CN112319848A - Aircraft accelerator lever testing arrangement - Google Patents
Aircraft accelerator lever testing arrangement Download PDFInfo
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- CN112319848A CN112319848A CN202011335176.4A CN202011335176A CN112319848A CN 112319848 A CN112319848 A CN 112319848A CN 202011335176 A CN202011335176 A CN 202011335176A CN 112319848 A CN112319848 A CN 112319848A
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- 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
Abstract
The invention relates to the technical field of detection of airplane components, in particular to a testing device for an aircraft throttle lever. The invention relates to an aircraft throttle lever testing device, which comprises: the testing mechanism is arranged on the testing platform and comprises a driving assembly and a clamping assembly connected with the driving assembly, the driving assembly is suitable for driving the clamping assembly to rotate, and the rotating axis of the clamping assembly is coaxial with the rotating shaft of the throttle lever; and the clamping assembly is provided with a force measuring unit, and the force measuring unit is suitable for measuring the loading force of the throttle lever when the clamping assembly rotates. According to the aircraft accelerator rod testing device, the stress direction of the clamping assembly on the accelerator rod is the tangential direction of the arc-shaped track, the stress direction is consistent with the force application direction of hands on the accelerator rod when the hands operate the accelerator rod, the operation condition of the accelerator table in actual use is accurately judged, and index tests such as the service life and reliability of the accelerator table to be put into use are completed.
Description
Technical Field
The invention relates to the technical field of detection of airplane components, in particular to a testing device for an aircraft throttle lever.
Background
In the manned aircraft attitude control system, the accelerator platform not only provides basic commands for the attitude control system, but also feeds back the motion state of the aircraft to a driver through reaction force. As one of the key components of the flight control system, the design and manufacturing quality of the flight control system are directly related to the accuracy and timeliness of the power output of an engine, and the service life, reliability and other indexes of an accelerator table to be put into use need to be tested.
During testing, in order to truly simulate the actual use condition of the throttle platform, the loading force applied to a single throttle lever and the loading forces applied to a plurality of throttle levers need to be tested, and the running condition of the throttle platform is judged according to the measured loading forces.
In order to solve the above technical problems, chinese patent document CN102175444B discloses a multi-throttle lever loading measuring device, which is a parallel four-bar linkage structure and includes a servo motor, an active rocker arm, a rear horizontal push rod, a throttle lever selecting device, a pull pressure sensor, a front horizontal push rod, a throttle lever extending device, and the rear horizontal push rod, the throttle lever selecting device, the pull pressure sensor, and the front horizontal push rod are connected coaxially.
As shown in fig. 1, the rear end horizontal push rod, the throttle lever selecting device, the pull pressure sensor, and the front horizontal push rod are connected and then coaxial, and the throttle lever receives a horizontal pulling force, i.e., a direction indicated by F1 in fig. 1, but in actual use, a loading force applied by a human hand to the throttle lever is not a horizontal direction, a movement locus of the human hand is an arc shape, and a force application direction thereof is a tangential direction of the arc locus, i.e., a direction indicated by F2 in fig. 1, that is, a difference exists between the loading force measured by the four-bar structure and the loading force applied by the human hand to the throttle lever in actual use, so that an actual use condition of the throttle table cannot be accurately simulated.
Disclosure of Invention
The invention provides an aircraft accelerator lever testing device, which aims to solve the problem that the actual use condition of an accelerator table cannot be accurately simulated due to the difference between the loading force measured by a four-bar structure and the loading force exerted on an accelerator lever by hands in actual use in the prior art.
The technical scheme of the invention is as follows:
an aircraft throttle lever testing device comprising: the testing mechanism is arranged on the testing platform and comprises a driving assembly and a clamping assembly connected with the driving assembly, the driving assembly is suitable for driving the clamping assembly to rotate, and the rotating axis of the clamping assembly is coaxial with the rotating shaft of the throttle lever; and the clamping assembly is provided with a force measuring unit, and the force measuring unit is suitable for measuring the loading force of the throttle lever when the clamping assembly rotates.
Preferably, the drive assembly comprises: swing mechanism, support piece, the centre gripping subassembly is located on the support piece, and swing mechanism is connected with support piece and rotates in order to drive support piece, and the pivot coaxial setting of the pivot axle center of support piece and throttle lever.
Preferably, the swing mechanism includes: the swing arm is driven by the second driving piece to swing, and the output shaft of the second driving piece is connected with the swing arm.
Preferably, the clamping assembly comprises a first clamp for clamping a single throttle lever, and a second clamp for clamping a plurality of throttles, the second clamp being connected with the support, the first clamp and the second clamp being disposed opposite to each other in the vertical direction.
Preferably, the drive assembly further includes a driving mechanism, the support member is disposed in parallel with the rotating shaft of the throttle lever, the driving mechanism is disposed on the support member, and the driving mechanism includes: the first driving piece is arranged on one side of the supporting piece, is connected with the first lead screw and is suitable for driving the first clamp to move along the axial direction of the first lead screw.
Preferably, the first gripper comprises: the mounting seat is connected with the supporting piece in a sliding mode along the length direction of the supporting piece; the third driving piece and the bidirectional screw rod are both arranged on the mounting seat, and the third driving piece drives the bidirectional screw rod to act; the first clamp holder further comprises a first clamping jaw and a second clamping jaw which are arranged on the bidirectional screw rod, and the third driving piece is suitable for driving the first clamping jaw and the second clamping jaw to be close to or far away from the bidirectional screw rod along the axial direction.
Preferably, the second gripper comprises: the fourth driving part is arranged on the supporting part and is opposite to the first driving part, the arc-shaped clamping jaw is fixedly connected with the fourth driving part, and the fourth driving part drives the arc-shaped clamping jaw to rotate so as to clamp a plurality of parallel throttle rods between the arc-shaped clamping jaw and the supporting part.
The technical scheme of the invention has the following beneficial effects:
1. the testing mechanism is arranged on the testing platform and comprises a driving assembly and a clamping assembly connected with the driving assembly, the driving assembly is suitable for driving the clamping assembly to rotate, and the rotating axis of the clamping assembly and the rotating shaft of the throttle lever are coaxially arranged; and the clamping assembly is provided with a force measuring unit, and the force measuring unit is suitable for measuring the loading force of the throttle lever when the clamping assembly rotates.
When the device is used, the aircraft throttle platform is installed on the test platform, the clamping assembly clamps the throttle rod to be measured, the driving assembly drives the clamping assembly to rotate, and the force measuring unit arranged on the clamping assembly directly measures the loading force of the throttle rod when the clamping assembly rotates.
Because the rotating axis of the clamping assembly and the rotating shaft of the throttle lever are coaxially arranged, the motion trail of the clamping assembly is arc-shaped, namely, the stress direction of the throttle lever by the clamping assembly is the tangential direction of the arc-shaped trail, and the direction is consistent with the force application direction of a hand on the throttle lever when the hand operates the throttle lever, so that the running condition of the throttle table in actual use is accurately judged, and index tests such as the service life, reliability and the like of the throttle table about to be put into use are completed.
2. The invention relates to an aircraft throttle lever testing device, a driving assembly comprises: swing mechanism, support piece, the centre gripping subassembly is located on the support piece, and swing mechanism is connected with support piece and rotates in order to drive support piece, and the pivot coaxial setting of the pivot axle center of support piece and throttle lever.
When the device is used for measuring, the swinging mechanism drives the support piece to rotate, the support piece drives the throttle lever to be tested to move through the clamping assembly, the rotating axis of the support piece is coaxially arranged with the rotating shaft of the throttle lever, the moving track of the support piece is arc-shaped, and the moving track of the clamping assembly is also arc-shaped and coaxially arranged with the center of the arc-shaped moving track and the rotating shaft of the throttle lever.
3. The clamping assembly comprises a first clamp used for clamping a single throttle lever and a second clamp used for clamping a plurality of throttles, the second clamp is connected with the supporting piece, and the first clamp and the second clamp are arranged oppositely in the vertical direction.
Drive assembly still includes actuating mechanism, and support piece is on a parallel with the pivot setting of throttle lever, and actuating mechanism locates on the support piece, and it includes: the first driving piece is arranged on one side of the supporting piece, is connected with the first lead screw and is suitable for driving the first clamp to move along the axial direction of the first lead screw.
When the device is used, the first driving piece drives the first lead screw to rotate, the first lead screw drives the first clamp holder to move axially along the first lead screw, after the first clamp holder moves to a single throttle rod to be tested, the first clamp holder moves to clamp and fix the single throttle rod, the swinging mechanism moves at the moment, the swinging mechanism drives the supporting piece to rotate, and the force measuring unit arranged on the first clamp holder measures the loading force on the throttle rod. After the measurement is finished, the first clamping device loosens the throttle lever, the first driving piece continues to drive the first lead screw to rotate, the first lead screw drives the first clamping device to move to another throttle lever to be measured, and the loading force on the throttle lever is measured again.
By continuously performing the actions, the loading force applied to each throttle lever is measured, and the running condition of the throttle platform when a single throttle lever is pushed is judged according to the measured loading force; then, the support piece is separated from the swing arm, the direction of the support piece is changed, the second clamp holder is arranged close to the throttle lever, the second clamp holder clamps all the throttle levers and then rotates under the action of the swing mechanism, the force measuring unit arranged on the second clamp holder measures the loading force applied to all the throttle levers, and the running condition of the throttle table when all the throttle levers are pushed is judged according to the measured loading force.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural diagram of a multi-throttle lever loading measuring device in the prior art;
FIG. 2 is a schematic structural diagram of a perspective view of the aircraft throttle lever test apparatus of the present invention;
FIG. 3 is a schematic view of the first holder of the present invention;
FIG. 4 is a schematic illustration of a partial view of a rear view of the aircraft throttle lever testing apparatus of the present invention.
Description of reference numerals:
1-a test platform; 2-fixing the base; 3-throttle lever; 4-a rotating shaft; 5-locking a handle; 6-a support member; 7-a second drive member; 8-swing arm; 9-a first gripper; 11-a force measuring unit; 12-a first drive member; 13-a through hole; 14-a mounting seat; 15-a third drive member; 16-a bidirectional lead screw; 17-a first jaw; 18-a second jaw; 19-a fourth drive; 20-arc-shaped clamping jaws; 21-arc-shaped groove.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The aircraft throttle lever testing device of the embodiment, as shown in fig. 2-4, includes: the testing device comprises a testing platform 1 and a testing mechanism, wherein the testing mechanism is arranged on the testing platform 1 and comprises a driving component and a clamping component connected with the driving component, the driving component is suitable for driving the clamping component to rotate, and the rotating axis of the clamping component is coaxially arranged with a rotating shaft 4 of the throttle lever 3; the clamping assembly is provided with a force measuring unit 11, the force measuring unit 11 is suitable for directly measuring the loading force of the throttle lever 3 when the clamping assembly rotates, and it should be noted that the force measuring unit 11 in this embodiment is a pressure sensor.
Still be equipped with the fixed baseplate 2 that is used for installing the throttle platform on test platform 1, 2 bottoms of fixed baseplate still are equipped with locking handle 5, fix the settlement position on test platform 1 with fixed baseplate 2 through locking handle 5.
When the device is used, the aircraft throttle platform is arranged on the fixed base 2, the throttle rod 3 which needs to be measured is clamped by the clamping assembly, the driving assembly drives the clamping assembly to rotate, and the force measuring unit 11 arranged on the clamping assembly measures the loading force of the throttle rod 3 when the clamping assembly rotates.
Because the rotation axis of the clamping component and the rotating shaft 4 of the throttle lever 3 are coaxially arranged, the motion trail of the clamping component is arc-shaped, namely, the stress direction of the clamping component on the throttle lever 3 is the tangential direction of the arc-shaped trail, and the direction is consistent with the force application direction of a hand on the throttle lever 3 when the hand operates the throttle lever 3, so that the running condition of the throttle table in actual use is accurately judged, and index tests such as the service life and reliability of the throttle table about to be put into use are completed.
Wherein, drive assembly includes: swing mechanism, support piece 6, the centre gripping subassembly is located on support piece 6, swing mechanism and support piece 6 pass through bolt-up connection in order to drive support piece 6 and rotate, and support piece 6's rotation axis sets up with the pivot 4 coaxial of throttle lever 3. When measuring, swing mechanism drive support piece 6 rotates, and support piece 6 passes through the action of centre gripping subassembly drive throttle lever 3 that needs the test, because support piece 6's rotation axle center sets up with the pivot 4 of throttle lever 3 is coaxial, and support piece 6's movement track is the arc, realizes that the movement track of centre gripping subassembly also is the arc and sets up with the pivot 4 coaxial of throttle lever 3 rather than the center.
Wherein, swing mechanism includes: second driving piece 7 and swing arm 8, the one end and the support piece 6 of swing arm 8 are connected, and its other end is connected with second driving piece 7, and the output shaft and the swing arm 8 of second driving piece 7 are connected in order to drive the swing arm 8 swing, and the output shaft is coaxial setting with pivot 4 of throttle lever 3, and the movement track that realizes support piece 6 is the arc.
Wherein, as shown in fig. 2, the clamping assembly comprises a first clamp 9 for clamping a single throttle lever 3, and a second clamp for clamping a plurality of throttles, the second clamp is connected with the support 6, and the first clamp 9 and the second clamp are arranged oppositely along the vertical direction.
The aircraft throttle lever testing arrangement of this embodiment, drive assembly still include actuating mechanism, and support piece 6 sets up in parallel with pivot 4 of throttle lever 3, and actuating mechanism locates on support piece 6, and it includes: the first driving part 12 and the first lead screw are arranged on the supporting part 6, the first driving part 12 is arranged on one side of the supporting part 6 and connected with the first lead screw, and is suitable for driving the first clamp 9 to move axially along the first lead screw.
When the device is used, the first driving piece 12 drives the first lead screw to rotate, the first lead screw drives the first clamp holder 9 to axially move along the first lead screw, after the first lead screw moves to a single throttle lever 3 to be tested, the first clamp holder 9 acts to clamp and fix the single throttle lever 3, the swinging mechanism acts at the moment, the swinging mechanism drives the supporting piece 6 to rotate, and the force measuring unit 11 arranged on the first clamp holder 9 measures the loading force on the throttle lever 3. After the measurement is finished, the first clamping device loosens the throttle rod 3, the first driving piece 12 continues to drive the first lead screw to rotate, the first lead screw drives the first clamping device 9 to move to another throttle rod 3 to be measured, and the loading force on the throttle rod 3 is measured again.
By continuously performing the above-mentioned actions, the loading force exerted on each throttle lever 3 is measured, and the operating condition of the throttle stand when a single throttle lever 3 is pushed is judged according to the measured loading force; then, after the bolts connecting the support member 6 and the swing arm 8 are unscrewed, the support member 6 and the swing arm 8 are separated, the direction of the support member 6 is changed, the second clamp holder is arranged close to the throttle lever 3, the second clamp holder clamps all the throttle levers 3 and then rotates under the action of the swing mechanism, the force measuring unit 11 arranged on the second clamp holder measures the loading force applied to all the throttle levers 3, and the operation condition of the throttle table when all the throttle levers 3 are pushed is judged according to the measured loading force.
Specifically, as shown in fig. 3, the first clamper 9 includes: the mounting seat 14, the third driving piece 15, the bidirectional screw rod 16 and the through hole 13 arranged on the mounting seat 14, the first clamp 9 is connected with the first screw rod through the through hole 13, and the mounting seat 14 is connected with the supporting piece 6 in a sliding manner along the length direction of the supporting piece 6; the third driving piece 15 and the bidirectional screw 16 are both arranged on the mounting seat 14, and the third driving piece 15 drives the bidirectional screw 16 to act; the first clamping device 9 further comprises a first clamping jaw 17 and a second clamping jaw 18 which are arranged on the bidirectional screw 16, and the third driving piece 15 is suitable for driving the first clamping jaw 17 and the second clamping jaw 18 to axially move close to or away from each other along the bidirectional screw 16.
Specifically, as shown in fig. 2 and 4, the second gripper includes: the fourth driving part 19 is arranged on the support part 6 and is opposite to the first driving part 12, the arc-shaped clamping jaw 20 is fixedly connected with the fourth driving part 19, and the fourth driving part 19 drives the arc-shaped clamping jaw 20 to rotate so as to clamp the plurality of parallel throttle rods 3 between the arc-shaped clamping jaw 20 and the support part 6. In order to facilitate the clamping of the throttle lever 3, an arc-shaped groove 21 matched with the structure of the throttle lever handle part is arranged on the supporting piece 6.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications of the invention may be made without departing from the spirit or scope of the invention.
Claims (7)
1. An aircraft throttle lever testing device, comprising:
a test platform (1);
the testing mechanism is arranged on the testing platform (1) and comprises a driving assembly and a clamping assembly connected with the driving assembly, the driving assembly is suitable for driving the clamping assembly to rotate, and the rotating axis of the clamping assembly is coaxial with the rotating shaft (4) of the throttle lever (3);
and a force measuring unit (11) is arranged on the clamping assembly, and the force measuring unit (11) is suitable for measuring the loading force of the throttle lever (3) when the clamping assembly rotates.
2. The aircraft throttle lever testing device of claim 1, wherein the drive assembly comprises:
swing mechanism, support piece (6), the centre gripping subassembly is located on support piece (6), swing mechanism with support piece (6) are connected in order to drive support piece (6) rotate, the rotation axle center of support piece (6) with pivot (4) coaxial setting.
3. The aircraft throttle lever testing device of claim 2, wherein the swing mechanism comprises:
second driving piece (7) and swing arm (8), the one end of swing arm (8) with support piece (6) are connected, its other end with second driving piece (7) are connected, the output shaft of second driving piece (7) with swing arm (8) are connected in order to drive swing arm (8) swing, the output shaft with pivot (4) coaxial setting.
4. The aircraft throttle lever test device of claim 3, characterized in that the clamping assembly comprises a first clamp (9) for clamping a single throttle lever (3) and a second clamp for clamping a plurality of throttles, the force measuring unit (11) being provided on each of the first clamp (9) and the second clamp;
the second gripper is connected with the support (6), and the first gripper (9) and the second gripper are arranged oppositely along the vertical direction.
5. The aircraft throttle lever test device of claim 4, wherein the drive assembly further comprises a drive mechanism, the support member (6) being arranged parallel to the rotation axis (4), the drive mechanism being provided on the support member (6) and comprising:
the first driving piece (12) and the first lead screw are mounted on the supporting piece (6), the first driving piece (12) is arranged on one side of the supporting piece (6) and connected with the first lead screw, and the first driving piece is suitable for driving the first clamp (9) to move axially along the first lead screw.
6. The aircraft throttle lever test device of claim 5, wherein the first gripper (9) comprises:
a mounting seat (14) which is connected with the support (6) in a sliding way along the length direction of the support (6);
the third driving piece (15) and the bidirectional lead screw (16) are both arranged on the mounting seat (14), and the third driving piece (15) drives the bidirectional lead screw (16) to act;
first clamping jaw (17) and second clamping jaw (18) are located on two-way lead screw (16), third driving piece (15) are suitable for the drive first clamping jaw (17) and second clamping jaw (18) are followed two-way lead screw (16) axial is close to or is kept away from, dynamometry unit (11) are located first clamping jaw (17) or on second clamping jaw (18).
7. The aircraft throttle lever testing device of claim 6, wherein the second gripper comprises:
fourth drive spare (19) and arc clamping jaw (20), fourth drive spare (19) are located on support piece (6) and with first drive spare (12) set up relatively, arc clamping jaw (20) with fourth drive spare (19) fixed connection, fourth drive spare (19) drive arc clamping jaw (20) rotate in order to be a plurality of side by side throttle pole (3) centre gripping in arc clamping jaw (20) with between support piece (6), dynamometry unit (11) are located on arc clamping jaw (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011335176.4A CN112319848B (en) | 2020-11-24 | 2020-11-24 | Aircraft accelerator lever testing arrangement |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011335176.4A CN112319848B (en) | 2020-11-24 | 2020-11-24 | Aircraft accelerator lever testing arrangement |
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| CN112319848A true CN112319848A (en) | 2021-02-05 |
| CN112319848B CN112319848B (en) | 2021-06-08 |
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| CN202011335176.4A Active CN112319848B (en) | 2020-11-24 | 2020-11-24 | Aircraft accelerator lever testing arrangement |
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| CN115042983A (en) * | 2022-08-11 | 2022-09-13 | 北京天创凯睿科技有限公司 | Measurement protection mechanism for automatic throttle of airplane, measurement mechanism and use method |
| CN115057002A (en) * | 2022-08-11 | 2022-09-16 | 北京天创凯睿科技有限公司 | Automatic following measuring device for automatic accelerator of airplane |
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| CN115042983B (en) * | 2022-08-11 | 2022-11-11 | 北京天创凯睿科技有限公司 | Measurement protection mechanism for airplane automatic accelerator, measurement mechanism and use method |
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|---|---|
| CN112319848B (en) | 2021-06-08 |
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