EP3908522A1 - A torque loading test device - Google Patents
A torque loading test deviceInfo
- Publication number
- EP3908522A1 EP3908522A1 EP19908782.6A EP19908782A EP3908522A1 EP 3908522 A1 EP3908522 A1 EP 3908522A1 EP 19908782 A EP19908782 A EP 19908782A EP 3908522 A1 EP3908522 A1 EP 3908522A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- test device
- loading test
- torque loading
- pinion gear
- torque
- Prior art date
- Legal status (The legal status 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 status listed.)
- Withdrawn
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000011068 loading method Methods 0.000 title claims abstract description 34
- 230000006835 compression Effects 0.000 claims abstract description 26
- 238000007906 compression Methods 0.000 claims abstract description 26
- 238000004088 simulation Methods 0.000 claims abstract description 5
- 238000012546 transfer Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 3
- 241000699655 Akodon torques Species 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 210000000056 organ Anatomy 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
Definitions
- the invention is related to a torque loading test device which enables simulation of the loads that come to the vehicles with wing drive system during flight within a test environment.
- patent application No CA2545705C is found.
- a system and a method which can make different loadings for the torque tests of the vehicle power transfer organs are disclosed.
- two helical gears connected to the first shaft are adapted with two helical pinion gears connected to the second shaft.
- the gears adapted with the pinion gears are not flat and a plurality of pinion gears is used.
- the invention aims to solve the abovementioned disadvantages by means of being inspired form the current conditions.
- the main aim of the invention is to simulate the loads that come to the vehicles with wing drive system during flight within a test environment by the torque loading test device.
- Another aim of the invention is to enable torque application to the wing drive system with a determined angle, rotatable at right and left directions.
- Another aim of the invention is to enable immediate response in case the wing drive system operates at high speeds and high torques by means of applying load to the wing drive shaft in a passive manner. Therefore the tests can be performed without making any active control.
- the invention is a torque loading test device which enables simulation of the loads that come to the vehicles with wing drive system during flight within a test environment, characterized by comprising the following;
- Figure 1 is a front perspective view of the torque loading test device.
- Figure 2 is a view for multi-wing tests of the torque loading test device.
- the invention is a torque loading test device (A) which enables simulation of the loads that come to the vehicles with wing drive system during flight within a test environment, characterized in comprising the following; a pinion gear (1) which receives rotary motion from the wing drive system, a spur gear (2) which is in contact with pinion gear (1) on the lower and upper parts of said pinion gear (1), compression springs (6) which are located on right and left sides of said spur gears (2), enables increasing the economic life of said torque loading test device (A) by means of being compressed with preloading.
- a torque sensor (10) which transfers the rotary motion from the wing drive system to the pinion gear (1 ) and a shaft (7) which aligns the compression springs (6) by means of passing said compression springs (6).
- a spring seat (8) which enables connection of the compression springs (6) with the shaft (7) at right and left sides of the spur gears (2) and a rail (3) which enables their linear motion in a horizontal manner.
- the inventive torque loading test device (A) comprises a roller bearing (4) which makes rotary motion by means of bearing with the pinion gear (1) and enables the linear motion of the spur gears (2) in the opposite direction and a rear wall (5) bearing with the roller bearing (4) in order to allow the pinion gear (1) performing only rotary motion.
- the torque force is created by means of the inventive torque loading test device in a manner such that, the horizontal force created by means of the compression springs (6) is transformed into the torque force by means of using the pinion gear (1 ) and the spur gear (2).
- the operating principle of the inventive torque loading test device (A) as shown with a perspective view in Figure 1 is as the following.
- the rotary motion which is transferred from the wing drive system to the torque loading test device (A) passes through the torque sensor (10), and is transferred to the pinion gear (1).
- the pinion gear (1) is located between two horizontal spur gears (2).
- the spur gears (2) are bearing on the rail (3) in an overlapping manner only for moving in a linear manner.
- Pinion gear (1) is bearing with the roller bearing (4) to the rear wall (4) only for performing rotary motion.
- the pinion gear (1) will try to rotate on the spur gears (2) by means of the rotary motion coming from the wing drive.
- Pinion gear (1) is bearing with the roller bearing (4) so that it will only perform rotary motion and the spur gears (2) will move linearly in an opposite direction to each other.
- the released compression springs will never be left without load and they will not create uncertainty and emptiness in the system. Also preloading will enable the rotary shaft (11) to be at the center when there is no motion on the torque loading test device (A).
- the aim of disposing four compression springs (6) on the lower portion and the upper portion of the rotation axis and in a mutual manner is to prevent creating forces which will compel linear motion except the rotation on the pinion gear (1) by means of creating linear forces that occurred during rotation movement in the opposite direction.
- the test system and the wing drive system will not be subjected to the other linear loads and thus a torque with high accuracy and certainty will be provided.
- all of the wings can be tested simultaneously by means of adding thereof into the main system from the torque loading test device (A) in proportion with the number of wing drive system to be tested.
- the torque loading device will have a long economic life because the system substantially consists of mechanical parts and different forces to be created at high torques will be reduced by means of the configuration of the compression springs (6).
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
TR2019/00150A TR201900150A2 (en) | 2019-01-07 | 2019-01-07 | Torque Load Tester |
PCT/TR2019/051094 WO2020145922A1 (en) | 2019-01-07 | 2019-12-17 | A torque loading test device |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3908522A1 true EP3908522A1 (en) | 2021-11-17 |
EP3908522A4 EP3908522A4 (en) | 2022-03-23 |
Family
ID=71520872
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19908782.6A Withdrawn EP3908522A4 (en) | 2019-01-07 | 2019-12-17 | A torque loading test device |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP3908522A4 (en) |
JO (1) | JOP20210182A1 (en) |
TR (1) | TR201900150A2 (en) |
WO (1) | WO2020145922A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112082788B (en) * | 2020-08-03 | 2023-01-10 | 北京自动化控制设备研究所 | Variable inertia follow-up large-load simulation test device of thrust vector servo mechanism |
CN112179787B (en) * | 2020-09-25 | 2022-09-30 | 中国直升机设计研究所 | Torsion test device for main paddle central part and support arm limited lock |
CN112706942A (en) * | 2020-11-11 | 2021-04-27 | 北京共创晶桔科技服务有限公司 | Unmanned aerial vehicle aging testing platform |
CN113716067B (en) * | 2021-08-30 | 2023-05-12 | 航宇救生装备有限公司 | Device and method for testing horizontal static stability of rotor craft with pontoon on water |
CN117302540A (en) * | 2023-09-14 | 2023-12-29 | 成都飞机工业(集团)有限责任公司 | Device and method for testing actuator of folding bolt of airplane wing |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3312105A (en) * | 1964-08-18 | 1967-04-04 | Chicago Pneumatic Tool Co | Fixed speed torque testing apparatus for rotary air tools |
US6827310B1 (en) * | 2003-09-22 | 2004-12-07 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus and method for fin actuation in a portable missile |
US6988420B2 (en) * | 2003-11-17 | 2006-01-24 | Lufkin Industries, Inc. | Method and apparatus for applying dynamic loads to a locked gear train for testing power transmission components |
CN201594043U (en) | 2009-12-25 | 2010-09-29 | 西安理工大学 | Performance testing platform of electric power steering system |
CN204008117U (en) * | 2014-08-22 | 2014-12-10 | 苏州昌飞自动化设备厂 | The torsion testing mechanism of suspension composite test device |
CN205665001U (en) * | 2016-04-14 | 2016-10-26 | 四川大学 | Freewheel clutch life -span testing arrangement |
EP3404395B1 (en) * | 2017-05-19 | 2020-01-29 | Goodrich Actuation Systems SAS | Test method and apparatus for flight actuator check device |
CN108051208A (en) * | 2017-12-28 | 2018-05-18 | 上海建桥学院 | Rack-and-pinion loads the rolling bearing fatigue life pilot system of radially alternating load |
-
2019
- 2019-01-07 TR TR2019/00150A patent/TR201900150A2/en unknown
- 2019-12-17 EP EP19908782.6A patent/EP3908522A4/en not_active Withdrawn
- 2019-12-17 WO PCT/TR2019/051094 patent/WO2020145922A1/en unknown
- 2019-12-17 JO JOP/2021/0182A patent/JOP20210182A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
WO2020145922A1 (en) | 2020-07-16 |
TR201900150A2 (en) | 2020-07-21 |
JOP20210182A1 (en) | 2023-01-30 |
EP3908522A4 (en) | 2022-03-23 |
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Legal Events
Date | Code | Title | Description |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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STAA | Information on the status of an ep patent application or granted ep patent |
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17P | Request for examination filed |
Effective date: 20210806 |
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AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
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A4 | Supplementary search report drawn up and despatched |
Effective date: 20220218 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: B64C 13/28 20060101ALI20220215BHEP Ipc: G01M 13/025 20190101ALI20220215BHEP Ipc: B64F 5/60 20170101AFI20220215BHEP |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230517 |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
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17Q | First examination report despatched |
Effective date: 20230804 |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20231215 |