Cross-media aircraft

Abstract

The utility model relates to the technical field of aircrafts, in particular to a cross-medium aircraft. A cross-medium aircraft comprises a fuselage. The rotor wing mechanism is used for hovering flight of the aircraft; the rotor mechanisms comprise propellers and driving mechanisms, and the driving mechanisms are arranged on the aircraft body, connected with the propellers and used for driving the propellers to rotate and applying vector tension to the propellers so as to control the attitude of the aircraft to be stable when the aircraft flies in the air in a hovering mode; the fixed wing mechanism comprises wings and folding parts, the wings are arranged on the fuselage and can be unfolded and folded relative to the fuselage, and the folding parts are used for driving the wings to be unfolded or folded; and the injection mechanism is arranged on the fuselage and used for providing underwater navigation power for the fuselage. The utility model provides a cross-medium aircraft which meets the requirements of stable hovering flight in the air, high endurance and high maneuverability.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a transmedium aircraft. Background Technology

[0002] A cross-medium aircraft (robot) is an amphibious aircraft capable of cruising in both air and water, achieving flight in the air and navigation in the water. Currently, cross-medium aircraft are mainly divided into three categories: rotorcraft, fixed-wing, and jet-powered. Additionally, some cross-medium aircraft that combine two types have emerged. However, these existing cross-medium aircraft all have some problems to varying degrees, and cannot achieve stable hovering flight in the air, thus failing to simultaneously meet the requirements of stable hovering flight, long endurance, and high maneuverability required for a cross-medium aircraft. Summary of the Invention

[0003] Therefore, it is necessary to provide a cross-medium aircraft that meets the requirements of stable hovering flight, long endurance, and high maneuverability.

[0004] A transmedium-based aircraft, comprising:

[0005] body;

[0006] A rotor mechanism is used for hovering flight of the aircraft; the rotor mechanism includes a propeller and a drive mechanism, the drive mechanism is located on the fuselage and connected to the propeller, and is used to drive the propeller to rotate and apply vector thrust to the propeller to control the attitude stability of the aircraft when hovering in the air;

[0007] A fixed-wing mechanism includes a wing and a folding component. The wing is mounted on the fuselage and can be deployed and retracted relative to the fuselage. The folding component is used to drive the wing to deploy or retract.

[0008] The jet propulsion system, located on the fuselage, is used to provide power to the fuselage for underwater navigation.

[0009] In one embodiment, the drive mechanism includes a drive component and a vector rotor component. The drive component is connected to the propeller and is used to drive the propeller to rotate. The vector rotor component is connected to the propeller and is used to apply a vector thrust.

[0010] In one embodiment, the propeller includes a first blade and a second blade that are distributed vertically along the length of the fuselage, and the drive component is used to drive the first blade to rotate clockwise and drive the second blade to rotate counterclockwise.

[0011] In one embodiment, the drive component includes a first direct drive member and a second direct drive member, the first direct drive member being connected to the first propeller blade and the second direct drive member being connected to the second propeller blade; the first propeller blade, the second propeller blade, the first direct drive member, and the second direct drive member are coaxially arranged along the fuselage height direction.

[0012] In one embodiment, the vector rotor component includes a coaxially arranged universal joint, a first vector rotor ring, a second vector rotor ring, and a control ring; the first vector rotor ring is sleeved on the universal joint and hinged to it; the second vector rotor ring is sleeved on the first vector rotor ring and hinged to it; the side of the second vector rotor ring away from the first vector rotor ring is drivenly connected to the second blade; the control ring is connected to the second vector rotor ring, and the control ring is connected to a tie rod assembly.

[0013] In one embodiment, the lever assembly includes a lever and a servo motor, the servo motor being mounted on the fuselage, one end of the lever being connected to the servo motor, and the other end being connected to the control ring.

[0014] In one embodiment, the propeller further includes a blade folding component for driving the first blade and the second blade to fold and unfold relative to the fuselage, respectively.

[0015] In one embodiment, the first blade includes a first connecting arm and a first blade, the blade folding component is used to connect the first blade and the first connecting arm, and the blade folding component is capable of driving the first blade to fold or unfold relative to the first connecting arm; the second blade includes a second connecting arm and a second blade, the blade folding component is used to connect the second blade and the second connecting arm, and the blade folding component is capable of driving the second blade to fold or unfold relative to the second connecting arm.

[0016] In one embodiment, along the length of the fuselage, the tail section of the fuselage is provided with multiple tail fins, and adjacent tail fins form a V-shaped structure.

[0017] In one embodiment, the injection mechanism is located inside the fuselage, and the tail of the injection mechanism is provided with an injection outlet, the inner wall of which is provided with multiple flow stabilizers.

[0018] Compared to existing technologies, this cross-medium aircraft uses a drive mechanism to apply vector thrust to the propeller, thereby controlling the aircraft's attitude stability during hovering flight and achieving stable hovering and stationary hovering capabilities. It is equipped with retractable wings and a jet propulsion system. In aerial flight, the wings can be deployed into a fixed-wing configuration, enabling long-endurance flight and high maneuverability. When navigating in water, the wings can be retracted and powered by the jet propulsion system, resulting in low drag and high maneuverability. This effectively meets the performance requirements of a cross-medium aircraft that simultaneously possesses stable hovering flight, long endurance, and high maneuverability. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application or the conventional technology, the drawings used in the description of the embodiments or the conventional technology will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the cross-medium aircraft structure provided in this application.

[0021] Figure 2 Partial schematic diagram of the transmedium aircraft provided in this application Figure 1 .

[0022] Figure 3 Partial schematic diagram of the transmedium aircraft provided in this application Figure 2 .

[0023] Figure 4 A bottom view of the fuselage provided for this application.

[0024] Reference numerals: 1. Fuselage; 11. Tail fin; 12. Jet nozzle; 13. Flow stabilizer; 2. Rotor mechanism; 21. Propeller; 21a. First blade; 211. First connecting arm; 212. First blade; 21b. Second blade; 213. Second connecting arm; 214. Second blade; 22. Drive mechanism; 22a. Drive component; 221. First direct drive component; 222. Second direct drive component; 22b. Vector rotor component; 223. Universal bracket; 224. First vector rotor ring; 225. Second vector rotor ring; 226. Control ring; 227. Connector; 23. Rod assembly; 231. Rod; 232. Servo; 3. Fixed wing mechanism; 31. Wing; 4. Jet mechanism; 5. Fairing; 61. Shock absorber; 62. Shock absorber ball. Detailed Implementation

[0025] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0026] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on the other component or there may be an intermediate component. When a component is considered to be "connected to" another component, it can be directly connected to the other component or there may be an intermediate component present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application's specification are for illustrative purposes only and do not represent the only possible implementation.

[0027] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0028] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature and the second feature are in indirect contact through an intermediate medium. Furthermore, "above," "over," and "on top" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0029] Unless otherwise defined, all technical and scientific terms used in this application have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The term "and / or" as used in this application includes any and all combinations of one or more of the associated listed items.

[0030] Please see Figures 1 to 4This application provides a cross-medium aircraft, including a fuselage 1, a rotor mechanism 2, a fixed-wing mechanism 3, and a jet mechanism 4. The rotor mechanism 2 is used for hovering flight of the aircraft. The rotor mechanism 2 includes a propeller 21 and a drive mechanism 22. The drive mechanism 22 is located on the fuselage 1 and connected to the propeller 21, used to drive the propeller 21 to rotate and apply vector thrust to the propeller 21 to control the attitude stability of the aircraft during hovering flight. The fixed-wing mechanism 3 includes a wing 31 and a folding component. The wing 31 is located on the fuselage 1 and can be deployed and retracted relative to the fuselage 1. The folding component is used to drive the wing 31 to deploy or retract. The jet mechanism 4 is located on the fuselage 1 and is used to provide power to the fuselage 1 for underwater navigation.

[0031] Understandably, when airborne, the wings 31 unfold into fixed wings, allowing the transmedium aircraft to fly stably with high endurance and maneuverability. When hovering is required, the wings 31 retract, the drive mechanism 22 drives the propeller 21 to rotate and applies vector thrust to the propeller 21, controlling the transmedium aircraft to hover and remain stationary with the propeller 21 pointing upwards, maintaining a stable attitude. When navigating in water, the wings 31 retract, and the jet mechanism 4 provides power, allowing the transmedium aircraft to navigate in water in a torpedo-like manner.

[0032] The cross-medium aircraft can achieve stable hovering and fixed-point hovering in the air using only propeller 21, as well as long-endurance flight and high maneuverability in the air and water. It effectively meets the performance requirements of a cross-medium aircraft that simultaneously possesses stable hovering flight, long endurance, and high maneuverability, adapting to various application scenarios and making its functions more complete.

[0033] For example, the folding component can use a slider to drive the wing 31 to retract, and the specific implementation method is existing technology and will not be described in detail. Additional components are not shown in the figure.

[0034] Specifically, the drive mechanism 22 includes a drive component 22a and a vector rotor component 22b. The drive component 22a is connected to the propeller 21 and is used to drive the propeller 21 to rotate. The vector rotor component 22b is connected to the propeller 21 and is used to apply vector thrust.

[0035] Understandably, the rotation of propeller 21 provides upward lift to fuselage 1, ensuring that fuselage 1 remains in a hovering state with propeller 21 pointing upwards (i.e., fuselage 1 nose-up). Vector rotor component 22b can control the direction of propeller thrust, which is vectored into horizontal and vertical forces. The vertical thrust cancels out the neutral force, while the horizontal force controls the direction. Providing vector thrust during hovering allows propeller 21 to tilt 360°, maintaining the attitude stability of fuselage 1 during hovering flight, and ensuring that fuselage 1 always hovers with its nose-up.

[0036] Furthermore, the propeller 21 includes a first blade 21a and a second blade 21b. The first blade 21a and the second blade 21b are distributed vertically along the length of the fuselage 1, and the drive component 22a is used to drive the first blade 21a to rotate clockwise and drive the second blade 21b to rotate counterclockwise.

[0037] Understandably, the first blade 21a and the second blade 21b rotate in opposite directions, which can counteract the reverse torque and further stabilize the hovering posture.

[0038] For example, the first blade 21a is located below the second blade 21b, and the drive component 22a is disposed between the first blade 21a and the second blade 21b. Of course, in other embodiments, the first blade 21a may also be disposed above the second blade 21b.

[0039] Furthermore, the drive component 22a includes a first direct drive member 221 and a second direct drive member 222. The first direct drive member 221 is connected to the first blade 21a, and the second direct drive member 222 is connected to the second blade 21b. Along the height direction of the fuselage 1, the first blade 21a, the second blade 21b, the first direct drive member 221, and the second direct drive member 222 are coaxially arranged.

[0040] The first direct drive component 221 and the second direct drive component 222 can drive the first blade 21a and the second blade 21b to rotate in a direct drive manner. Compared with motor reduction gear sets or non-direct drive components, this significantly reduces the size of the device and the weight of the aircraft, making it easier to achieve hovering flight and maintain long endurance. Secondly, using direct drive to control the rotation speed results in higher precision, no speed change device, faster response, and effectively reduces mechanical transmission losses.

[0041] For example, both the first direct drive unit 221 and the second direct drive unit 222 can be direct drive motors. Alternatively, they can be selected according to actual needs.

[0042] In one embodiment, the vector rotor component 22b includes a coaxially arranged universal joint 223, a first vector rotor ring 224, a second vector rotor ring 225, and a control ring 226. The first vector rotor ring 224 is sleeved on the universal joint 223 and hinged to it. The second vector rotor ring 225 is sleeved on the first vector rotor ring 224 and hinged to it. The side of the second vector rotor ring 225 away from the first vector rotor ring 224 is drive-connected to the second blade 21b. The control ring 226 is connected to the second vector rotor ring 225 and is connected to a tie rod assembly 23.

[0043] In this embodiment, the universal bracket 223 is connected to the propeller 21 and is coaxially arranged.

[0044] Understandably, when the drive component 22a drives the propeller 21 to rotate, the propeller 21 drives the universal joint 223, the first vector rotor ring 224, and the second vector rotor ring 225 to rotate together. The control ring 226 and the second vector rotor ring 225 are rotatably connected; that is, rotation of the second vector rotor ring 225 will not cause rotation of the control ring 226. When the pull rod assembly 23 inputs a pulling force to the control ring 226, the control ring 226 causes the second vector rotor ring 225 to perform a seesaw motion relative to the first vector rotor ring 224 (with the hinge point as the fulcrum). The first vector rotor ring 224 and the second vector rotor ring 225 form an angle, resulting in vector tilt. By changing the amount of change in the pull rod 231, the first vector rotor ring 224 and the second vector rotor ring 225 can be controlled to form a 360° vector tilt. The vector tilt is then transmitted to the second blade 21b through the drive connection, enabling the propeller 21 to tilt 360°.

[0045] In this configuration, the pitch of the propeller 21 remains constant, and the propeller 21 can form a vector angle with the horizontal plane, changing the overall direction of the thrust. Compared to the variable-pitch rotor structure of a helicopter, this design is simpler, has a lower failure rate, and significantly reduces the size of the device.

[0046] For example, the first vector rotor ring 224 is hinged to the universal bracket 223 through two opposite fulcrums, so that the first vector rotor ring 224 can perform a seesaw motion relative to the universal bracket 223.

[0047] For example, the second vector rotor ring 225 is hinged to the first vector rotor ring 224 through two opposing fulcrums, thereby enabling the second vector rotor ring 225 to perform a seesaw motion relative to the first vector rotor ring 224. Furthermore, the fulcrum connecting the first vector rotor ring 224 to the universal bracket 223, and the fulcrum connecting the second vector rotor ring 225 and the first vector rotor ring 224, are arranged in a cross shape, ensuring that the seesaw motion of the two rotor rings does not restrict each other.

[0048] For example, the second vector rotor ring 225 is connected to the second blade 21b via two oppositely arranged connectors 227. The two ends of each connector 227 are movably connected to the second vector rotor ring 225 and the second blade 21b, respectively. The connection points of the connectors 227 with the second vector rotor ring 225, and with the fulcrum connecting the second vector rotor ring 225 and the first vector rotor ring 224, are also arranged in a cross shape to avoid obstructing the seesaw motion of the second vector rotor ring 225.

[0049] For example, the above-mentioned hinge can be implemented by means of rivets, bolts, etc.

[0050] In one embodiment, the lever assembly 23 includes a lever 231 and a servo motor 232. The servo motor 232 is mounted on the fuselage 1. One end of the lever 231 is connected to the servo motor 232, and the other end is connected to the control ring 226. The servo motor 232 controls the pulling angle and pulling force of the lever 231.

[0051] For example, the lever 231 is connected to the servo motor 232 and the control ring 226 through a ball joint 227, which allows for relative rotation during the connection.

[0052] Furthermore, the propeller 21 also includes a blade folding component, which is used to drive the first blade 21a and the second blade 21b to fold and unfold relative to the fuselage 1, respectively.

[0053] Understandably, both propeller 21 and wings 31 can be folded. When both are folded, the aircraft is basically only the size of fuselage 1, thus enabling it to be converted into a rocket form, resulting in low drag and low noise when sailing underwater.

[0054] Furthermore, the first blade 21a includes a first connecting arm 211 and a first blade 212. The blade folding component is used to connect the first blade 212 and the first connecting arm 211, and the blade folding component can drive the first blade 212 to fold or unfold relative to the first connecting arm 211.

[0055] For example, the center of the first connecting arm 211 is connected to the first direct drive member 221. The first blade 212 is configured as two blades, symmetrically connected to both ends of the first connecting arm 211. The first blade 212 is hinged to the first connecting arm 211, so that the first blade 212 can be flipped up and down relative to the first connecting arm 211 with the connection point as the fulcrum, so as to realize the unfolding or folding of the blade.

[0056] Furthermore, the second blade 21b includes a second connecting arm 213 and a second blade 214. The blade folding component is used to connect the second blade 214 and the second connecting arm 213, and the blade folding component can drive the second blade 214 to fold or unfold relative to the second connecting arm 213.

[0057] For example, the center of the second connecting arm 213 is connected to the second direct drive member 222. The second blade 214 is configured as two blades, symmetrically connected to both ends of the second connecting arm 213. The second blade 214 is hinged to the second connecting arm 213, so that the second blade 214 can be flipped up and down relative to the second connecting arm 213 with the connection point as the fulcrum, so as to realize the unfolding or folding of the blade.

[0058] For example, the blade folding component can use a small motor to directly drive the blade to rotate relative to its connection with the connecting arm, thereby causing the blade to flip and fold. The specific principle is existing technology and will not be described in detail.

[0059] In one embodiment, along the length of the fuselage 1, a plurality of tail fins 11 are provided at the tail end of the fuselage 1, with adjacent tail fins 11 forming a V-shape. The tail fins 11 are located on the outer wall of the fuselage 1. The aforementioned V-shape means that, when projected along the length of the fuselage 1, the projections of two adjacent tail fins 11 can form a V-shape. In this configuration, the tail fins 11 have a small cross-sectional area, resulting in low drag and enabling various maneuvers to be performed.

[0060] For example, four tail fins 11 are provided, evenly distributed around the fuselage 1. Of course, the number is not limited to this and can be selected according to actual needs.

[0061] Furthermore, the jetting mechanism 4 is located inside the body 1, and the tail of the jetting mechanism 4 is provided with a jetting outlet 12. The inner wall of the jetting outlet 12 is provided with multiple flow stabilizing plates 13. The flow stabilizing plates 13 can improve the stability of the jetting water flow and reduce noise.

[0062] For example, the jetting mechanism 4 uses a shaftless ducted propeller, which is highly efficient and can prevent aquatic plants from getting tangled in the propeller 21.

[0063] In one embodiment, a water storage structure, such as a water tank or a water pump, may also be provided inside the fuselage 1 to increase the weight of the fuselage 1 underwater. The specific structure is prior art and will not be described in detail.

[0064] In one embodiment, a fairing 5 is provided on the second blade 21b, and the fairing 5 is shaped like a rocket nose.

[0065] In one embodiment, a shock-absorbing plate 61 and a shock-absorbing ball 62 are provided on the fuselage 1, and the aforementioned servo motor 232 is mounted on the shock-absorbing plate 61. Multiple shock-absorbing balls 62 are provided and are respectively mounted at different positions on the shock-absorbing plate 61. Exemplarily, the shock-absorbing plate 61 and the shock-absorbing ball 62 are made of flexible materials such as rubber, resin, or plastic.

[0066] The wings 31 can be retracted to form an angle with the fuselage 1, preferably an acute angle. When the wings 31 are retracted to this extent, in conjunction with the tail double V tail 11 control surfaces, ground effect is generated when the aircraft is close to the ground (water surface), making the aircraft a ground effect vehicle.

[0067] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0068] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the scope of protection of this application. Therefore, the patent protection scope of this application should be determined by the appended claims.

Claims

1. A trans-medium aircraft, characterized in that, The utility model relates to a kind of aircraft, including: Machine body (1); Rotor mechanism (2) for the aerial hovering flight of the aircraft; The rotor mechanism (2) includes propeller (21) and driving mechanism (22), the driving mechanism (22) is located in machine body (1) and is connected with the propeller (21), for driving the propeller (21) rotation, and the propeller (21) is applied to vector tension to control the attitude stability of the aircraft when aerial hovering flight; Fixed wing mechanism (3) includes wing (31) and folding component, the wing (31) is located on machine body (1), can be unfolded and retracted relative to machine body (1), and the folding component is used to drive the wing (31) unfold or retract; Injection mechanism (4) is located on machine body (1), for providing power for the underwater navigation of the machine body (1).

2. The trans-medium aircraft of claim 1, wherein, The driving mechanism (22) includes driving component (22a) and vector rotor component (22b), the driving component (22a) is connected with the propeller (21), for driving the propeller (21) rotation;The vector rotor component (22b) is connected with the propeller (21), for applying vector tension.

3. The trans-medium vehicle of claim 2, wherein, The propeller (21) includes first blade (21a) and second blade (21b) that are distributed upside down along the length direction of the machine body (1), and the driving component (22a) is used to drive the first blade (21a) forward rotation and drive the second blade (21b) reverse rotation.

4. The trans-medium vehicle of claim 3, wherein, The driving component (22a) includes first direct drive (221) and second direct drive (222), the first direct drive (221) is connected with the first blade (21a), and the second direct drive (222) is connected with the second blade (21b);Along the height direction of the machine body (1), the first blade (21a), the second blade (21b), the first direct drive (221), the second direct drive (222) are coaxially arranged.

5. The trans-medium vehicle of claim 4, wherein, The vector rotor component (22b) includes universal support (223), first vector rotor ring (224), second vector rotor ring (225) and control ring (226) arranged coaxially;The first vector rotor ring (224) is sleeved outside the universal support (223), and is hinged with the universal support (223);The second vector rotor ring (225) is sleeved outside the first vector rotor ring (224), and is hinged with the first vector rotor ring (224);The side, away from the first vector rotor ring (224), of the second vector rotor ring (225) is drivingly connected with the second blade (21b);The control ring (226) is connected with the second vector rotor ring (225), and the control ring (226) is connected with pull rod assembly (23).

6. The trans-medium vehicle of claim 5, wherein, The pull rod assembly (23) includes pull rod (231) and steering gear (232), the steering gear (232) is located on machine body (1), one end of the pull rod (231) is connected with the steering gear (232), and the other end is connected with the control ring (226).

7. The trans-medium vehicle of claim 3, wherein, The propeller (21) further comprises a propeller folding component for driving the first propeller blade (21a) and the second propeller blade (21b) to fold and unfold relative to the fuselage (1) respectively.

8. The trans-medium vehicle of claim 7, wherein, The first propeller blade (21a) comprises a first connecting arm (211) and a first blade (212), the propeller folding component is used for connecting the first blade (212) and the first connecting arm (211), and the propeller folding component can drive the first blade (212) to fold or unfold relative to the first connecting arm (211); the second propeller blade (21b) comprises a second connecting arm (213) and a second blade (214), the propeller folding component is used for connecting the second blade (214) and the second connecting arm (213), and the propeller folding component can drive the second blade (214) to fold or unfold relative to the second connecting arm (213).

9. The trans-medium vehicle of claim 1, wherein, Along the length direction of the fuselage (1), a plurality of tail wings (11) are arranged at the tail of the fuselage (1), and adjacent two tail wings (11) are in a V-shaped structure.

10. The trans-medium vehicle of claim 9, wherein, The spraying mechanism (4) is arranged inside the fuselage (1), and the tail of the spraying mechanism (4) is provided with a spraying outlet (12), and the inner wall of the spraying outlet (12) is provided with a plurality of flow stabilizing plates (13).

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