A frequency domain stability analysis of a phase plane control system

Hattis, P. D.; Kubiak, E. T.; Penchuk, A.

doi:10.2514/3.19934

Cited by 22 publications

(8 citation statements)

References 3 publications

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“…The PWM method is a mature technology of thruster control and is widely used [6][7][8], but its high-frequency on/off thruster valve operation and valve lifetime are the main causes of the failure problems studied in this paper. Motion-based diagnosis has been proven to be effective [19], and Kalman filtering has been applied in engineering for a long time, however, some shortcomings The computer configuration is: Intel(R) Core(TM) i5-4200H CPU @ 2.80GHz, RAM 4.00GB, Windows 8 operating system.…”

Section: Discussionmentioning

confidence: 99%

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Blended Filter-Based Detection for Thruster Valve Failure and Control Recovery Evaluation for RLV

Sun

Zhang

2019

Algorithms

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Security enhancement and cost reduction have become crucial goals for second-generation reusable launch vehicles (RLV). The thruster is an important actuator for an RLV, and its control normally requires a valve capable of high-frequency operation, which may lead to excessive wear or failure of the thruster valve. This paper aims at developing a thruster fault detection method that can deal with the thruster fault caused by the failure of the thruster valve and play an emergency role in the cases of hardware sensor failure. Firstly, the failure mechanism of the thruster was analyzed and modeled. Then, thruster fault detection was employed by introducing an angular velocity signal, using a blended filter, and determining an isolation threshold. In addition, to support the redundancy management of the thruster, an evaluation method of the nonlinear model-based numerical control prediction was proposed to evaluate whether the remaining fault-free thruster can track the attitude control response performance under the failure of the thruster valve. The simulation results showed that the method is stable and allowed for the effective detection of thruster faults and timely evaluation of recovery performance.

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Section: Discussionmentioning

confidence: 99%

“…However, the PWM method requires a thruster that is capable of high-frequency operation, which may lead to excessive wear of the thruster valve. In addition, the PWM duty cycle of the thruster system is subject to a certain practical limit [8].…”

Section: Introductionmentioning

confidence: 99%

Blended Filter-Based Detection for Thruster Valve Failure and Control Recovery Evaluation for RLV

Sun

Zhang

2019

Algorithms

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“…The shuttle RCS system was derived from the Apollo and Skylab programs; however, because the shuttle has only one plane of symmetry, rotational coupling problems led to numerous changes [3,4]. The design of the X-33 ultimately incorporated 10 RCS jets into the vehicle design, which were placed in such a way that resulted in significant rotational coupling between the roll, pitch, and yaw axes [5].…”

Section: Introductionmentioning

confidence: 99%

“…The PWM method, as will be seen in a comparison with the proposed method of this paper, was found to use less propellant when regulating attitude around low-amplitude terminal limit cycles near zero error, but at the expense of higher jet cycling. In addition, there are practical limits to PWM duty cycles for RCS systems, for example, shuttle RCS thrusters have an 80 ms cycle-time granularity [4].…”

Section: Introductionmentioning

confidence: 99%

Quantized Control Allocation of Reaction Control Jets and Aerodynamic Control Surfaces

Doman

Gamble

Ngo

2009

Journal of Guidance, Control, and Dynamics

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A mixed-integer linear programming approach to mixing continuous and pulsed control effectors is proposed. The method is aimed at applications involving reentry vehicles that are transitioning from exoatmospheric flight to endoatmospheric flight. In this flight phase, aerodynamic surfaces are weak and easily saturated, and vehicles typically rely on pulsed reaction control jets for attitude control. Control laws for these jets have historically been designed using single-axis phase-plane analysis, which has proven to be sufficient for many applications where multiaxis coupling is insignificant and when failures have not been encountered. Here, we propose using a mixed-integer linear programming technique to blend continuous control effectors and pulsed jets to generate moments commanded by linear or nonlinear control laws. When coupled with fault detection and isolation logic, the control effectors can be reconfigured to minimize the impact of control effector failures or damage. When the continuous effectors can provide the desired moments, standard linear programming methods can be used to mix the effectors; however, when the pulsed effectors must be used to augment the aerodynamic surfaces, mixed-integer linear programming techniques are used to determine the optimal combination of jets to fire. The reaction jet control allocator acts as a nonuniform quantizer that applies a moment vector to the vehicle, which approximates the desired moment generated by a continuous control law. Lyapunov theory is applied to develop a method for determining the region of attraction associated with a quantized vehicle attitude control system.

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“…Implementation of both of these approaches can be found in the open literature. Phase-plane based on-off control using RCJs is employed for the Apollo command module [3], Mars Science Laboratory [4], Space Shuttle [5] and Near Earth Asteroid Scout CubeSat [6], to name a few. To address the multiaxis coupling problem, which is challenging to handle using the phase-plane analysis, an alternative mixed-integer linear programming formulation is proposed in [7], where RJCs are blended together with aerodynamic control surfaces.…”

Section: Introductionmentioning

confidence: 99%

Controlling a launch vehicle at exoatmospheric flight conditions via adaptive control allocation

Yıldız¹

2020

Turk J Elec Eng & Comp Sci

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The focus of this paper is the control of a reusable launch vehicle at exoatmospheric flight conditions, in the presence of actuator effectiveness uncertainty. Since during exoatmospheric flight, dynamic pressure is nonexistent, aerodynamic control surfaces cannot be used. Under these conditions, reaction control jet actuators can provide the necessary thrust to control the vehicle. Reaction control jets have only 2 states, namely, on and off, and continuous control inputs can be implemented with the help of pulse width modulation, which is also employed in this paper. A continuous controller is designed in the outer loop and a control allocator is used to distribute the total control input among redundant actuators, whose effectiveness are assumed to be unknown. The unknown actuator effectiveness is addressed with the help of an adaptive control allocator. A representative model of a reusable launch vehicle equipped with reaction control jets is used to demonstrate the effectiveness of the overall control scheme.

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A frequency domain stability analysis of a phase plane control system

Cited by 22 publications

References 3 publications

Blended Filter-Based Detection for Thruster Valve Failure and Control Recovery Evaluation for RLV

Blended Filter-Based Detection for Thruster Valve Failure and Control Recovery Evaluation for RLV

Quantized Control Allocation of Reaction Control Jets and Aerodynamic Control Surfaces

Controlling a launch vehicle at exoatmospheric flight conditions via adaptive control allocation

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