Flight test of the flight control system

Gao, Yakui; An, Gang; Chen, Zhi

doi:10.1016/b978-0-12-822990-3.00008-5

Test Techniques for Flight Control Systems of Large Transport Aircraft 2021

DOI: 10.1016/b978-0-12-822990-3.00008-5

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Flight test of the flight control system

Yakui Gao¹,

Gang An²,

Zhi Chen³

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2024

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Cited by 3 publications

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“…The flight controller of UAV generally consists of main control module, signal receiving and complex flight control system. It has port modules such as autonomous navigation, operation and storage [1], communication module and driving module of several actuators. Although the core function of the controller is powerful, it has large volume, high power consumption and high price.…”

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confidence: 99%

Design of UAV Flight Control System

2022

IJFET

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In order to improve the control performance of UAV. For a small UAV, the hardware design scheme of UAV flight control computer with STM32 as the processing core is proposed and implemented. The overall scheme design, specific hardware selection and interface design of the system are given in detail. STM32, as the main controller, expands the parallel A/D, D/A, asynchronous serial communication interface and memory around, enriches the system hardware interface resources, and selects the peripheral expansion circuit with complex programmable logic controller (CPID) to realize interrupt control. This flight control computer has the characteristics of small volume and strong autonomous navigation ability.

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confidence: 99%

Design of UAV Flight Control System

2022

IJFET

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Economic feasibility of modifications to the design of transport aircraft

2021

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The relevance of the subject matter is conditioned by the need to fully justify the implementation of modifications to the structures of transport aircraft from an economic standpoint, in order to save money during their construction and improve the functioning of the system for planning further design developments in this line. The purpose of this study is to establish a coherent model of the economic feasibility of aircraft modifications, which allows effectively solving the issues of cost savings in their design and subsequent launch into mass production and operation. The leading approach in this study is a combination of analytical research of the issues of transport aircraft modification with empirical research of the economic feasibility of such measures, in the context of creating a coherent concept of the need for a set of measures to improve the structure of air transport. The findings indicate the presence of a clear relationship between a wide range of parameters that determine the indicators of economic feasibility of modernizing transport aircraft, as well as significant economic advantages of a high-quality modification of the aircraft design.

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Vibration Qualification Campaign on Main Landing Gear System for High-Speed Compound Helicopter

Chiariello,

Carandente Tartaglia,

Arena

et al. 2024

Aerospace

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Vibrations in helicopters have strong implications for their performance and safety, leading to the increased fatigue of components and reduced operational efficiency. As helicopters are designed to land on several types of surfaces, the landing gear system dissipates the impact on the ground and maintains stability during landing and take-off. These vibrations can arise from a variety of sources, such as aerodynamic loads, mechanical imbalances, and engine instabilities. In the present work, the authors describe the vibration qualification process of the main landing gear tailored to fast helicopters within the Clean Sky 2 Racer program. The method entails devising preliminary load sets that deform the structure in its key excited mode shapes to assess stresses and address the experimental campaign. A full-scale prototype model is then tested for sine sweep and random vibrations as per the Airbus Helicopter requirements in order to reach the final qualification and acceptance stage. Although the discussion centers on a landing gear structure, the described process could be extended to other critical equipment as well.

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Flight test of the flight control system

Cited by 3 publications

References 0 publications

Design of UAV Flight Control System

Design of UAV Flight Control System

Economic feasibility of modifications to the design of transport aircraft

Vibration Qualification Campaign on Main Landing Gear System for High-Speed Compound Helicopter

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