CN110576970A - A hydrofoil and airbag composite water surface take-off and landing device - Google Patents

Abstract

A hydrofoil and airbag composite water surface take-off and landing device, including the following: (1) at least one hydrofoil, and a hydrofoil retractable device; (2) at least one airbag, and an airbag inflation and deflation device; (3) The airbag includes a flexible wall. When the aircraft is gliding at high speed on the water surface, the hydrofoil is used to provide the dynamic lifting force of the aircraft. The strength of the hydrofoil can completely resist the huge hydraulic impact; Keep a certain distance from the water surface to avoid water ingress into the engine and corrosion of the body; when the aircraft flies in the air at high speed, the above-mentioned hydrofoils and airbags are all retracted, which will not increase the additional windward area of the aircraft.

Description

A hydrofoil and airbag composite water surface take-off and landing device

technical field

The invention belongs to the field of water take-off and landing devices for watercraft, and in particular relates to a hydrofoil and airbag composite water surface take-off and landing device.

Background technique

The seaplane uses the hull or buoys under the belly to take off, land and park on the water. Its main advantages are that it can be used on vast rivers, lakes, rivers, and sea waters. It has good safety, economical ground support facilities, and unlimited aircraft tonnage. Therefore, it can be widely used in maritime patrol, anti-submarine, and rescue. The main disadvantages of seaplanes are: affected by the shape of the hull or external buoys, the weight of the fuselage is large, and the aerodynamic resistance is large. Therefore, in terms of flight speed, cruising range, and fuel economy, they cannot compare with land-based aircraft. For example, China's most advanced seaplane AG600 has a maximum level flight speed of 500 km/h, a maximum flight range of 4,500 km, and a service ceiling of 6,000 meters, while China's most advanced land takeoff and landing transport aircraft Yun 20 has a maximum level flight speed of 920 km meters per hour, the maximum range is 7,800 kilometers, and the service ceiling is 13,000 meters.

In order to solve this problem, in the 1950s, Convair Corporation of the United States proposed a plan to use water skids (which can be understood as hydrofoils with a small aspect ratio)—"Sea Dart" (Sea Dart) water jet fighter. Its characteristics are: during the take-off and landing process, the water skid under the belly of the aircraft is stretched out, providing dynamic lifting force for the aircraft to make it slide on the water surface; during flight, the water skid is retracted, flush with the belly of the aircraft, and will not increase flight resistance. The problem is that when the aircraft is at a low taxiing speed or at a standstill, the water skid loses its lifting force, and a large part of the aircraft's volume is buried in the water. In order to solve the problem of water entering the engine intake and exhaust ports, the installation position of the engine needs to be raised, which causes the propulsion force of the engine to deviate from the center of gravity of the aircraft. During the rapid acceleration process, there will be a large force forcing the nose down. moment. On November 4, 1954, the "Sea Javelin" disintegrated in mid-air during a demonstration flight, killing the test pilot, and the immediate cause was this defect. The Chinese patent "Folding Inflatable Float and Seaplane Using the Folding Inflatable Float" (application number CN201110404181.0) proposes to use an inflatable buoy that can be inflated and deflated to solve the lifting force problem of the seaplane after it is stationary. Its characteristics are: using the folding bracket mechanism, it is located in the folding inflatable buoy, and its two ends are connected with the two ends of the hydraulic drive device to realize the folding and unfolding of the folding inflatable buoy; the skin is covered on the periphery of the folding bracket mechanism, and its The inside constitutes a closed space isolated from the outside world, which is used to shape the buoy when the folding support mechanism is unfolded; the inflation and deflation device is located outside the skin, and is used to charge and deflate the closed space formed by the skin. If this scheme is implemented, the following problems will arise: when the plane just lands or is close to take-off, the speed can reach more than 200 km/h, and the water has a huge impact on the buoy, which will cause the buoy composed of skin to face the danger of disintegration.

Contents of the invention

In order to solve the above-mentioned problems, the invention provides a hydrofoil and airbag composite water surface take-off and landing device, which solves three major problems at the same time: the hydraulic impact of the water vehicle when it is gliding at high speed on the water surface; providing the lifting force and lifting height when the water surface is still; The windward area when flying in the air.

A hydrofoil and airbag composite water surface take-off and landing device, comprising the following contents:

(1) At least one hydrofoil, and a hydrofoil retractable device; (2) At least one airbag, and an airbag inflation and deflation device; (3) The airbag includes a flexible wall.

The hydrofoil is airtightly combined with the flexible capsule wall, and the hydrofoil constitutes the rigid lower capsule wall of the airbag.

There is a wing groove, the inner contour of which is similar to the outer contour of the hydrofoil, and the hydrofoil can be embedded in the wing groove.

The wing grooves are airtightly combined with the flexible bladder wall, and the wing grooves constitute the rigid upper bladder wall of the airbag.

The hydrofoil retractable device includes a front hydraulic cylinder and a rear hydraulic cylinder, the lower end of the front hydraulic cylinder and the lower end of the rear hydraulic cylinder are connected to the inner surface of the hydrofoil; it also includes a Set of hydraulic control system.

The displacement of the rear hydraulic cylinder is greater than the displacement of the front hydraulic cylinder.

The airbag is divided into a plurality of independent chambers through a flexible diaphragm.

The composite water landing gear is installed under the belly of the aircraft.

The composite water landing gear is symmetrically installed under the wings of the aircraft.

When the aircraft is gliding at high speed on the water surface, the hydrofoil is used to provide the dynamic lifting force of the aircraft. The strength of the hydrofoil can completely resist the huge hydraulic impact; Keep a certain distance to avoid engine water ingress and body corrosion; when the aircraft flies in the air at high speed, the above-mentioned hydrofoils and airbags are all retracted, which will not increase the additional windward area of the aircraft.

Description of drawings

Fig. 1 is a schematic diagram of the hydrofoil and airbag composite water surface take-off and landing device in a retracted state-front view;

Fig. 2 is a schematic view of the hydrofoil and airbag composite water surface take-off and landing device in a retracted state-left view;

Fig. 3 is a schematic view of the hydrofoil and airbag composite water surface take-off and landing device in an open state-front view.

In the figure: 1. Aircraft; 2. Hydrofoil; 3. Airbag; 4. Bag wall; 5. Diaphragm; 6. Chamber; 7. Inner surface of hydrofoil; 8. Wing slot; 9. Front hydraulic cylinder; 10. Rear hydraulic cylinder; 11, landing gear compartment; 12, belly, 13, wing; 14, auxiliary buoy.

In the figure: 1. Aircraft; 2. Hydrofoil; 3. Airbag; 4. Bag wall; 5. Diaphragm; 6. Chamber; 7. Inner surface of hydrofoil; 8. Wing slot; 9. Front hydraulic cylinder; 10. Rear hydraulic cylinder; 11, landing gear compartment; 12, belly, 13, wing; 14, auxiliary buoy.

specific embodiment

The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

Fig. 1 ~ Fig. 3 have shown the embodiment of the present invention on a large transport plane.

The aircraft 1 retains the land landing gear, and the landing gear cabin 11 has built-in wheeled landing gear. Figures 1 to 2 show the state of the aircraft flying at high speed in the air. There is a folded hydrofoil 2 on the belly 12 (the water skid and the hydrofoil are collectively referred to as the hydrofoil in this manual), and its appearance is similar to that of the belly. 12 Smooth transitions without additional wind resistance.

Fig. 3 is a schematic diagram of an aircraft taxiing and stopping on water. For the convenience of expression, the flexible bag wall 4 is made transparent. At this time, the hydrofoil 2 is stretched out, and the air bag 3 is inflated. The front part of the hydrofoil inner surface 7 is connected with the lower end of the front hydraulic cylinder 9 , and the rear part of the hydrofoil inner surface 7 is connected with the lower end of the rear hydraulic cylinder 10 . The displacement of the rear hydraulic cylinder 10 is greater than the displacement of the front hydraulic cylinder 9. In this way, in the maximum opening state of the hydrofoil 2, the hydrofoil 2 has an inclination relative to the central axis of the aircraft, which can provide a large upward force when landing and taking off. water power. These two hydraulic cylinders are controlled by a set of hydraulic system, which is composed of hydraulic pump, solenoid valve, hydraulic pipeline and hydraulic controller, which are not expressed in the figure.

On the belly 12, there is a wing groove 8, the inner contour of which matches the outer contour of the hydrofoil 2. When the hydrofoil 2 is retracted, as shown in Figures 1 and 2, it can be embedded in the wing groove 8, so that the hydrofoil 2 The outer surface and the belly 12 of the smooth transition.

As shown in Fig. 3, an airbag 3 is also included, and the aircraft utilizes a set of inflation device to inflate and expand when the aircraft taxis on the water surface and stops. The periphery of the airbag 3 is a circle of flexible wall 4 , the wall 4 is airtightly combined with the inner surface of the hydrofoil 7 , and the hydrofoil 2 constitutes the rigid lower wall of the airbag 3 . The wing groove 8 is airtightly combined with the bag wall 4 , and the wing groove 8 constitutes the rigid upper bag wall of the airbag 3 . The interior of the airbag 3 is divided into a plurality of independent chambers 6 by a flexible diaphragm 5, so that even if there is air leakage in individual chambers, the aircraft can still be kept away from the water surface. The inflation and deflation of each chamber is realized by a set of inflation and deflation devices, including air pumps, air switching valves, air pipelines and pneumatic controllers, which are not shown in the figure.

In the embodiment shown in Fig. 1 to Fig. 3, the hydrofoil and airbag composite water surface take-off and landing device are installed below the belly 12 of the aircraft 1, below the wings 13, and auxiliary buoys 14 are symmetrically installed, for correcting the position of the aircraft 1 on the water surface. roll. The buoy 14 can also be replaced by the composite water surface take-off and landing device of the present invention to provide dynamic and static buoyancy. Or the positions of the belly 12 and the buoy 14 all use the device of the present invention to provide multi-point water support.

The hydrofoil 2 and the airbag 3 can also be separately arranged in different positions of the aircraft: for example, the hydrofoil is installed on the belly, while the airbag is installed on both sides of the wing, the height direction of the hydrofoil is lower, and the height direction of the airbag is upper. When the aircraft is gliding on the water surface at high speed, the hydrofoil contacts with the water to provide dynamic lifting force, and the airbag does not contact the water surface. When taxiing at low speed or standing still, the distance between the aircraft and the water surface decreases, and the airbags contact the water surface to provide static buoyancy.

In addition to being used for seaplanes, the present invention can also be popularized for other aircraft that take off and land on water, such as water ground effect aircraft and water ferry aircraft.

The above-mentioned embodiments only introduce some specific solutions for realizing the present invention, and do not include all the embodiments. Based on this embodiment and the ideas of the present invention, non-innovative modifications and variations made by other skilled persons to the above embodiments using known technologies all fall within the scope of protection required by the present invention.

Claims (9)

1. A hydrofoil and airbag composite water surface take-off and landing device, characterized in that: (1) at least one hydrofoil, and a hydrofoil retractable device; (2) at least one airbag, and the inflation and deflation of the airbag device; (3) the balloon includes a flexible wall. 2. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: said hydrofoil is airtightly combined with said flexible bag wall, and said hydrofoil constitutes the center of the airbag. Rigid inferior capsule wall. 3. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: there is a wing groove, the inner contour of which is similar to the outer contour of the hydrofoil, and the hydrofoil can be embedded in the in the wing slot. 4. A hydrofoil and airbag composite water surface take-off and landing device according to claim 3, characterized in that: said wing groove is airtightly combined with said flexible bag wall, and said wing groove constitutes an airbag rigid upper capsule wall. 5. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: said hydrofoil retractable device includes a front hydraulic cylinder and a rear hydraulic cylinder, and said front hydraulic cylinder The lower end of the cylinder is connected with the lower end of the rear hydraulic cylinder, connected with the inner surface of the hydrofoil, and also includes a hydraulic control system. 6. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: the displacement of the rear hydraulic cylinder is greater than the displacement of the front hydraulic cylinder. 7. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: the airbag is divided into a plurality of independent chambers by a flexible diaphragm. 8. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: the composite water landing gear is installed under the belly of the aircraft. 9. A hydrofoil and airbag composite water surface take-off and landing device according to claim 1, characterized in that: the composite water landing gear is symmetrically installed under the wing of the aircraft.