Author: Jarosław Stanisławski
Title: Numerical analysis of the dynamic properties of a helicopter
ISBN: 978-83-63539-58-0
Cover: paperback, glued binding
The year of publication: 2020
Publisher: Lukasiewicz Research Network – Institute of Aviation Publishing Houses
Quantity pages: 125
Language of publication: polish
Description: Ensuring a high level of safety in the use of helicopters is one of the main tasks assigned to designers at the design phase, as well as to the flying crews and ground service during the operation of rotorcraft. Meeting the requirements specified in the helicopter construction regulations is a prerequisite for obtaining a certificate of airworthiness of the structure. Despite the fulfillment of numerous conditions defined in the construction regulations, it is not possible to completely eliminate occurring of accidents. Research on the causes of helicopter accidents has shown that in the vast majority of events, their occurrence can be associated with human errors. Technical faults were the cause of fewer accidents. For many years, the Institute of Aviation has been conducting research related to the development and testing of rotorcraft in terms of construction safety. Computer simulation allows to detect unfavorable features of the structure at an early stage of the designing process, and then correct the relevant parameters. The ability to determine the rotor characteristics is the basis for further analysis of the helicopter’s properties: checking the strength of the structure, estimating the performance, predicting the vibration level, flight simulation. The work presents methods of simulation calculations concerning the issues of helicopter flight mechanics, as well as loads and deformations of the main rotors. The focus was put on several problems of a narrower scope related to the safe usage of helicopters: recognition of damage to rotor blades, determination of H-V zones, carrying out obstacle avoidance maneuvers, the impact of new solutions on loads and performance, and the operation of helicopter structure elements in selected flight states.
