Novel amphibious variable aircraft based on novel buoy and power system

Abstract

The invention discloses a novel amphibious variable aircraft based on a novel buoy and a power system, and relates to the technical field of aircrafts, the novel amphibious variable aircraft comprises a main fuselage and wings connected to two sides of the main fuselage, power nacelle mechanisms are arranged at the middle sections of the wings, buoy mechanisms are arranged at the ends, away from the main fuselage, of the wings, and the buoy mechanisms comprise buoys; a tilting assembly is arranged outside the buoy, and a water suction and drainage assembly is arranged inside the buoy; a tail fin is arranged at the tail of the main fuselage, and a horizontal stabilizer is arranged on the tail fin. According to the novel amphibious variable aircraft based on the novel buoy and the power system, the design of the tiltable buoy is adopted, the appearance of the buoy mechanism is the same as the airfoil profile of the aircraft, it is guaranteed that the aircraft can rapidly complete water suction and drainage operation while the ineffective weight is reduced, and the novel amphibious variable aircraft is simple in structure and convenient to maintain.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a novel amphibious variable aircraft based on a novel pontoon and a power system. Background Art

[0002] For existing cross-media aircraft, they are mainly divided into two categories. One category is represented by fixed-wing and underwater cruise missiles, which splash into the water and eject out of the water, and use foldable and retractable wings to switch between different modes. The other category is represented by multi-rotors, which are equipped with devices such as pontoons to land on water, and achieve the purpose of diving by sucking water into a sealed water tank. Such aircraft usually use air-water dual-purpose propellers to meet the requirements under different conditions.

[0003] Currently, for the two mainstream aircraft, the traditional fixed-wing retraction mechanism occupies a large volume and weight, seriously affecting the performance of the aircraft. Usually, it has high requirements for sea conditions during switching, and there is a certain degree of uncontrollability. For multi-axis aircraft using air-water dual-purpose propellers, the air-water dual-purpose propellers are not the best choice in both working modes, but a compromise product that makes a compromise between the two different modes, resulting in a significant reduction in efficiency. Moreover, the non-fluid shape of the multi-axis aircraft itself is not suitable for underwater navigation, which will bring greater resistance.

[0004] In view of these disadvantages, this patent proposes and designs a novel variable amphibious aircraft, which can intelligently transform according to the two operating environments of air and water, and flexibly change the working mode adaptively. Summary of the Invention

[0005] The purpose of the present invention is to provide a novel amphibious variable aircraft based on a novel pontoon and a power system, so as to solve the problems of low efficiency, difficult controllability during switching, and non-repeatability of existing aircraft in different states.

[0006] To achieve the above purpose, the present invention provides a novel amphibious variable aircraft based on a novel pontoon and a power system, including a main fuselage and wings connected to both sides of the main fuselage. A power nacelle mechanism is provided at the middle section of the wings, and a pontoon mechanism is provided at the end of the wings far from the main fuselage. The pontoon mechanism includes a pontoon, a tiltable assembly is provided outside the pontoon, and a water suction and drainage assembly is provided inside the pontoon; A tail fin is provided at the tail of the main fuselage, and a horizontal stabilizer is provided on the tail fin.

[0007] Preferably, small propellers are provided at the tails of the two power nacelle mechanisms, a forward rotor is provided at the head of one power nacelle mechanism, and a reverse rotor is provided at the head of the other power nacelle mechanism.

[0008] Preferably, the power nacelle mechanism includes a nacelle, a double-output shaft motor is arranged inside the nacelle, one end of the double-output shaft motor is drivingly connected to one end of a front power output shaft through a front gear set, and the other end of the front power output shaft is connected to a forward rotor or a reverse rotor; The other end of the double-output shaft motor is drivingly connected to one end of a rear power output shaft through a rear gear set, and the other end of the rear power output shaft is connected to the small propeller.

[0009] Preferably, the front gear set includes a front drive gear and a front transmission gear, the front transmission gear is sleeved on the front power output shaft, and the front drive gear is sleeved on one side output end of the double-output shaft motor through a front one-way bearing; The rear gear set includes a rear drive gear and a rear transmission gear, the rear transmission gear is sleeved on the rear power output shaft, and the rear drive gear is sleeved on the other side output end of the double-output shaft motor through a rear one-way bearing.

[0010] Preferably, two sets of water suction and drainage assemblies are provided, and both sets of water suction and drainage assemblies include a first stepping motor, a syringe barrel and a water suction manifold. One end of the water suction manifold extends to the outside of the pontoon mechanism, and the other end extends to the inside of the syringe barrel. A lead screw is also arranged in the syringe barrel, a piston is sleeved on the lead screw, the end of the lead screw is connected to the first stepping motor, and the first stepping motor is arranged at one end of the syringe barrel.

[0011] Preferably, the tiltable assembly includes a second stepping motor, a gear set and a rotating shaft. The gear set includes two meshing driving gears and driven gears. The driven gear is sleeved on the rotating shaft, the rotating shaft is connected to the pontoon mechanism, the driving gear is sleeved on the output end of the second stepping motor, and the second stepping motor is fixedly connected to the wing.

[0012] Preferably, the gear ratio of the driving gear to the driven gear is 1:4.

[0013] Preferably, a control device and a battery are arranged inside the main fuselage.

[0014] Therefore, the present invention adopts the above-mentioned novel amphibious variable-body aircraft based on a novel pontoon and power system, and has the following beneficial effects: (1) The present invention adopts a tiltable ballast water tank pontoon design, and the pontoon has the same shape as the aircraft airfoil, which reduces the ineffective weight while ensuring that the aircraft can quickly complete the water suction and drainage operations, and has a simple structure and is easy to maintain.

[0015] (2) The present invention adopts a power cabin design and uses two propeller blades for different environments, enabling the product to have high efficiency in both flight and underwater submersible modes. Compared with other products on the market, it significantly reduces the ineffective weight. Moreover, due to the adoption of a flying wing design, the product has a large lift area, effectively improving the payload.

[0016] (3) The present invention designs a cross-media attitude conversion method with fast switching speed, simple and repeatable switching control. It can complete multiple repeatable switches among three attitudes: dynamic submersible navigation, vertical takeoff and landing in the air, and fixed-wing level flight, and has strong self-sustaining ability (maximum endurance time); and is capable of completing tasks such as reconnaissance, search and rescue, and covert approach and continuous positioning of high-value enemy units.

[0017] The technical solution of the present invention will be further described in detail below through the accompanying drawings and embodiments. Description of the Drawings

[0018] Figure 1 It is a schematic structural diagram of an embodiment of a new amphibious variable-body aircraft based on a new float and power system of the present invention; Figure 2 It is a process diagram of the conversion of the fixed-wing flight attitude to the vertical takeoff attitude to the submersible attitude of the aircraft of the present invention; Figure 3 It is a schematic diagram of the horizontal state of the float and the fuselage of the present invention; Figure 4 It is a schematic diagram of the vertical state of the float and the fuselage of the present invention; Figure 5 It is a schematic structural diagram of the float mechanism of the present invention; Figure 6 It is a schematic structural diagram of the tiltable component of the present invention; Figure 7 It is a left perspective view of the power nacelle mechanism of the present invention; Figure 8 It is a partial structural schematic diagram of the power nacelle mechanism of the present invention; Figure 9 It is a schematic diagram of the mechanism of the front gear set and the rear gear set of the present invention; Figure numerals: 1, main fuselage; 11, tail fin; 12, horizontal stabilizer; 2, wing; 3, power nacelle mechanism; 31, small propeller; 32, forward rotor; 33, reverse rotor; 34, nacelle; 35, double-output shaft motor; 36, front gear set; 361, front drive gear; 362, front transmission gear; 363, front one-way bearing; 37, front power output shaft; 38, rear gear set; 381, rear drive gear; 382, ​​rear transmission gear; 383, rear one-way bearing; 39, rear power output shaft; 4, buoy mechanism; 41, buoy; 42, first stepper motor; 43, pump; 44, water suction manifold; 45, screw; 46, piston; 47, second stepper motor; 48, gear set; 481, driving gear; 482, driven gear; 49, rotating shaft. DETAILED DESCRIPTION

[0019] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0020] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0021] Example See also Figures 1-9 The present invention provides a new type of amphibious transformable aircraft based on a new type of float and power system, which can be transformed into a level flight mode, a vertical take-off mode and a dynamic diving mode according to different missions to adapt to different mission environments. It includes a main body 1 and wings 2 connected to both sides of the main body. A power nacelle mechanism 3 is arranged at the middle position of the wing 2. The power nacelle mechanism 3 realizes a set of power to drive two blades with different purposes in a time-sharing manner. A float mechanism 4 is arranged at the end of the wing 2 away from the main body. The float mechanism 4 can simultaneously serve as a ballast water tank and a surface landing gear float, and can contribute part of the lift to balance its own weight during flight. The float mechanism includes a float 41. A tilting component is arranged on the outside of the float 41, and a suction and discharge component is arranged on the inside of the float.

[0022] The tail of the main fuselage 1 is provided with a tail fin 11, which is responsible for heading stability during flight and underwater heading maintenance. The tail fin 11 is provided with a horizontal stabilizer 12, which is responsible for auxiliary stability in the pitch direction during flight and acts as a landing gear to bear the weight of the aircraft in the vertical take-off mode and ground parking. The main fuselage 1 is used to accommodate control equipment and batteries.

[0023] The tails of the two power nacelle mechanisms 3 are both provided with small propellers 31, which are arranged in pairs to provide propulsion when sailing underwater. The head of one power nacelle mechanism 3 is provided with a forward rotor 32, and the head of the other power nacelle mechanism 3 is provided with a reverse rotor 33. The counter-rotation of the rotors is used to offset the torque and eliminate the adverse effects on flight. When sailing in water, the rotors are locked on the fuselage plane under the action of the one-way bearing to reduce resistance.

[0024] The power nacelle mechanism 3 includes a nacelle 34, and a double-shaft motor 35 is arranged inside the nacelle 34. One end of the double-shaft motor 35 is connected to one end of a front power output shaft 37 through a front gear set 36, and the other end of the front power output shaft 37 is connected to the forward rotor 32 or the reverse rotor 33. The other end of the double-shaft motor 35 is connected to one end of a rear power output shaft 39 through a rear gear set 38, and the other end of the rear power output shaft 39 is connected to the small propeller 31.

[0025] The front gear set 36 includes a front drive gear 361 and a front transmission gear 362, the front transmission gear 362 is sleeved on the front power output shaft 37, and the front drive gear 361 is sleeved on one side of the output end of the double-output shaft motor 35 through a front one-way bearing 363. The rear gear set 38 includes a rear drive gear 381 and a rear transmission gear 382, ​​the rear transmission gear 382 is sleeved on the rear power output shaft 39, and the rear drive gear 381 is sleeved on the other side of the output end of the double-output shaft motor 35 through a rear one-way bearing 383.

[0026] This design uses a double-shaft motor 35, which drives the front gear set 36 and the rear gear set 38 with different gear ratios in the forward and reverse directions respectively. The front one-way bearing 363 and the rear one-way bearing 383 with opposite directions are installed on the gears to achieve the effect of driving the rotors and the small propeller 31 on both sides when the double-shaft motor 35 turns in different directions. When the double-shaft motor 35 turns in a certain direction, the inner ring of the front one-way bearing 363 and the rear one-way bearing 383 mesh with the outer ring to drive the outer ring, and when it turns in the opposite direction, it is idle and slips. When the three-phase AC power output by the electric regulator is reversed, the double-shaft motor 35 turns inversely, one set of the two one-way bearings changes from driving to idle and slipping, and the other set changes from idle to meshing with the external gear for power output. In this way, the purpose of driving the two sets of air and underwater power in time-sharing without interfering with each other is achieved through the same power system.

[0027] There are two sets of water suction and drainage components. Both sets of water suction and drainage components include a first stepping motor 42, a piston pump 43, and a water suction manifold 44. One end of the water suction manifold 44 extends to the outside of the buoyancy mechanism 4, and the other end extends into the piston pump 43. A lead screw 45 is also arranged inside the piston pump 43. A piston 46 is sleeved on the lead screw 45. The end of the lead screw 45 is connected to the first stepping motor 42. The first stepping motor 42 is arranged at one end of the piston pump 43. Driven by the first stepping motor 42 to rotate, the piston 46 moves back and forth to push water to be sucked in or discharged from the water suction manifold 44.

[0028] The tiltable component includes a second stepping motor 47, a gear set 48, and a rotating shaft 49. The gear set 48 includes two meshing driving gears 481 and driven gears 482. The driven gear 482 is sleeved on the rotating shaft 49. The rotating shaft 49 is connected to the buoyancy mechanism 4. The driving gear 481 is sleeved on the output end of the second stepping motor 47. The second stepping motor 47 is fixedly connected to the wing. The buoy 41 is driven to tilt by the second stepping motor 47 through the gear set 48. The gear ratio of the driving gear 481 to the driven gear 482 is 1:4.

[0029] Using the second stepping motor 47 installed on the wing and the gear set 48 with a known transmission ratio, the angle between the current position of the buoy 41 and the installation zero position (i.e., the horizontal state with the main fuselage 1) is calculated, so as to accurately determine the position of the buoy 41. Inside the buoy 41, the first stepping motor 42 is used to drive the lead screw to push the piston to move. The first stepping motor 42 can accurately calculate the position of the piston 46 at this moment according to its own number of rotation circles, so as to roughly estimate the water absorption volume. When the piston 46 moves backward, a vacuum appears inside the piston pump 43, and water is sucked into the piston pump 43 under the action of pressure, causing the overall weight of the aircraft to increase and thus sink underwater. When moving forward, the water is pressed out of the cabin, making the aircraft float on the water surface.

[0030] The following further illustrates this embodiment in conjunction with the drawings.

[0031] Through variable airfoils, a new power system, and intelligent flight attitude conversion, a new type of amphibious aircraft that can adapt to both air and water environments and has no structural dead weight is formed.

[0032] As Figure 1 shows the overall shape of the aircraft. As Figure 2 shows the switching process of the aircraft. First, when approaching the water surface, the aircraft decelerates under the action of the rudder surface and assumes a vertical takeoff and landing hovering attitude. At this time, the buoys 41 on both sides of the wing 2 are driven by the second stepping motor 47 installed on the wing 2 to rotate to be perpendicular to the fuselage, as Figure 3As shown. Then, the aircraft will slowly fall into the water, and the two side floats 41 provide additional stabilizing torque and buoyancy to ensure that the part of the main beam of the wing 2 above the water surface floats on the water surface. Subsequently, the first stepping motor 42 inside the float 41 drives the lead screw 45 to push the piston 46 backward, sucking water into the pump barrel 43, increasing the weight so that the total buoyancy of the aircraft is slightly less than the total weight. Subsequently, the aircraft slowly sinks into the water, and the float 41 rotates underwater to be horizontal with the main fuselage 1. After the power system is started, the small propeller 31 at the rear propels the aircraft to turn it upside down (that is, at this time the wing 2 acts as a hydrofoil to press the aircraft into the water). At this moment, the aircraft completes the transformation. When taking off from the water, the aircraft first adjusts the aircraft to a vertical attitude with the water surface under the combined action of the engine and the control surface, and the float 41 rotates to be perpendicular to the fuselage. Then the pump barrel 43 drains water so that the two side rotors of the aircraft are exposed above the water surface. Subsequently, the forward rotor 32 and the reverse rotor 33 start to work, vertically lifting the aircraft out of the water and entering the vertical takeoff and landing mode. Then the pump barrel 43 rotates back to a horizontal position with the fuselage, and the aircraft executes the tail-sitter vertical takeoff switching logic, that is, the fuselage accelerates forward and switches to level flight after reaching the safe switching speed.

[0033] Therefore, the present invention adopts the above-mentioned novel amphibious variable-body aircraft based on a novel float and power system, with a tiltable float design, and the outer shape of the float mechanism is the same as the airfoil of the aircraft, which reduces the ineffective weight while ensuring that the aircraft can quickly complete the water suction and drainage operations, and has a simple structure and is easy to maintain.

[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that they can still modify or equivalently replace the technical solutions of the present invention, and these modifications or equivalent replacements cannot make the modified technical solutions deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A new type of amphibious transformable aircraft based on a new type of float and power system, characterized by: It comprises a main body and wings connected to both sides of the main body, a power nacelle mechanism is arranged at the middle section of the wing, a buoy mechanism is arranged at the end of the wing away from the main body, the buoy mechanism comprises a buoy, a tilting assembly is arranged outside the buoy, and a suction and discharge assembly is arranged inside the buoy; A tail fin is arranged at the tail of the main fuselage, and a horizontal stabilizer is arranged on the tail fin.

2. A novel amphibious transformable aircraft based on a novel float and power system according to claim 1, characterized in that: The tails of the two groups of power nacelle mechanisms are both provided with small propellers, the heads of one group of power nacelle mechanisms are provided with forward rotors, and the heads of the other group of power nacelle mechanisms are provided with reverse rotors.

3. A novel amphibious transformable aircraft based on a novel float and power system according to claim 2, characterized in that: The power nacelle mechanism comprises a nacelle, a double-shaft motor is arranged inside the nacelle, one end of the double-shaft motor is connected to one end of a front power output shaft through a front gear set, and the other end of the front power output shaft is connected to a forward rotor or a reverse rotor; The other end of the double-output shaft motor is connected to one end of the rear power output shaft through a rear gear set, and the other end of the rear power output shaft is connected to the small propeller.

4. A novel amphibious transformable aircraft based on a novel float and power system according to claim 3, characterized in that: The front gear set includes a front drive gear and a front transmission gear, the front transmission gear is sleeved on the front power output shaft, and the front drive gear is sleeved on one side output end of the dual-output shaft motor through a front one-way bearing; The rear gear set includes a rear drive gear and a rear transmission gear. The rear transmission gear is sleeved on the rear power output shaft, and the rear drive gear is sleeved on the other side output end of the dual-output shaft motor through a rear one-way bearing.

5. The novel amphibious transformable aircraft based on the novel float and power system according to claim 1 is characterized in that: The suction and drainage components are provided in two groups, and both groups of the suction and drainage components include a first stepper motor, a pump and a water suction manifold. One end of the water suction manifold extends to the outside of the float mechanism, and the other end extends to the inside of the pump. A screw rod is also provided in the pump, and a piston is sleeved on the screw rod. The end of the screw rod is connected to the first stepper motor, and the first stepper motor is arranged at one end of the pump.

6. The novel amphibious transformable aircraft based on the novel float and power system according to claim 1 is characterized in that: The tiltable assembly includes a second stepper motor, a gear set and a rotating shaft. The gear set includes two meshing driving gears and a driven gear. The driven gear is sleeved on the rotating shaft. The rotating shaft is connected to the buoy mechanism. The driving gear is sleeved on the output end of the second stepper motor. The second stepper motor is fixedly connected to the wing.

7. A new type of amphibious transformable aircraft based on a new type of float and power system according to claim 6, characterized in that: The gear ratio of the driving gear and the driven gear is 1:

4.

8. The novel amphibious transformable aircraft based on the novel float and power system according to claim 1 is characterized by: The main body is provided with a control device and a battery.

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