Development and Implementation of Electromechanical Actuators for the X-38 Atmospheric Test Vehicles

Albright, John; Moore, Landon

doi:10.2514/6.2008-6569

Cited by 12 publications

(8 citation statements)

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“…Rotor faults of EMA motor include rotor shaft eccentricity and rotor demagnetisation [11, 34]. The rotor shaft eccentricity is caused by rotor manufacturing errors, which breaks electromagnetic balance and causes abnormal vibration during operation.…”

Section: Fault Modes Of Emamentioning

confidence: 99%

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

Yin

Chen

et al. 2022

IET Electric Power Appl

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As More/All Electric Aircraft gradually become a research hotspot, electromechanical actuators (EMAs), which can directly convert electrical energy into mechanical energy, have gained more and more attention. However, since the reliability of EMA cannot meet the requirements of actual aircrafts, the practical application of EMA is severely limited. Therefore, fault diagnosis, prognosis and health management (DPHM), which can realise condition‐based maintenance (CBM), has become the key technology in the application of EMA. The aim is to summarise the research on EMA fault modes, fault diagnosis, prognosis and health management systematically and comprehensively. First, the basic structure and common fault modes of EMAs are introduced, and the failure mechanism of EMA is studied. Then, the algorithms of DPHM for EMAs are reviewed in detail. The perception strategies of data acquisition are analysed, and the EMA fault diagnosis methods, including model‐based and data‐driven methods, are reviewed. The research of remaining useful life (RUL) prediction and fault‐tolerant control are introduced. After that, some problems of the existing research on EMA DPHM and their potential solutions are put forward. Finally, several possible developing directions of research on EMA DPHM are predicted.

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Section: Fault Modes Of Emamentioning

confidence: 99%

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

Yin

Chen

et al. 2022

IET Electric Power Appl

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“…The EMAs follow the same path in the different domain. The first development in space applications stimulate the EMA's advance from the 1970s, 23,24 and it is also found their functionality on the Space Shuttle, X-38 Crew Return Vehicle, 25 and unmanned aerial vehicle 26 flight controls. This review places extra emphasis on their electrical actuation solutions for commercial aircrafts and helicopters.…”

Section: Development and Applicationmentioning

confidence: 99%

“…For example, the EMAs were certified on flight test vehicles in a qualification test procedure. 25 The procedure was operated on a spring stand (as well a thermal/vacuum chamber). The testing result indicated that the EMAs were simple to use and had minimal risks to ground operations.…”

Section: Testing System In a Thermal Vacuum Environmentmentioning

confidence: 99%

A review of electromechanical actuators for More/All Electric aircraft systems

Qiao

Liu

Shi

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part C:

169

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Conventional hydraulic actuators in aircraft systems are high maintenance and more vulnerable to high temperatures and pressures. This usually leads to high operating costs and low efficiency. With the rapid development of More/All Electric technology, power-by-wire actuators are being broadly employed to improve the maintainability, reliability, and manoeuvrability of future aircraft. This paper reviews the published application and development of the airborne linear electromechanical actuator. First, the general configuration, merits, and limitations of the gear-drive electromechanical actuator and the direct-drive electromechanical actuator are analysed. Second, the development state of the electromechanical actuator testing systems is elaborated in three aspects, namely the performance testing based on room temperature, testing in a thermal vacuum environment, and iron bird. Common problems and tendencies of the testing systems are summarized. Key technologies and research challenges are revealed in terms of fault-tolerant motor, high-thrust mechanical transmission, multidisciplinary modelling, thermal management, and thermal analysis. Finally, the trend for future electromechanical actuators in More/All Electric Aircraft applications is summarized, and future research on the airborne linear electromechanical actuators is discussed.

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“…In earlier days, linear electro-hydraulic actuators were used especially in the lower stages of the launch vehicles where there is a requirement for large actuation forces. The electromechanical actuator is being the best choice for the optimum design of control actuators [1], [2], [3] in field of aerospace; mainly because of their simplicity, reliability and the reduced need for maintenance in comparison with the hydraulic systems.…”

Section: Introductionmentioning

confidence: 99%

Optimal controller based servo system design for the thrust vector control of liquid propellant engine of three stage launch vehicle

Suchitra

Kurian

Jones

2014

2014 Annual International Conference on Emerging Research Areas: Magnetics, Machines and Drives (AICERA/iCMMD)

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Thrust Vector Control (TVC) ActuationSystem gimbals the rocket nozzle that provides precise steering for the launch vehicle. A small rotation of the gimbal is sufficient for generating a significant amount of force or thrust at the gimbal point. The force generated via TVC actuation system stabilizes and steers the vehicle in the required direction to overcome the wind-gust disturbances and balance the aerodynamic movements. The State space model of the linear actuator is considered for the servo system design. The Linear Quadratic Regulator (LQR) is an optimal method in modern control theory that uses state-space technique to analyze or scrutinize the servo systems. The system can be stabilized, using full state feedback under the assumption that all state variables are measurable and are available for feedback. This technique nearly eliminates the trial and error complexity of conventional compensator based design methodology for the TVC actuation systems. NOMENCLATUREB e Viscous damping coefficient of engine B m Viscous damping of torque motor J e Engine Moment of inertia (MI) J m MI of torque motor Rotating Assembly K cf Current loop feedback gain Kl Actuator mounting structure stiffness Kp Position sensor (LVDT) scalar factor K T Torque sensitivity of motor lm Actuator lever arm length nb Ball screw gear ratio N ch Number of operating channels of torque motor I.

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Development and Implementation of Electromechanical Actuators for the X-38 Atmospheric Test Vehicles

Cited by 12 publications

References 0 publications

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

A review of fault diagnosis, prognosis and health management for aircraft electromechanical actuators

A review of electromechanical actuators for More/All Electric aircraft systems

Optimal controller based servo system design for the thrust vector control of liquid propellant engine of three stage launch vehicle

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