A tilt-rotor retractable tandem dual-rotor trans-medium aircraft

Abstract

This invention discloses a tilt-rotor retractable tandem dual-rotor transmedium aircraft, including a fuselage and front and rear lift mechanisms located at the front and rear of the fuselage. The front and rear lift mechanisms include corresponding front and rear upper rotors, front and rear upper rotor drive devices for driving the rotation of the front and rear upper rotors, front and rear lower rotors, front and rear lower rotor drive devices for driving the rotation of the front and rear lower rotors, front and rear upper rotor lifting devices connected between the front and rear upper rotor drive devices and the front and rear lower rotor drive devices, and front and rear tilt drive devices for driving the front and rear upper rotor lifting devices to rotate about the fuselage axis. This solution improves upon the basic characteristics of traditional tandem dual-rotor UAVs, meeting the demand for heavy payloads in the UAV market. Through the design of dual counter-rotors, it effectively solves the problems of poor longitudinal stability and low yaw efficiency in ordinary tandem dual-rotor aircraft.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft, and in particular to a tandem dual-rotor transmedium aircraft with a tilt-rotor retractable rotor. Background Technology

[0002] Tandem rotor helicopters offer numerous advantages. For instance, the counter-rotating rotors can counteract fuselage torque, eliminating the need for a tail rotor for balancing and significantly improving hovering efficiency. Their compact design and wide center of gravity range also enhance payload efficiency and capacity. The CH-47 Chinook is currently the most successful tandem rotor helicopter in the world. In terms of miniaturization, tandem rotor unmanned helicopters currently under research and design outperform fixed-wing UAVs of the same weight and power in terms of payload capacity, making them suitable for applications requiring high payloads, such as agricultural plant protection, fire rescue, supply resupply, and photography. However, stability is limited by the tandem rotor design, resulting in lower longitudinal stability. Yaw efficiency is also low due to the differential aerodynamic control of the rotors. While coaxial rotor designs also exist, with four rotors, they are structurally complex and inefficient. To address this issue and improve payload capacity, some engineers added four rotors to the tandem dual-rotor design, adopting a multi-rotor drone layout. This significantly improved stability, but due to the limited space and small blade size, the payload capacity increase was limited, and the footprint was larger than before. Other engineers designed a series of tandem tri-rotor, quad-rotor, pent-rotor, and hexa-rotor drones, but none of these offered significant improvements in maneuverability. The increased payload capacity resulted in increased energy consumption, and the turbulent airflow caused by too many rotors led to a decrease in stability.

[0003] In summary, tandem UAVs have a higher payload ratio than other types of UAVs, offering a payload advantage unmatched by other UAV types. While conventional tandem dual-rotor UAVs can carry a larger payload than quadcopters and fixed-wing UAVs, their stability and maneuverability are inferior, making them less suitable for combat and rescue applications. To address payload capacity issues, stability is often prioritized, and payload capacity is increased by enlarging the structure and adding power.

[0004] Based on the above issues, it can be seen that there is still room for improvement in the optimization of tandem UAVs, especially in terms of longitudinal stability and yaw efficiency. Summary of the Invention

[0005] The purpose of this invention is to provide a tilt-rotor retractable tandem dual-rotor transmedium aircraft to solve the problems of poor longitudinal stability and low yaw efficiency in existing aircraft.

[0006] To address the aforementioned technical problems, this invention provides a tiltrotor retractable tandem dual-rotor transmedium aircraft, comprising a fuselage, a front lift mechanism located at the front of the fuselage, and a rear lift mechanism located at the rear of the fuselage; the front lift mechanism includes a front upper rotor, a front upper wing drive device for driving the front upper rotor, a front lower rotor, a front lower wing drive device for driving the front lower rotor, and a front upper wing lift mechanism connecting the front upper wing drive device and the front lower wing drive device. The device includes a front tilt drive device that drives the front upper wing elevator to rotate about the fuselage axis; the rear lift mechanism includes a rear upper rotor, a rear upper wing drive device that drives the rear upper rotor to rotate, a rear lower rotor, a rear lower wing drive device that drives the rear lower rotor to rotate, a rear upper wing elevator device connected between the rear upper wing drive device and the rear lower wing drive device, and a rear tilt drive device that drives the rear upper wing elevator to rotate about the fuselage axis.

[0007] In one embodiment, a structural beam is provided inside the fuselage, the structural beam extending along the axial direction of the fuselage, and the front tilt drive device and the rear tilt drive device are respectively installed at both ends of the structural beam.

[0008] In one embodiment, the fuselage has an upper front through-hole and a lower front through-hole respectively at the top and bottom of the front part; the front tilt drive device is located inside the fuselage, one end of the front tilt drive device passes through the upper front through-hole and is connected to the upper front wing drive device, and the other end of the front tilt drive device passes through the lower front through-hole and is connected to the lower front wing drive device; both the upper front through-hole and the lower front through-hole are used to provide space for the front tilt drive device to tilt and rotate inside it.

[0009] In one embodiment, the fuselage has an upper rear through-hole and a lower rear through-hole at its upper and lower rear sides, respectively; the rear tilt drive device is located inside the fuselage, one end of the rear tilt drive device passes through the upper rear through-hole and connects to the upper rear wing drive device, and the other end of the rear tilt drive device passes through the lower rear through-hole and connects to the lower rear wing drive device; both the upper rear through-hole and the lower rear through-hole provide space for the rear tilt drive device to tilt and rotate within it.

[0010] In one embodiment, the front upper wing lifting device includes a front lifting motor and a front screw drive unit that is driven by the front lifting motor to extend and retract, the front screw drive unit being connected to the front upper wing driving device.

[0011] In one embodiment, the front screw drive unit includes a front coupling, a front screw, a front threaded sleeve, a front push rod, a front slider, and a front guide rail; the front coupling connects the output shaft of the front lifting motor and the front screw; the front screw is threadedly connected to the front threaded sleeve; the front threaded sleeve is fixedly connected to the front push rod; the front slider is provided outside the front push rod; the front slider is slidably mounted on the front guide rail; the arrangement trajectory of the front guide rail is consistent with the axial direction of the front screw.

[0012] In one embodiment, the front upper wing lifting device further includes a front base, on which the front lifting motor and the front guide rail are fixedly mounted, and the front base is rotatably connected to the front tilt drive device.

[0013] In one embodiment, the rear upper wing lifting device includes a rear lifting motor and a rear screw drive unit that is driven to extend and retract by the rear lifting motor, the rear screw drive unit being connected to the rear upper wing driving device.

[0014] In one embodiment, the rear screw drive unit includes a rear coupling, a rear screw, a rear threaded sleeve, a rear push rod, a rear slider, and a rear guide rail; the rear coupling connects the output shaft of the rear lifting motor and the rear screw; the rear screw is threadedly connected to the rear threaded sleeve; the rear threaded sleeve is fixedly connected to the rear push rod; the rear slider is provided outside the rear push rod; the rear slider is slidably mounted on the rear guide rail; the arrangement trajectory of the rear guide rail is consistent with the axial direction of the rear screw.

[0015] In one embodiment, the rear upper wing lifting device further includes a rear base, on which the rear lifting motor and the rear guide rail are fixedly mounted, and the rear base is rotatably connected to the rear tilt drive device.

[0016] The beneficial effects of this invention are as follows:

[0017] (1) In terms of payload ratio, the four rotors work together to effectively improve the payload capacity and meet the needs of small and medium-sized UAVs for a large payload ratio.

[0018] (2) In terms of stability, the design of the front upper rotor and the rear upper rotor being able to be raised and lowered brings the center of gravity of the UAV closer to the bottom. By raising the rotor to complete a series of actions, the flight stability is significantly improved.

[0019] (3) In terms of maneuverability, the four rotors work together. When yawing during stable maneuvers, the front and rear pairs of rotors are offset in the same direction. When yawing or rotating during rapid maneuvers, the front and rear pairs of rotors are offset in opposite directions and can rotate around the axis. Only the rear pair of rotors is offset and can rotate around the axis of the front rotor. Attached Figure Description

[0020] To more clearly illustrate the technical solution of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the structure provided in an embodiment of the present invention;

[0022] Figure 2 yes Figure 1 A partial top view of the structure;

[0023] Figure 3 yes Figure 1 A partial structural bottom view;

[0024] Figure 4 yes Figure 1 Internal structure diagram;

[0025] Figure 5 yes Figure 4 Schematic diagram of the cross-sectional structure of the front upper wing elevator;

[0026] Figure 6 yes Figure 4 A cross-sectional structural diagram of the rear upper wing elevator.

[0027] The attached figures are labeled as follows:

[0028] 10. Fuselage; 11. Legs; 12. Structural beam; 13. Front upper through hole; 14. Front lower through hole; 15. Rear upper through hole; 16. Rear lower through hole;

[0029] 20. Front lift mechanism; 21. Front upper rotor; 22. Front upper rotor drive device; 23. Front lower rotor; 24. Front lower rotor drive device; 25. Front upper rotor lifting device; 251. Front lifting motor; 252. Front coupling; 253. Front screw; 254. Front threaded sleeve; 255. Front push rod; 256. Front slider; 257. Front guide rail; 258. Front base; 259. Front fixing bolt; 26. Front tilt drive device;

[0030] 30. Rear lift mechanism; 31. Rear upper rotor; 32. Rear upper wing drive device; 33. Rear lower rotor; 34. Rear lower wing drive device; 35. Rear upper wing lifting device; 351. Rear lifting motor; 352. Rear coupling; 353. Rear screw; 354. Rear threaded sleeve; 355. Rear push rod; 356. Rear slider; 357. Rear guide rail; 358. Rear base; 359. Rear fixing bolt; 36. Rear tilt drive device. Detailed Implementation

[0031] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0032] This invention provides a tilt-rotor retractable tandem dual-rotor transmedium aircraft, the implementation of which is as follows: Figure 1 and Figure 4 As shown, it includes a fuselage 10, a front lift mechanism 20 located at the front of the fuselage 10, and a rear lift mechanism 30 located at the rear of the fuselage 10.

[0033] Regarding the aforementioned front lifting mechanism 20, as Figure 1 and Figure 4 As shown, this embodiment includes a front lift mechanism 20 comprising a front upper rotor 21, a front upper rotor drive device 22 for driving the front upper rotor 21 to rotate, a front lower rotor 23, a front lower rotor drive device 24 for driving the front lower rotor 23 to rotate, a front upper rotor lifting device 25 connected between the front upper rotor drive device 22 and the front lower rotor drive device 24, and a front tilt drive device 26 for driving the front upper rotor lifting device 25 to rotate about the fuselage 10 axis.

[0034] The front upper rotor 21, as described Figure 1 As shown, it is located on the upper front of the fuselage 10 and is a two-bladed rotor structure.

[0035] The front upper wing drive device 22, as Figure 1 As shown, it is located above the front of the fuselage 10 and below the front upper rotor 21. In this embodiment, the front upper rotor drive device 22 is a motor, which is connected and fixed to the front upper rotor 21 by its own output shaft. Therefore, when the front upper rotor drive device 22 is running, it can drive the front upper rotor 21 to rotate at high speed, so as to generate driving force above the front of the fuselage 10.

[0036] The front lower rotor 23, as described Figure 1 As shown, it is located at the lower front of the fuselage 10 and is a two-bladed rotor structure.

[0037] The front lower wing drive device 24, as described Figure 1As shown, it is located below the front of the fuselage 10 and above the front lower rotor 23. In this embodiment, the front lower rotor drive device 24 is a motor, which is connected and fixed to the front lower rotor 23 by its own output shaft. Therefore, when the front lower rotor drive device 24 is running, it can drive the front lower rotor 23 to rotate at high speed, so as to generate driving force below the front of the fuselage 10.

[0038] The aforementioned upper front wing lifting device 25 is used to control the lifting of the upper front rotor 21; therefore, any device capable of controlling the vertical movement of the upper front rotor 21 can be considered as the upper front wing lifting device 25. Figure 4 and Figure 5 As shown, this embodiment includes a front upper wing lifting device 25 comprising a front lifting motor 251 and a front screw transmission unit that is driven by the front lifting motor 251 to extend and retract. The front screw transmission unit is connected to the front upper wing drive device 22, thus realizing lifting control by using screw transmission for linear movement.

[0039] Specifically, the front screw drive unit at this time includes a front coupling 252, a front screw 253, a front threaded sleeve 254, a front push rod 255, a front slider 256, and a front guide rail 257. The front coupling 252 connects the output shaft of the front lifting motor 251 and the front screw 253, so that when the front lifting motor 251 is running, the front screw 253 can be synchronously rotated. The front screw 253 is threaded into the front threaded sleeve 254, so that when the front screw 253 rotates, it can achieve linear reciprocating movement control of the front threaded sleeve 254. The front threaded sleeve 254 and the front push rod 256 are connected to the front screw 257. The front threaded sleeve 254 is fixed in place to ensure that it can drive the front push rod 255 to move synchronously in a straight line when the front push rod 254 moves in a straight line. The front push rod 255 is provided with a front slider 256 to ensure that the front push rod 255 can drive the front slider 256 to move synchronously in a straight line when it moves in a straight line. The front slider 256 is slidably mounted on the front guide rail 257 to ensure that the front slider 256 can only move in a straight line along the trajectory of the front guide rail 257. The arrangement trajectory of the front guide rail 257 is consistent with the axial direction of the front screw 253, thus limiting the lifting trajectory of the front upper wing lifting device 25.

[0040] Furthermore, in order to achieve the rotatable connection between the front upper wing elevator 25 and the front tilt drive 26, such as Figure 4 and Figure 5 As shown, this embodiment includes a front upper wing lifting device 25, which also includes a front base 258. A front lifting motor 251 and a front guide rail 257 are fixedly installed on the front base 258. The front base 258 is rotatably connected to the front tilt drive device 26.

[0041] Specifically, in this embodiment, the front base 258 is roughly a rectangular column. At the bottom of the front base 258, it is connected and fixed to the top of the front lifting motor 251 using front fixing bolts 259 to achieve a firm assembly with the front lifting motor 251. Inside the front base 258, it is set as a hollow structure to facilitate the installation of the front screw drive unit. On the side of the front base 258, it is rotatably connected to the front tilt drive device 26. For example, in this embodiment, the front tilt drive device 26 is essentially a servo motor, so it is only necessary to rotatably connect the output shaft of the front tilt drive device 26 to the side of the front base 258.

[0042] Regarding the aforementioned rear lifting mechanism 30, such as Figure 1 and Figure 4 As shown, this embodiment includes a rear lift mechanism 30 comprising a rear upper rotor 31, a rear upper rotor drive device 32 for driving the rear upper rotor 31 to rotate, a rear lower rotor 33, a rear lower rotor drive device 34 for driving the rear lower rotor 33 to rotate, a rear upper rotor lifting device 35 connected between the rear upper rotor drive device 32 and the rear lower rotor drive device 34, and a rear tilt drive device 36 for driving the rear upper rotor lifting device 35 to rotate about the fuselage 10 axis.

[0043] The rear upper rotor 31, as described Figure 1 As shown, it is located on the upper rear part of the fuselage 10 and is a two-bladed rotor structure.

[0044] The rear upper wing drive device 32, as described Figure 1 As shown, it is located above the rear of the fuselage 10 and below the rear upper rotor 31. In this embodiment, the rear upper rotor drive device 32 is a motor, which is connected and fixed to the rear upper rotor 31 by its own output shaft. So when the rear upper rotor drive device 32 is running, it can drive the rear upper rotor 31 to rotate at high speed, so as to generate driving force above the rear of the fuselage 10.

[0045] The rear lower rotor 33, as described Figure 1 As shown, it is located at the lower rear of the fuselage 10 and is a two-bladed rotor structure.

[0046] The rear lower wing drive device 34, as described Figure 1 As shown, it is located at the lower rear of the fuselage 10 and above the rear lower rotor 33. In this embodiment, the rear lower rotor drive device 34 is a motor, which is connected and fixed to the rear lower rotor 33 by its own output shaft. So when the rear lower rotor drive device 34 is running, it can drive the rear lower rotor 33 to rotate at high speed, so as to generate driving force at the lower rear of the fuselage 10.

[0047] The rear upper wing lifting device 35 is used to control the lifting of the rear upper rotor 31, so any device capable of controlling the vertical movement of the rear upper rotor 31 can be considered as the rear upper wing lifting device 35; and such Figure 4 and Figure 6 As shown, this embodiment includes a rear upper wing lifting device 35 comprising a rear lifting motor 351 and a rear screw transmission unit that is driven by the rear lifting motor 351 to extend and retract. The rear screw transmission unit is connected to the rear upper wing drive device 32, thus realizing lifting control by using screw transmission for linear movement.

[0048] Specifically, the rear screw drive unit at this time includes a rear coupling 352, a rear screw 353, a rear threaded sleeve 354, a rear push rod 355, a rear slider 356, and a rear guide rail 357. The rear coupling 352 connects the output shaft of the rear lifting motor 351 and the rear screw 353, so that when the rear lifting motor 351 is running, it can realize the synchronous rotation control of the rear screw 353. The rear screw 353 is threaded into the rear threaded sleeve 354, so that when the rear screw 353 rotates, it can realize the linear reciprocating movement control of the rear threaded sleeve 354. The rear threaded sleeve 354 and the rear push rod 356 are connected to the rear screw 357. The rear threaded sleeve 354 is fixed in place to ensure that it can drive the rear push rod 355 to move synchronously in a straight line when the rear threaded sleeve 354 moves in a straight line. The rear push rod 355 is provided with a rear slider 356 to ensure that the rear push rod 355 can drive the rear slider 356 to move synchronously in a straight line when it moves in a straight line. The rear slider 356 is slidably mounted on the rear guide rail 357 to ensure that the rear slider 356 can only move in a straight line along the trajectory of the rear guide rail 357. The arrangement trajectory of the rear guide rail 357 is consistent with the axial direction of the rear screw 353, thus limiting the lifting trajectory of the rear upper wing lifting device 35.

[0049] Furthermore, in order to achieve the rotatable connection between the rear upper wing elevator 35 and the rear tilt drive 36, such as Figure 4 and Figure 6 As shown, this embodiment includes a rear upper wing lifting device 35, which also includes a rear base 358. A rear lifting motor 351 and a rear guide rail 357 are fixedly installed on the rear base 358. The rear base 358 is rotatably connected to the rear tilting drive device 36.

[0050] Specifically, in this embodiment, the rear base 358 is roughly a rectangular column. At the bottom of the rear base 358, it is connected and fixed to the top of the rear lifting motor 351 using rear fixing bolts 359 to achieve a firm assembly with the rear lifting motor 351. Inside the rear base 358, it is set as a hollow structure to facilitate the installation of the rear screw drive unit. On the side of the rear base 358, it is rotatably connected to the rear tilt drive device 36. For example, in this embodiment, the rear tilt drive device 36 is essentially a servo motor, so it is only necessary to rotatably connect the output shaft of the rear tilt drive device 36 to the side of the rear base 358.

[0051] Regarding the aforementioned fuselage 10, as Figure 1 As shown, the fuselage 10 in this embodiment is roughly elongated. The head and tail of the fuselage 10 are both approximately conical structures, but the tip of the conical structure and the connecting transition structures at various parts of the fuselage are all arc-shaped transitions, thereby ensuring the overall streamlined design of the fuselage 10 to reduce the drag experienced by the fuselage 10 during flight. The bottom of the fuselage 10 is equipped with landing gear 11 to facilitate the landing operation of the aircraft.

[0052] Among them, such as Figure 4 As shown, in this embodiment, a structural beam 12 is provided inside the fuselage 10. The structural beam 12 extends along the axial direction of the fuselage 10, and a front tilt drive device 26 and a rear tilt drive device 36 are respectively installed at both ends of the structural beam 12. In order to ensure that the front tilt drive device 26 and the rear tilt drive device 36 are firmly installed, this embodiment also provides two structural beams 12, so as to use two structural beams 12 to install and fix the upper and lower parts of the front tilt drive device 26 and the rear tilt drive device 36, thereby improving the installation firmness of the front tilt drive device 26 and the rear tilt drive device 36.

[0053] In addition, in order not to affect the tilting operation of the front tilt drive 26, such as Figures 1 to 3 As shown, in this embodiment, a front upper through hole 13 and a front lower through hole 14 are respectively provided on the upper and lower parts of the front of the fuselage 10. Both the front upper through hole 13 and the front lower through hole 14 are circular holes. Since the front tilt drive device 26 is located inside the fuselage 10, one end of the front tilt drive device 26 can pass through the front upper through hole 13 and connect to the front upper wing drive device 22, while the other end of the front tilt drive device 26 can pass through the front lower through hole 14 and connect to the front lower wing drive device 24.

[0054] Obviously, the diameters of the upper front through-hole 13 and the lower front through-hole 14 are much larger than the radial dimension of the front tilt drive device 26. Therefore, both the upper front through-hole 13 and the lower front through-hole 14 can be used to provide space for the front tilt drive device 26 to tilt and rotate inside it. At the same time, by reasonably limiting the diameter of the upper front through-hole 13 and the lower front through-hole 14, it is also possible to prevent the front tilt drive device 26 from tilting too much due to loss of control, thus leaving an important safety guarantee for flight safety.

[0055] Similarly, in order not to affect the tilting operation of the rear tilt drive 36, such as Figures 1 to 3 As shown, in this embodiment, a rear upper through hole 15 and a rear lower through hole 16 are respectively provided at the upper and lower rear parts of the fuselage 10. Both the rear upper through hole 15 and the rear lower through hole 16 are circular holes. Since the rear tilt drive device 36 is located inside the fuselage 10, one end of the rear tilt drive device 36 can pass through the rear upper through hole 15 and connect to the rear upper wing drive device 32, while the other end of the rear tilt drive device 36 can pass through the rear lower through hole 16 and connect to the rear lower wing drive device 34.

[0056] Similarly, the diameters of the upper rear through-hole 15 and the lower rear through-hole 16 are much larger than the radial dimension of the rear tilt drive device 36. Therefore, both the upper rear through-hole 15 and the lower rear through-hole 16 can be used to provide space for the rear tilt drive device 36 to tilt and rotate inside it. At the same time, by reasonably limiting the diameter of the upper rear through-hole 15 and the lower rear through-hole 16, the problem of excessive tilting due to loss of control of the rear tilt drive device 36 can also be prevented, thus leaving an important safety guarantee for flight safety.

[0057] To better illustrate the working principle of this invention, the following description will be presented in conjunction with multiple scenarios.

[0058] I. Forward and backward flight

[0059] When forward flight is required, the front upper rotor 21 can be raised using the front upper rotor drive device 22 so that the relative height of the front upper rotor 21 is higher than that of the rear upper rotor 31; when backward flight is required, the rear upper rotor 31 can be raised using the rear upper rotor drive device 32 so that the relative height of the rear upper rotor 31 is higher than that of the front upper rotor 21.

[0060] By adopting this control method, not only can a higher forward speed be obtained, but the plane on which the rotor is located can also be separated to avoid turbulence, and the center of gravity of the aircraft can be kept at a low position to improve stability.

[0061] II. Tilt on the same side

[0062] By using the front tilt drive device 26 and the rear tilt drive device 36 to tilt each rotor to the same side, the aircraft can achieve efficient lateral movement.

[0063] III. Non-same-side tilt

[0064] By using the front tilt drive device 26 and the rear tilt drive device 36 to tilt each rotor on different sides, so that the two pairs of rotors tilt differently, the aircraft can rotate in place with the center of the fuselage 10 as the axis.

[0065] IV. Unilateral tilt

[0066] When only one of the front tilt drive device 26 and the rear tilt drive device 36 is tilting, only one pair of rotors will tilt, and the rotation axis of the aircraft can be quickly transferred to the position of the front rotor or the rear rotor axis.

[0067] In summary, by adopting the tandem twin-rotor transmedium aircraft described above, at least the following beneficial effects can be obtained:

[0068] (1) In terms of payload ratio, the four rotors work together to effectively improve the payload capacity and meet the needs of small and medium-sized UAVs for a large payload ratio.

[0069] (2) In terms of stability, the design of the front upper rotor 21 and the rear upper rotor 31 being able to be raised and lowered brings the center of gravity of the UAV closer to the bottom. By raising the rotors to complete a series of actions, the flight stability is significantly improved.

[0070] (3) In terms of maneuverability, the four rotors work together. When yawing during stable maneuvers, the front and rear pairs of rotors are offset in the same direction. When yawing or rotating during rapid maneuvers, the front and rear pairs of rotors are offset in opposite directions and can rotate around the axis. Only the rear pair of rotors is offset and can rotate around the axis of the front rotor.

[0071] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A tilt-rotor retractable tandem dual-rotor transmedium aircraft, characterized in that, It includes a fuselage, a front lift mechanism located at the front of the fuselage, and a rear lift mechanism located at the rear of the fuselage; The front lift mechanism includes a front upper rotor, a front upper rotor drive device for driving the front upper rotor to rotate, a front lower rotor, a front lower rotor drive device for driving the front lower rotor to rotate, a front upper rotor lifting device connected between the front upper rotor drive device and the front lower rotor drive device, and a front tilt drive device for driving the front upper rotor lifting device to rotate about the fuselage axis. The front upper wing lifting device includes a front lifting motor and a front screw transmission unit that is driven by the front lifting motor to extend and retract. The front screw transmission unit is connected to the front upper wing driving device. The front screw drive unit includes a front coupling, a front screw, a front threaded sleeve, a front push rod, a front slider, and a front guide rail; The front coupling connects the output shaft of the front lifting motor and the front screw. The front screw is threadedly connected to the front threaded sleeve; The front threaded sleeve is connected and fixed to the front push rod; The front push rod is provided with the front slider; The front slider is slidably mounted on the front guide rail; The arrangement trajectory of the front guide rail is consistent with the axial direction of the front screw; The front upper wing lifting device also includes a front base, on which the front lifting motor and the front guide rail are fixedly installed, and the front base is rotatably connected to the front tilt drive device. The rear lift mechanism includes a rear upper rotor, a rear upper wing drive device for driving the rear upper rotor to rotate, a rear lower rotor, a rear lower wing drive device for driving the rear lower rotor to rotate, a rear upper wing lifting device connected between the rear upper wing drive device and the rear lower wing drive device, and a rear tilt drive device for driving the rear upper wing lifting device to rotate about the fuselage axis.

2. The tandem twin-rotor transmedium aircraft according to claim 1, characterized in that, The fuselage is equipped with a structural beam that extends along the axial direction of the fuselage. The front tilt drive device and the rear tilt drive device are respectively installed at both ends of the structural beam.

3. The tandem twin-rotor transmedium aircraft according to claim 1, characterized in that, The front part of the fuselage is provided with an upper front through hole and a lower front through hole, respectively. The forward tilt drive device is located inside the fuselage. One end of the forward tilt drive device passes through the upper forward through hole and is connected to the upper forward wing drive device. The other end of the forward tilt drive device passes through the lower forward through hole and is connected to the lower forward wing drive device. The upper front through-hole and the lower front through-hole are both used to provide space for the front tilt drive device to tilt and rotate inside it.

4. The tandem twin-rotor transmedium aircraft according to claim 1, characterized in that, The rear of the fuselage is provided with an upper rear through hole and a lower rear through hole, respectively. The rear tilt drive device is located inside the fuselage. One end of the rear tilt drive device passes through the rear upper through hole and is connected to the rear upper wing drive device, and the other end of the rear tilt drive device passes through the rear lower through hole and is connected to the rear lower wing drive device. The upper rear through-hole and the lower rear through-hole are both used to provide space for the rear tilt drive device to tilt and rotate inside it.

5. The tandem twin-rotor transmedium aircraft according to claim 1, characterized in that, The rear upper wing lifting device includes a rear lifting motor and a rear screw transmission unit that is driven by the rear lifting motor to extend and retract. The rear screw transmission unit is connected to the rear upper wing driving device.

6. The tandem twin-rotor transmedium aircraft according to claim 5, characterized in that, The rear screw drive unit includes a rear coupling, a rear screw, a rear threaded sleeve, a rear push rod, a rear slider, and a rear guide rail; The rear coupling connects the output shaft of the rear lifting motor and the rear screw. The rear screw is threaded into the rear threaded sleeve; The rear threaded sleeve is connected and fixed to the rear push rod; The rear push rod is provided with a rear slider; The rear slider is slidably mounted on the rear guide rail; The arrangement trajectory of the rear guide rail is consistent with the axial direction of the rear screw.

7. The tandem twin-rotor transmedium aircraft according to claim 6, characterized in that, The rear upper wing lifting device also includes a rear base, on which the rear lifting motor and the rear guide rail are fixedly installed, and the rear base is rotatably connected to the rear tilting drive device.

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