RU2001117407A - Device for mounting an aircraft with an engine in a wind tunnel - Google Patents

Device for mounting an aircraft with an engine in a wind tunnel

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Publication number
RU2001117407A
RU2001117407A RU2001117407/28A RU2001117407A RU2001117407A RU 2001117407 A RU2001117407 A RU 2001117407A RU 2001117407/28 A RU2001117407/28 A RU 2001117407/28A RU 2001117407 A RU2001117407 A RU 2001117407A RU 2001117407 A RU2001117407 A RU 2001117407A
Authority
RU
Russia
Prior art keywords
aforementioned
supports
longitudinal axis
respect
length
Prior art date
Application number
RU2001117407/28A
Other languages
Russian (ru)
Other versions
RU2271527C2 (en
Inventor
Жан-Поль ДЕМЭ
Лоран КАРТОН
Original Assignee
Аэроспасьяль Матра Миссиль
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from FR0007927A external-priority patent/FR2810734B1/en
Application filed by Аэроспасьяль Матра Миссиль filed Critical Аэроспасьяль Матра Миссиль
Publication of RU2001117407A publication Critical patent/RU2001117407A/en
Application granted granted Critical
Publication of RU2271527C2 publication Critical patent/RU2271527C2/en

Links

Claims (10)

1. Устройство (12), предназначенное для крепления летательного аппарата (10) с двигателем в аэродинамической трубе при изучении поведения вышеупомянутого аппарата (10) с работающим двигателем при различных положениях, причем, вышеупомянутое устройство содержит несколько шарнирных опор (14, 16), предназначенных для соединения аппарата (10) с неподвижной конструкцией (15) аэродинамической трубы, со смещенным расположением по отношению к зонам обтекания воздухом, расположенным вокруг передней части аппарата, а также перед двигателем и позади его, и, по меньшей мере, одна из вышеупомянутых опор содержит средства (28) регулировки длины, отличающееся тем, что средства (28) регулировки длины соединены со средствами (42) дистанционного управления, предназначенными для изменения положения аппарата в текущий момент.1. A device (12) designed to mount an aircraft (10) with an engine in a wind tunnel when studying the behavior of the aforementioned device (10) with the engine running at various positions, the aforementioned device containing several hinged supports (14, 16) designed for connecting the apparatus (10) with the fixed structure (15) of the wind tunnel, with a displaced arrangement with respect to the air flow around the front of the apparatus, as well as in front of and behind the engine, and, at least one of the aforementioned supports comprises length adjusting means (28), characterized in that the length adjusting means (28) are connected to remote control means (42) for changing the position of the apparatus at the current moment. 2. Устройство по п.1, отличающееся тем, что опоры состоят из передней опоры (14) неизменной длины, содержащей шарнирные устройства (20) с по меньшей мере, двумя степенями свободы, допускающие поворот вокруг двух осей (В, С), ориентированных по двум взаимно перпендикулярным направлениям и перпендикулярных продольной оси (А) аппарата, и двух задних опор (16), включающих каждая средства (28) регулировки длины и соединения (30, 32), установленные с возможностью поворота.2. The device according to claim 1, characterized in that the supports consist of a front support (14) of constant length containing articulated devices (20) with at least two degrees of freedom, allowing rotation around two axes (B, C) oriented in two mutually perpendicular directions and perpendicular to the longitudinal axis (A) of the apparatus, and two rear supports (16), including each means (28) for adjusting the length and connection (30, 32), mounted for rotation. 3. Устройство по п.2, отличающееся тем, что передняя опора (14) ориентирована строго радиально по отношению к продольной оси аппарата (10) и расположена в вертикальной плоскости (Р2), проходящей через вышеупомянутую продольную ось (А), а задние опоры (16) ориентированы радиально по отношению к вышеупомянутой продольной оси (А) аппарата и расположены симметрично по отношению к вышеупомянутой вертикальной плоскости (Р2), когда обе задние опоры (16) находятся в исходном положении.3. The device according to claim 2, characterized in that the front support (14) is oriented strictly radially with respect to the longitudinal axis of the apparatus (10) and is located in a vertical plane (P2) passing through the aforementioned longitudinal axis (A), and the rear supports (16) are oriented radially with respect to the aforementioned longitudinal axis (A) of the apparatus and are located symmetrically with respect to the aforementioned vertical plane (P2) when both rear supports (16) are in the initial position. 4. Устройство по п.3, отличающееся тем, что в его исходном положении обе задние опоры (16) образуют с вышеупомянутой вертикальной плоскостью (Р2) такой угол, чтобы крепление аппарата (10) посредством устройства (12) был бы изостатическим.4. The device according to claim 3, characterized in that in its initial position both rear supports (16) form such an angle with the aforementioned vertical plane (P2) that the fastening of the device (10) by means of the device (12) would be isostatic. 5. Устройство по п.4, отличающееся тем, что вышеупомянутой угол практически равен 45°.5. The device according to claim 4, characterized in that the aforementioned angle is practically equal to 45 °. 6. Устройство по любому из пп.3-5, отличающееся тем, что задние опоры (16) смещены назад вдоль вышеупомянутой продольной оси (А) аппарата (10) примерно на один метр по отношению к передней опоре (14).6. A device according to any one of claims 3 to 5, characterized in that the rear supports (16) are offset back along the aforementioned longitudinal axis (A) of the apparatus (10) by about one meter with respect to the front support (14). 7. Устройство по любому из пп.2-6, отличающееся тем, что средствами регулирования длины являются гидравлические домкраты (28), приводимые в действие по длине.7. The device according to any one of claims 2 to 6, characterized in that the means for adjusting the length are hydraulic jacks (28), driven in length. 8. Устройство по любому из пп.2-7, отличающееся тем, что каждая из вышеупомянутых опор(14, 16) расположена внутри кожуха (44, 46) обтекаемой формы.8. A device according to any one of claims 2 to 7, characterized in that each of the aforementioned supports (14, 16) is located inside a streamlined casing (44, 46). 9. Устройство по любому из пп.2-8, отличающееся тем, что первые средства охлаждения предусмотрены для охлаждения соединений (32) и имеют возможность поворота, расположенных в непосредственной близости от аппарата.9. A device according to any one of claims 2 to 8, characterized in that the first cooling means are provided for cooling the compounds (32) and have the ability to rotate located in the immediate vicinity of the apparatus. 10. Устройство по любому из пп.2-9, отличающееся тем, что средства (56, 58) для угловых измерений соединены с шарнирными поворотными устройствами (20), причем, предусмотрены вторые устройства охлаждения для охлаждения средств (58) для угловых измерений, расположенных в непосредственной близости от аппарата.10. A device according to any one of claims 2 to 9, characterized in that the means (56, 58) for angular measurements are connected to articulated rotary devices (20), moreover, second cooling devices are provided for cooling the means (58) for angular measurements, located in close proximity to the device.
RU2001117407/11A 2000-06-21 2001-06-20 Device for holding aircraft with engine in aerodynamic tube RU2271527C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0007927 2000-06-21
FR0007927A FR2810734B1 (en) 2000-06-21 2000-06-21 DEVICE FOR SUPPORTING A MOTOR FLYING MACHINE IN A BLOWER

Publications (2)

Publication Number Publication Date
RU2001117407A true RU2001117407A (en) 2003-06-27
RU2271527C2 RU2271527C2 (en) 2006-03-10

Family

ID=8851496

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001117407/11A RU2271527C2 (en) 2000-06-21 2001-06-20 Device for holding aircraft with engine in aerodynamic tube

Country Status (9)

Country Link
US (1) US6571618B2 (en)
EP (1) EP1167941B1 (en)
JP (1) JP2002089368A (en)
AT (1) ATE428107T1 (en)
CA (1) CA2350150C (en)
DE (1) DE60138244D1 (en)
ES (1) ES2326618T3 (en)
FR (1) FR2810734B1 (en)
RU (1) RU2271527C2 (en)

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DE102007062736B3 (en) * 2007-12-27 2009-10-08 Airbus Deutschland Gmbh Device for the pivotable attachment of an active surface, in particular a spoiler on a wind tunnel model of an aircraft
JP5611120B2 (en) * 2011-05-23 2014-10-22 三菱航空機株式会社 Lightning strike test apparatus, lightning strike test system, and lightning strike test method
CN108645591B (en) * 2018-06-27 2024-02-20 中国空气动力研究与发展中心高速空气动力研究所 V-shaped tail supporting device for flat fusion aircraft in transonic wind tunnel
CN111220342B (en) * 2020-03-18 2024-04-05 中国空气动力研究与发展中心高速空气动力研究所 High-speed wind tunnel embedded test model throwing mechanism
CN112161528B (en) * 2020-09-07 2023-01-13 蓝箭航天空间科技股份有限公司 Posture adjusting device for rocket assembly
CN114509234B (en) * 2022-04-20 2022-07-05 中国空气动力研究与发展中心超高速空气动力研究所 Flexible pipeline device for mixed heating gas jet flow gas supply of hypersonic wind tunnel
CN115127771B (en) * 2022-07-22 2024-03-29 中国空气动力研究与发展中心高速空气动力研究所 Transverse asymmetric weak disturbance wave detection and disturbance source positioning method for high-speed wind tunnel
CN115585978B (en) * 2022-12-09 2023-03-14 中国航空工业集团公司沈阳空气动力研究所 Test device for two-degree-of-freedom motion of transonic wind tunnel
CN118010292B (en) * 2024-04-09 2024-06-18 中国空气动力研究与发展中心高速空气动力研究所 Sub-transonic progressive direct connection wind tunnel test model supporting device and design method

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