Normal catamaran type electric water manned aircraft

Abstract

The utility model discloses a normal kind of double buoy electric water manned aircraft, and two floats are connected to the aircraft main body through support frame assembly, and the support frame assembly includes the first joint and the second joint fixed on the left float, the first support rod, the second support rod and the third support rod arranged in order from front to back for connecting the left float and the aircraft main body, the fourth support rod, the fifth support rod and the sixth support rod for connecting the right float and the aircraft main body, two horizontal support rods are vertically fixed between two floats, the top of first support rod and fourth support rod is connected to the front joint of the bottom surface of the aircraft main body, the bottom of second support rod and the bottom of first support rod are connected to the first joint, and the top of second support rod is inclined upward and connected to the left side of the aircraft main body with the top of third support rod, and the bottom of third support rod is connected to the second joint in a downward inclination. The support frame assembly adopts triangular layout, and the angle and the interval between the aircraft and the float, the float and the float are guaranteed.

Description

Technical Field

[0001] This utility model relates to electric manned aircraft, and more particularly to a normal type of electric seaplane with dual floats. Background Technology

[0002] Currently, there are numerous types of land-based fixed-wing aircraft both domestically and internationally. However, the operation of these aircraft places high demands on airport runway infrastructure. Utilizing water resources or artificial canals as aircraft takeoff and landing sites can significantly reduce investment in airfield construction, even achieving a zero-investment state. However, many water areas are protected zones such as scenic spots and aquaculture areas. Fuel-powered aircraft operating in these areas generate significant engine noise and fuel leaks, impacting the environment and hindering aquaculture development. Fuel-powered aircraft also have short maintenance intervals, complex maintenance procedures, high maintenance costs, and generate waste lubricating oil that can cause environmental pollution. Furthermore, the safety hazards associated with storage, transportation, and use must be considered during operation, and relevant hazardous materials storage and transportation qualifications are required.

[0003] Therefore, it is necessary to improve the lower structure of the fuselage to allow for the installation of target floats on the aircraft, meeting the requirements for seaplane operations. In the existing technology, application number CN201810875389.2, entitled "A Seaplane Strut Structure," includes a front strut and a rear strut. The front strut includes a front main strut, an auxiliary strut, a front transverse strut, a front fuselage diagonal strut, a fuselage side connecting joint, an upper connecting joint for the front diagonal strut, a lower connecting joint for the front diagonal strut, an upper connecting joint for the front float, and a front float side connecting joint. Two fuselage side connecting joints are installed on each of the left and right sides of the fuselage, and two upper connecting joints for the front float and one connecting joint are installed on the upper part of each of the left and right floats. The front float side connection joints are connected to the fuselage side connection joints at the upper ends and to the upper connection joints of the front floats at the lower ends. The front transverse support rods are located on the lower part of the front fuselage and are arranged transversely. The left and right sides are connected to the front float side connection joints on the left and right floats respectively. The upper connection joints of the front diagonal support rods are installed on the lower part of the fuselage and are symmetrically distributed on the left and right. The lower connection joints of the front diagonal support rods are installed in the middle of the front transverse support rods. The upper end of the front belly diagonal support rods is connected to the upper connection joints of the front diagonal support rods and the lower end is connected to the lower connection joints of the front diagonal support rods, and they are symmetrically distributed on the left and right.

[0004] The patented design features a double-beam strut structure that forms multiple stable triangles in space. The front and rear struts each include multiple support rods and joints, but the triangular supports are mainly concentrated at the front and rear of the aircraft, with no stable triangular supports on the left and right sides.

[0005] Therefore, a normal-type twin-pontoon electric manned seaplane is needed to achieve stable support between the pontoons and the main body of the aircraft. Utility Model Content

[0006] The purpose of this invention is to provide a normal type of dual-buoy electric manned seaplane that achieves stable support between the floats and the aircraft body.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A normal type of electric manned seaplane with dual floats includes an aircraft body, a right float, and a left float, wherein the right float and the left float are fixedly connected to the bottom side of the aircraft body through a support frame assembly;

[0009] The support frame assembly includes a pair of parallel horizontal support rods, a first and a second joint fixed to the left float, a third and a fourth joint fixed to the right float, a first support rod, a second support rod, and a third support rod arranged sequentially from front to back to connect the left float and the aircraft body, and a fourth support rod, a fifth support rod, and a sixth support rod to connect the right float and the aircraft body.

[0010] The fourth, fifth, and sixth support rods are symmetrically arranged with respect to the first, second, and third support rods, and the first, second, third, and fourth joints are symmetrically arranged with respect to the main body of the aircraft in the left-right direction.

[0011] Two horizontal support rods are vertically fixed between the right and left buoys;

[0012] The top ends of the first and fourth support rods are connected together to the front connector on the bottom surface of the aircraft body. The bottom ends of the second and first support rods are connected to the first connector of the left float. The top end of the second support rod is inclined upward and connected to the rear connector on the left side of the aircraft body along with the top end of the third support rod. The bottom end of the third support rod is inclined downward and connected to the second connector of the left float.

[0013] The bottom end of the fifth support rod and the bottom end of the fourth support rod are connected to the third joint of the right float; the top end of the fifth support rod is inclined upward and connected to the rear joint on the right side of the aircraft body along with the top end of the sixth support rod; the bottom end of the sixth support rod is inclined downward and connected to the fourth joint of the right float.

[0014] The first joint, the second joint, the third joint, and the fourth joint correspond to the four end positions of a pair of horizontal support rods.

[0015] Furthermore, it also includes a left rudder connected to the stern of the left buoy and a right rudder connected to the stern of the right buoy.

[0016] Furthermore, the support frame assembly also includes two inclined steel cables for connecting the right buoy and the left buoy, with the two inclined steel cables located on the diagonal of the rectangle formed by the horizontal support rod.

[0017] Furthermore, the support frame assembly also includes a pair of staggered stay cables, one of which is used to connect the left float to the right side of the aircraft's main body bottom surface, and the other is used to connect the right float to the left side of the aircraft's main body bottom surface. The bottom ends of the pair of stay cables are located near the second and fourth joints.

[0018] Furthermore, the left wing of the aircraft body is provided with a left wing sparb, the right wing is provided with a right wing sparb, a guide slot is provided inside the aircraft body, and the left wing and the right wing are respectively provided with rear lugs;

[0019] The left wing sparb is inserted into the left side of the aircraft body, and the right wing sparb is inserted into the right side of the aircraft body. The left and right wing spars are fitted together front and back and fixedly connected by fasteners. The two rear lugs are inserted into the two ends of the guide slot holes respectively, and the two rear lugs are fixedly connected to the guide slot holes by pins.

[0020] Furthermore, the left and right wings of the aircraft body are respectively provided with front pins, and the left or right wing spars are respectively located between the front pins and the rear lugs;

[0021] Flanges for inserting the front pin are fixed on both sides of the fuselage of the aircraft.

[0022] Furthermore, the motor for driving the propeller of the aircraft body is located in front of the cockpit door.

[0023] The above technical solution, a normal-type dual-float electric manned seaplane of this utility model, has the following beneficial effects:

[0024] The horizontal support rods, fourth support rod, and first support rod are arranged in a triangular configuration. The first support rod, second support rod, and aircraft body are also arranged in a triangular configuration. Symmetrically, the fourth and fifth support rods are arranged in a triangular configuration with the aircraft body. The second and third support rods are arranged in a triangular configuration with the left float, and the fifth and sixth support rods are arranged in a triangular configuration with the right float. This triangular layout of the support frame assembly ensures proper angles and spacing between the aircraft and floats, and between floats themselves. The support rods also increase the distance between the aircraft fuselage and other structures and the water surface, reducing the risk of the wings touching the water. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0026] Figure 1A schematic diagram of the structure of the dual-float electric manned seaplane provided by this utility model;

[0027] Figure 2 An exploded view of the installation structure of the right and left wings provided for this utility model;

[0028] Figure 3 A front view structural schematic diagram of the dual-float electric manned seaplane provided by this utility model;

[0029] Figure 4 A schematic diagram of the left-side structure of the dual-float electric manned seaplane provided by this utility model;

[0030] Figure 5 A top view of the structure of the dual-float electric manned seaplane provided by this utility model;

[0031] Figure 6 A top-view structural diagram of the dual-buoy electric manned seaplane provided by this utility model.

[0032] In the diagram: 1. Right wing stabilizer; 2. Right aileron; 3. Right flap; 4. Aircraft body; 5. Rudder; 6. Elevator; 7. Horizontal stabilizer; 8. Left wing stabilizer; 9. Left flap; 10. Left aileron; 11. Windshield; 12. Engine nacelle fairing; 13. Propeller; 14. Propeller fairing; 15. Right float; 16. Front battery compartment; 17. Left float; 18. Left hydrofoil; 19. Rear battery compartment; 20. Cockpit door; 22. Right hydrofoil; 23. Cable guide; 24. Guide slot; 25. Rear lug; 26. Front pin; 27. Flange.

[0033] First support rod 211; second support rod 212; third support rod 213; horizontal support rod 214; first connector 215; second connector 216. Detailed Implementation

[0034] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0035] It should be noted that the terms "above," "one end," "up," etc. used in this document indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description. Similar expressions are only for illustrative purposes and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "part," "two parts," etc. are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0036] like Figure 1-6The above describes a normal type of electric manned seaplane with dual floats, which includes an aircraft body 4, a right float 15, and a left float 17. The right float 15 and the left float 17 are fixedly connected to the bottom side and bottom surface of the aircraft body 4 through a support frame assembly.

[0037] The support frame assembly includes a pair of parallel horizontal support rods 214, a first connector 215 and a second connector 216 fixed to the left float, a third connector and a fourth connector fixed to the right float, a first support rod 211, a second support rod 212 and a third support rod 213 arranged sequentially from front to back to connect the left float 17 and the aircraft body 4, and a fourth support rod, a fifth support rod and a sixth support rod to connect the right float 15 and the aircraft body 4.

[0038] The fourth, fifth, and sixth support rods are symmetrically arranged with respect to the first, second, and third support rods, and the first and second joints are symmetrically arranged with respect to the aircraft body in the left-right direction. The first joint, second joint, first support rod, second support rod, third support rod, and left float are symmetrically arranged to obtain the third joint, fourth joint, fourth support rod, fifth support rod, sixth support rod, and right float.

[0039] Two horizontal support rods 214 are vertically fixed between the two pontoons.

[0040] The bottom surface of the aircraft body has three joints: a front joint located at the nose and two rear joints symmetrically arranged in the left and right directions. The rear joints are located near the bottom surface of the cockpit door 20.

[0041] The top ends of the first support rod 211 and the fourth support rod are connected together to the front connector on the bottom surface of the aircraft body. The first support rod 211 and the fourth support rod are symmetrically distributed in an inverted V shape. The bottom end of the second support rod 212 and the bottom end of the first support rod 211 are connected to the first connector 215 of the left float 17. The second support rod 212 and the first support rod 211 are arranged at an angle. The top end of the second support rod 212 is tilted upward and backward and connected to the rear connector on the left side of the aircraft body along with the top end of the third support rod 213. The bottom end of the third support rod 213 is tilted downward and backward and connected to the second connector 216 of the left float. The first support rod 211, the second support rod 212 and the third support rod 213 are distributed in a Z shape as a whole, but they are not in the same plane.

[0042] Symmetrically, the bottom ends of the fifth and fourth support rods are connected to the third joint of the right float; the top end of the fifth support rod is tilted upward and backward and connected to the rear joint on the right side of the aircraft body along with the top end of the sixth support rod; the bottom end of the sixth support rod is tilted downward and connected to the fourth joint of the right float.

[0043] The first connector 215, the second connector 216, the third connector, and the fourth connector correspond to and are close to the four ends of a pair of horizontal support rods 214. Thus, the horizontal support rods 214, the first support rod 211, and the fourth support rod are arranged in a triangular configuration at the front of the aircraft; the first and second support rods, and the second and third support rods are arranged in two triangular configurations on the left side of the aircraft; and the fourth and fifth support rods, and the fifth and sixth support rods, are arranged in two triangular configurations on the right side of the aircraft. This achieves the fixation of the angle and spacing between the aircraft and the floats, and between the floats themselves.

[0044] Preferably, it also includes a left hydroplaning rudder 18 connected to the stern of the left float 17 and a right hydroplaning rudder 22 connected to the stern of the right float 15. The floats of the twin-float electric seaplane are mainly composed of... Figure 1 The aircraft consists of a right float (15), a left float (17), a left rudder (18), and a right rudder (22). This dual float design provides two points of buoyancy support, allowing the aircraft to maintain balance during parking, taxiing, takeoff, and landing even in the event of crosswinds, waves, or other disturbances. The dual float design also increases the overall altitude of the aircraft and prevents the tail from hitting water during takeoff. As independent components, the floats are highly sealed, preventing water ingress and having no impact on the avionics or propulsion systems. In case of emergency, the dual floats can serve as an emergency flotation device, preventing the aircraft from sinking.

[0045] Preferably, the support frame assembly further includes two inclined steel cables for connecting the right pontoon and the left pontoon, with the two inclined steel cables located on the diagonals of the rectangle formed by the horizontal support rod 214. The two inclined steel cables are arranged in an alternating pattern.

[0046] The support frame assembly also includes a pair of cross-arranged stay cables 23, one of which connects the left float to the right side of the aircraft's underside, and the other connects the right float to the left side of the aircraft's underside. The bottom ends of the pair of stay cables 23 are located near the second and fourth joints. Thus, the two stay cables 23 and the rear horizontal support rod 214 form a triangular arrangement.

[0047] The aircraft fuselage and the left and right floats are connected by a support frame assembly consisting mainly of six support rods and four inclined steel cables, forming multiple stable triangular structures. This ensures that the installation spacing between the left and right floats and the installation angle between the left and right floats and the aircraft fuselage remain stable. Each float has two mounting points, one at the front and one at the rear. These mounting points are designed with a first connector, a second connector, a third connector, and a fourth connector. One end of each of these four connectors is fixedly connected to the corresponding left or right float with screws, and the other end is connected to the corresponding first, second, third, fourth, fifth, and sixth support rods with screws. At this point, the aircraft fuselage and the floats are stably connected.

[0048] Preferably, the left wing of the aircraft body is provided with a left wing sparb, and the right wing is provided with a right wing sparb. The interior of the aircraft body is provided with a guide slot 24. The left wing and the right wing are respectively provided with rear lugs 25. The left wing sparb passes through the left fuselage of the aircraft body, and the right wing sparb passes through the right fuselage of the aircraft body. The left wing sparb and the right wing sparb are attached together front and back, spliced ​​into one piece, and fixedly connected by fasteners. The two rear lugs 25 are respectively inserted into the two ends of the guide slot 24, and the two rear lugs 25 are fixedly connected to the guide slot 24 by pins.

[0049] The left and right wings of the aircraft are each equipped with a leading pin 26, with the left or right wing spars located between the leading pin and the rear trunnion, respectively. Flanges 27 for inserting the leading pins are fixed to both sides of the fuselage. Through the design of the leading pin and rear trunnion, this wing has two positioning points, one at the front and one at the rear.

[0050] Specifically, the wings are mainly composed of Figure 1 The aircraft is composed of a right wing stabilizer (1), right aileron (2), and right flap (3), and a left wing stabilizer (8), left flap (9), and left aileron (10). It employs a high-wing configuration with a large wing clearance above the water surface, minimizing the risk of contact with the water or water-based buoys during taxiing, takeoff, and landing. High-wing aircraft generally exhibit high stability during taxiing and flight. The wings primarily generate lift during flight. The pilot controls the rudder and elevator on the tailplane for heading and pitch control. Takeoff, climb, level flight, descent, and landing are achieved through the pilot's control of the ailerons, rudder, elevator, and throttle. Figure 2 The wings shown are directly connected to the fuselage. The left and right wings are inserted into the fuselage from the respective wing mounting sections. At this point, each wing spars is threaded through by two pins, which are then tightened. Each wing has a positioning pin on its inner leading edge, which is simultaneously inserted into the fuselage positioning hole during wing installation. The aft portion of the wing end face has two rear lugs, each with two pre-drilled pin holes. Corresponding to the wing being threaded through the fuselage, pins are inserted through the internal fuselage structure and connected to the lug pin holes. At this point, the aircraft wings and fuselage are rigidly connected.

[0051] Preferably, the motor that drives the propeller of the aircraft body is located in front of the cockpit door.

[0052] like Figure 1 As shown, a manned electric seaplane mainly consists of: two wings, a fuselage, a tail, an engine, support rods, and floats. The fuselage is the main structure, and all components are rigidly connected to it, ultimately forming an electric seaplane. The interior of the fuselage houses the motor bay, battery bay, control system, avionics system, instrument panel, seats, and baggage compartment.

[0053] The fuselage is mainly composed of Figure 1The aircraft consists of the main fuselage (4), windshield (11), front battery compartment (16), cockpit door (20), rear battery compartment (19), and motor nacelle fairing (12). Supported by twin floats, the fuselage is completely isolated from water, preventing water ingress. The aircraft offers excellent visibility.

[0054] The tail fin is mainly composed of Figure 1 The system consists of a central rudder (5), an elevator (6), and a horizontal stabilizer (7). The tail fin layout takes into account the height above the water surface and the distance from the motor, reducing the risk of water contact and minimizing the impact of propeller slippage.

[0055] The vertical stabilizer in the tail section is manufactured as a single piece with the fuselage. The horizontal stabilizer 7 has two pins on its leading edge. During installation, the pins are aligned with the pin holes at the rear of the fuselage, and then the horizontal stabilizer is installed vertically onto the fuselage using the screws at the top of the horizontal stabilizer. This completes the tail section installation.

[0056] The engine mainly consists of a propeller 13, a propeller fairing 14, and an electric motor located within the motor nacelle fairing 12. It adopts a forward-pull layout and a streamlined aircraft design to reduce wind resistance and power consumption. The motor is mounted forward of the cockpit door, far from the tail, resulting in less reaction force and reduced yaw moment. The first to sixth support rods feature a streamlined cross-section, ensuring structural strength while reducing wind resistance. The twin floats are designed with dual hydroplaners at the tail, increasing maneuverability on water. Normal directional control is maintained even in strong winds. Each float has a hydroplaner at its end, increasing turning efficiency on water. The engine is a direct-drive motor; the front end of the motor is connected to the flange with screws, and the flange is also connected to the propeller with screws. The rear end of the motor is connected to the aircraft fuselage via a motor mounting bracket, fastened with bolts. The motor drives the propeller to rotate, generating forward thrust, propelling the aircraft forward, and at a certain speed, the wings generate lift.

[0057] Because the aircraft is equipped with twin floats, the buoyancy of which allows the aircraft to be parked on the water. The aircraft floats also have the characteristics of a "boat," allowing them to glide on the water. Therefore, during takeoff and landing, the floats provide both the buoyancy required by the aircraft and the gliding characteristics on the water, thus enabling the aircraft to take off and land on the water. The twin-float design ensures high lateral stability during parking, taxiing, takeoff, and landing; the aircraft has a large tilt angle, reducing the risk of wingtip water contact; the cockpit and floats are separate, allowing the floats and struts to act as a buffer in emergencies; the sealed twin floats can act as buoys to protect the pilot in case of aircraft damage; the large distance between the fuselage and the water surface reduces the risk of water ingress and protects internal electrical components; the pilot has a high field of vision, allowing them to observe obstacles further away during takeoff and landing; the use of electric motors for power output results in low noise and no pollution; there is no fuel, lubricating oil, or fuel leakage; the simple structure and operation facilitate long maintenance intervals and low maintenance costs; no fuel transportation or storage is required, eliminating the risk of flammable liquid combustion; the battery can be charged using household power; the front-mounted motor reduces wind resistance and power consumption.

[0058] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A normal-type dual-float electric manned seaplane, comprising an aircraft body, a right float, and a left float, characterized in that, The right and left floats are fixedly connected to the bottom of the aircraft body via a support frame assembly. The support frame assembly includes a pair of parallel horizontal support rods, a first and a second joint fixed to the left float, a third and a fourth joint fixed to the right float, a first support rod, a second support rod, and a third support rod arranged sequentially from front to back to connect the left float and the aircraft body, and a fourth support rod, a fifth support rod, and a sixth support rod to connect the right float and the aircraft body. The fourth, fifth, and sixth support rods are symmetrically arranged with respect to the first, second, and third support rods, and the first, second, third, and fourth joints are symmetrically arranged with respect to the main body of the aircraft in the left-right direction. Two horizontal support rods are vertically fixed between the right and left buoys; The top ends of the first and fourth support rods are connected together to the front connector on the bottom surface of the aircraft body. The bottom ends of the second and first support rods are connected to the first connector of the left float. The top end of the second support rod is inclined upward and connected to the rear connector on the left side of the aircraft body along with the top end of the third support rod. The bottom end of the third support rod is inclined downward and connected to the second connector of the left float. The bottom end of the fifth support rod and the bottom end of the fourth support rod are connected to the third joint of the right float; the top end of the fifth support rod is inclined upward and connected to the rear joint on the right side of the aircraft body along with the top end of the sixth support rod; the bottom end of the sixth support rod is inclined downward and connected to the fourth joint of the right float. The first joint, the second joint, the third joint, and the fourth joint correspond to the four end positions of a pair of horizontal support rods.

2. The normal-type twin-buoy electric manned seaplane according to claim 1, characterized in that, It also includes a left rudder connected to the stern of the left buoy and a right rudder connected to the stern of the right buoy.

3. The normal-type twin-buoy electric manned seaplane according to claim 1, characterized in that, The support frame assembly also includes two inclined steel cables for connecting the right pontoon and the left pontoon, with the two inclined steel cables located on the diagonal of the rectangle formed by the horizontal support rod.

4. A normal-type twin-buoy electric manned seaplane according to claim 1, characterized in that, The support frame assembly also includes a pair of staggered stay cables, one of which connects the left float to the right side of the aircraft's main body bottom surface, and the other connects the right float to the left side of the aircraft's main body bottom surface. The bottom ends of the pair of stay cables are located near the second and fourth joints.

5. A normal-type twin-buoy electric manned seaplane according to claim 1, characterized in that, The left wing of the aircraft body is provided with a left wing sparb, and the right wing is provided with a right wing sparb. A guide slot is provided inside the aircraft body, and the left wing and the right wing are respectively provided with rear lugs. The left wing sparb is inserted into the left side of the aircraft body, and the right wing sparb is inserted into the right side of the aircraft body. The left and right wing spars are fitted together front and back and fixedly connected by fasteners. The two rear lugs are inserted into the two ends of the guide slot holes respectively, and the two rear lugs are fixedly connected to the guide slot holes by pins.

6. A normal-type twin-buoy electric manned seaplane according to claim 5, characterized in that, The left and right wings of the main body of the aircraft are respectively provided with front pins, and the left or right wing spars are respectively located between the front pins and the rear lugs; Flanges for inserting the front pin are fixed on both sides of the fuselage of the aircraft.

7. A normal-type twin-buoy electric manned seaplane according to claim 1, characterized in that, The motor that drives the propeller of the aircraft body is located in front of the cockpit door.

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