Configuration-variable aircraft

Abstract

The invention provides a variable configuration aircraft. The variable-configuration aircraft comprises two flow guide columns which are arranged in parallel, a plurality of connecting frames are fixedly installed between the two flow guide columns, folding mechanisms are arranged in the flow guide columns, a lifting propeller is fixedly installed at one end of each folding mechanism, two openings are formed in the sides, away from each other, of the two flow guide columns, and the two openings are communicated with the connecting frames. The folding mechanism is used for withdrawing the lifting propellers from the corresponding openings and then moving the lifting propellers out, and an underwater propelling propeller is arranged at one end of the flow guide column. The variable-configuration aircraft has the advantages of being ingenious in structural design, reliable in mode conversion, high in space utilization rate and high in function expansibility.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more particularly to a variable configuration aircraft. Background Technology

[0002] Transmedia vehicles, capable of both air and underwater operation, have broad application prospects in military reconnaissance, resource exploration, and emergency rescue. These vehicles require resolving the contradictions between efficient air flight and low-drag underwater navigation in terms of aerodynamic / hydrodynamic shape and propulsion methods. Traditional solutions often combine fixed rotors with independent underwater propulsion. However, during underwater navigation, exposed rotors increase drag and can become weak points prone to entanglement or damage. Furthermore, ensuring watertightness during mode transitions to prevent water ingress is a significant technical challenge. Existing deformable designs often suffer from complex structures, slow transition speeds, or insufficient sealing reliability.

[0003] Therefore, it is necessary to provide a new variable-configuration aircraft to solve the above-mentioned technical problems. Summary of the Invention

[0004] The technical problem solved by this invention is to provide a variable configuration aircraft with ingenious structural design, reliable mode switching, high space utilization, and strong functional expandability.

[0005] To solve the above-mentioned technical problems, the variable configuration aircraft provided by the present invention includes: two parallel guide columns, a plurality of connecting frames fixedly installed between the two guide columns, a folding mechanism provided inside the guide columns, a lifting propeller fixedly installed at one end of the folding mechanism, two openings opened on the opposite side of the two guide columns, the folding mechanism being used to retract the lifting propeller from the corresponding opening and move it out, and an underwater propulsion propeller provided at one end of the guide columns.

[0006] Preferably, the guide column is hollow, and both ends of the guide column are tapered.

[0007] Preferably, the folding mechanism includes a rotating seat fixedly installed inside the guide column, a rotating rod rotatably installed on the top of the rotating seat, a rotating ring fixedly sleeved on the outer side of the rotating rod, one end of a connecting rod fixedly installed on one side of the rotating ring, the lifting propeller being connected to the other end of the connecting rod, a first motor fixedly installed inside the guide column, a first gear fixedly installed on the output shaft of the first motor, a second gear fixedly sleeved on the outer side of the rotating rod, and the second gear meshing with the first gear.

[0008] Preferably, the other end of the connecting rod is provided with an angle adjustment mechanism, which is used to adjust the tilt angle of the lifting propeller.

[0009] Preferably, the angle adjustment mechanism includes a mounting groove formed at the other end of the connecting rod, in which a second motor is fixedly mounted, and a mounting block is fixedly mounted on the output shaft of the second motor. The end of the mounting block away from the second motor extends out of the mounting groove and is fixedly connected to the outer wall of the lifting propeller.

[0010] Preferably, a bearing is fixedly sleeved on the outer side of the mounting block, and the outer wall of the bearing is fixedly connected to the inner wall of the mounting groove.

[0011] Preferably, the guide column is provided with a sealing mechanism, which is used to seal the opening when the lifting propeller is completely retracted into the guide column.

[0012] Preferably, the sealing mechanism includes an internal gear ring rotatably installed inside the guide column, the internal gear ring being located at the center of the guide column, connecting plates being fixedly installed on both sides of the internal gear ring, a sealing plate being fixedly installed on the side of the connecting plate away from the internal gear ring, a third motor being fixedly installed on the inner wall of the guide column, a third gear being fixedly installed on the output shaft of the third motor, and the third gear meshing with the internal gear ring.

[0013] Preferably, the sealing plate is rotatably and sealingly connected to the inner wall of the guide column.

[0014] Preferably, the connecting frame is hollow.

[0015] Compared with related technologies, the variable configuration aircraft provided by this invention has the following advantages:

[0016] This invention provides a variable-configuration aircraft that combines a retractable lift propeller mechanism, a fixed external underwater propulsion propeller, and a multifunctional hollow connecting frame integrating wiring conduits and equipment mounting functions. This achieves efficient and reliable switching between airborne and underwater modes, resulting in significant improvements in versatility, performance optimization, and functional expansion. Specifically, through the coordinated operation of a motor-driven folding mechanism and a sealing mechanism, the lift propeller can be quickly and reliably retracted into a streamlined guide column and the opening tightly sealed, thus achieving a smooth and safe transition from multi-rotor airborne flight mode to underwater vehicle mode. The system features a fully convertible design. By adopting a fixed-mount underwater propulsion propeller, the complex tail-end storage mechanism is eliminated. This ensures efficient underwater propulsion while greatly simplifying the tail structure and improving the overall reliability and immediate deployment capability of the system. Furthermore, by designing the connecting frame as a hollow structure and giving it the functions of wiring, piping, and loading mission equipment, not only is the utilization of internal space optimized and the resistance of exposed cables and pipes reduced, but a modular payload platform is also constructed. This allows for the rapid and flexible configuration of functional modules according to different mission requirements such as reconnaissance, detection, and transportation, greatly expanding the mission adaptability and application scenarios of the aircraft. Attached Figure Description

[0017] Figure 1 A schematic diagram of the structure of the variable configuration aircraft provided by the present invention after the elevator propeller is deployed;

[0018] Figure 2 for Figure 1 A structural schematic diagram from another perspective is shown;

[0019] Figure 3 for Figure 1 The diagram shows a cross-sectional view of the structure.

[0020] Figure 4 for Figure 1 A schematic diagram showing the connection structure of the lifting propeller, folding mechanism, and angle adjustment mechanism;

[0021] Figure 5 for Figure 4 A schematic diagram of the cross-sectional structure from another perspective is shown;

[0022] Figure 6 for Figure 5 An enlarged structural diagram of part A shown;

[0023] Figure 7 for Figure 1 The diagram shows the structure of the sealing mechanism.

[0024] Figure 8A schematic diagram of the structure of the variable configuration aircraft provided by the present invention after the lift propeller is housed inside the guide column;

[0025] Figure 9 for Figure 8 The schematic diagram of the cross-sectional structure.

[0026] The diagram is labeled as follows: 1. Guide column, 2. Connecting frame, 3. Underwater propulsion propeller, 4. Folding mechanism, 401. Rotating seat, 402. Rotating rod, 403. Rotating ring, 404. Connecting rod, 405. First motor, 406. First gear, 407. Second gear, 5. Lifting propeller, 6. Angle adjustment mechanism, 601. Mounting slot, 602. Mounting block, 603. Second motor, 604. Bearing, 7. Sealing mechanism, 701. Internal gear ring, 702. Connecting piece, 703. Sealing piece, 704. Third motor, 705. Third gear, 706. Sealing strip, 8. Opening. Detailed Implementation

[0027] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0028] Please refer to the following: Figures 1-9 ,in, Figure 1 A schematic diagram of the structure of the variable configuration aircraft provided by the present invention after the elevator propeller is deployed; Figure 2 for Figure 1 A structural schematic diagram from another perspective is shown; Figure 3 for Figure 1 The diagram shows a cross-sectional view of the structure. Figure 4 for Figure 1 A schematic diagram showing the connection structure of the lifting propeller, folding mechanism, and angle adjustment mechanism; Figure 5 for Figure 4 A schematic diagram of the cross-sectional structure from another perspective is shown; Figure 6 for Figure 5 An enlarged structural diagram of part A shown; Figure 7 for Figure 1 The diagram shows the structure of the sealing mechanism. Figure 8 A schematic diagram of the structure of the variable configuration aircraft provided by the present invention after the lift propeller is housed inside the guide column; Figure 9 for Figure 8The cross-sectional structural diagram is shown. The variable configuration aircraft includes: two parallel guide columns 1, with multiple connecting frames 2 fixedly installed between the two guide columns 1. A folding mechanism 4 is provided inside each guide column 1, and a lifting propeller 5 is fixedly installed at one end of each folding mechanism 4. Two openings 8 are opened on the opposite sides of each of the two guide columns 1. The folding mechanism 4 is used to retract and remove the lifting propeller 5 from the corresponding openings 8. By designing the lifting propeller 5 to be completely retracted into the guide column 1, the lifting propeller 5 can be retracted during underwater navigation to avoid increasing drag, preventing collisions or biological entanglement, and to obtain better hydrodynamic performance by utilizing the streamlined shell of the guide column 1. An underwater propulsion propeller 3 is provided at one end of each guide column 1.

[0029] The guide column 1 is hollow, and both ends of the guide column 1 are tapered. The hollow design of the guide column 1 can provide space for the internal mechanism, and the tapered design of both ends can further reduce the navigation resistance in air and water.

[0030] The folding mechanism 4 includes a rotating seat 401 fixedly installed inside the guide column 1. A rotating rod 402 is rotatably mounted on the top of the rotating seat 401. A rotating ring 403 is fixedly sleeved on the outer side of the rotating rod 402. One end of a connecting rod 404 is fixedly installed on one side of the rotating ring 403. The lifting propeller 5 is connected to the other end of the connecting rod 404. A first motor 405 is fixedly installed inside the guide column 1. A first gear 406 is fixedly installed on the output shaft of the first motor 405. A second gear 407 is fixedly sleeved on the outer side of the rotating rod 402. The second gear 407 meshes with the first gear 406. The principle is that the first motor 405 drives the first gear 406 to rotate, which in turn drives the meshing second gear 407 and the rotating rod 402 to rotate, thereby driving the rotating ring 403, the connecting rod 404 and the lifting propeller 405 to rotate, fold or unfold around the axis of the rotating rod 402. By converting linear folding motion into rotational motion, the structure is compact and easy to arrange in the narrow space of the guide column.

[0031] The other end of the connecting rod 404 is provided with an angle adjustment mechanism 6, which is used to adjust the tilt angle of the lift propeller 5. This allows the aircraft to not only achieve vertical take-off and landing in the air, but also to provide a horizontal thrust component through the tilting lift propeller 5, thereby achieving forward, backward or lateral maneuvers and enhancing the flexibility of flight control.

[0032] The angle adjustment mechanism 6 includes a mounting groove 601 at the other end of the connecting rod 404. A second motor 603 is fixedly installed in the mounting groove 601. A mounting block 602 is fixedly installed on the output shaft of the second motor 603. The end of the mounting block 602 away from the second motor 603 extends out of the mounting groove 601 and is fixedly connected to the outer wall of the lifting propeller 5. The second motor 603 directly drives the mounting block 602 to rotate, which in turn drives the lifting propeller 5 to deflect at the end of the connecting rod 404, thereby changing its thrust direction. The control logic is simple and direct.

[0033] A bearing 604 is fixedly sleeved on the outer side of the mounting block 602, and the outer wall of the bearing 604 is fixedly connected to the inner wall of the mounting groove 601.

[0034] The guide column 1 is equipped with a sealing mechanism 7, which is used to seal the opening 8 when the lifting propeller 5 is completely retracted into the guide column 1.

[0035] The sealing mechanism 7 includes an internal gear ring 701 rotatably mounted inside the guide column 1. The internal gear ring 701 is located at the center of the guide column 1. Connecting pieces 702 are fixedly mounted on both sides of the internal gear ring 701. A sealing piece 703 is fixedly mounted on the side of the connecting piece 702 away from the internal gear ring 701. A third motor 704 is fixedly mounted on the inner wall of the guide column 1. A third gear 705 is fixedly mounted on the output shaft of the third motor 704. The third gear 705 meshes with the internal gear ring 701. The working principle is as follows: the third motor 704 drives the third gear 705 to rotate, which in turn drives the internal gear ring 701 to rotate. This, in turn, drives the sealing plates 703 on both sides to rotate synchronously through the connecting plate 702. When it is necessary to open the opening 8, the sealing plate 703 rotates 180° to the inner wall of the side away from the opening 8 from the guide column 1. When it is necessary to close the opening 8, the sealing plate 703 rotates 180° to cover the opening 8. This design uses one drive source to synchronously control the sealing plates 703 of the two openings 8, which has good synchronicity and simple and reliable control.

[0036] The sealing piece 703 is rotatably sealed to the inner wall of the guide column 1, which ensures that when the sealing piece covers the opening, it can form a reliable sealing surface with the inner wall of the guide column, effectively preventing liquid from seeping in. A layer of silicone material with good sealing properties can be provided on one side where the sealing piece 703 is in contact with the inner wall of the guide column 1.

[0037] The connecting frame 2 is hollow. The hollow structure of the connecting frame 2 can reduce the overall weight while ensuring structural strength. Its internal cavity can be used to arrange lines, pipes (such as cooling pipes) or to accommodate other equipment, which improves space utilization. The connecting frame 2 can also be used as a support frame for external objects to achieve stable support for the objects.

[0038] The working principle of the variable configuration aircraft provided by this invention is as follows:

[0039] When the aircraft needs to take off, firstly, the third motor 704 of the sealing mechanism 7 works, driving the sealing plate 703 to rotate and open the opening 8 on the side wall of the guide column 1. Then, the first motor 405 of the folding mechanism 4 works, driving the connecting rod 404 to rotate and extend the lifting propeller 5 from the opening 8 to the horizontal working position and lock it. The four lifting propellers 5 are started. According to the flight control command, by adjusting their respective speed and angle, the deflection angle of the adjustment mechanism 6 can be adjusted, and the aircraft can realize complex flight maneuvers such as vertical take-off, hovering, forward, backward, left and right translation, pitch and roll. The underwater propulsion propeller 3 at the tail can be turned off or started as needed. When started during high-speed forward flight, it can provide additional forward thrust to increase speed and range.

[0040] When the aircraft needs to transition from air to water to perform a mission, it flies to a height of about 1.5 meters above the target water area and starts the first motor 405, which drives the folding mechanism 4 to rotate and retract the four lifting propellers 5 in sequence into the guide column 1. Immediately afterwards, the third motor 704 immediately activates, driving the sealing plate 703 to rotate rapidly and tightly seal the corresponding opening 8. The sealing strip 706 ensures a reliable seal. At this time, the outer contour of the aircraft becomes a smooth streamline, and the aircraft can land on the water surface in a controlled manner. It can then begin to dive by adjusting the remaining buoyancy or fine-tuning the tail thruster 3.

[0041] After fully submerging underwater, the aircraft switches to underwater navigation mode. A dry chamber is formed inside the guide column 1, which is tightly protected by the sealing mechanism 7. The elevator propeller 5 stops working, and one or two underwater propulsion propellers 3 at the tail become the main propulsion power. Through differential speed or in conjunction with the control surfaces at the rear of the guide column, the aircraft can achieve three degrees of freedom of movement underwater. In this mode, the underwater mission payloads (such as sonar, depth sensors, underwater cameras, manipulators, etc.) mounted in the equipment compartment inside or outside the connecting frame 2 begin to work and perform detection, observation or operation tasks.

[0042] After the underwater mission is completed, the aircraft rises to near the water surface. The third motor 704 drives the sealing mechanism 7 to open the opening 8, and the first motor 405 drives the folding mechanism 4 to quickly push out the lifting propeller 5. The lifting propeller 5 starts at high speed, generating strong lift, lifting the aircraft from the water and lifting it into the air. After leaving the water, the aircraft returns to the air flight mode and can return to base or continue aerial operations.

[0043] Compared with related technologies, the variable configuration aircraft provided by this invention has the following advantages:

[0044] This invention provides a variable-configuration aircraft that combines a retractable lift propeller mechanism 5, a fixed external underwater propulsion propeller 3, and a multi-functional hollow connecting frame 2 integrating wiring conduits 202 and equipment mounting functions. This achieves efficient and reliable switching between airborne and underwater modes, resulting in significant improvements in versatility, performance optimization, and functional expansion. Specifically, through the coordinated operation of a motor-driven folding mechanism 4 and a sealing mechanism 7, the lift propeller 5 can be quickly and reliably retracted into the streamlined guide column 1 and the opening 8 tightly sealed, thus enabling the transformation from multi-rotor airborne flight mode to underwater submersible mode. Smooth and safe transition; by adopting a fixed-mounted underwater propulsion propeller 3, the complex tail-end storage mechanism is eliminated, which greatly simplifies the tail structure while ensuring efficient underwater propulsion, and improves the overall reliability and immediate deployment capability of the system; furthermore, by designing the connecting frame 2 as a hollow structure and endowing it with the functions of wiring, pipe laying and loading mission equipment, not only is the utilization of internal space optimized and the resistance of exposed messy cables and pipes reduced, but a modular payload platform is also constructed, which can quickly and flexibly configure functional modules according to different mission requirements such as reconnaissance, detection and transportation, greatly expanding the mission adaptability and application scenario range of the aircraft.

[0045] The above description is merely an embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural or procedural transformations made based on the content of the present invention specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A variable-configuration aircraft, characterized in that, include: Two parallel guide columns are provided, and multiple connecting frames are fixedly installed between the two guide columns. A folding mechanism is provided inside the guide columns, and a lifting propeller is fixedly installed at one end of the folding mechanism. Two openings are opened on the side of the two guide columns that are far apart from each other. The folding mechanism is used to retract the lifting propeller from the corresponding opening and move it out. An underwater propulsion propeller is provided at one end of the guide columns.

2. The variable configuration aircraft according to claim 1, characterized in that, The guide column is hollow, and both ends of the guide column are tapered.

3. The variable configuration aircraft according to claim 1, characterized in that, The folding mechanism includes a rotating seat fixedly installed inside the guide column. A rotating rod is rotatably installed on the top of the rotating seat. A rotating ring is fixedly sleeved on the outer side of the rotating rod. One end of a connecting rod is fixedly installed on one side of the rotating ring. The lifting propeller is connected to the other end of the connecting rod. A first motor is fixedly installed inside the guide column. A first gear is fixedly installed on the output shaft of the first motor. A second gear is fixedly sleeved on the outer side of the rotating rod. The second gear meshes with the first gear.

4. The variable configuration aircraft according to claim 2, characterized in that, The other end of the connecting rod is provided with an angle adjustment mechanism, which is used to adjust the tilt angle of the lifting propeller.

5. The variable configuration aircraft according to claim 4, characterized in that, The angle adjustment mechanism includes a mounting groove at the other end of the connecting rod. A second motor is fixedly installed in the mounting groove. A mounting block is fixedly installed on the output shaft of the second motor. The end of the mounting block away from the second motor extends out of the mounting groove and is fixedly connected to the outer wall of the lifting propeller.

6. The variable configuration aircraft according to claim 5, characterized in that, A bearing is fixedly sleeved on the outside of the mounting block, and the outer wall of the bearing is fixedly connected to the inner wall of the mounting groove.

7. The variable configuration aircraft according to claim 1, characterized in that, The guide column is equipped with a sealing mechanism, which is used to seal the opening when the lifting propeller is completely retracted into the guide column.

8. The variable configuration aircraft according to claim 7, characterized in that, The sealing mechanism includes an internal gear ring rotatably installed inside the guide column, the internal gear ring being located at the center of the guide column, connecting plates being fixedly installed on both sides of the internal gear ring, a sealing plate being fixedly installed on the side of the connecting plate away from the internal gear ring, a third motor being fixedly installed on the inner wall of the guide column, a third gear being fixedly installed on the output shaft of the third motor, and the third gear meshing with the internal gear ring.

9. The variable configuration aircraft according to claim 1, characterized in that, The sealing plate is rotatably and sealingly connected to the inner wall of the guide column.

10. The variable configuration aircraft according to claim 1, characterized in that, The connecting frame is hollow.

Images