Simulation of Runway Irregularities in a Novel Test Rig for Fully Electrical Landing Gear Systems

Martin, Andrea De; Jacazio, Giovanni; Sorli, Massimo

doi:10.3390/aerospace9020114

Cited by 5 publications

(7 citation statements)

References 14 publications

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“…The main purposes of the proposed iron-bird are to support the testing and certification of a novel E-Brake system and to foster the definition of dedicated prognostic logic. The iron bird is organized as depicted in in Figure 1 [9]. The mechanical structure can be divided between a fixed part and a moving platform integral with the landing gear leg, complete with a wheel and electrical brake.…”

Section: Design Requirements and Test-rig Architecturementioning

confidence: 99%

“…To this end, the E-LISA iron bird is able to reproduce fully comprehensive test scenarios and conditions, following the workflow described in [8]. The E-LISA iron bird, firstly presented in [9], aims at providing a significant advancement on the current state-of-the-art by defining a new test-rig able to cover different tests procedures without resorting to different test-benches and acts as a technological demonstrator for new prognostic functionalities for the electrical brake system. The paper is organized as follows.…”

Section: Introductionmentioning

confidence: 99%

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Sizing and control system definition of an intelligent facility for qualification tests and prognostic research activities for electrical landing gear systems

Bertolino

2023

Theoretical and Applied Mechanics - AIMETA 2022

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Abstract. The evolution towards “more electric” aircrafts has seen a decisive push in the last decade affecting both the propulsion components and the aircraft systems. An interesting and fast-developing application field of electro-mechanical actuators is that of the aeronautical brakes. The E-LISA research project under way within the Clean Sky 2 framework has the objective of developing an innovative iron bird dedicated to executing tests on the landing gear of a small aircraft transport equipped with electro-mechanical landing gear and electrical brake. The paper details the process required to the definition of such iron bird, with a particular focus on the control system.

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Section: Design Requirements and Test-rig Architecturementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Sizing and control system definition of an intelligent facility for qualification tests and prognostic research activities for electrical landing gear systems

Bertolino

2023

Theoretical and Applied Mechanics - AIMETA 2022

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“…To replicate the Landing Gear system behavior, we resort to the high-fidelity model provided in (De Martin et al 2022), capable of representing the entire landing procedure under the assumption of symmetric touch-down, thus with null roll angle and equal weight repartition between the two main landing gear legs. In such model the aircraft is represented as a rigid body subjected to the aerodynamic components of Lift due to the aircraft wing (L), anterior wing (Lfw), tail wing (Lt), and Drag (D).…”

Section: Simulation Modelmentioning

confidence: 99%

“…The E-LISA iron bird consists of a multi-functional intelligent test facility integrating hardware and software, allowing all the tests and analyses perceived as fundamental to be performed to demonstrate the maturity of an electro-mechanical landing gear, hence paving the way for its implementation in a small passenger aircraft and will include prognostics and health management (PHM) functionalities for the electrical brake system. Such tests include the simulation of complete landing procedures under different operating conditions such as runway friction (wet/dry), presence of waving and irregularities along the runway, variable aircraft weight, and approach speed as detailed in (De Martin et al 2022). This paper deals with the preliminary analysis needed to develop a comprehensive PHM system for the E-Brake, focusing on the feature selection, fault detection and prognosis of wear in the brake pads without the addition of dedicated sensors considering the case study of a real E-Brake system, currently under development.…”

Section: Introductionmentioning

confidence: 99%

Prognosis of Wear Progression in Electrical Brakes for Aeronautical Applications

Martin

Jacazio²,

Parisi³

et al. 2022

PHME_CONF

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The evolution towards “more electric” aircrafts has seen a decisive push in the last decade, due to the growing environmental concerns and the development of new market segments (flying taxis). Such push interested both the propulsion components and the aircraft systems, with the latter seeing a progressive trend in replacing the traditional solutions based on hydraulic power with electrical or electromechanical devices. Although more attention is usually devised towards the flight control actuation, an interesting and fast-developing application field for electro-mechanical systems is that of the aeronautical brakes. Electro-mechanical brakes, or E-Brakes hereby onwards, would present several advantages over their hydraulic counterparts, mainly related to the avoidance of leakage issues and the simplification of the system architecture. The more difficult heat dissipation, associated with the thermal issues that usually constitute one of the most significant sizing constraints for electromechanical actuators, limits so far, their application (or proposal of application) to light-weight vehicles. Within this context, the development of PHM solutions would align with the need for an on-line monitoring of a relatively unproven component. This paper deals with the preliminary stages of the development of such PHM system for an E-Brake to be employed on a future executive class aircraft, where the brake is actuated through four electro-mechanical actuators. Since literature on fault diagnosis and prognosis for electrical motors is fairly extensive, we focused this preliminary analysis on the development of PHM techniques suitable to monitor and prognose the evolution of the brake pads wear instead. The paper opens detailing the system architecture and continues presenting the high-fidelity dynamic model used to build synthetic data-sets representative of the possible operating conditions faced by the E-Brake within realistic operative scenarios. Such data are then used to foster a preliminary feature selection process, where physics-based indexes are compared and evaluated. Simulated degradation histories are then used to test the application of data-driven fault detection algorithm and the possible application of particle-filtering routines for prognosis.

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“…In 2001, Shi Haiwen conducted the landing gear rotating drop test for different imitation runways [14]. In 2022, De Martin developed an innovative "iron bird" for executing tests including the simulation of complete landing procedures on an innovative landing gear of a small aircraft [15]. Giannella, V. validated the design of this test machine by structural analyses [16].…”

Section: Introductionmentioning

confidence: 99%

Landing Performance Study for Four Wheels Twin Tandem Landing Gear Based on Drop Test

2022

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The drop tests of a twin tandem landing gear with different filling parameters are carried out in two different landing attitudes (level and tail-down). The overload coefficient and power absorption efficiency are obtained. Curves of dynamic oscillation and pressure change for the pitch damper are obtained. The results show that twin tandem landing gear has a good ability to absorb the work of landing impact. Under landing weight, the vertical overload coefficients during level landing and tail-down landing are 1.14 and 1.07, respectively, when the corresponding efficiencies of its buffer system are 80.9% and 83.3%. During tail-down landing, the work absorbed by the pitch damper accounts for only 14.9% of the maximum pitching kinetic energy of the trolley. When the orifice diameter of the pitch damper keeps the same, its peak axial load does not change significantly with the change of its initial pressure. When the initial pressure of the pitch damper keeps the same, the decrease of its orifice diameter is beneficial to the vibration attenuation of the trolley. The smaller recoil channel may lead to a significant increase in the peak pressure of the pitch damper, which should be a consideration in its design.

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Simulation of Runway Irregularities in a Novel Test Rig for Fully Electrical Landing Gear Systems

Cited by 5 publications

References 14 publications

Sizing and control system definition of an intelligent facility for qualification tests and prognostic research activities for electrical landing gear systems

Sizing and control system definition of an intelligent facility for qualification tests and prognostic research activities for electrical landing gear systems

Prognosis of Wear Progression in Electrical Brakes for Aeronautical Applications

Landing Performance Study for Four Wheels Twin Tandem Landing Gear Based on Drop Test

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