WO2020145922A1 - A torque loading test device - Google Patents

A torque loading test device Download PDF

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Publication number
WO2020145922A1
WO2020145922A1 PCT/TR2019/051094 TR2019051094W WO2020145922A1 WO 2020145922 A1 WO2020145922 A1 WO 2020145922A1 TR 2019051094 W TR2019051094 W TR 2019051094W WO 2020145922 A1 WO2020145922 A1 WO 2020145922A1
Authority
WO
WIPO (PCT)
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.)
Ceased
Application number
PCT/TR2019/051094
Other languages
French (fr)
Inventor
Mete ANAKLI
Caner TÜRKER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Aselsan Elektronik Sanayi ve Ticaret AS
Original Assignee
Aselsan Elektronik Sanayi ve Ticaret AS
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
Application filed by Aselsan Elektronik Sanayi ve Ticaret AS filed Critical Aselsan Elektronik Sanayi ve Ticaret AS
Priority to EP19908782.6A priority Critical patent/EP3908522A4/en
Publication of WO2020145922A1 publication Critical patent/WO2020145922A1/en
Priority to JOJO/P/2021/0182A priority patent/JOP20210182B1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

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; pinion gear (1) which receives rotary motion from the wing drive system, 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.

Description

A TORQUE LOADING TEST DEVICE
Field of the Invention
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.
State of the Art
When the wing shaft is moved by means of the torque loading test device, the variable torque in proportion with the wing angle is loaded on the wing drive system. Therefore the system can be tested under the loads which can be encountered during flight. In the present state of the art, there are structures used for simulating the loads that come to the wing drive system during flight within a test environment.
In the present state of the art, the torque is provided by means of two frictional plates. One plate is stable and the other is mounted to the rotating section. In the prior art since torque is applied equally at each rotation angle, it was not appropriate for wind drive system tests. In addition to this when the wing drive system operates at high speeds and at high torques, it was unable to give response immediately. For this reason, the tests were made by means of performing an active control.
As a result of the researches made, patent application No CA2545705C is found. In said patent application, a system and a method which can make different loadings for the torque tests of the vehicle power transfer organs are disclosed. In this system two helical gears connected to the first shaft are adapted with two helical pinion gears connected to the second shaft. In the system within the present application the gears adapted with the pinion gears are not flat and a plurality of pinion gears is used.
As a result due to above mentioned disadvantages and the insufficiency of the current solutions in terms of the subject, an improvement in the relevant technical field is required. Aim of the Invention
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.
In order to fulfill the abovementioned aims, 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;
• pinion gear which receives rotary motion from the wing drive system,
• spur gear which is in contact with the pinion gear on the lower and upper parts of said pinion gear,
• compression springs which are located on the right and left sides of said spur gears, enables increasing the economic life of said torque loading test device by means of being compressed with preloading.
The structural and characteristic features of the present invention will be understood clearly by the following drawings and the detailed description made with reference to these drawings and therefore the evaluation shall be made by taking these figures and the detailed description into consideration.
Figures Clarifying the Invention
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.
Description of the Part References
A. Torque loading test device 6. Compression spring
1. Pinion gear 7. Mil
2. Spur gear 8. Spring seat
3. Rail 9. Side wall
4. Roller bearing 10. Torque sensor
5. Rear wall 11. Rotary shaft
Detailed Description of the Invention
In this detailed description, the preferred embodiments of the inventive torque loading test device (A) is described only for clarifying the subject matter.
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. In addition to this, it comprises 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). Also it comprises 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. On the right and left sides of the spur gears (2), compression springs (6), shafts (7) which will align the spring by means of passing through said compression springs (6) and spring seats (8) are disposed. Accordingly, the compressions springs (6) are trapped between the spur gear (2) and the side wall (9). While the spur gears (2) move in the opposite direction, they will create spring force by means of compressing the compression springs (6). The linear forces in the opposite direction created by means of the pinion gear (1 ) and the spur gear (2) will create torque force in the same direction on the pinion gear (1). In this manner, it is tested whether the system subject to testing reaches the required angles during required duration under the torque or not.
When the compression springs (6) are mounted to the inventive torque loading test device, equal preloading is given to both sides. This condition is obtained by means of using compression springs (6) which have similar features for right and left directions. In this manner, substantially similar torques are provided for both directions, thus the economic life of the torque loading device is extended by means of providing maximum 25% compression on the compression springs (6). The preloading amount is given in a manner such that at maximum rotation angles, minimum force is on the springs. The spur gears (2) will move in the opposite direction when the pinion gear (1) starts to rotate by means of the preloading process, while two compression springs (6) is compressed more, the other two compression springs (6) are released. Accordingly, 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). In 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. In this manner except the torque force created by the compression springs (6), 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. As can be seen from Figure 2, 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.
Once the system is confirmed and authenticated, it is not required to make control during testing process; also its maintenance costs are reduced since no electronic equipment is required except the sensor and the reader which may be used optionally. 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).

Claims

1. 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 by comprising;
• A pinion gear (1) which receives rotary motion from the wing drive system,
• A spur gear (2) which is in contact with the 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.
2. The torque loading test device (A) according to claim 1 , characterized by comprising; a torque sensor (10) which transfers the rotary motion from the wing drive system to said pinion gear (1).
3. The torque loading test device (A) according to claim 1 , characterized by comprising; a shaft (7) which aligns the compression springs (6) by means of passing said compression springs (6).
4. The torque loading test device (A) according to claim 1 , characterized by comprising; 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).
5. The torque loading test device (A) according to claim 1 , characterized by comprising; a rail (3) which enables the linear motion of the spur gears (2) in a horizontal manner.
6. The torque loading test device (A) according to claim 1 , characterized by comprising; 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.
7. The torque loading test device (A) according to claim 1 , characterized by comprising; a rear wall (5) bearing with the roller bearing (4) in order to allow the pinion gear (1) performing only rotary motion.
PCT/TR2019/051094 2019-01-07 2019-12-17 A torque loading test device Ceased WO2020145922A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19908782.6A EP3908522A4 (en) 2019-01-07 2019-12-17 TORQUE LOAD TESTER
JOJO/P/2021/0182A JOP20210182B1 (en) 2019-01-07 2021-07-07 Torque load testing device

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2019/00150A TR201900150A2 (en) 2019-01-07 2019-01-07 Torque Load Tester
TR2019/00150 2019-01-07

Publications (1)

Publication Number Publication Date
WO2020145922A1 true WO2020145922A1 (en) 2020-07-16

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ID=71520872

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2019/051094 Ceased WO2020145922A1 (en) 2019-01-07 2019-12-17 A torque loading test device

Country Status (4)

Country Link
EP (1) EP3908522A4 (en)
JO (1) JOP20210182B1 (en)
TR (1) TR201900150A2 (en)
WO (1) WO2020145922A1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112082788A (en) * 2020-08-03 2020-12-15 北京自动化控制设备研究所 A thrust vector servo mechanism variable inertia follow-up large load simulation test device
CN112179787A (en) * 2020-09-25 2021-01-05 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
CN113607399A (en) * 2021-08-04 2021-11-05 杭州卓易特科技有限公司 Spring Torque Testing Equipment
CN113716067A (en) * 2021-08-30 2021-11-30 航宇救生装备有限公司 Device and method for testing overwater transverse static stability of rotorcraft with buoys
CN115144177A (en) * 2022-06-30 2022-10-04 中国船舶重工集团公司第七一九研究所 A passive steering gear simulation loading system and method
CN116735197A (en) * 2023-05-24 2023-09-12 中国船舶集团有限公司第七〇四研究所 Passive stabilizer actuating mechanism loading rack with adjustable torque
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
CN118518235A (en) * 2024-07-23 2024-08-20 南京大漠大航空科技有限公司 A torque testing device and a testing method for a rotary-wing unmanned aerial vehicle

Citations (8)

* Cited by examiner, † Cited by third party
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
US20050103556A1 (en) 2003-11-17 2005-05-19 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 Electric Power Steering System Performance Test Platform
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
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
EP3404395A1 (en) 2017-05-19 2018-11-21 Goodrich Actuation Systems SAS Test apparatus for flight actuator check device

Patent Citations (9)

* Cited by examiner, † Cited by third party
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
US20050103556A1 (en) 2003-11-17 2005-05-19 Lufkin Industries, Inc. Method and apparatus for applying dynamic loads to a locked gear train for testing power transmission components
CA2545705C (en) 2003-11-17 2009-03-17 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 Electric Power Steering System Performance Test Platform
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
EP3404395A1 (en) 2017-05-19 2018-11-21 Goodrich Actuation Systems SAS Test 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

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Title
See also references of EP3908522A4

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112082788A (en) * 2020-08-03 2020-12-15 北京自动化控制设备研究所 A thrust vector servo mechanism variable inertia follow-up large load simulation test device
CN112179787A (en) * 2020-09-25 2021-01-05 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
CN113607399A (en) * 2021-08-04 2021-11-05 杭州卓易特科技有限公司 Spring Torque Testing Equipment
CN113716067A (en) * 2021-08-30 2021-11-30 航宇救生装备有限公司 Device and method for testing overwater transverse static stability of rotorcraft with buoys
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
CN115144177A (en) * 2022-06-30 2022-10-04 中国船舶重工集团公司第七一九研究所 A passive steering gear simulation loading system and method
CN116735197A (en) * 2023-05-24 2023-09-12 中国船舶集团有限公司第七〇四研究所 Passive stabilizer actuating mechanism loading rack with adjustable torque
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
CN118518235A (en) * 2024-07-23 2024-08-20 南京大漠大航空科技有限公司 A torque testing device and a testing method for a rotary-wing unmanned aerial vehicle

Also Published As

Publication number Publication date
EP3908522A4 (en) 2022-03-23
TR201900150A2 (en) 2020-07-21
JOP20210182A1 (en) 2023-01-30
JOP20210182B1 (en) 2025-10-01
EP3908522A1 (en) 2021-11-17

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