CN209814272U - Retractable seaplane hydrofoil type undercarriage device - Google Patents
Retractable seaplane hydrofoil type undercarriage device Download PDFInfo
- Publication number
- CN209814272U CN209814272U CN201822023499.4U CN201822023499U CN209814272U CN 209814272 U CN209814272 U CN 209814272U CN 201822023499 U CN201822023499 U CN 201822023499U CN 209814272 U CN209814272 U CN 209814272U
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- hydrofoil
- seaplane
- connecting rod
- motor
- gear
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Abstract
The utility model provides a retractable seaplane hydrofoil type undercarriage device, including fixing left fixed plate and the right fixed plate on the aircraft, be connected with rotation axis and hydrofoil between two fixed plates, install drive arrangement, two connecting rod slide mechanism and the fixing support that the structure is identical on left fixed plate and the right fixed plate respectively, fixing support between two fixed plates passes through the rotation axis and connects. The utility model discloses combine together the hydrofoil with the undercarriage and apply on the seaplane for the seaplane can move at the surface of water safely and steadily, the hydrodynamic lift that the hydrofoil produced simultaneously lifts the aircraft off the surface of water, thereby reduce the hydrodynamic drag that the surface of water slided before the aircraft takes off with the area of surface of water contact, the surface of water distance of taking off has been reduced, the required power of engine has been reduced, consequently compare with traditional seaplane and select for use lighter engine of weight for use, the performance of complete machine has been improved.
Description
Technical Field
The utility model relates to an aircraft undercarriage field specifically is a retractable seaplane hydrofoil type undercarriage device.
Background
A seaplane is an airplane capable of taking off and landing on water.
At present, a traditional seaplane is not provided with a special landing gear, usually, a step-off hull is designed at the bottom of a fuselage or a buoy is installed below the fuselage to meet the requirements of taking off or landing on water, but the taking-off process of the seaplane designed by the step-off hull or the buoy faces huge hydrodynamic resistance, the required power of an engine is increased when the seaplane takes off on the water, and the required power of the engine is greatly reduced when the seaplane takes off on the water compared with that when the seaplane slides on the water, so that the power of the engine is easily unmatched, the weight of the engine is increased, and the effective load of the seaplane is reduced.
The hydrodynamic resistance of the traditional seaplane can be reduced by additionally arranging hydrofoils when the seaplane takes off from the water surface. The principle of the hydrofoil generating lift is the same as that of the wing, but the density of water is about 800 times of that of air, so that a larger hydrodynamic lift can be generated by a smaller hydrofoil immersion area. When the seaplane with the hydrofoils slides on the water surface, the plane body can be lifted off the water surface without contacting with the water surface by virtue of the lifting force generated by the hydrofoils like a hydrofoil boat, so that the submerged area of the whole plane is reduced, the resistance is reduced, and the required power of an engine is reduced.
Conventional seaplanes have the following drawbacks:
1. and a special water surface landing gear device is not installed, and the taking-off and landing process is unstable.
2. The hydrodynamic resistance is large in the water surface takeoff process, the takeoff distance is long, and the requirement on the power of an engine is high
3. The power of the engine is not matched, so that the weight of the power system is larger.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve prior art's problem, provide a retractable seaplane hydrofoil type undercarriage device, combine together hydrofoil and undercarriage and use on seaplane for seaplane can be at the surface of water motion safely steadily, compares with traditional seaplane and can choose for use lighter engine of weight for use, has improved the performance of complete machine.
The utility model comprises a left fixed plate and a right fixed plate which are fixed on an airplane, a rotating shaft and a hydrofoil are connected between the two fixed plates, a driving device with the same structure, a two-connecting-rod slideway mechanism and a fixed support are respectively arranged on the left fixed plate and the right fixed plate, and the fixed support between the two fixed plates is connected through the rotating shaft;
the driving device comprises a worm wheel, a worm, a motor bracket, a first motor and a coupler, wherein the worm wheel is arranged on the rotating shaft, the first motor is fixed on the fixing plate through the motor bracket, the motor is connected with the worm through the coupler, the motor drives the worm to rotate, and the worm drives the rotating shaft to rotate through the worm wheel;
the two-connecting-rod slideway mechanism comprises a slideway, a first connecting rod, a second connecting rod and a sliding block, wherein one end of the second connecting rod is fixed on the worm wheel, the other end of the second connecting rod is connected with the hydrofoil, and the worm wheel rotates to drive the second connecting rod to rotate; the slide is fixed on the fixed plate, the slide block is installed on the slide and slides along the slide, one end of the first connecting rod is hinged with the slide block, and the other end of the first connecting rod is hinged with the position, close to the hydrofoil, of the second connecting rod. Because the length distance between the left and the right of the slide is limited, the two connecting rod slide mechanisms play a role in limiting the retraction height of the hydrofoil, and prevent the hydrofoil from being too high in recovery height or too low in lowering height.
Further improved, two ends of the hydrofoil are provided with hydrofoil control mechanisms for controlling the change of the attack angle of the hydrofoil. The hydrofoil control mechanism is installed in the protection casing, and the protection casing plays the effect that prevents hydrofoil control mechanism and water contact. The hydrofoil control mechanism comprises a first gear, a second motor and a second gear, wherein the first gear and the second gear are meshed with each other, the first gear is connected with the second motor, the second gear is connected with the hydrofoil, and the second motor drives the hydrofoil to rotate sequentially through the first gear and the second gear, so that the change of the attack angle of the hydrofoil is realized.
The hydrofoil is further improved by adopting an NACA2412 wing type, the hydrofoil is a main lifting force device of the device, the hydrofoil 4 slides in water to generate hydrodynamic lifting force, and after the airplane reaches a certain speed, the lifting force generated by the hydrofoil lifts the airplane away from the water surface, so that the contact area of the airplane and the water surface is reduced, and the hydrodynamic resistance of the airplane sliding on the water surface before taking off is reduced.
The utility model has the advantages that:
1. the hydrofoil and the landing gear are combined and applied to the seaplane, so that the seaplane can move on the water surface safely and stably, the airplane is lifted away from the water surface by the hydrodynamic lift force generated by the hydrofoil, the contact area of the airplane and the water surface is reduced, the hydrodynamic resistance of the airplane sliding on the water surface before the airplane takes off is reduced, the take-off distance on the water surface is reduced, and the required power of an engine is reduced.
2. The hydrofoil control mechanism is installed, the attack angle of the hydrofoil can be freely adjusted, so that the plane can move more stably on the water surface, and meanwhile, the hydrofoil control mechanism has stronger water surface wave adaptability and enlarges the takeoff condition of the seaplane.
3. In military terms, the seaplane provided with the retractable seaplane hydrofoil type landing gear device can perform seaplane rescue, anti-diving, investigation and naval vessel rapid striking capability by virtue of the rapid water surface motion capability and the seaplane take-off and landing capability of the seaplane. The seaplane provided with the retractable seaplane hydrofoil type undercarriage device can fly for a long time on the water surface due to small hydrodynamic resistance, so that sea-sweepers can be executed for assault battles.
4. In civilian aspect, the seaplane of installation retractable seaplane hydrofoil type undercarriage device has the function of seaplane and hydrofoil ship concurrently, is applicable to marine sightseeing, traffic transportation and flight experience between the island.
Drawings
FIG. 1 is a general view of a retractable seaplane hydrofoil type landing gear arrangement;
FIG. 2 is a schematic view of a retractable seaplane hydrofoil type landing gear assembly left drive train set;
FIG. 3 is a schematic view of a right drive train set of a retractable seaplane hydrofoil type landing gear assembly;
FIG. 4 is a schematic view of a wing angle of attack control mechanism for a retractable seaplane hydrofoil type landing gear assembly;
FIG. 5 is a view of the retractable seaplane hydrofoil type landing gear assembly with the hydrofoil in the submerged state;
figure 6 is a view of a retractable seaplane hydrofoil type landing gear assembly with the hydrofoil retracted.
In the figure, a left fixing plate 1, a rotating shaft 2, a right fixing plate 3, a hydrofoil 4, a slideway 5, a first connecting rod 6, a second connecting rod 7, a fixed support 8, a worm wheel 9, a worm 10, a motor bracket 11, a first motor 12, a coupler 13, a sliding block 14, a protective cover 15, a first gear 16, a second motor 17 and a second gear 18.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings.
The utility model discloses overall structure is as shown in figure 1, including fixing left fixed plate 1 and the right fixed plate 3 on the aircraft, be connected with rotation axis 2 and hydrofoil 4 between two fixed plates, install the identical drive mechanism group of structure on left fixed plate 1 and the right fixed plate 3 respectively, left side drive mechanism group is as shown in figure 2, right side drive mechanism group is as shown in figure 3. The transmission mechanism group comprises a driving device, two connecting rod slideway mechanisms and a fixed support 8, and the fixed support between the two fixed plates is connected through a rotating shaft 2;
the driving device comprises a worm wheel 9, a worm 10, a motor bracket 11, a first motor 12 and a coupling 13, wherein the worm wheel 9 is arranged on the rotating shaft 2, the first motor 12 is fixed on the fixing plate through the motor bracket 11, the first motor 12 is connected with the worm 10 through the coupling 13, the first motor 12 drives the worm 10 to rotate, and the worm 10 drives the rotating shaft 2 to rotate through the worm wheel 9;
the two-connecting-rod slideway mechanism comprises a slideway 5, a first connecting rod 6, a second connecting rod 7 and a sliding block 14, wherein one end of the second connecting rod 7 is fixed on a worm wheel 9, the other end of the second connecting rod 7 is connected with the hydrofoil 4, and the worm wheel 9 rotates to drive the second connecting rod 7 to rotate; the slide way 5 is fixed on the fixing plate, the slide block 14 is installed on the slide way 5 and slides along the slide way 5, one end of the first connecting rod 6 is hinged with the slide block 14, and the other end of the first connecting rod is hinged with the second connecting rod 7 close to the hydrofoil 4. Because the length distance between the left and the right of the slide way 5 is limited, the two connecting rod slide way mechanisms play a role in limiting the retraction height of the hydrofoil 4, and prevent the hydrofoil 4 from being too high in recovery height or too low in lowering height.
In further improvement, two ends of the hydrofoil 2 are provided with hydrofoil control mechanisms for controlling the change of the attack angle of the hydrofoil 2. The hydrofoil control mechanism is mounted in a protective cover 15, which protective cover 15 serves to prevent the hydrofoil control mechanism from coming into contact with water. The hydrofoil control mechanism is shown in fig. 4 and comprises a first gear 16, a second motor 17 and a second gear 18, wherein the first gear 16 and the second gear 18 are meshed with each other, the first gear 16 is connected with the second motor 17, the second gear 18 is connected with the hydrofoil 4, and the second motor 17 drives the hydrofoil 4 to rotate sequentially through the first gear 16 and the second gear 18, so that the change of the attack angle of the hydrofoil 4 is realized.
Further improved, the hydrofoil 4 adopts an NACA2412 wing shape, the hydrofoil 4 is a main lifting force device of the device, the hydrofoil 4 slides in water to generate hydrodynamic lifting force, after the airplane reaches a certain speed, the lifting force generated by the hydrofoil 4 lifts the airplane away from the water surface, and the contact area of the airplane and the water surface is reduced, so that the hydrodynamic resistance of the water surface sliding before the airplane takes off is reduced.
Fig. 5 is a view of the underwater state of the hydrofoil of the retractable seaplane hydrofoil type landing gear device, which is mainly characterized in that the slide block 14 moves to the rightmost end, and the hydrofoil 4 is under the water surface.
Fig. 6 is a view showing the retraction state of the hydrofoil of the retractable seaplane hydrofoil type landing gear device, which is mainly characterized in that the slide block 14 moves to the leftmost end, and the hydrofoil 4 is at the highest end and is retracted into the fuselage. When the device is in a state shown in figure 6, the hydrofoil 4 is in an underwater environment, when the aircraft takes off, the hydrofoil 4 is separated from the water surface, at this time, the hydrofoil 4 needs to be recovered into the aircraft body, at this time, the motor 12 is started, and when the aircraft takes off from the left to the right, the motor 12 rotates anticlockwise to drive the worm 10 to rotate anticlockwise, the worm 10 rotates clockwise to drive the worm wheel 9 meshed with the worm to rotate clockwise, the worm 9 rotates clockwise to drive the second connecting rod 7 to rotate clockwise, so that the sliding block 14 translates leftwards on the sliding way 5, the hydrofoil 4 is lifted upwards to gradually enter the aircraft body, and finally, the hydrofoil 4 is in a state. The lowering operation of the hydrofoil 4 is the reverse of the above process, and the principle is the same as that of the hydrofoil 4 recovery process.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The utility model discloses the concrete application way is many, and the above-mentioned only is the preferred embodiment of the utility model, should point out, to ordinary skilled person in this technical field, under the prerequisite that does not deviate from the utility model discloses the principle, can also make a plurality of improvements, and these improvements also should be regarded as the utility model discloses a scope of protection.
Claims (5)
1. A retractable seaplane hydrofoil type undercarriage device is characterized in that: the airplane wing fixing device comprises a left fixing plate (1) and a right fixing plate (3) which are fixed on an airplane, a rotating shaft (2) and a hydrofoil (4) are connected between the two fixing plates, a driving device, two connecting rod slideway mechanisms and a fixed support (8) which are identical in structure are respectively installed on the left fixing plate (1) and the right fixing plate (3), and the fixed support between the two fixing plates is connected through the rotating shaft (2);
the driving device comprises a worm wheel (9), a worm (10), a motor support (11), a motor (12) and a coupler (13), wherein the worm wheel (9) is installed on the rotating shaft (2), the first motor (12) is fixed on the fixing plate through the motor support (11), the motor (12) is connected with the worm (10) through the coupler (13), the first motor (12) drives the worm (10) to rotate, and the worm (10) drives the rotating shaft (2) to rotate through the worm wheel (9);
the two-connecting-rod slideway mechanism comprises a slideway (5), a first connecting rod (6), a second connecting rod (7) and a sliding block (14), wherein one end of the second connecting rod (7) is fixed on a worm wheel (9), the other end of the second connecting rod is connected with the hydrofoil (4), and the worm wheel (9) rotates to drive the second connecting rod (7) to rotate; the slide way (5) is fixed on the fixing plate, the sliding block (14) is installed on the slide way (5) and slides along the slide way (5), one end of the first connecting rod (6) is hinged with the sliding block (14), and the other end of the first connecting rod is hinged with the second connecting rod (7) close to the hydrofoil (4).
2. A retractable seaplane hydrofoil type landing gear arrangement according to claim 1, wherein: and hydrofoil control mechanisms for controlling the change of the attack angle of the hydrofoil (4) are arranged at the two ends of the hydrofoil (4).
3. A retractable seaplane hydrofoil type landing gear arrangement according to claim 2, wherein: the hydrofoil control mechanism comprises a first gear (16), a second motor (17) and a second gear (18), wherein the first gear (16) and the second gear (18) are meshed with each other, the first gear (16) is connected with the second motor (17), the second gear (18) is connected with the hydrofoil (4), and the second motor (17) drives the hydrofoil (4) to rotate sequentially through the first gear (16) and the second gear (18).
4. A retractable seaplane hydrofoil type landing gear arrangement according to claim 2 or 3, wherein: the hydrofoil control mechanism is arranged in the protective cover (15).
5. A retractable seaplane hydrofoil type landing gear arrangement according to claim 1, wherein: the hydrofoil (4) adopts an NACA2412 airfoil profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822023499.4U CN209814272U (en) | 2018-12-04 | 2018-12-04 | Retractable seaplane hydrofoil type undercarriage device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822023499.4U CN209814272U (en) | 2018-12-04 | 2018-12-04 | Retractable seaplane hydrofoil type undercarriage device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209814272U true CN209814272U (en) | 2019-12-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822023499.4U Expired - Fee Related CN209814272U (en) | 2018-12-04 | 2018-12-04 | Retractable seaplane hydrofoil type undercarriage device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209814272U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109353503A (en) * | 2018-12-04 | 2019-02-19 | 南京航空航天大学 | Deployable and collapsible hydroski type landing gear |
-
2018
- 2018-12-04 CN CN201822023499.4U patent/CN209814272U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109353503A (en) * | 2018-12-04 | 2019-02-19 | 南京航空航天大学 | Deployable and collapsible hydroski type landing gear |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191220 Termination date: 20211204 |