Determination of loads in the ultralight helicopter blades
The article describes research that was carried out on coaxial a single-seat ultralight helicopter Rotorschmiede VA-115 which is manufactured by German firm RS Helikopter GmbH. The purpose of the work was to determine the blades’ loads necessary for further blade fatigue analysis and ground bench t...
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| Format: | Article |
| Language: | English |
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Vilnius Gediminas Technical University
2023-11-01
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| Series: | Aviation |
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| Online Access: | https://mma.vgtu.lt/index.php/Aviation/article/view/20236 |
| _version_ | 1827631361650851840 |
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| author | Vitaly Dudnik |
| author_facet | Vitaly Dudnik |
| author_sort | Vitaly Dudnik |
| collection | DOAJ |
| description |
The article describes research that was carried out on coaxial a single-seat ultralight helicopter Rotorschmiede VA-115 which is manufactured by German firm RS Helikopter GmbH. The purpose of the work was to determine the blades’ loads necessary for further blade fatigue analysis and ground bench tests. The methodology for the load determination consisted of deformation measurements using strain gauges in various flight modes from hovering to maximum speed flight, including climb, descent, acceleration, and braking. Ultralight helicopters occupy the smallest cost niche and, as a rule, full-fledged fatigue studies are not performed for such helicopters. The requirements for ultralight helicopters are also quite loyal, allowing them to pass such experiments. Analysis of the data shows that the amplitude of bending moments on the lower rotor is higher by 1.2 to 2 times the value on the upper rotor. The absolute maximum value of the bending moment is significantly greater at the minimum weight, although the oscillation amplitude becomes smaller. The presented data can be useful for designers of ultralight and UAV helicopters with teetering hinge rotors.
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| first_indexed | 2024-03-09T14:19:55Z |
| format | Article |
| id | doaj.art-b12702bcf40544efbfc66890faefb037 |
| institution | Directory Open Access Journal |
| issn | 1648-7788 1822-4180 |
| language | English |
| last_indexed | 2024-03-09T14:19:55Z |
| publishDate | 2023-11-01 |
| publisher | Vilnius Gediminas Technical University |
| record_format | Article |
| series | Aviation |
| spelling | doaj.art-b12702bcf40544efbfc66890faefb0372023-11-28T16:22:18ZengVilnius Gediminas Technical UniversityAviation1648-77881822-41802023-11-0127410.3846/aviation.2023.20236Determination of loads in the ultralight helicopter bladesVitaly Dudnik0Faculty of Mechanical Engineering, Silesian University of Technology, Gliwice, Poland; Design Department, RS Helikopter GmbH, Munich, Germany The article describes research that was carried out on coaxial a single-seat ultralight helicopter Rotorschmiede VA-115 which is manufactured by German firm RS Helikopter GmbH. The purpose of the work was to determine the blades’ loads necessary for further blade fatigue analysis and ground bench tests. The methodology for the load determination consisted of deformation measurements using strain gauges in various flight modes from hovering to maximum speed flight, including climb, descent, acceleration, and braking. Ultralight helicopters occupy the smallest cost niche and, as a rule, full-fledged fatigue studies are not performed for such helicopters. The requirements for ultralight helicopters are also quite loyal, allowing them to pass such experiments. Analysis of the data shows that the amplitude of bending moments on the lower rotor is higher by 1.2 to 2 times the value on the upper rotor. The absolute maximum value of the bending moment is significantly greater at the minimum weight, although the oscillation amplitude becomes smaller. The presented data can be useful for designers of ultralight and UAV helicopters with teetering hinge rotors. https://mma.vgtu.lt/index.php/Aviation/article/view/20236ultralight helicoptermain rotorbladeflighttests |
| spellingShingle | Vitaly Dudnik Determination of loads in the ultralight helicopter blades Aviation ultralight helicopter main rotor blade flight tests |
| title | Determination of loads in the ultralight helicopter blades |
| title_full | Determination of loads in the ultralight helicopter blades |
| title_fullStr | Determination of loads in the ultralight helicopter blades |
| title_full_unstemmed | Determination of loads in the ultralight helicopter blades |
| title_short | Determination of loads in the ultralight helicopter blades |
| title_sort | determination of loads in the ultralight helicopter blades |
| topic | ultralight helicopter main rotor blade flight tests |
| url | https://mma.vgtu.lt/index.php/Aviation/article/view/20236 |
| work_keys_str_mv | AT vitalydudnik determinationofloadsintheultralighthelicopterblades |