RU2157977C2 - Method for measurement of free thrust of helicopter main rotor in the hover mode - Google Patents
Method for measurement of free thrust of helicopter main rotor in the hover mode Download PDFInfo
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- RU2157977C2 RU2157977C2 RU98102251A RU98102251A RU2157977C2 RU 2157977 C2 RU2157977 C2 RU 2157977C2 RU 98102251 A RU98102251 A RU 98102251A RU 98102251 A RU98102251 A RU 98102251A RU 2157977 C2 RU2157977 C2 RU 2157977C2
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Abstract
Description
Изобретение относится к вертолетостроению, а именно к методам испытаний вертолетов. The invention relates to helicopter engineering, and in particular to helicopter test methods.
Известны методы определения тяги несущего винта вертолета, описанные в [1] стр.39-41. Согласно первому методу вертолет загружают до весов, несколько меньших или больших, чем ожидаемая тяга несущего винта, и выполняют висения на нескольких высотах при различных режимах работы двигателя. По найденным экспериментальным зависимостям параметра режима двигателя (например, оборотов турбокомпрессора) от высоты висения и массы вертолета определяют тягу несущего винта на взлетном режиме. Этот метод очень трудоемкий, т.к. требует многократной загрузки вертолета балластом, многочисленных зависаний вертолета, точных измерений и трудоемкой обработки. Known methods for determining the thrust of the rotor of a helicopter, described in [1] p. 39-41. According to the first method, the helicopter is loaded to weights somewhat smaller or larger than the expected thrust of the rotor, and hangs at several heights at various engine operating modes. The experimental dependences of the parameter of the engine mode (for example, the speed of the turbocompressor) on the altitude and mass of the helicopter determine the thrust of the rotor in the take-off mode. This method is very laborious because requires multiple loading of the helicopter with ballast, numerous helicopter hangs, accurate measurements and time-consuming processing.
Согласно другому методу, который мы приняли за прототип, вертолет загружают до веса, несколько меньшего, чем предполагаемая тяга несущего винта, и с помощью троса внешней подвески крепят к наземному якорю, выполняют висение и при работе двигателей на взлетном режиме измеряют усилие в тросе-[1]. According to another method, which we took for the prototype, the helicopter is loaded to a weight slightly less than the expected thrust of the rotor, and using an external suspension cable it is attached to the ground anchor, it hangs and when the engines are in take-off mode, the force in the cable is measured [ 1].
Второй метод проще в исполнении, но требует специально оборудованной стоянки с динамометрической привязью. Кроме того, усилия в тросе носят колебательный характер, что снижает точность их измерения. The second method is simpler to execute, but requires a specially equipped parking with a dynamometer leash. In addition, the efforts in the cable are oscillatory in nature, which reduces the accuracy of their measurement.
Задача изобретения - дать простой и удобный в эксплуатации способ измерения свободной тяги несущего винта вертолета, не требующий использования специально оборудованной стоянки. The objective of the invention is to provide a simple and easy to use method of measuring the free thrust of the rotor of a helicopter, which does not require the use of specially equipped parking.
Предполагается загрузить вертолет до веса, несколько меньшего предполагаемой свободной тяги несущего винта вертолета, выполнить вертикальный набор высоты на взлетном режиме работы двигателей, определить среднюю вертикальную скорость, например, с помощью секундомера и радиовысотомера, на высотах, где влиянием близости Земли можно пренебречь (например, на высотах от двух до четырех-пяти радиусов несущего винта), и скорость ветра. Свободная тяга несущего винта вертолета может быть определена по формуле
T = G + K1Vy-K2W,
где G - вес вертолета (кгс);
Vy - средняя вертикальная скорость вертолета (м/с);
W - скорость ветра (м/с).It is supposed to load the helicopter to a weight slightly less than the assumed free thrust of the rotor of the helicopter, perform vertical climb at take-off operation of the engines, determine the average vertical speed, for example, using a stopwatch and radio altimeter, at altitudes where the influence of the Earth's proximity can be neglected (for example, at heights of two to four to five rotor radii), and wind speed. The free thrust of the rotor of the helicopter can be determined by the formula
T = G + K 1 V y -K 2 W,
where G is the weight of the helicopter (kgf);
V y - the average vertical speed of the helicopter (m / s);
W - wind speed (m / s).
Коэффициенты K1 и K2, учитывающие воздушную скорость вертолета, определяются расчетом, например, по импульсной теории несущего винта. Для вертолетов типа Ми-8МТ и их модификаций
На предприятии КНПП "Вертолеты Ми" выполнялись измерения тяги несущего винта вертолетов Ми-8МТ, причем вертикальная скорость вертолета определялась на высотах от 20 до 40 м с помощью секундомера, скорость ветра измерялась анемометром или бралась по данным метеостанции. Измерения повторялись трехкратно и учитывалось изменение полетной массы вертолета вследствие выгорания топлива.The coefficients K 1 and K 2 , taking into account the air speed of the helicopter, are determined by calculation, for example, according to the pulse theory of the rotor. For Mi-8MT helicopters and their modifications
At the KNPP Mi Helicopters enterprise, measurements were taken of the rotor thrust of the Mi-8MT helicopters, the vertical speed of the helicopter being determined at heights of 20 to 40 m using a stopwatch, wind speed was measured with an anemometer or taken according to weather station data. The measurements were repeated three times and took into account the change in the flight mass of the helicopter due to fuel burnout.
Источники информации
1. Акимов А. И. Аэродинамика и летные испытания вертолетов. М.: 1988, стр. 39-41.Sources of information
1. Akimov A. I. Aerodynamics and flight tests of helicopters. M .: 1988, pp. 39-41.
Claims (1)
T = G + K1Vy - K2W,
где G - вес вертолета;
Vy - средняя вертикальная скорость набора высоты вертолета;
W - скорость ветра;
T = G + K 1 V y - K 2 W,
where G is the weight of the helicopter;
V y - the average vertical speed of climb of a helicopter;
W is the wind speed;
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU98102251A RU2157977C2 (en) | 1998-02-12 | 1998-02-12 | Method for measurement of free thrust of helicopter main rotor in the hover mode |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU98102251A RU2157977C2 (en) | 1998-02-12 | 1998-02-12 | Method for measurement of free thrust of helicopter main rotor in the hover mode |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU98102251A RU98102251A (en) | 1999-11-27 |
| RU2157977C2 true RU2157977C2 (en) | 2000-10-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU98102251A RU2157977C2 (en) | 1998-02-12 | 1998-02-12 | Method for measurement of free thrust of helicopter main rotor in the hover mode |
Country Status (1)
| Country | Link |
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| RU (1) | RU2157977C2 (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4736331A (en) * | 1982-05-26 | 1988-04-05 | United Technologies Corporation | Helicopter power available to hover indicator |
| EP0477948A2 (en) * | 1990-09-27 | 1992-04-01 | Kaman Aerospace Corporation | Real time load monitoring system with remote sensing |
| EP0502811A2 (en) * | 1991-03-06 | 1992-09-09 | United Technologies Corporation | Helicopter weight measurement |
| RU2035029C1 (en) * | 1990-05-15 | 1995-05-10 | Чичикайло Владимир Васильевич | Installation for measuring forces and momentum in testing propellers |
-
1998
- 1998-02-12 RU RU98102251A patent/RU2157977C2/en not_active IP Right Cessation
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4736331A (en) * | 1982-05-26 | 1988-04-05 | United Technologies Corporation | Helicopter power available to hover indicator |
| RU2035029C1 (en) * | 1990-05-15 | 1995-05-10 | Чичикайло Владимир Васильевич | Installation for measuring forces and momentum in testing propellers |
| EP0477948A2 (en) * | 1990-09-27 | 1992-04-01 | Kaman Aerospace Corporation | Real time load monitoring system with remote sensing |
| EP0502811A2 (en) * | 1991-03-06 | 1992-09-09 | United Technologies Corporation | Helicopter weight measurement |
Non-Patent Citations (1)
| Title |
|---|
| Акимов А.И. и др. Летные испытания вертолетов. - М.: Машиностроение, 1980, с. 58 и 59. Акимов А.И. Аэродинамика и летные характеристики вертолетов. - М.: Машиностроение, 1968, с. 39 - 45. * |
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| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20070213 |