is applied to the flexible manipulator to suppress the vibrating motion of the flexible appendage and alleviate effect of it on the platform primarily. Furthermore, the mitigation of periodic disturbance is caused by the excitation of flexible appendages.The mitigation is studied by disturbance-rejection filter. The filter considers the inevitable existence of nonlinear coupling between the platform motion and manipulator vibration motion, the disturbance frequency is an important factor need to be intensively studies. We present an Adaptive Notch Filter(ANF) that is based on close-loop system identification method. The filter helps identify the disturbance frequency and update the parameters of the DRF adaptively. Simulation results confirm the ability of the proposed controller in high-speed and precise attitude switching maneuver while suppressing the manipulator vibration.

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Section: Chuzystar@gmailcommentioning

confidence: 98%

Section: B Adaptive Disturbance Rejection Filtermentioning

confidence: 99%

Section: Chuzystar@gmailcommentioning

confidence: 99%

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Vibration Control of Maneuvering Spacecraft with Flexible Manipulator Using Adaptive Disturbance Rejection Filter and Command Shaping Technology

Chu

Cui

2012

2012 Sixth International Conference on Internet Computing for Science and Engineering

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“…Sinusoidal disturbance rejection is a fundamental control objective, which arises in a wide variety of applications, including active noise cancellation, 1 helicopter vibration suppression, 2 active rotor balancing, 3 and vibration reduction in spacecraft. 4 For an accurately modeled linear time-invariant (LTI) system, the internal-model principle can be used to design a feedback controller capable of rejecting sinusoidal disturbances of known frequencies. [5][6][7][8] In this case, disturbance rejection is accomplished by incorporating copies of the disturbance dynamics in the feedback loop.…”

Section: Introductionmentioning

confidence: 99%

Adaptive harmonic steady‐state control for rejection of sinusoidal disturbances acting on a completely unknown system

Kamaldar

Hoagg

2017

Adaptive Control & Signal

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This paper presents an adaptive harmonic steady-state (AHSS) controller that addresses the problem of rejecting sinusoids with known frequencies that act on a completely unknown asymptotically stable linear time-invariant system. We analyze the stability and closed-loop performance of AHSS for multi-input multi-output systems that are square (ie, the number of controls equals the number of performance measurements). In this case, we show that AHSS asymptotically rejects disturbances, that is, the performance measurement tends to 0. We also present a numerical study of the steady-state and transient performance of AHSS for square and nonsquare systems.

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“…The adaptive technique, as a popular tool, has been effectively used for dealing with parameter uncertainties resulting from failures or disturbances [10,11]. In [12], the asymptotic tracking property of arbitrary smooth bounded reference output signals is addressed, with simultaneous rejection of disturbances generated by an unknown linear exosystem.…”

mentioning

confidence: 99%

Aircraft Turbulence Compensation Using Adaptive Multivariable Disturbance Rejection Techniques

Wen

Tao

Yang

et al. 2015

Journal of Guidance, Control, and Dynamics

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NomenclatureD δ e = aerodynamic drag derivative with respect to elevator deflection angle L p , N p = roll and yaw moment derivatives with respect to roll rate L r , N r = roll and yaw moment derivatives with respect to yaw rate L r , L β = aerodynamic roll moment derivative with respect to yaw rate and sideslip angle L α , D α , T α = aerodynamic lift, drag, and thrust derivatives with respect to angle of attack L _ α = aerodynamic lift derivative with respect to rate of change angle of attack L β , N β = roll and yaw moment derivatives with respect to sideslip angle L δ e , M δ e = aerodynamic roll and pitch moment derivatives with respect to elevator deflection angle L 0 , D 0 = benchmark aerodynamic lift and drag derivatives with respect to angle of attack M V , M q = aerodynamic pitch moment derivative with respect to aircraft flight speed V and pitch rate M α , M _ α = aerodynamic pitch moment derivative with respect to α and _ α m, g = mass of the aircraft, gravity acceleration N δa , L δa = yaw and roll moment derivatives with respect to aileron deflection angle N δr , L δr = yaw and roll moment derivatives with respect to rudder deflection angle p, q, r = body axis components of the angular velocity p W , q W , r W = local air mass angular velocities resulting from the wind gradients T, δ T , T δ T = engine thrust, throttle, and aerodynamic thrust derivative with respect to the throttle T V , D V , L V = thrust, aerodynamic drag, and aerodynamic lift derivatives with respect to airspeed V u; v; wu A ; v A ; w A = body axis components of, aircraft flight velocity, and aircraft track velocity V W ; u W , v W , w W = local turbulence velocity and body axis components of V W V 0 , α 0 , γ 0 = benchmark flight velocity, angle of attack, and flight-path angle Y β , Y p , Y r = side force derivatives with respect to sideslip angle, roll rate, yaw rate Y δa , Y δr = side force derivatives with respect to aileron deflection angle and rudder deflection angle α, β = angle of attack and sideslip angle α K , β K = angle of attack and sideslip angle due to V K α W , β W = angle of attack and sideslip angle due to V W θ, ϕ, ψ = Euler pitch, roll, and yaw angle σ = angle between thrust and body x b axis

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Investigation of Periodic-Disturbance Identification and Rejection in Spacecraft

Cited by 24 publications

References 12 publications

Vibration Control of Maneuvering Spacecraft with Flexible Manipulator Using Adaptive Disturbance Rejection Filter and Command Shaping Technology

Vibration Control of Maneuvering Spacecraft with Flexible Manipulator Using Adaptive Disturbance Rejection Filter and Command Shaping Technology

Adaptive harmonic steady‐state control for rejection of sinusoidal disturbances acting on a completely unknown system

Aircraft Turbulence Compensation Using Adaptive Multivariable Disturbance Rejection Techniques

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