CN112829924B - Retractable duck steering mechanism - Google Patents
Retractable duck steering mechanism Download PDFInfo
- Publication number
- CN112829924B CN112829924B CN202011636799.5A CN202011636799A CN112829924B CN 112829924 B CN112829924 B CN 112829924B CN 202011636799 A CN202011636799 A CN 202011636799A CN 112829924 B CN112829924 B CN 112829924B
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- telescopic
- push rod
- deflection
- duck
- duck rudder
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/34—Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members
- B64C9/36—Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention provides a telescopic duck rudder mechanism which comprises an installation bracket, a telescopic device, a deflection device and a duck rudder surface, wherein a first installation bracket and a second installation bracket are fixed on the installation bracket; the telescopic device comprises a push rod and a first driving assembly used for driving the push rod to do telescopic motion, the push rod and the first driving assembly are both installed on a first installation support, the push rod is in sliding fit with the first installation support, and one end of the push rod, far away from the first installation support, is fixedly connected with the duck rudder surface; the deflection device comprises a deflection shaft sleeve and a second driving assembly used for driving the deflection shaft sleeve to rotate, the deflection shaft sleeve and the second driving assembly are both installed on the second installation support, the deflection shaft sleeve is matched with the second installation support in a rotating and sliding mode, and one end, far away from the second installation support, of the deflection shaft sleeve is fixedly connected with the duck rudder face. The duck rudder can extend out of the aircraft or retract into the aircraft according to needs, can perform deflection motion according to needs, and is favorable for improving the control precision of the flight trajectory of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft structure design, in particular to a telescopic duck rudder mechanism.
Background
In the technical field of aircraft structural design, a duck rudder is a key component for generating aircraft control force. The telescopic structure aircraft has certain application in the structural design. The existing telescopic mechanism is generally used for an airfoil and the like, and controls one-dimensional rotation or movement of the airfoil.
With the increasingly prominent multitask requirement, the conventional variable-wing-surface aircraft cannot meet the actual requirement of accurately controlling the flight path, and a duck rudder telescopic mechanism is required to realize adjustable output of control force. At present, an aircraft adopting duck rudders for control in active service mainly adopts a launching barrel wall as an initial constraint mechanism of the duck rudders, the duck rudders are constrained and released to extend out of a cabin body in the moment that the aircraft goes out of the barrel, and the duck rudders cannot be retracted into the cabin body of the aircraft again along with the whole flight process of the aircraft.
In the initial stage of the trajectory, in order to meet the requirement of quick turning, a duck rudder needs to extend out of a projectile body to output control force, in the middle stage of the trajectory, the requirement of resistance reduction is outstanding, bulges on the surface of a cabin body need to be reduced as far as possible, and a control surface needs to be retracted into the cabin body. At the tail end of the trajectory, the aircraft needs to pay large overload, the duck rudder needs to extend out of the cabin body again, control force is output, and accurate control of the trajectory is achieved.
Therefore, the inventor considers that the development of a duck rudder mechanism capable of being opened or contracted as required is urgently needed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a telescopic duck rudder mechanism.
The telescopic duck rudder mechanism comprises an installation bracket, a telescopic device, a deflection device and a duck rudder surface, wherein the installation bracket, the telescopic device, the deflection device and the duck rudder surface are installed in an aircraft; the telescopic device comprises a push rod and a first driving assembly for driving the push rod to do telescopic motion, the push rod and the first driving assembly are both arranged on a first mounting bracket, the push rod is in sliding fit with the first mounting bracket, and one end of the push rod, which is far away from the first mounting bracket, is fixedly connected with the duck rudder surface; the deflection device comprises a deflection shaft sleeve and a second driving assembly used for driving the deflection shaft sleeve to rotate, the deflection shaft sleeve and the second driving assembly are both installed on a second installation support, the deflection shaft sleeve is matched with the second installation support in a rotating and sliding mode, and one end, far away from the second installation support, of the deflection shaft sleeve is fixedly connected with the duck rudder face.
Preferably, first drive assembly includes the spiral and pushes away the dish and be used for driving spiral and push away dish pivoted driving motor, spiral pushes away a dish rotating turret and establishes in first installing support, the sliding tray has been seted up on the spiral pushes away the dish, the orbit of sliding tray is the arc, just the week side border position that the one end of sliding tray is close to the spiral pushes away dish, the other end of sliding tray is close to the central point that the spiral pushed away the dish puts, the sliding tray internal slipping is provided with the sliding pin, sliding pin and push rod fixed connection.
Preferably, a connecting shaft is coaxially arranged on the spiral pushing disc, the connecting shaft is arranged in the first mounting bracket through a bearing rotating frame, the driving motor is fixedly mounted on the first mounting bracket, and an output shaft of the driving motor is fixedly connected with the connecting shaft.
Preferably, the push rod includes that telescopic push rod and flexible pull out and insert the push rod, telescopic push rod and flexible pull out and insert the push rod and pass through the coaxial fixed connection of screw, telescopic push rod keeps away from the flexible one end of pulling out and inserting the push rod and explores in first installing support and rather than sliding fit, the flexible one end of pulling out and inserting the push rod and keeping away from telescopic push rod and duck rudder face fixed connection.
Preferably, the telescopic pulling and inserting push rod is provided with a shifting fork end at the end far away from the telescopic push rod, a sliding groove is formed in the root of the duck rudder surface, and a transmission pin is connected between the shifting fork and the sliding groove.
Preferably, the telescopic push rod and the telescopic plugging push rod are both arranged in the deflection shaft sleeve.
Preferably, the second driving assembly comprises a turbine disc, a turbine rod and a deflection motor, the turbine disc and the turbine rod are rotatably erected on the second mounting bracket, the turbine disc is meshed with the turbine rod, the deflection motor is mounted on the second mounting bracket, an output shaft of the deflection motor is coaxially and fixedly connected with the turbine rod, and the deflection shaft sleeve is coaxially connected with the turbine disc through a key.
Preferably, the shape of the duck rudder surface is approximately triangular.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the duck rudder, the push rod is driven to do telescopic motion through the first driving component, so that the duck rudder surface is driven to do telescopic motion, and then the deflection shaft sleeve is driven to rotate through the second driving component, so that deflection of the duck rudder surface is realized, the duck rudder can extend out of the aircraft or retract into the aircraft according to needs, deflection motion can be performed according to needs, and the control precision of the flight trajectory of the aircraft is improved;
2. according to the invention, the telescopic push rod and the telescopic pull push rod are arranged in the re-deflection shaft sleeve, so that on one hand, the decoupling of the contraction and expansion and deflection actions of the duck rudder surface is realized, and on the other hand, the space utilization rate is improved, so that the integral structure of the duck rudder structure is more compact;
3. according to the invention, through the matching of the arc-shaped sliding groove and the telescopic push rod in sliding fit with the first mounting bracket, the control on the expansion or the contraction of the duck rudder surface is realized, and the stability of the expansion or the contraction of the duck rudder surface is improved.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a drawing mainly showing the intention of the overall structure of a duck steering mechanism;
FIG. 2 is an exploded view of the overall structure of the retractor according to the invention;
fig. 3 is a schematic view of the overall structure of the deflection apparatus according to the present invention.
Reference numerals are as follows: 1. a mounting bracket; 11. a first mounting bracket; 12. a second mounting bracket; 2. a telescoping device; 3. a deflection device; 31. a deflection rotating shaft sleeve; 4. a duck rudder surface; 41. a chute; 5. a push rod assembly; 51. a telescopic push rod; 52. a telescopic plugging push rod; 53. a fork end; 531. a drive pin; 6. a first drive assembly; 61. a spiral pushing disc; 611. a connecting shaft; 612. a sliding groove; 613. a slide pin; 62. a drive motor; 7. a second drive assembly; 71. a turbine disk; 72. a turbine rod; 73. a deflection motor.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, the retractable duck rudder mechanism provided by the invention comprises a mounting bracket 1, a retractable device 2, a deflection device 3 and a duck rudder surface 4 which are mounted in an aircraft, wherein the retractable device 2, the deflection device 3 and the duck rudder surface 4 are all mounted on the mounting bracket 1. And the telescopic device 2 controls the duck rudder surface 4 to do telescopic motion, and the deflection device 3 controls the duck rudder surface 4 to do deflection motion.
As shown in fig. 1, the mounting bracket 1 is a metal plate, the mounting bracket 1 is disc-shaped, and a first mounting bracket 11 and a second mounting bracket 12 are fixedly mounted at the center position of the mounting bracket 1 by bolts. The telescopic device 2 is mounted on a first mounting bracket 11 and the deflector device 3 is mounted on a second mounting bracket 12.
As shown in fig. 1 and fig. 2, the telescoping device 2 includes a push rod assembly 5 and a first driving assembly 6, the first driving assembly 6 includes a spiral push disc 61 and a driving motor 62, the spiral push disc 61 is disc-shaped, a connecting shaft 611 is integrally formed in the middle of the spiral push disc 61, and the central axis of the connecting shaft 611 is collinear with the central axis of the spiral push disc 61. Any end of the connecting shaft 611 is rotatably mounted on the mounting bracket 1 through a bearing, the other end of the connecting shaft 611 is rotatably connected with the first mounting bracket 11 through a bearing, and the spiral push disc 61 is in the first mounting bracket 11 and is in rotating fit with the first mounting bracket 11.
The driving motor 62 is mounted on the first mounting bracket 11 through a bolt, an output shaft of the driving motor 62 extends into the first mounting bracket 11 from outside to inside, the output shaft of the driving motor 62 is rotatably matched with the first mounting bracket 11, and the output shaft of the driving motor 62 is fixedly connected with one end of the connecting shaft 611 away from the mounting bracket 1 coaxially through the matching of a key and a groove. The driving motor 62 is started to drive the connecting shaft 611 to rotate, and further drive the spiral pushing disc 61 to rotate.
The spiral pushing disk 61 is provided with a sliding groove 612, the sliding groove 612 is arranged according to a spiral equation, the track of the sliding groove 612 is arc-shaped, any end of the sliding groove 612 is close to the peripheral side edge position of the spiral pushing disk 61, and the other end of the sliding groove 612 is close to the middle part of the spiral pushing disk 61. A sliding pin 613 is embedded in the sliding groove 612, and the sliding pin 613 is in sliding fit with the sliding groove 612. The push rod assembly 5 comprises a telescopic push rod 51 and a telescopic pulling and inserting push rod 52, the axis of the telescopic push rod 51 is perpendicular to the axis of the connecting shaft 611, the telescopic push rod 51 and the telescopic pulling and inserting push rod 52 are connected through a bolt in a coaxial and fixed manner, the telescopic push rod 51 and the telescopic pulling and inserting push rod 52 can rotate relatively, and one end, far away from the telescopic pulling and inserting push rod 52, of the telescopic push rod 51 is extended into the first mounting bracket 11 and is in sliding fit with the first mounting bracket 11.
The sliding pin 613 penetrates through one end of the telescopic push rod 51 in the first mounting bracket 11 and is in interference fit with the telescopic push rod. When the spiral pushing disk 61 rotates, the sliding pin 613 is slidably engaged with the sliding groove 612, and the first mounting bracket 11 is slidably engaged with the telescopic push rod 51, so that the telescopic push rod 51 performs a stable telescopic motion.
The shape of the duck control surface 4 is approximately triangular, the root of the duck control surface 4 is provided with a sliding groove 41, one end of the telescopic pulling and inserting push rod 52, which is far away from the telescopic push rod 51, is integrally formed with a shifting fork end 53, and a transmission pin 531 is connected between the shifting fork end 53 and the sliding groove 41. When the telescopic push rod 51 makes telescopic motion, the duck control surface 4 is driven to make telescopic motion through the telescopic pull-plug push rod 52, so that the duck control surface 4 can extend out of or retract into the aircraft.
As shown in fig. 1 and 3, the deflecting device 3 includes a deflecting shaft sleeve 31 and a second driving assembly 7, the deflecting shaft sleeve 31 and the second driving assembly 7 are both installed on the second installation support 12, the deflecting shaft sleeve 31 is in rotational sliding fit with the second installation support 12, the central axis of the deflecting shaft sleeve 31 is parallel to the central axis of the telescopic push rod 51, and one end of the deflecting shaft sleeve 31 far away from the second installation support 12 is fixedly connected with the duck rudder surface 4 through a pin.
The second drive assembly 7 comprises a turbine disc 71, a turbine rod 72 and a yaw motor 73, the yaw sleeve 31 is coaxially connected to the middle of the turbine disc 71 by a key and slot engagement which prevents relative rotation between the yaw sleeve 31 and the turbine disc 71. The eccentric shaft sleeve 31 is rotatably mounted in the second mounting bracket 12 through a bearing, the central axis of the turbine rod 72 is parallel to the central axis of the connecting shaft 611, the turbine rod 72 is rotatably mounted in the second mounting bracket 12 through a bearing, and the turbine rod 72 is engaged with the turbine disc 71.
The deflection motor 73 is fixed on the second mounting bracket 12 through a bolt, an output shaft of the deflection motor 73 extends into the second mounting bracket 12 and is in running fit with the second mounting bracket 12, and the output shaft of the deflection motor 73 is coaxially and fixedly connected with one end of the turbine rod 72, which is far away from the mounting bracket 1, through the fit of a key and a groove. The deflection motor 73 is started to drive the turbine rod 72 to rotate, so as to drive the turbine disc 71 and the deflection shaft sleeve 31 to rotate, and the deflection motion of the duck rudder surface 4 is realized.
As shown in fig. 1, 2 and 3, the telescopic push rod 51 and the telescopic plugging push rod 52 are both installed in the eccentric shaft sleeve 31 and spaced from the eccentric shaft sleeve, and the telescopic push rod 51 is not driven to rotate when the eccentric shaft sleeve 31 rotates; when the telescopic push rod 51 and the telescopic plugging push rod 52 push the duck rudder surface 4 to do telescopic motion, the deflection shaft sleeve 31 and the duck rudder surface 4 do telescopic motion together.
Principle of operation
Before the aircraft gives deflection and before the aircraft gives a deflection instruction, the duck rudder surface 4 is in a contraction state; after receiving a working instruction, the driving motor 62 is started to drive the spiral pushing disc 61 to rotate, and the duck rudder is pushed to expand through the cooperation of the telescopic push rod 51 and the telescopic pulling and inserting push rod 52; after the duck rudder surface is unfolded in place, the deflection motor 73 is started, and drives the turbine rod 72 to rotate, so that the duck rudder surface 4 is driven to deflect through the turbine disc 71 and the deflection shaft sleeve 31; when the duck rudder needs to be contracted again, the driving motor 62 drives the spiral pushing disc 61 to rotate, the telescopic push rod 51 and the telescopic pulling and inserting push rod 52 are controlled to move, the duck rudder surface 4 is pulled, and the duck rudder is pulled back to be in a contracted state; therefore, smooth contraction, expansion and deflection of the duck rudder of the aircraft are ensured, and the control precision of the flight path of the aircraft is improved.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, are not to be construed as limiting the present application.
The foregoing description has described specific embodiments of the present invention. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (7)
1. A telescopic duck rudder mechanism is characterized by comprising an installation bracket (1), a telescopic device (2), a deflection device (3) and a duck rudder surface (4) which are installed in an aircraft, wherein a first installation bracket (11) and a second installation bracket (12) are fixed on the installation bracket (1);
the telescopic device (2) comprises a push rod assembly (5) and a first driving assembly (6) used for driving the push rod assembly (5) to do telescopic motion, the push rod assembly (5) and the first driving assembly (6) are both installed on a first installation support (11), the push rod assembly (5) is in sliding fit with the first installation support (11), and one end, far away from the first installation support (11), of the push rod assembly (5) is fixedly connected with the duck control surface (4);
the deflection device (3) comprises a deflection shaft sleeve (31) and a second driving assembly (7) for driving the deflection shaft sleeve (31) to rotate, the deflection shaft sleeve (31) and the second driving assembly (7) are both installed on a second installation support (12), the deflection shaft sleeve (31) is in rotating sliding fit with the second installation support (12), and one end, far away from the second installation support (12), of the deflection shaft sleeve (31) is fixedly connected with the duck rudder surface (4);
first drive assembly (6) are including spiral push disk (61) and be used for driving spiral push disk (61) pivoted driving motor (62), spiral push disk (61) rotate to erect in first installing support (11), sliding tray (612) have been seted up on spiral push disk (61), the orbit of sliding tray (612) is the arc, just the week side border position of sliding tray (61) is close to the one end of sliding tray (612), the central point that the other end of sliding tray (612) is close to spiral push disk (61) puts, the sliding tray (612) internal sliding is provided with slide pin (613), slide pin (613) and push rod assembly (5) fixed connection.
2. The telescopic duck rudder mechanism as claimed in claim 1, wherein a connecting shaft (611) is coaxially arranged on the spiral pushing disk (61), the connecting shaft (611) is rotatably erected in the first mounting bracket (11) through a bearing, the driving motor (62) is fixedly mounted on the first mounting bracket (11), and an output shaft of the driving motor (62) is fixedly connected with the connecting shaft (611).
3. The telescopic duck rudder mechanism according to claim 1, wherein the push rod assembly (5) comprises a telescopic push rod (51) and a telescopic plugging push rod (52), the telescopic push rod (51) and the telescopic plugging push rod (52) are coaxially and fixedly connected through screws, one end of the telescopic push rod (51), which is far away from the telescopic plugging push rod (52), extends into the first mounting bracket (11) and is in sliding fit with the first mounting bracket, and one end of the telescopic plugging push rod (52), which is far away from the telescopic push rod (51), is fixedly connected with the duck rudder surface (4).
4. The telescopic duck rudder mechanism according to claim 3, wherein one end of the telescopic pulling and inserting push rod (52) far away from the telescopic push rod (51) is provided with a shifting fork end (53), the root of the duck rudder surface (4) is provided with a sliding groove (41), and a transmission pin (531) is connected between the shifting fork and the sliding groove (41).
5. The telescopic duck rudder mechanism as claimed in claim 3, wherein the telescopic push rod (51) and the telescopic plugging push rod (52) are both mounted in the deflection shaft sleeve (31).
6. The telescopic duck rudder mechanism as claimed in claim 1, wherein the second driving assembly (7) comprises a turbine disc (71), a turbine rod (72) and a deflection motor (73), the turbine disc (71) and the turbine rod (72) are both rotatably erected on the second mounting bracket (12), the turbine disc (71) is meshed with the turbine rod (72), the deflection motor (73) is mounted on the second mounting bracket (12), an output shaft of the deflection motor (73) is coaxially and fixedly connected with the turbine rod (72), and the deflection shaft sleeve (31) is coaxially connected with the turbine disc (71) through a key.
7. The telescopic duck rudder mechanism according to claim 1, wherein the shape of the duck rudder surface (4) is approximately triangular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011636799.5A CN112829924B (en) | 2020-12-31 | 2020-12-31 | Retractable duck steering mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011636799.5A CN112829924B (en) | 2020-12-31 | 2020-12-31 | Retractable duck steering mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112829924A CN112829924A (en) | 2021-05-25 |
| CN112829924B true CN112829924B (en) | 2022-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011636799.5A Active CN112829924B (en) | 2020-12-31 | 2020-12-31 | Retractable duck steering mechanism |
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| Country | Link |
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| CN (1) | CN112829924B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115096146B (en) * | 2022-07-18 | 2023-07-18 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB326757A (en) * | 1929-06-05 | 1930-03-20 | Albert Eustace Short | Improvements in amphibian aircraft |
| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| CN111855131A (en) * | 2020-04-28 | 2020-10-30 | 中国航天空气动力技术研究院 | Remote rudder controlled wind tunnel free flight test device and method |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6543720B2 (en) * | 1998-10-13 | 2003-04-08 | Paul Vincent Ladd | Directional control and aerofoil system for aircraft |
| SE519764C2 (en) * | 2000-08-31 | 2003-04-08 | Bofors Defence Ab | Canardfenaggregat |
| FR2864613B1 (en) * | 2003-12-31 | 2006-03-17 | Giat Ind Sa | DEVICE FOR DEPLOYING AND DRIVING GOVERNS OF A PROJECTILE |
| IL241201B (en) * | 2015-09-06 | 2019-11-28 | Uvision Air Ltd | Foldable wings for an unmanned air vehicle |
| CN109625244B (en) * | 2018-12-24 | 2021-08-17 | 湖南云箭集团有限公司 | Foldable sweepforward rudder wing assembly |
-
2020
- 2020-12-31 CN CN202011636799.5A patent/CN112829924B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB326757A (en) * | 1929-06-05 | 1930-03-20 | Albert Eustace Short | Improvements in amphibian aircraft |
| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| CN111855131A (en) * | 2020-04-28 | 2020-10-30 | 中国航天空气动力技术研究院 | Remote rudder controlled wind tunnel free flight test device and method |
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| CN112829924A (en) | 2021-05-25 |
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