CN220339632U - Loading device for function test of spoiler of airplane - Google Patents
Loading device for function test of spoiler of airplane Download PDFInfo
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- CN220339632U CN220339632U CN202320701771.8U CN202320701771U CN220339632U CN 220339632 U CN220339632 U CN 220339632U CN 202320701771 U CN202320701771 U CN 202320701771U CN 220339632 U CN220339632 U CN 220339632U
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- spoiler
- support
- loading
- actuator
- loading device
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- 238000012360 testing method Methods 0.000 title claims abstract description 43
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 54
- 229910052742 iron Inorganic materials 0.000 claims abstract description 27
- 238000011990 functional testing Methods 0.000 claims abstract description 8
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 238000003466 welding Methods 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
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Abstract
The application provides a loading device for aircraft spoiler functional test, loading device includes: the spoiler support bracket is arranged on the iron bird test bed; wherein, the spoiler is arranged on the plane of the II beam of the frame of the iron bird test stand 30; the spoiler loading actuator, one end of the spoiler loading actuator is connected with the spoiler support bracket, and the other end of the spoiler loading actuator is connected with the spoiler; one end of the spoiler driving actuator is arranged on the II beam plane of the iron bird test bench 30 frame, and the other end of the spoiler driving actuator is connected with the spoiler; the application provides a loading device for spoiler function test can simulate the pneumatic load that spoiler sky receives more lifelike.
Description
Technical Field
The application belongs to the technical field of aircraft test experiments, and particularly relates to a loading device for an aircraft spoiler function test.
Background
The control point of the spoiler on the aircraft is positioned below the middle connecting joint, one end of the spoiler driving actuator is connected to the control point, and the other end of the spoiler driving actuator is connected to the plane of the flap II beam.
At present, a loading test of an aircraft spoiler, which is usually a static test of the aircraft spoiler, cannot load and analyze pneumatic loads received by the spoiler in actual flight of the aircraft.
Disclosure of Invention
To the technical problem, the application provides a loading device for aircraft spoiler function test, loading device includes:
the spoiler support bracket is arranged on the iron bird test bed; wherein, the spoiler is arranged on the plane of the II beam of the frame of the iron bird test stand 30;
the spoiler loading actuator, one end of the spoiler loading actuator is connected with the spoiler support bracket, and the other end of the spoiler loading actuator is connected with the spoiler;
and one end of the spoiler driving actuator is arranged on the II beam plane of the iron bird test bench 30 frame, and the other end of the spoiler driving actuator is connected with the spoiler.
Preferably, the spoiler support bracket includes:
one end of the main support is connected with the 29 frames of the iron bird test stand;
the double-ear support is arranged at the other end of the main support; one end of the spoiler loading actuator is connected with the double-lug support;
one end of the inclined support is connected with the main support, and the other end of the inclined support is connected with a II beam of the iron bird test bench 30 frame;
one end of the side support is connected with the main support, and the other end of the side support is connected with a 29 frame of the iron bird test stand;
preferably, the spoiler support bracket further comprises:
the first base plate is arranged between one end of the main support and the 29 frames of the iron bird test stand;
the second base plate is arranged between the other end of the inclined support and the II beam of the iron bird test bench 30 frame;
and the third base plate is arranged between the other end of the side support and the 29 frames of the iron bird test stand.
Preferably, the loading device further comprises:
the spoiler loading connector is arranged on the spoiler and is connected with the other end of the spoiler loading actuator.
Preferably, the spoiler is connected with the II beam plane of the frame of the iron bird test stand 30 through a double-lug joint.
Preferably, the back of the plane of the II beam of the frame of the iron bird test stand 30 is provided with a reinforced square tube.
The beneficial technical effect of this application:
the loading device for the spoiler function test can simulate the pneumatic load borne by the spoiler in the air more realistically, and provides technical support for researching the spoiler function characteristics.
Drawings
FIG. 1 is a left side view of a loading device for aircraft spoiler functional testing according to an embodiment of the present application;
FIG. 2 is a front view of a loading device for aircraft spoiler functional test according to an embodiment of the present application;
FIG. 3 is a schematic view of a spoiler load actuator according to an embodiment of the present disclosure;
FIG. 4 is a spoiler support bracket mounting view provided by an embodiment of the present application;
wherein: 1-spoiler loading an actuator; 2-spoiler loading joint; 3-spoilers; 4-spoiler driving actuators; 5-spoiler support brackets; 6-a binaural support; 7-a main support; 8-inclined support; 9-side support; 10-a first backing plate; 11-a second backing plate; 12-II beams; 13-a third backing plate.
Detailed Description
Referring to fig. 1-4, the application provides a loading device for a spoiler function test of an aircraft, so as to solve the problem that the conventional spoiler loading mode is limited to a static test, so that pneumatic load applied to a spoiler in actual flight of the aircraft cannot be loaded and analyzed.
The application provides a loading device for aircraft spoiler function test, include: as shown in fig. 1, a loading device for a spoiler function test of an aircraft is composed of a spoiler loading actuator 1, a spoiler loading joint 2, a spoiler support bracket 5, a double-lug support 6, a main support 7, an inclined support 8, a side support 9, a first backing plate 10, a second backing plate 11, a ii beam 12 and a third backing plate 13.
The spoiler is installed on a plane of a II beam 12 of the iron bird rack, 8 spoiler supporting brackets 5 are arranged left and right, each spoiler is driven by 1 spoiler driving actuator 4, each spoiler loading actuator 1 and each spoiler driving actuator 4 adopt a one-to-one opposite-top loading mode, and when all spoilers 3 work, 8 spoiler loading actuators 1 are adopted for coordinated loading.
The application provides a loading device for an airplane spoiler function test, wherein a spoiler servo loading supporting structure is connected with an iron bird test bench by bolts, and welding stress is reduced to the minimum at a welding position, so that welding deformation is avoided; the spoiler mounting support is reinforced at the back of the plane of the II beam, so that the mounting of other parts is not affected; the influence of the loading support on the rotational inertia of the spoiler is reduced as much as possible; the effective control arm length of the loading point from the spoiler rotating shaft is increased, the calculation of the magnitude of the pneumatic load loading force follows the hinge moment balance principle, so that the concentrated load acting on the spoiler loading point can be reduced; the motion trail of the spoiler is followed by the selection of the loading points, so that the nonlinear influence of the loading force is small; the rigidity of the loading device of the newly designed airplane spoiler functional test is enough to ensure that the natural vibration frequency of the loading device is more than six times of the natural frequency of the tested part;
through technical research on the spoiler function test loading device, the pneumatic load borne by the spoiler in the air can be simulated more realistically, and technical support is provided for researching the spoiler function characteristics.
Wherein, the installation support of the spoiler loading actuator is connected with the plane support rack of the iron bird platform II beam 12, and the main support 7 of the installation support adopts a 200 multiplied by 8 steel square tube; since the main support 7 is subjected to a turning moment, a diagonal support 8 must be added to overcome the turning moment, and the diagonal support 8 is a 200×200×8 steel square tube; to increase the stability of the mounting support, a side support 9 is added to the side of the main support 7, and the side support 9 adopts 160×160×6 steel square tubes.
In order not to cause the deformation of the plane of the II beam 12, the installation support is connected with the iron bird table through bolts, the only welding place is the reinforcing square tube at the back of the II beam 12, and the reinforcing square tube at the back of the II beam 12 has two functions: firstly, the rigidity of the plane of the II beam 12 is increased; and secondly, the pulling force on the main support is increased through the inclined support 8.
The operating point of the spoiler 3 is located below the middle connecting joint, the loading point and the operating point are opposite to each other by the loading support mounting plane above the middle connecting joint, so that the influence of nonlinear factors of force in the loading process is ensured to be minimum in the whole stroke motion process of the spoiler, and only the influence of the weight of the spoiler loading joint 2 on the rotational inertia of the spoiler can simulate the aerodynamic load of the spoiler in the air realistically.
The load is provided by a spoiler loading actuator 1, the spoiler loading actuator is arranged on a support of the spoiler loading actuator, and the telescopic end is connected with middle joints of left and right side 1#, 2#, 3# and 4# spoilers through the support, and the spoilers on the left and right sides along the course are symmetrical.
Claims (6)
1. A loading device for aircraft spoiler functional test, the loading device comprising:
the spoiler support bracket (5) is arranged on the iron bird test bed; the spoiler is arranged on the plane of the II beam (12) of the frame of the iron bird test stand 30;
the spoiler loading actuator (1), one end of the spoiler loading actuator (1) is connected with the spoiler support bracket (5), and the other end of the spoiler loading actuator (1) is connected with the spoiler;
the device comprises a spoiler driving actuator (4), wherein one end of the spoiler driving actuator (4) is arranged on the plane of a II beam (12) of a frame of the iron bird test stand 30, and the other end of the spoiler driving actuator (4) is connected with a spoiler.
2. Loading device for aircraft spoiler functional tests according to claim 1, characterized in that the spoiler support bracket (5) comprises:
a main support (7), wherein one end of the main support (7) is connected with a 29 frame of the iron bird test stand;
the double-ear support (6) is arranged at the other end of the main support (7); one end of the spoiler loading actuator (1) is connected with the double-lug support (6);
one end of the inclined support (8) is connected with the main support (7), and the other end of the inclined support is connected with a II beam (12) of the iron bird test stand 30 frame;
and one end of the side support (9) is connected with the main support (7), and the other end of the side support (9) is connected with the 29 frames of the iron bird test stand.
3. Loading device for aircraft spoiler functional tests according to claim 2, characterized in that the spoiler support bracket (5) further comprises:
a first backing plate (10) arranged between one end of the main support (7) and the 29 frames of the iron bird test stand;
the second base plate (11) is arranged between the other end of the inclined support (8) and the II beam of the frame of the iron bird test bench 30;
and a third backing plate (13) arranged between the other end of the side support (9) and the 29 frames of the iron bird test stand.
4. The loading device for aircraft spoiler functional test according to claim 1, further comprising:
the spoiler loading connector (2) is arranged on the spoiler and is connected with the other end of the spoiler loading actuator (1).
5. The loading device for aircraft spoiler functional test according to claim 1, wherein the spoiler is connected to the plane of the ii-beam (12) of the frame of the bird test stand 30 by means of a binaural joint.
6. The loading device for the aircraft spoiler function test according to claim 1, wherein a reinforcing square tube is arranged on the back of the plane of the ii beam (12) of the frame of the bird test stand 30.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320701771.8U CN220339632U (en) | 2023-04-03 | 2023-04-03 | Loading device for function test of spoiler of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320701771.8U CN220339632U (en) | 2023-04-03 | 2023-04-03 | Loading device for function test of spoiler of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220339632U true CN220339632U (en) | 2024-01-12 |
Family
ID=89456605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320701771.8U Active CN220339632U (en) | 2023-04-03 | 2023-04-03 | Loading device for function test of spoiler of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220339632U (en) |
-
2023
- 2023-04-03 CN CN202320701771.8U patent/CN220339632U/en active Active
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