CN115042961A - Lambda-shaped actuating cylinder driving mechanism - Google Patents
Lambda-shaped actuating cylinder driving mechanism Download PDFInfo
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- CN115042961A CN115042961A CN202210614479.2A CN202210614479A CN115042961A CN 115042961 A CN115042961 A CN 115042961A CN 202210614479 A CN202210614479 A CN 202210614479A CN 115042961 A CN115042961 A CN 115042961A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 25
- 238000010146 3D printing Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 abstract description 11
- 230000033001 locomotion Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 241000283690 Bos taurus Species 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- 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
- B64C13/38—Transmitting means with power amplification
- B64C13/40—Transmitting means with power amplification using fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
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Abstract
The application belongs to the field of driving mechanisms and structural designs of airplane control surfaces, and particularly relates to a lambda-shaped actuator cylinder driving mechanism; the lambda-shaped actuator cylinder is provided with a lambda-shaped outer cylinder (4) and an actuator shaft (3), the lambda-shaped outer cylinder (4) is provided with a support arm (41), and the support arm (41) is hinged with the control surface rotating shaft O; the actuating shaft (3) is hinged with a rocker arm (1) hinged on a control surface rotating shaft O through a connecting rod (2), and the lambda-shaped outer cylinder (4) is connected with a main bearing structure of the airplane; the force transmission route of the traditional control surface design is changed, the main bearing structure is not needed to support the fixed section of the actuating cylinder, the arrangement limit of the main bearing structure of the airplane is widened, and the structural design domain of the airplane is increased.
Description
Technical Field
The application belongs to the field of driving mechanisms and structural designs of airplane control surfaces, and particularly relates to a lambda-shaped actuating cylinder driving mechanism.
Background
The airplane control surface is widely applied to a straight cylinder type actuating cylinder to drive a control surface rocker arm so as to deflect the control surface around a rotating axis. The output end of the straight cylinder type actuating cylinder is hinged with the driving point of the control surface rocker arm, and the fixed end of the straight cylinder type actuating cylinder is hinged or fixedly supported on a main bearing structure of the airplane to transfer the reaction force driven by the control surface. The fixed end hinge mechanism of the ram is schematically illustrated in figure 3. In the figure, the actuation axis y and the outer cylinder z constitute a conventional straight cylinder actuation cylinder. When the actuating shaft y extends and slides in the outer cylinder z, the rocker arm x can be driven to rotate around the point O. When the fixed end of the actuating cylinder is fixedly supported, a connecting rod is added between the actuating shaft y and the rocker arm to meet the requirement of freedom of movement. In the figure, the x rocker arm; a y actuating shaft; z outer cylinder; o: a control surface rotating shaft; a: a rocker arm drive point; b, fixing end hinge point; e is used as a sliding pair of the shaft and the outer cylinder.
a) The mechanism occupies a large space as a whole, a main bearing structure is arranged at the fulcrum of the actuating cylinder to balance the output force of the actuating cylinder in order to meet the requirement of the arrangement of the actuating cylinder, however, the arrangement of the main bearing structure is greatly limited by the arrangement of airplane components and sometimes difficult to realize;
b) the load Fc at the point C is equivalent to the output driving load F of the actuating cylinder, the size of the load Fc is related to the load of a control plane, the load of the large control plane is up to hundreds of thousands of cattle, and the requirement on a main bearing structure is high;
c) in the motion process, the actuator cylinder swings at a small angle, so that a pipeline on the actuator cylinder is driven to swing, and a sufficient motion space is reserved for avoiding the risk of collision with a peripheral structure.
Disclosure of Invention
For reducing the restriction that the pressurized strut installation was arranged main bearing structure, adopt lambda shape actuating mechanism, change the pressurized strut and pass the year route, make main load pass the control plane and mainly bear bearing structure, the pressurized strut strong point load can reduce by a wide margin, and can eliminate the pressurized strut small-angle swing, the lambda shape pressurized strut actuating mechanism of this application specifically includes:
the lambda-shaped actuator cylinder is provided with a lambda-shaped outer cylinder and an actuator shaft, the lambda-shaped outer cylinder is provided with a support arm, and the support arm is hinged with the control surface rotating shaft O; the actuating shaft is hinged with a rocker arm hinged on the control surface rotating shaft O through a connecting rod, and the lambda-shaped outer cylinder is connected with a main bearing structure of the airplane.
Preferably, the lambda-shaped outer cylinder is hinged with the main bearing structure of the airplane through a pull rod, and the main bearing structure of the airplane is used for providing a fulcrum for force for the lambda-shaped outer cylinder.
Preferably, the λ -shaped outer cylinder has two parallel cylinders, each of which has an actuating shaft, and the parallel cylinders not only provide a more stable power source, but also provide additional safety measures, and when the cylinder cylinders are damaged, the other cylinder can still work normally.
Preferably, the included angle between the axis of the support arm and the axis of the actuating shaft is 30-70 degrees, and the included angle of 30-70 degrees enables the mechanism to have a larger transmission angle according to the actual working environment, the transmission angle is the complementary angle of a pressure angle and is generally used for describing the transmission performance of a mechanical mechanism, and the larger the transmission angle is, the better the mechanical performance of the mechanism is.
Preferably, the total length of the actuating shaft and the connecting rod is 0.5-2.5 times of the length of the rocker arm.
Preferably, the support arm is in a triangular prism shape as a whole, one side surface of the support arm is fixedly connected with the lambda-shaped outer cylinder, and a hinge lug piece is arranged on a diagonal of the side surface.
Preferably, the support arm has the fretwork, and the fretwork can reduce structure weight under the condition of not reducing structural strength by a wide margin.
Preferably, the hinged lug plate is provided with a plurality of lug plates which are axially and equidistantly distributed along the central hole of the lug plate, and the plurality of lug plates can improve the structural stability.
Preferably, one end of the lambda-shaped outer cylinder, which is far away from the actuating shaft, is provided with a pull rod hinge lug.
Preferably, the λ -shaped outer cylinder and the arm are integrally formed by 3D printing.
The advantages of the present application include:
a) the force transmission route of the traditional control surface design is changed, the main bearing structure is not needed to support the fixed section of the actuating cylinder, the arrangement limit of the main bearing structure of the airplane is widened, and the structural design domain of the airplane is increased.
b) The outer cylinder of the lambda-shaped actuator cylinder can further give full play to the bearing capacity of materials, the structural weight is reduced through optimization, and the lambda-shaped drive actuator cylinder can be conveniently produced and manufactured by means of the technologies of 3D printing, precision manufacturing and the like;
c) the lambda-shaped actuator cylinder fuses a traditional bearing structure and a driving structure, has two functions of bearing and driving, breaks through the idea of structural design of traditional multi-part and two-system, fuses the two and increases the design domain.
Drawings
FIG. 1 is a schematic view of a preferred embodiment of the λ actuator cylinder drive mechanism of the present application;
FIG. 2 is a partial view of a preferred embodiment of the λ actuator cylinder arm of the present application;
fig. 3 is a schematic diagram of a conventional ram drive mechanism.
Wherein, 1-rocker arm; 2-a connecting rod; 3-an actuating shaft; a 4-lambda-shaped outer cylinder; 5-a pull rod; an x-rocker arm; y-actuation axis; z-outer barrel; o-control plane rotation axis; a-rocker arm drive point; b-a hinge point; c-actuator hinge pivot; d-a pull rod hinge fulcrum; e-actuating shaft and outer cylinder sliding pair.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As shown in fig. 1, in order to reduce the limitation of the installation arrangement of the actuator cylinders on the main bearing structure, a lambda-shaped driving mechanism is adopted, the transmission path of the actuator cylinders is changed, so that the main load is transmitted back to the main bearing support structure of the control surface, namely the main bearing structure where the rocker arm is located, the load of the support points of the actuator cylinders can be greatly reduced, and the small-angle swing of the actuator cylinders can be eliminated. The utility model provides a lambda shape pressurized strut actuating mechanism, concrete structure is:
the lambda-shaped actuator cylinder is provided with a lambda-shaped outer cylinder 4 and an actuator shaft 3, the lambda-shaped outer cylinder 4 is provided with a support arm 41, and the support arm 41 is hinged with the control surface rotating shaft O; the actuating shaft 3 is hinged with a rocker arm 1 hinged on a control surface rotating shaft O through a connecting rod 2, the lambda-shaped outer cylinder 4 is connected with a main bearing structure of the airplane, wherein the lambda-shaped outer cylinder 4, the pull rod 5 and a machine body supporting structure form a stable triangle, and the actuating cylinder does not move.
Further, the lambda-shaped outer cylinder 4 is hinged with a main bearing structure of the airplane through a pull rod 5, and the main bearing structure of the airplane is used for providing a fulcrum of force for the lambda-shaped outer cylinder 4.
Furthermore, the lambda-shaped outer cylinder 4 is provided with two parallel cylinder cylinders, each cylinder is provided with an actuating shaft 3, the parallel cylinder cylinders not only can provide a more stable power source, but also can provide additional safety measures, when the cylinder actuating cylinders are damaged, another cylinder can be provided for normal operation, in addition, the parallel cylinder cylinders have the reinforcing effect in the parallel direction, namely the lambda-shaped actuating cylinders cannot shake in the parallel direction.
Furthermore, the included angle between the axis of the support arm 41 and the axis of the actuating shaft 3 is 60 degrees, and according to the actual working environment, the 60 degree included angle enables the mechanism to have a larger transmission angle, the transmission angle is the complementary angle of the pressure angle and is generally used for describing the transmission performance of the mechanical mechanism, and the larger the transmission angle is, the better the mechanical performance of the mechanism is.
Further, the total length of the actuating shaft 3 and the connecting rod 2 is 1.2 times of the length of the rocker arm 1.
Further, the support arm 41 is in a triangular prism shape as a whole, one side surface of the support arm is fixedly connected with the lambda-shaped outer cylinder 4, and a hinge lug is arranged on a diagonal of the side surface.
Further, the support arm 41 is hollow, and the hollow can greatly reduce the structural weight without reducing the structural strength.
Furthermore, articulated auricle has a plurality ofly, and a plurality of auricles are followed auricle centre bore axial equidistance and are distributed, and a plurality of auricles can improve structural stability.
Further, one end of the lambda-shaped outer cylinder 4 far away from the actuating shaft 3 is provided with a pull rod hinge lug 42.
Further, the λ -shaped outer cylinder 4 is integrally formed with the arm 41 by 3D printing.
The motion principle of the mechanism is as follows: an OE section is led out from the straight cylinder and the outer cylinder and hinged to a control surface rotating shaft O, the output force F of the actuating cylinder is along the EB direction, the included angle between OE and EB is small, and the OE direction bears the reaction force F OE The size is comparable to F. The CD rod only bears the axial force, the arm of force OD is increased to be K times of that of F force, K can reach more than 5, and F is DC The supporting force of the fixed section of the actuating cylinder is greatly reduced by about 1/K of F, and a main bearing structure is not needed in the state; in the mechanism, the lambda-shaped outer cylinder 4 is improved from the original state of mainly bearing the hydraulic load of the actuating cylinder to the state of bearing the hydraulic load and the support reaction force of the actuating cylinder, so that the bearing utilization rate of the material of the outer cylinder of the actuating cylinder is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A λ -shaped cylinder drive mechanism comprising:
the lambda-shaped actuator cylinder is provided with a lambda-shaped outer cylinder (4) and an actuator shaft (3), the lambda-shaped outer cylinder (4) is provided with a support arm (41), and the support arm (41) is hinged with the control surface rotating shaft O; the actuating shaft (3) is hinged with a rocker arm (1) hinged on a control surface rotating shaft O through a connecting rod (2), and the lambda-shaped outer cylinder (4) is connected with a main bearing structure of the airplane.
2. A lambda cylinder drive according to claim 1, characterized in that the lambda cylinder (4) is articulated to the main load-bearing structure of the aircraft by means of a tie rod (5).
3. A lambda cylinder drive according to claim 1, characterized in that the outer cylinder (4) of the lambda cylinder has two juxtaposed cylinders, each of said cylinders having an actuating shaft (3).
4. A lambda cylinder drive according to claim 1, characterized in that the angle between the axis of the arm (41) and the axis of the actuator shaft (3) is 30 ° to 70 °.
5. A lambda cylinder drive according to claim 4, characterized in that the total length of the actuator shaft (3) and the connecting rod (2) is 0.5 to 2.5 times the length of the rocker arm (1).
6. A lambda cylinder drive according to claim 3, characterized in that the arm (41) is generally triangular prism shaped with one side fixedly connected to the outer cylinder (4) and the opposite corner of the side having a hinge tab.
7. A lambda cylinder drive according to claim 4, characterized in that the arm (41) is hollowed out.
8. A lambda cylinder drive mechanism according to claim 3, wherein said hinge tab has a plurality of tabs axially spaced along the tab central aperture.
9. A lambda cylinder drive according to claim 1, characterized in that the end of the lambda cylinder (4) remote from the actuating shaft (3) is provided with a pull rod hinge tab (42).
10. A λ -shaped cylinder drive mechanism according to claim 1, characterised in that the λ -shaped outer cylinder (4) is integrally formed with the arm (41) by 3D printing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210614479.2A CN115042961A (en) | 2022-05-27 | 2022-05-27 | Lambda-shaped actuating cylinder driving mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210614479.2A CN115042961A (en) | 2022-05-27 | 2022-05-27 | Lambda-shaped actuating cylinder driving mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN115042961A true CN115042961A (en) | 2022-09-13 |
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| CN202210614479.2A Pending CN115042961A (en) | 2022-05-27 | 2022-05-27 | Lambda-shaped actuating cylinder driving mechanism |
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2022
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