CN219884075U - Target aircraft aileron driving structure - Google Patents
Target aircraft aileron driving structure Download PDFInfo
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- CN219884075U CN219884075U CN202321166452.8U CN202321166452U CN219884075U CN 219884075 U CN219884075 U CN 219884075U CN 202321166452 U CN202321166452 U CN 202321166452U CN 219884075 U CN219884075 U CN 219884075U
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- connecting rod
- target aircraft
- transmission connecting
- rocker arm
- steering engine
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- 230000005540 biological transmission Effects 0.000 claims abstract description 45
- 238000000034 method Methods 0.000 description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The utility model discloses an aileron driving structure of a target aircraft, which relates to the technical field of target aircraft, wherein the aileron driving structure of the target aircraft is positioned in a wing of the target aircraft, the aileron driving structure of the target aircraft comprises a steering engine, a rocker arm, two linkage connecting rods and two transmission connecting rods, a power output end of the steering engine is connected with the rocker arm, the rocker arm is respectively hinged with one end of each linkage connecting rod, the other end of each linkage connecting rod is respectively hinged with one end of one transmission connecting rod, and each transmission connecting rod is used for being connected with a control surface. The target aircraft aileron driving structure solves the problems of poor reliability, heavy structural weight, high cost and large resistance of a double rudder engine control structure.
Description
Technical Field
The utility model relates to the technical field of target aircraft, in particular to a target aircraft aileron driving structure.
Background
Target aircraft are mainly used for military use and civil use. The control technology of the aileron of the target aircraft mainly realizes the actions of correcting the rolling gesture, turning left, turning right and the like of the target aircraft, and changes the flight route and the flight gesture in real time. Most target aircraft adopt double rudder control surfaces, and the driving mode has the problems of more parts, poor reliability, heavy structural weight, high cost and the like, so that a target aircraft aileron driving structure is needed, and the technical problems in the prior art are solved.
Disclosure of Invention
The utility model aims to provide a target aircraft aileron driving structure, which solves the problems of poor reliability, heavy structural weight, high cost and large resistance of a double rudder engine control structure.
In order to achieve the above object, the present utility model provides the following solutions:
the utility model provides a target aircraft aileron driving structure which is positioned in a target aircraft wing and comprises a steering engine, a rocker arm, two linkage connecting rods and two transmission connecting rods, wherein the power output end of the steering engine is connected with the rocker arm, the rocker arm is respectively hinged with one end of each linkage connecting rod, the other end of each linkage connecting rod is respectively hinged with one end of one transmission connecting rod, and each transmission connecting rod is used for being connected with a control surface.
Preferably, the steering engine is mounted in the target aircraft wing through the steering engine mounting bracket.
Preferably, the rocker arm comprises a rocker arm body and two supporting rods, the two supporting rods are symmetrically arranged on two sides of the rocker arm body, the rocker arm body is connected with a power output end of the steering engine, and the other end of the supporting rod is hinged with the other end of the linkage connecting rod.
Preferably, when the steering engine is located at the initial position, the supporting rod is perpendicular to the linkage connecting rod, the linkage connecting rod and the transmission connecting rod are perpendicular, and the supporting rod is perpendicular to the transmission connecting rod.
Preferably, the rocker arm is hinged with one end of the linkage connecting rod through a first universal ball head.
Preferably, a second universal ball head is arranged between the other end of the linkage connecting rod and one end of the transmission connecting rod respectively;
when the steering engine is located at the initial position, the first universal ball head and the second universal ball head are vertically arranged.
Preferably, one end of the transmission connecting rod is connected with the connecting rod of the second universal ball head.
Preferably, the aircraft wing driving device further comprises a transmission connecting rod support, wherein the transmission connecting rod support is arranged on the aircraft wing, the transmission connecting rod penetrates through a through hole in the transmission connecting rod support, and the transmission connecting rod is in rotary connection with the transmission connecting rod support.
Compared with the prior art, the utility model has the following technical effects:
the utility model has simple structure, greatly reduces the occurrence of faults caused by structural members, reduces the cost, has light structure weight and high reliability, ensures that the target aircraft aileron driving structure is positioned in the target aircraft wing, reduces the resistance of the target aircraft in the flying process, reduces corresponding fuel consumption, increases the flying endurance, and simultaneously can prevent the influence of rainy days on the target aircraft aileron driving structure caused by rainwater in the structure, and prevents the damage to the structural members caused by collision in the falling process from causing unexpected loss.
Drawings
In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the target aircraft aileron drive structure of the present utility model;
FIG. 2 is a schematic view of the attachment of the target aircraft aileron drive structure to the control surface of the present utility model;
FIG. 3 is a schematic view of the driving structure of the aileron of the target aircraft of the present utility model;
wherein: the steering engine comprises a wing 1, a control surface 2, a steering engine 3-execution mounting bracket, a steering engine 4-execution, a steering engine rocker 5-rocker arm, a linkage connecting rod 6-transmission connecting rod 7-transmission connecting rod 8-transmission connecting rod bracket, a first universal ball head 9-and a second universal ball head 10-.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by a person skilled in the art based on the embodiments of the utility model without any inventive effort, are intended to fall within the scope of the utility model.
The utility model aims to provide a target aircraft aileron driving structure, which solves the problems of poor reliability, heavy structural weight, high cost and large resistance of a double rudder engine control structure.
In order that the above-recited objects, features and advantages of the present utility model will become more readily apparent, a more particular description of the utility model will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1 to 3: the embodiment provides a target aircraft aileron driving structure, the target aircraft aileron driving structure is located in a target aircraft wing 1, the target aircraft aileron driving structure comprises a steering engine 4, a rocker arm 5, a steering engine mounting bracket 3, a transmission connecting rod bracket 8, two linkage connecting rods 6 and two transmission connecting rods 7, the steering engine mounting bracket 3 is fixed with a cross beam of the wing 1 through four M4 screws, the steering engine 4 is installed in the target aircraft wing 1 through the steering engine mounting bracket 3, the power output end of the steering engine 4 is fixedly connected with the rocker arm 5 through one M3 screw, the rocker arm 5 is hinged with one end of the linkage connecting rod 6 respectively, the other end of the linkage connecting rod 6 is hinged with one end of the transmission connecting rod 7 respectively, the transmission connecting rod bracket 8 is fixed with the skin of the wing 1 through two M4 screws, the transmission connecting rod 7 passes through a through hole on the transmission connecting rod bracket 8, the transmission connecting rod 7 and the transmission connecting rod bracket 8 can rotate relatively, and each transmission connecting rod 7 is used for being connected with a control surface 2.
Specifically, in this embodiment, the rocker arm 5 includes a rocker arm body and two struts, the two struts are symmetrically disposed on two sides of the rocker arm body, the rocker arm body is connected with a power output end of the steering engine 4, the other end of the strut is hinged with one end of the linkage connecting rod 6 through a first universal ball head 9, the strut is connected with a connecting rod of the first universal ball head 9, a second universal ball head 10 is disposed between the other end of the linkage connecting rod 6 and one end of a transmission connecting rod 7 respectively, and one end of the transmission connecting rod 7 is fixedly connected with a connecting rod of the second universal ball head 10 through 1M 3 screw.
In this embodiment, when the steering engine 4 is located at the initial position, the supporting rod is perpendicular to the linkage connecting rod 6, the linkage connecting rod 6 and the transmission connecting rod 7 are perpendicular, the supporting rod is perpendicular to the transmission connecting rod 7, and the first universal ball 9 and the second universal ball 10 are perpendicular.
When the embodiment is used, after the target aircraft is electrified, communication is established with the command control station, the command control station modifies parameters of the steering engine 4, and the steering engine 4 drives the linkage connecting rod 6 and the transmission connecting rod 7 to move so as to adjust the neutral positions of the two ailerons and realize left and right turns. Specifically, after the target aircraft is electrified, the steering engine 4 returns to the 0 bit, when the command control station sends a take-off command, the flight control computer sends the command to the steering engine 4 according to the current flight attitude, the steering engine 4 immediately executes the flight control computer command, and the control surface 2 is driven to change the flight attitude. For example, when the steering engine 4 drives the rocker arm to rotate anticlockwise (based on the placement direction of fig. 1), the two transmission connecting rods 7 drive the two ailerons to swing in different directions respectively; when the steering engine 4 drives the rocker arm to rotate clockwise (based on the placement direction of fig. 1), the two transmission connecting rods 7 respectively drive the two ailerons to swing in different directions (the swing direction is opposite to that when the steering engine 4 drives the rocker arm to rotate anticlockwise).
The embodiment has simple structure, greatly reduces the occurrence of faults caused by structural members, reduces the cost, has light structural weight and high reliability, ensures that the target aircraft aileron driving structure is positioned in the target aircraft wing 1, reduces the resistance of the target aircraft in the flight process, reduces corresponding fuel consumption, increases the flight endurance, and meanwhile, has a built-in structure, can prevent the influence of rainy days on the target aircraft aileron driving structure caused by rainwater, and prevents the damage to the structural members caused by collision in the landing process to bring unexpected losses.
The principles and embodiments of the present utility model have been described in this specification with reference to specific examples, the description of which is only for the purpose of aiding in understanding the method of the present utility model and its core ideas; also, it is within the scope of the present utility model to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the utility model.
Claims (8)
1. A target aircraft aileron drive structure, characterized by: the target aircraft aileron driving structure is located in a target aircraft wing and comprises a steering engine, a rocker arm, two linkage connecting rods and two transmission connecting rods, wherein the power output end of the steering engine is connected with the rocker arm, the rocker arm is hinged with one end of each linkage connecting rod, the other end of each linkage connecting rod is hinged with one end of one transmission connecting rod, and each transmission connecting rod is used for being connected with a control surface.
2. The target aircraft aileron drive structure of claim 1, wherein: the steering engine is mounted in the wing of the target aircraft through the steering engine mounting bracket.
3. The target aircraft aileron drive structure of claim 1, wherein: the rocker arm comprises a rocker arm body and two supporting rods, the two supporting rods are symmetrically arranged on two sides of the rocker arm body, the rocker arm body is connected with a power output end of the steering engine, and the other end of the supporting rod is hinged to the other end of the linkage connecting rod.
4. A target aircraft aileron drive structure according to claim 3, wherein: when the steering engine is located at an initial position, the supporting rod is perpendicular to the linkage connecting rod, the linkage connecting rod is perpendicular to the transmission connecting rod, and the supporting rod is perpendicular to the transmission connecting rod.
5. The target aircraft aileron drive structure of claim 1, wherein: the rocker arm is hinged with one end of the linkage connecting rod through a first universal ball head.
6. The target aircraft aileron drive structure of claim 5, wherein: a second universal ball head is arranged between the other end of the linkage connecting rod and one end of one transmission connecting rod respectively;
when the steering engine is located at the initial position, the first universal ball head and the second universal ball head are vertically arranged.
7. The target aircraft aileron drive structure of claim 6, wherein: one end of the transmission connecting rod is connected with the connecting rod of the second universal ball head.
8. The target aircraft aileron drive structure of claim 1, wherein: the wing-mounted target aircraft further comprises a transmission connecting rod support, the transmission connecting rod support is arranged on the wing of the target aircraft, the transmission connecting rod penetrates through a through hole in the transmission connecting rod support, and the transmission connecting rod is in rotary connection with the transmission connecting rod support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321166452.8U CN219884075U (en) | 2023-05-16 | 2023-05-16 | Target aircraft aileron driving structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321166452.8U CN219884075U (en) | 2023-05-16 | 2023-05-16 | Target aircraft aileron driving structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219884075U true CN219884075U (en) | 2023-10-24 |
Family
ID=88401196
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321166452.8U Active CN219884075U (en) | 2023-05-16 | 2023-05-16 | Target aircraft aileron driving structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219884075U (en) |
-
2023
- 2023-05-16 CN CN202321166452.8U patent/CN219884075U/en active Active
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