CN219545069U - Double-wing tilting rotor craft applied to water surface take-off and landing - Google Patents

Abstract

The utility model discloses a double-wing tilting rotor craft applied to take-off and landing on water surface, which has the technical proposal that the double-wing tilting rotor craft comprises a machine body; a wing system disposed on the fuselage; a rotor system coupled to the wing system; the fixed pontoon is arranged on the wing system; the inflatable pontoon is arranged at the lower side of the machine body and used for providing buoyancy when the inflatable pontoon slides on water, and the inflatable pontoon is connected with the machine body through a telescopic rod. The utility model provides a double-wing tilting rotor aircraft applied to taking off and landing on a water surface, which aims to solve the problem that the risk of executing tasks in the water environment is too large due to huge economic loss and the like caused by the fact that the existing water aircraft is greatly influenced by the sea environment and a rescue helicopter cannot fly back down when falling into the water.

Description

Double-wing tilting rotor craft applied to water surface take-off and landing

Technical Field

The utility model relates to the technical field of aircraft technology and mechanical engineering, in particular to a double-wing tilting rotor aircraft applied to water surface take-off and landing.

Background

A surface aircraft refers to an aircraft capable of taxiing, takeoff, landing and berthing on the surface of the water. The seaplane is divided into a ship body type (i.e. a special-shaped body designed according to the water surface sliding requirement) and a pontoon type (the landing gear of the land plane is replaced by the pontoon). The seaplane has the advantages of being capable of being used on water surfaces of water areas such as wide rivers, lakes, rivers and seas, good in safety, economical in ground auxiliary facilities, unlimited in tonnage of the airplane and the like; but the main disadvantages are that the hull is not suitable for high-speed flight due to the limitation of the shape of the hull, the weight of the fuselage structure is heavy, the requirement on wave resistance is high, the maintenance is inconvenient and the manufacturing cost is high.

Therefore, with the development of helicopter technology, the task of marine rescue is mostly replaced by a helicopter, the helicopter has the characteristic of hovering, can hover above a rescue target during rescue without considering a complex sea surface wave environment, can vertically lift up and down, does not need to run off and land, can follow a rescue ship, and can carry out ocean rescue on a large ship equipped with a parking apron, and carry out various tasks such as reconnaissance, counterdiving, equipment throwing and recycling, transportation and the like. However, the helicopter on the sea surface has low flying speed and short voyage, and when the rescue helicopter hovers for rescue, the helicopter is pressed into the sea by vertical air flow above the sea surface, and the flying fails, so that the situation of a rescue object is realized.

The tiltrotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, and has the capability of vertical take-off, landing and hovering of a common helicopter and the capability of high-speed cruising flight of a turboprop. The helicopter has the same shape as a fixed wing aircraft, a small buoy can be additionally arranged at the tail end of a wing, and meanwhile, a mature rapid inflation buoy technology is used, so that the tiltrotor aircraft has the characteristics of a rescue helicopter and a water plane.

Because the device is mainly used in the marine environment, the device can quickly reach a task place, can fly slowly under the low-altitude condition at the task place, can meet the large carrying capacity of a single machine during rescue or random throwing and recycling, and has better stability in the flying process under the complex air flow environment above the sea.

In view of the above, there is a need for an aircraft capable of taking off and landing vertically and hovering in the air, with a large load, a high sailing speed, an excellent wind resistance, and a high stability, and capable of taking off and landing on the water surface.

Disclosure of Invention

Aiming at the defects of the prior art, the utility model aims to provide a double-wing tilting rotor craft applied to taking off and landing on the water surface, so as to solve the problem that the risk of executing tasks in the water environment is too large due to huge economic loss and the like caused by the fact that the existing water craft is greatly influenced by the sea environment and a rescue helicopter cannot fly down when falling into the water.

In order to achieve the above purpose, the present utility model provides the following technical solutions:

a twin-wing tiltrotor aircraft for surface take-off and landing, comprising:

a body;

a wing system disposed on the fuselage;

a rotor system coupled to the wing system;

the fixed pontoon is arranged on the wing system;

the inflatable pontoon is arranged at the lower side of the machine body and used for providing buoyancy when the inflatable pontoon slides on water, and the inflatable pontoon is connected with the machine body through a telescopic rod.

As a further improvement of the utility model, the wing system comprises an upper wing and a lower wing, wherein the upper wing is connected with the fuselage and horizontally arranged, the rotor wing system is arranged at one end of the upper wing far away from the fuselage, the lower wing comprises a horizontal wing section and a transition wing section, the horizontal wing section is arranged below the upper wing and is connected with the fuselage at one end, and the transition wing section is used for connecting one end of the horizontal wing section far away from the fuselage and one end of the upper wing connected with the rotor wing system, so that the upper wing and the lower wing form an annular wing structure.

As a further development of the utility model, the upper wing is also articulated with an aileron.

As a further improvement of the utility model, the lower side of the upper wing is also provided with an air inlet, and a negative pressure area is formed between the air inlet and the side wall of the fuselage.

As a further improvement of the utility model, any one of the inflatable pontoons is provided with two groups of telescopic rods, any one group of telescopic rods is arranged in a V-shaped mode, the telescopic rods are hinged to the joint of the machine body, and the joint of the telescopic rods and the inflatable pontoon is fixedly connected.

As a further improvement of the utility model, the tail part of the fuselage is also provided with a tail wing.

As a further improvement of the utility model, the tail wing is provided with a tail wing control surface.

As a further development of the utility model, the underside of the fuselage is also provided with a hatch.

The utility model has the beneficial effects that:

1. the wing system enables the aircraft to have larger loading capacity in the integrated aircraft through structural arrangement of the upper wing and the lower wing, and the aircraft can meet low-altitude and low-speed flight, and reduce the flight resistance of the aircraft body so as to enable the aircraft to have good navigation speed;

2. the design that the large upper wing is hinged with the small aileron is adopted, the water clearance of the upper wing is large, the aircraft can better adapt to the complex airflow environment of the sea surface, the aircraft has better stability, the rotor wing systems are arranged at the two ends of the upper wing, the distance between the rotor wing systems and the water surface is large, and the influence of sea waves on the operation of the rotor wing systems is reduced when the aircraft slides on the water to take off;

3. the engine is arranged in the fuselage in a middle, watertight treatment is carried out at the installation position of the engine, and meanwhile, the air inlet channel is positioned above the fuselage and close to the upper wing, so that the aircraft can be more suitable for the environment with multiple splash on the sea surface and high air humidity;

4. when the quick-inflation retractable inflatable pontoon is used for running and taking off and landing on the water surface, the telescopic rod is used for controlling the extension and retraction of the inflatable pontoon to finish taking off and landing, and the fixed pontoons positioned on the two sides of the lower auxiliary wing can enhance the transverse stability of the aircraft on the water surface;

5. the aircraft disclosed by the utility model can not only be used for vertical take-off, landing and hovering like a helicopter, but also have good wading and higher sailing speed like a water aircraft, and have better application potential in complex scenes such as ocean rescue, marine reconnaissance, anti-diving, equipment throwing and recycling, water transportation and the like.

Drawings

Fig. 1 is an overall profile view of a dual wing tiltrotor aircraft according to the present utility model.

Figure 2 is a front view of a dual wing tiltrotor aircraft according to the present utility model.

Fig. 3 is a top view of a dual wing tiltrotor aircraft according to the present utility model.

Figure 4 is a side view of a dual wing tiltrotor aircraft according to the present utility model.

Fig. 5 is a schematic view of a twin-wing tiltrotor aircraft of the present utility model when the aircraft is on-water jogging landing.

Fig. 6 is a schematic view of a dual wing tiltrotor aircraft of the present utility model when hovering in the air.

Fig. 7 is a schematic view of a twin-wing tiltrotor aircraft of the present utility model while in air for patrol.

FIG. 8 is a schematic view of the collapsible air pontoon according to the utility model in operation.

FIG. 9 is a schematic illustration of the collapsible inflatable pontoon according to the utility model retracted into the main body.

Reference numerals: 1. a body; 2. an upper wing; 3. a lower wing; 4. fixing the pontoon; 5. aileron; 6. a tail wing; 7. tail fin control surface; 8. a rotor system; 9. a cabin door; 10. an inflatable pontoon; 11. a telescopic rod; 12. and (5) an air inlet channel.

Detailed Description

The utility model will now be described in further detail with reference to the drawings and examples. Wherein like parts are designated by like reference numerals. It should be noted that the words "front", "back", "left", "right", "upper" and "lower" used in the following description refer to directions in the drawings, and the words "bottom" and "top", "inner" and "outer" refer to directions toward or away from, respectively, the geometric center of a particular component.

Referring to fig. 1 to 9, in a specific embodiment of the dual-wing tilt rotor aircraft for taking off and landing on water according to the present utility model, the dual-wing tilt rotor aircraft comprises a fuselage 1, a wing system, a rotor system 8, a fixed buoy 4 and an inflatable buoy 10, wherein the wing system is arranged on the fuselage 1, the rotor system 8 is connected with the wing system, the fixed buoy 4 is arranged on the wing system and is used for improving the lateral stability of the aircraft when the aircraft slides along the water, the inflatable buoy 10 is arranged on the lower side of the fuselage 1 and is used for providing the buoyancy of the aircraft when the aircraft slides along the water, the inflatable buoy 10 is connected with the fuselage 1 through a telescopic rod 11, the tail part of the fuselage 1 is further provided with a tail fin 6, the tail fin 6 is arranged in a V-shaped configuration, the tail fin 6 is provided with a control surface of the tail fin 6, and the lower side of the fuselage 1 is further arranged on a cabin door 9, so that the whole aircraft can realize air and cruising water surface sliding.

The wing system comprises an upper wing 2 and a lower wing 3, wherein the upper wing 2 is connected with a fuselage 1 and horizontally arranged, the rotor system 8 is arranged at one end of the upper wing 2, which is far away from the fuselage 1, the lower wing 3 comprises a horizontal wing section and a transition wing section, the horizontal wing section is arranged below the upper wing 2 and one end of the horizontal wing section is connected with the fuselage 1, the transition wing section is used for connecting one end of the horizontal wing section, which is far away from the fuselage 1, with one end of the upper wing 2, which is connected with the rotor system 8, so that the upper wing 2 and the lower wing 3 form an annular wing structure, an aileron 5 is hinged on the upper wing 2, an air inlet 12 is arranged at the lower side of the upper wing 2, and a negative pressure region is formed between the air inlet 12 and the side wall of the fuselage 1. The design of articulated little aileron 5 on the big upper wing 2 is adopted to upper wing 2 is big from the water clearance, can better adapt to the complicated air current environment of sea, make the aircraft possess better stability, rotor system 8 installs at upper wing 2 both ends for rotor system 8 is big from the surface of water distance, reduce the influence of wave to rotor system 8 operation when the running takes off on water, and put in the engine, in engine mounted position carries out watertight treatment, intake duct 12 is located the upper wing 2 department of being close to above the fuselage 1 simultaneously, can make the aircraft adapt to more, sea many splashes, the environment that air humidity is big.

Any one of the inflatable pontoons 10 is provided with two groups of telescopic rods 11, any one group of telescopic rods 11 form V-shaped arrangement, the telescopic rods 11 are hinged to the joint of the machine body 1, and the joint of the telescopic rods 11 and the inflatable pontoons 10 is fixedly connected.

Working principle and effect:

when converting from the front flying state to the hover state:

the whole aircraft is lifted to a height first, and the rotor system 8 slowly tilts backwards until the rotor system 8 is vertical to the plane of the upper wing 2; while the aileron 5 of the upper wing 2 is deflected downwards until the rudder of the aileron 5 is vertical downwards.

Upon transition from the hover state to the forward fly state:

the whole aircraft is lifted first, the rotor system 8 is slowly tilted forward until the rotor system 8 is parallel to the plane of the wing, and the aileron 5 of the upper wing 2 is deflected upwards until the control surface of the aileron 5 is overlapped with the upper wing 2.

From cruise condition to landing on the water:

the rotor system 8 is slowly tilted up by 45 degrees, and simultaneously the ailerons 5 of the upper wing 2 are deflected downwards, the engine reduces power, and the control surfaces of the tail wings 6 are subjected to attitude control, so that the whole aircraft slowly reduces in height along an oblique downward direction in a posture of lifting the head.

When reaching the water surface, the cabin door 9 is controlled to be opened, the telescopic rod 11 ejects the inflating buoy 10 in a contracted state, the inflating buoy 10 is inflated rapidly to an expanded state, the output power of the aircraft is reduced slowly until the inflating buoy 10 in the expanded state contacts the water surface, and then the fixed buoy 4 contacts the water surface until the rotor system 8 stops rotating. At this point, rotor system 8 continues to tilt up 45 degrees until the rotor plane is parallel to the sea level, preventing sea water from wetting the blades of rotor system 8, and then controlling the control surfaces of ailerons 5 and tail fins 6 to return to the original position.

The process from surface to cruise:

the rotor system 8 slowly tilts forwards for 45 degrees from a vertical state, the aircraft starts to provide power for the rotor system 8, the ailerons 5 of the upper wings 2 deflect downwards, the whole aircraft starts to slide forwards on the water surface, the control surfaces of the tail wings 6 control the attitude, and the head lifting moment is given to the aircraft; as the power of rotor system 8 increases, the slow departure of the aircraft from the water in an upward-angled direction in a head-up attitude is a complete departure of stationary buoy 4 from the water, followed by a complete departure of inflated buoy 10 in an inflated state.

After the aircraft climbs to a certain height, the inflatable buoy 10 in an expanded state starts to exhaust until the inflatable buoy 10 in a contracted state changes into a contracted state, the telescopic rod 11 pulls the inflatable buoy 10 in the contracted state back into the aircraft body 1, the cabin door 9 is closed, the rotor system 8 continues to tilt forward for 45 degrees until the direction of the rotor system 8 is flush with the advancing direction of the aircraft, and the control surfaces of the aileron 5 and the tail wing 6 are controlled to return to the initial position, so that the aircraft can fly cruising in this posture.

The above description is only a preferred embodiment of the present utility model, and the protection scope of the present utility model is not limited to the above examples, and all technical solutions belonging to the concept of the present utility model belong to the protection scope of the present utility model. It should be noted that modifications and adaptations to the present utility model may occur to one skilled in the art without departing from the principles of the present utility model and are intended to be within the scope of the present utility model.

Claims (8)

1. A twin-wing tiltrotor aircraft for surface take-off and landing, comprising:

a body (1);

-a wing system arranged on the fuselage (1);

-a rotor system (8), the rotor system (8) being connected to a wing system;

a fixed pontoon (4), the fixed pontoon (4) being arranged on the wing system;

the inflatable buoy (10), the inflatable buoy (10) is arranged on the lower side of the body (1) and is used for providing buoyancy when the inflatable buoy slides on water, and the inflatable buoy (10) is connected with the body (1) through a telescopic rod (11).

2. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 1, wherein: the wing system comprises an upper wing (2) and a lower wing (3), wherein the upper wing (2) is connected with the fuselage (1) and horizontally arranged, the rotor wing system (8) is arranged on the upper wing (2) and away from one end of the fuselage (1), the lower wing (3) comprises a horizontal wing section and a transition wing section, the horizontal wing section is arranged below the upper wing (2) and connected with the fuselage (1) at one end, and the transition wing section is used for connecting one end, far away from the fuselage (1), of the horizontal wing section and one end, connected with the rotor wing system (8), of the upper wing (2) and one end, connected with the upper wing (2), of the lower wing (3) to form an annular wing structure.

3. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 2, wherein: an aileron (5) is also hinged on the upper wing (2).

4. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 2, wherein: an air inlet channel (12) is further formed in the lower side of the upper wing (2), and a negative pressure area is formed between the air inlet channel (12) and the side wall of the machine body (1).

5. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 1, wherein: any one of the inflatable pontoons (10) is provided with two groups of telescopic rods (11), any one group of telescopic rods (11) form a V-shaped arrangement, the joint of the telescopic rods (11) and the machine body (1) is hinged, and the joint of the telescopic rods (11) and the inflatable pontoons (10) is fixedly connected.

6. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 1, wherein: the tail part of the machine body (1) is also provided with a tail wing (6).

7. A twin-wing tiltrotor aircraft for use in surface take-off and landing as defined in claim 6, wherein: the tail wing (6) is provided with a control surface of the tail wing (6).

8. A twin-wing tiltrotor aircraft for use in surface take-off and landing according to any of claims 1 to 7, wherein: the lower side of the machine body (1) is also arranged on the cabin door (9).