CN117842354A - Retractable longitudinal shaking reducing device - Google Patents
Retractable longitudinal shaking reducing device Download PDFInfo
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- CN117842354A CN117842354A CN202311785325.0A CN202311785325A CN117842354A CN 117842354 A CN117842354 A CN 117842354A CN 202311785325 A CN202311785325 A CN 202311785325A CN 117842354 A CN117842354 A CN 117842354A
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- retractable
- pitch
- reducing device
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- hydrofoil
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- 230000007246 mechanism Effects 0.000 claims abstract description 53
- 230000009467 reduction Effects 0.000 abstract description 29
- 238000005096 rolling process Methods 0.000 abstract description 17
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 14
- 238000007667 floating Methods 0.000 abstract description 3
- 230000033001 locomotion Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 3
- 230000004308 accommodation Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
A retractable pitching reduction device belongs to the technical field of pitching reduction. The invention solves the problem that the existing universal anti-rolling device is not suitable for amphibious aircraft bodies. The T-shaped wing main body comprises a support column, a first rotating shaft fixedly arranged at one end of the support column and a pair of hydrofoils rotatably arranged at two sides of the first rotating shaft, wherein the pair of hydrofoils are arranged in a T shape with the support column in an unfolding state, the other end of the support column is rotatably arranged at the bow of an airplane through a second rotating shaft, the rotation of the support column around the second rotating shaft is controlled through a first driving mechanism, and the rotation of the two hydrofoils around the first rotating shaft is correspondingly controlled through two second driving mechanisms. The first driving mechanism and the two second driving mechanisms realize the gradual folding and unfolding function of the T-shaped wing main body. The retraction and the extension of the two hydrofoils are realized through two second driving mechanisms; the support column is retracted by the first driving mechanism. The retractable pitch reducing device has smaller influence on the navigation resistance of the water surface floating body.
Description
Technical Field
The invention relates to a retractable pitching reduction device, and belongs to the technical field of pitching reduction.
Background
The amphibious aircraft inevitably generates various sways in stormy waves, namely roll, pitch, yaw, roll, heave and heave. The rocking motion, in addition to producing linear motion in the aeronautical direction, can also cause the production of angular velocity, varying angular acceleration and linear acceleration, which can be unsafe factors when an amphibious aircraft slides in waves. When the amphibious aircraft is designed to move, the reduction of heave, pitch and roll motions is particularly important, if the swing amplitude is large, serious influence can be caused on the navigation of the amphibious aircraft in waves, such as poor comfort and low working efficiency of personnel, and the large swing acceleration can increase additional resistance to influence the performance of airborne equipment, damage the body structure and even endanger the life safety of passengers.
Compared with rolling movement, the amphibious aircraft has larger pitching moment, the rolling reduction device is required to generate larger lifting force to compensate and offset the pitching moment, and the problems of volume limitation of the rolling reduction device, increased sailing resistance caused by an additional device and the like in actual shipping are considered, so that a pitching reduction method which is high in efficiency and capable of being practically applied is not available. After the roll stabilization technology has been very mature, pitch stabilization is an urgent need to address the problem of improving the wave resistance of amphibious aircraft.
Disclosure of Invention
The invention aims to solve the technical problems and further provides a retractable pitching reduction device.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a receive and release type subtracts pitching device, includes T type wing main part, first actuating mechanism and two second actuating mechanism, wherein T type wing main part includes the pillar, installs firmly in the first pivot of pillar one end and rotates a pair of hydrofoil of installing in first pivot both sides, a pair of under the hydrofoil expansion state with the pillar is T font and arranges, and the other end of pillar is installed at the aircraft bow through the rotation of second pivot, through the rotation of first actuating mechanism control pillar around the second pivot, corresponds the rotation of two hydrofoils of control around first pivot through two second actuating mechanism.
Further, the first driving mechanism comprises a guide rail, a sliding block and a connecting rod, wherein the guide rail is fixedly arranged at the bow of the airplane, the sliding block is arranged on the guide rail in a sliding manner through motor driving, and two ends of the connecting rod are respectively connected with the sliding block and the support column.
Further, the connecting rod is in rotary connection with the sliding block and the side face of the supporting column.
Further, the second driving mechanism is a unidirectional telescopic mechanism, and two ends of the second driving mechanism are respectively connected with the support column and the hydrofoil.
Further, the second driving mechanism is a hydraulic cylinder or an electric telescopic rod.
Further, one end of the second driving mechanism is rotatably connected with the hydrofoil.
Further, the other end of the second driving mechanism is fixedly connected with the support column.
Further, the axial direction of the second rotating shaft is arranged along the width direction of the machine body.
Further, the guide rail is arranged obliquely upwards along the length direction of the airplane.
The amphibious aircraft adopting the retractable type pitching reduction device comprises an amphibious aircraft body, wherein a containing cabin is formed below the bow of the amphibious aircraft body, the containing cabin is provided with a cabin door, the cabin door and the outer contour of the amphibious aircraft body are arranged along with the shape, when the retractable type pitching reduction device is in a retracted state, the retractable type pitching reduction device is positioned in the containing cabin, the cabin door is normally closed, when the retractable type pitching reduction device is in an expanded state, the cabin door is normally open, and the retractable type pitching reduction device extends out of the containing cabin.
Compared with the prior art, the invention has the following effects:
according to the invention, the T-shaped wing is used as the anti-rolling attachment to be installed on the bow of the body of the amphibious aircraft, so that the anti-pitching requirement of the amphibious aircraft can be met.
The first driving mechanism and the two second driving mechanisms realize the gradual folding and unfolding function of the T-shaped wing main body. Wherein the retraction of the two hydrofoils is mainly realized by the extension and retraction of the two second driving mechanisms; the support column is mainly retracted and released through the first driving mechanism.
Compared with the prior art, the retractable pitching reducing device is adopted as the pitching reducing attachment body, so that the influence on the navigation resistance of the water surface floating body is smaller. The T-shaped wing main body is in a complete unfolding state in the whole anti-rolling process, a stable triangle structure is formed between the hydrofoil and the support column of the second driving mechanism in the state, and certain strength support is provided for the whole anti-rolling attachment body in the water outlet and water inlet and wave sliding process of the amphibious aircraft, so that the durability of the anti-rolling attachment body is further enhanced.
Drawings
FIG. 1 is a schematic perspective view of a retractable pitch-reducing device;
FIG. 2 is a schematic side view of a retracting pitch-reducing device (hydrofoil semi-stowed state);
FIG. 3 is a schematic view of the installation location of a retractable pitch-reducing device on an amphibious aircraft;
FIG. 4 is a schematic view of a semi-stowed post;
FIG. 5 is a schematic view of the fully stowed position of the support post;
fig. 6 is a schematic view of the roll reduction principle of the retractable pitch reduction device.
In the figure:
1. a T-wing body; 11. a support post; 12. a first rotating shaft; 13. a hydrofoil; 131. an inclined plane; 21. a guide rail; 22. a slide block; 23. a connecting rod; 3. a second driving mechanism; 4. a second rotating shaft; 5. a connecting rod; 100. a bow; 101. an amphibious aircraft body.
Detailed Description
The technical solutions of the embodiments of the present invention will be clearly and completely described with reference to fig. 1 to 6, and it is apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
It should be noted that, the descriptions of the directions of "left", "right", "upper", "lower", "top", "bottom", and the like of the present invention are defined based on the relation of orientations or positions shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the structures must be constructed and operated in a specific orientation, and thus, the present invention should not be construed as being limited thereto. In the description of the present invention, the meaning of "plurality" is two or more unless specifically defined otherwise.
In the description of the present invention, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The first embodiment is as follows: referring to fig. 1 to 6, a retractable pitch reducing device is described in this embodiment, and the pitch reducing device includes a T-shaped wing body 1, a first driving mechanism and two second driving mechanisms 3, where the T-shaped wing body 1 includes a strut 11, a first rotating shaft 12 fixedly installed at one end of the strut 11, and a pair of hydrofoils 13 rotatably installed at two sides of the first rotating shaft 12, where the pair of hydrofoils 13 are arranged in a T-shape with the strut 11 in a deployed state, and the other end of the strut 11 is rotatably installed at a bow 100 of an aircraft through the second rotating shaft 4, and the rotation of the strut 11 around the second rotating shaft 4 is controlled through the first driving mechanism, and the rotation of the two hydrofoils 13 around the first rotating shaft 12 is correspondingly controlled through the two second driving mechanisms 3.
The amphibious aircraft body has the special appearance characteristic of front width and back shrinkage, and the universal anti-rolling attachment device is difficult to use. The invention selects the T-shaped wing as the anti-rolling attachment body to be arranged on the bow 100 of the body of the amphibious aircraft, so as to meet the anti-pitching requirement of the amphibious aircraft.
Compared with the prior art, the retractable pitching reducing device is adopted as the pitching reducing attachment body, so that the influence on the navigation resistance of the water surface floating body is smaller. The T-shaped wing main body 1 is in a fully unfolded state in the whole anti-rolling process, a stable triangle structure is formed among the second driving mechanism 3, the hydrofoil 13 and the strut 11 in the state, and certain strength support is provided for the whole anti-rolling attachment body in the water outlet and water inlet process and the wave sliding process of the amphibious aircraft, so that the durability of the anti-rolling attachment body is further enhanced.
To accommodate the retractable pitch-reducing device, accommodation chambers equipped with cabin doors are respectively provided on both sides of the lower interior of the aircraft bow 100. In the folding state of the folding and unfolding type longitudinal reduction device, the device is integrally arranged in the accommodating cabin, and the cabin door is closed; in the deployed state of the retractable pitch-reducing device, the door is normally open, the T-wing body 1 extends out of the accommodation compartment, and the pair of hydrofoils 13 are deployed.
The first driving mechanism and the two second driving mechanisms 3 realize the gradual folding and unfolding function of the T-shaped wing main body 1. Wherein the retraction and extension of the two hydrofoils 13 are mainly realized by the extension and retraction of the two second driving mechanisms 3; the support 11 is stored and released mainly by the first drive mechanism.
A connecting rod 5 can be arranged between the second driving mechanism 3 and the hydrofoil 13, so that the hydrofoil 13 can be conveniently unfolded and folded.
Realization of the rolling reduction effect of the retractable type rolling reduction device:
when the retractable pitch reducing device is fully unfolded, the amphibious aircraft is dampened and performs sliding motion in waves. The direction of the water flow at the upper part of the hydrofoil 13 is at an angle to the upper surface of the hydrofoil 13, so that the water flow tends to move away from the hydrofoil 13 in the normal direction, and a low pressure is generated at the upper part of the hydrofoil 13. At the lower surface of the hydrofoil 13, the direction of the water flow is also angled from the lower surface of the hydrofoil 13, so that the water flow tends to approach the hydrofoil 13 along the surface normal, and the pressure at the bottom of the hydrofoil 13 increases. The lift force is generated by the pressure difference on the upper surface and the lower surface of the hydrofoil 13 due to the incoming flow, so that a longitudinal moment is provided to restrain heave and pitch motions of the amphibious aircraft, and the pitching reduction effect of the T-shaped wing main body 1 is realized.
The first driving mechanism comprises a guide rail 21, a sliding block 22 and a connecting rod 23, wherein the guide rail 21 is fixedly arranged on the bow 100 of the airplane, the sliding block 22 is arranged on the guide rail 21 in a sliding manner through motor driving, and two ends of the connecting rod 23 are respectively connected with the sliding block 22 and the strut 11. The guide rail 21 is fixedly mounted in the receiving compartment of the aircraft bow 100. The slide block 22 is driven by a motor to work, and the slide block 22 moves along the straight line of the guide rail 21 to drive the support 11 to rotate around the second rotating shaft 4, so that the support 11 and the hydrofoil 13 connected to one end of the support 11 are retracted into the accommodating cabin.
The connecting rod 23 is rotatably connected with the sliding block 22 and the connecting rod 23 is rotatably connected with the side face of the supporting column 11. So designed, the strut 11 can smoothly rotate around the second rotating shaft 4 when the slide block 22 moves linearly.
The second driving mechanism 3 is a unidirectional telescopic mechanism, and two ends of the second driving mechanism are respectively connected with the strut 11 and the hydrofoil 13. So designed, rotation of the hydrofoil 13 about the first axis of rotation 12 is facilitated.
The second driving mechanism 3 is a hydraulic cylinder or an electric telescopic rod.
One end of the second driving mechanism 3 is rotatably connected with the hydrofoil 13. So designed, the hydrofoil 13 can smoothly rotate around the first rotating shaft 12 when the second driving mechanism 3 acts.
The other end of the second driving mechanism 3 is fixedly connected with the support 11.
A bevel 131 is formed on a side surface of the pair of foils 13, which is close to the strut 11, at an opposite end portion thereof, and when the foils 13 are retracted in the direction of the strut 11, the bevel 131 is bonded to the side surface of the strut 11. By machining the inclined plane 131 on the hydrofoil 13, interference with the side surface of the strut 11 when the hydrofoil 13 is retracted is effectively prevented, and smooth retraction of the hydrofoil 13 is facilitated.
The axial direction of the second rotating shaft 4 is set along the width direction of the machine body. So designed, the hydrofoil 13 can rotate under the action of the rotating shaft through the support 11, and when the hydrofoil rotates anticlockwise by a small angle, the anti-rolling attachment body can be separated from the water surface.
The guide rail 21 is disposed obliquely upward in the longitudinal direction of the aircraft. By the design, the hydrofoil 13 and the strut 11 can be folded towards the bow of the airplane, so that the aerodynamic interference of the anti-rolling attachment body on the airplane during the air flight is reduced.
The working process comprises the following steps:
when the amphibious aircraft has water demand, the cabin door of the accommodating cabin is opened, and the retractable pitching reduction device is gradually changed from a retracted state to an extended state; when the amphibious aircraft has a water separation requirement, the retractable pitching reducing device is gradually changed from the unfolding state to the folding state, and the cabin door is closed after the amphibious aircraft is completely folded.
Taking the retracting process of the retracting type longitudinal reduction device as an example, the following concrete description is given:
firstly, the second driving mechanism 3 contracts, the hydrofoil 13 is pulled to rotate around the first rotating shaft 12 until the upper surface inclined plane 131 of the hydrofoil 13 is attached to the side surface of the supporting column 11, and the retraction work of the hydrofoil 13 is completed;
and then the motor drives the sliding block 22 to move along the guide rail 21, the sliding block 22 drives the connecting rod 23 to move, and then the support 11 is driven to rotate around the second rotating shaft 4 until the retractable pitch reducing device is completely retracted into the accommodating cabin of the amphibious aircraft, the cabin door is closed, and the integral retraction work of the retractable pitch reducing device is completed.
The second embodiment is as follows: the embodiment will be described with reference to fig. 1 to 6, in which the amphibious aircraft adopting the retractable pitch reduction device includes an amphibious aircraft body 101, a receiving cabin is provided below a bow 100 of the amphibious aircraft body 101, the receiving cabin is provided with a cabin door, the cabin door and the external contour of the amphibious aircraft body 101 are set along with the shape, when the retractable pitch reduction device is in a retracted state, the retractable pitch reduction device is located in the receiving cabin, the cabin door is normally closed, when the retractable pitch reduction device is in an extended state, the cabin door is normally opened, and the retractable pitch reduction device extends out of the receiving cabin. The amphibious aircraft body 101 in the present invention is a prior art, and the specific structural components thereof will not be described herein. According to the invention, the T-shaped wings are gradually retracted and placed in the amphibious aircraft body, and the cabin door and the outer contour of the amphibious aircraft body 101 are arranged along the shape, so that the original pneumatic appearance of the amphibious aircraft is not damaged in the retracted state of the retractable longitudinal reduction and adjustment device, and adverse effects on the flying performance of the amphibious aircraft during air flight are avoided. The characteristics of the hull appearance of the amphibious aircraft body are fully considered, and the pitching reduction requirements of most amphibious aircraft can be met. The closing and opening of the door is controlled by the aircraft main control system, and the structure for realizing the closing and opening actions is the same as the structure of the aircraft landing gear door, and will not be described here again.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (10)
1. A retractable pitch reducing device, characterized in that: including T type wing main part (1), first actuating mechanism and two second actuating mechanism (3), wherein T type wing main part (1) include pillar (11), install first pivot (12) and the rotation of pillar (11) one end install a pair of hydrofoil (13) in first pivot (12) both sides, a pair of hydrofoil (13) under the state of expanding be T font arrangement with pillar (11), the other end of pillar (11) is installed in aircraft bow (100) through second pivot (4) rotation, through the rotation of first actuating mechanism control pillar (11) around second pivot (4), correspond the rotation of control two hydrofoils (13) around first pivot (12) through two second actuating mechanism (3).
2. A retractable pitch-reducing device as defined in claim 1, wherein: the first driving mechanism comprises a guide rail (21), a sliding block (22) and a connecting rod (23), wherein the guide rail (21) is fixedly arranged on the bow part (100) of the airplane, the sliding block (22) is arranged on the guide rail (21) in a sliding manner through motor driving, and two ends of the connecting rod (23) are respectively connected with the sliding block (22) and the supporting column (11).
3. A retractable pitch-reducing device as defined in claim 2, wherein: the connecting rod (23) is rotatably connected with the sliding block (22) and the connecting rod (23) is rotatably connected with the side surface of the support (11).
4. A retractable pitch-reducing device as defined in claim 1, wherein: the second driving mechanism (3) is a unidirectional telescopic mechanism, and two ends of the second driving mechanism are respectively connected with the support column (11) and the hydrofoil (13).
5. The retractable pitch-reducing device of claim 4, wherein: the second driving mechanism (3) is a hydraulic cylinder or an electric telescopic rod.
6. A retractable pitch reducing device as defined in claim 4 or 5, wherein: one end of the second driving mechanism (3) is rotationally connected with the hydrofoil (13).
7. The retractable pitch-reducing device of claim 6, wherein: the other end of the second driving mechanism (3) is fixedly connected with the support column (11).
8. A retractable pitch-reducing device as defined in claim 1, wherein: the axis direction of the second rotating shaft (4) is arranged along the width direction of the machine body.
9. A retractable pitch-reducing device as defined in claim 2, wherein: the guide rail (21) is arranged obliquely upwards along the length direction of the airplane.
10. An amphibious aircraft employing a retractable pitch-reducing device as claimed in any one of claims 1 to 9, wherein: including amphibious aircraft body (101), hold the cabin has been seted up to amphibious aircraft body (101) bow (100) below, hold the cabin and be provided with the hatch door, just hatch door and amphibious aircraft body (101) external profile follow-up setting, when the receipts put and subtract the pitch device to pack up the state, it is located and holds the cabin, and the hatch door normal close, and receive and put and subtract the pitch device to expand the state, the hatch door normal open, receive and put and subtract the pitch device to stretch out and hold the cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311785325.0A CN117842354A (en) | 2023-12-25 | 2023-12-25 | Retractable longitudinal shaking reducing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311785325.0A CN117842354A (en) | 2023-12-25 | 2023-12-25 | Retractable longitudinal shaking reducing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117842354A true CN117842354A (en) | 2024-04-09 |
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ID=90528106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311785325.0A Pending CN117842354A (en) | 2023-12-25 | 2023-12-25 | Retractable longitudinal shaking reducing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117842354A (en) |
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2023
- 2023-12-25 CN CN202311785325.0A patent/CN117842354A/en active Pending
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