A quadcopter and two propeller tandem wing adjustable flight carrier

Abstract

The utility model discloses a four rotor and two propeller series wing adjustable flight carrier, including fuselage and wing device, and the front wing group includes the front wing of installing in the both sides of the front part of fuselage, the both ends of front wing each install a front power device, install a front propeller on every front power device, the rear wing group includes the rear wing of installing in the both sides of the back of fuselage, install rear power device on the rear wing, install rear propeller on rear power device, the front power device is connected with the outer end of front wing through a 90 degree steering mechanism of steering, the utility model provides the aircraft when taking off and landing, and the front propeller is perpendicular to the fuselage, is four rotor aircraft, realizes vertical take -off and landing, solves the problem that the conventional fixed wing aircraft needs to set runway and takes off, after the aircraft flies stably, adjusts the front propeller and the fuselage parallel, becomes the fixed wing aircraft, to improve the load and voyage.

Description

Technical Field

[0001] This utility model relates to the field of flight vehicle structure technology, and in particular to a flight vehicle with adjustable quadcopter and two-propeller tandem wings. Background Technology

[0002] Conventional quadcopter or multi-rotor aircraft, due to their inherent structural limitations, have poor aerodynamics, high drag, require significant power support, and are unsuitable for large payloads and long ranges. While conventional fixed-wing aircraft overcome the limitations of conventional quadcopter aircraft in terms of large payloads and long ranges, they require runways for takeoff and landing, cannot perform vertical takeoff and landing, and have stringent takeoff requirements, making them unsuitable for various applications. To address these issues, this invention provides a quadcopter and a two-propeller tandem adjustable aircraft to solve these problems. Summary of the Invention

[0003] The purpose of this invention is to provide a quadcopter and a dual-propeller tandem wing adjustable flight vehicle that can take off and land vertically and has a long range, without the need for a dedicated airport with a dedicated runway.

[0004] The above-mentioned technical objective of this utility model is achieved through the following technical solution: A quadcopter and two-propeller tandem adjustable flight vehicle includes a fuselage and a wing assembly. The wing assembly includes a front wing group and a rear wing group. The front wing group includes front wings mounted on both sides of the front of the fuselage. A front power unit is mounted at each end of the front wing. A front propeller is mounted on each front power unit. The rear wing group includes rear wings mounted on both sides of the rear of the fuselage. A rear power unit is mounted on the rear wing. A rear propeller is mounted on the rear power unit. The front power unit is connected to the outer end of the front wing via a 90-degree steerable mechanism. The steerable mechanism drives the front power unit and its front propeller to rotate within a range of 0-90 degrees, allowing the front propeller to switch back and forth between the vertical and horizontal working directions, and to operate normally during continuous changes.

[0005] Specifically, when the front propeller is turned to a direction perpendicular to the fuselage and pointing upwards, the front propeller acts as a rotor, generating vertical lift; when the front propeller is turned to a direction parallel to the fuselage and pointing straight ahead, the front propeller acts as a propeller of a fixed-wing aircraft, generating thrust that pulls the aircraft forward.

[0006] Furthermore, the steering mechanism includes a rotating shaft, a transmission block, a mounting plate, a steering motor, and a positioning structure. The outer end of the rotating shaft is fixedly connected to the housing of the front power unit, and the other end of the rotating shaft is fixedly connected to the transmission block installed inside the front wing. The transmission block is connected to the steering motor installed on the mounting plate.

[0007] The positioning structure includes a positioning block, a positioning groove, a guide rod, a positioning spring, and a positioning wound iron core. Four positioning grooves are evenly distributed on the upper end of the transmission block facing the steering motor. Two positioning blocks are respectively inserted into two guide rods on the outside of the transmission block. The positioning spring is fitted on the guide rod and pushes the positioning block into the positioning groove for positioning. Two positioning wound iron cores are mounted on the mounting plate. When the positioning wound iron cores are energized, the magnetic attraction generated attracts the positioning block to compress the positioning spring, causing the positioning block to disengage from the positioning groove.

[0008] Specifically, the steering mechanism described above enables the front propeller to be steered, and the positioning structure enables the positioning after the steering, transmitting the force to the canard and fuselage, thus achieving an effective switch between the two flight modes.

[0009] Furthermore, the upper end of the duct on the rear wing where the rear power unit is mounted is equipped with an automatically opening and closing rectifier baffle. During vertical takeoff, the rectifier baffle is in the open state, and the rear propeller acts as the rotor, generating vertical upward lift; when the rectifier baffle is closed, the rear propeller portion becomes part of the rear wing, and has minimal impact on the aerodynamic characteristics of the aircraft.

[0010] Furthermore, the rectifier baffles are multiple in number, forming a circular rectifier cover that can cover the duct. Each rectifier baffle is connected to the rear wing at both ends via a mounting shaft and bearings. A small gear is mounted on the end of the mounting shaft on one side of the rectifier baffle. This small gear meshes with a rack installed in a slide groove. The rack can slide relative to the slide groove. One end of the rack is connected to the side wall of one end of the slide groove via a tension spring. A permanent magnet is fixedly mounted on the other end of the rack. A wound iron core that attracts the rack to slide is mounted on the other end of the slide groove. Through this rectifier baffle mounting structure design, the tension spring moves the rack, causing the rectifier baffle to be in a normally closed state. During vertical takeoff, the coil of the positioning wound iron core is energized, attracting the rack to move and opening the rectifier baffle to allow airflow.

[0011] Furthermore, the lower end of the duct is equipped with an automatically opening and closing fairing. Similarly, during vertical takeoff, the fairing is in the open state, and the rear propeller acts as the rotor, generating vertical lift; when the fairing is closed, the rear propeller section becomes part of the rear wing, and has minimal impact on the aerodynamic characteristics of the aircraft.

[0012] Furthermore, one side of the fairing is hinged to the duct sidewall via a hinge shaft. A hinge gear is mounted at one end of the hinge shaft, meshing with a drive gear. The drive gear is mounted on the motor shaft of the fairing-closing motor, which is mounted on the rear wing. The other side of the fairing is equipped with a locking block, and the duct sidewall has a locking pin mechanism that engages with the locking block for locking. The fairing is directly driven to open and close by the fairing-closing motor. After closing, it is automatically locked by the locking pin mechanism to prevent the fairing from opening during forward flight.

[0013] Furthermore, the pin mechanism includes a pin, a limiting permanent magnet block, a limiting plate, a stop block, a pin spring, and a pin winding iron core. The pin is inserted into the insertion hole of the limiting plate. The limiting permanent magnet block is located at the end of the pin that contacts the limiting plate. The stop block is located on the pin. The pin spring is fitted onto the pin between the stop block and the limiting plate and pushes the end of the pin into the insertion hole of the pin block. The pin winding iron core is installed on the rear wing outside the limiting permanent magnet block. When the coil of the pin winding iron core is energized, the generated magnetic attraction pulls the pin out of the insertion hole of the locking block.

[0014] Furthermore, the rear power unit and the rear propeller mounted thereon are integrated with the rear wing via a mounting bracket. During forward flight, the rear propeller, covered by a fairing and baffle, becomes part of the rear wing, reducing its impact on airflow.

[0015] Furthermore, both the front and rear power units utilize external rotor brushless DC motors. Alternatively, the power unit can employ gasoline or diesel engines, or a hybrid powertrain. The advantages of using electric motors include fast response and ease of control.

[0016] In summary, the present invention has the following beneficial effects: When the aircraft provided by the present invention takes off and lands, the front propeller is perpendicular to the fuselage, making it a quadcopter, thus achieving vertical take-off and landing and solving the problem that conventional fixed-wing aircraft need to set up runways for take-off and landing; after the aircraft stabilizes in flight, the front propeller is adjusted to be parallel to the fuselage, thus becoming a fixed-wing aircraft, thereby increasing payload and range. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall external structure of the aircraft of this utility model; Figure 2 This is a schematic diagram of the external structure of the front propeller when it is operating in a horizontal reverse direction. Figure 3 This is a schematic diagram showing the connection between the front power unit and the forewing via the steering mechanism; Figure 4 This is a magnified view of a portion of the steering mechanism; Figure 5 This is a schematic diagram of the external structure of the rear wing and fairing. Figure 6 This is a schematic diagram of the installation and adjustment structure of the rectifier baffle; Figure 7 This is a schematic diagram showing the rear wing with the fairing open. Figure 8 This is a schematic diagram of the installation structure with the fairing closed. Figure 9 This is a schematic diagram of the installation of the latch structure; Figure 10 Partial sectional view of the rear wing; In the diagram, 1. Fuselage; 2. Canard; 3. Front power plant; 4. Front propeller; 5. Rear wing; 6. Rear power plant; 7. Rear propeller; 8. Steering mechanism; 9. Radiator baffle; 10. Fairing; 11. Duct; 12. Shaft; 13. Transmission block; 14. Mounting plate; 15. Steering motor; 16. Positioning block; 17. Positioning slot; 18. Guide rod; 19. Positioning spring; 20. Positioning winding core; 21. 1. Mounting shaft; 22. Pinion; 23. Rack; 24. Slide groove; 25. Permanent magnet; 26. Winded iron core; 27. Tension spring; 28. Hinge shaft; 29. ​​Hinge gear; 30. Drive gear; 31. Closing motor; 32. Locking block; 33. Pin mechanism; 34. Pin; 35. Limiting permanent magnet; 36. Limiting plate; 37. Stop block; 38. Pin spring; 39. Pin wound iron core; 40. Mounting bracket. Detailed Implementation

[0018] The present invention will be further described in detail below with reference to the accompanying drawings. The technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present invention.

[0019] like Figure 1-2As shown, a quadcopter and two-propeller tandem adjustable flight vehicle includes a fuselage 1 and a wing assembly. The wing assembly includes a front wing group and a rear wing group. The front wing group includes front wings 2 installed on both sides of the front of the fuselage 1. A front power unit 3 is installed at each end of the front wing 2. A front propeller 4 is installed on each front power unit 3. The rear wing group includes rear wings 5 ​​installed on both sides of the rear of the fuselage 1. A rear power unit 6 is installed on the rear wing 5. A rear propeller 7 is installed on the rear power unit 6. The front power unit 3 is connected to the outer end of the front wing 2 through a steering mechanism 8 that can turn 90 degrees. The steering mechanism 8 drives the front power unit 3 and the front propeller 4 on the front power unit 3 to rotate within a range of 0-90 degrees, so that the front propeller 4 can switch back and forth between the vertical and horizontal working directions and can operate normally when continuously changing.

[0020] Specifically, when the front propeller 4 is turned to be perpendicular to the fuselage 1 and pointing upwards, the front propeller 4 acts as a rotor, generating vertically upward lift; when the front propeller 4 is turned to be parallel to the fuselage 1 and pointing straight forward, the front propeller acts as a propeller of a fixed-wing aircraft, generating a thrust that pulls the aircraft forward.

[0021] Furthermore, such as Figure 3 and Figure 4 As shown, the steering mechanism 8 includes a rotating shaft 12, a transmission block 13, a mounting plate 14, a steering motor 15, and a positioning structure. The outer end of the rotating shaft 12 is fixedly connected to the housing of the front power unit 3, and the other end of the rotating shaft 12 is fixedly connected to the transmission block 13 installed inside the front wing 2. The transmission block 13 is connected to the steering motor 15 installed on the mounting plate 14.

[0022] The positioning structure includes a positioning block 16, a positioning groove 17, a guide rod 18, a positioning spring 19, and a positioning winding core 20. The four positioning grooves 17 are evenly distributed on the transmission block 13 at one end facing the steering motor 15. The two positioning blocks 16 are respectively inserted into the two guide rods 18 on the outside of the transmission block 13. The positioning spring 19 is fitted on the guide rod 18 and pushes the positioning block 16 into the positioning groove 17 for positioning. The two positioning winding cores 20 are installed on the mounting plate 14. After the positioning winding core 20 is energized, the magnetic attraction generated attracts the positioning block 16 and compresses the positioning spring 19, causing the positioning block 16 to disengage from the positioning groove 17.

[0023] Specifically, the steering mechanism 8 is used to turn the front propeller 4, and the positioning structure is used to achieve positioning after turning. The force is then transmitted to the canard 2 and the fuselage 1, thus achieving an effective switch between the two flight modes.

[0024] Furthermore, such as Figure 5 , Figure 6 and Figure 10 As shown, the upper port of the duct 11 on the rear wing 5, where the rear power unit 6 is mounted, is equipped with an automatically opening and closing rectifier baffle 9. During vertical takeoff, the rectifier baffle 9 is in the open state, and the rear propeller 7 acts as the rotor, generating vertical upward lift; when the rectifier baffle 9 is closed, the rear propeller 7 becomes part of the rear wing, and has minimal impact on the aerodynamic characteristics of the aircraft.

[0025] Furthermore, the number of rectifier baffles 9 is multiple, forming a circular rectifier cover that can cover the duct 11. Each rectifier baffle 9 is connected to the rear wing 5 at both ends via a mounting shaft 21 and a bearing. A small gear 22 is mounted on the end of the mounting shaft 21 on one side of the rectifier baffle 9. The small gear 22 meshes with a rack 23 installed in a slide groove 24. The rack 23 can slide relative to the slide groove 24. One end of the rack 23 is connected to one side wall of the slide groove 24 via a tension spring 27. A permanent magnet 25 is fixedly mounted on the other end of the rack 23. A wound iron core 26 that attracts the rack 23 to slide is mounted on the other end of the slide groove 24. Through the above-described installation structure design of the rectifier baffle 9, the tension spring 27 moves the rack 23, causing the rectifier baffle 9 to be in a normally closed state. During vertical takeoff, the coil of the positioning wound iron core 20 is energized, attracting the rack 23 to move and opening the rectifier baffle 9 to allow airflow.

[0026] Furthermore, such as Figure 7 , Figure 8 and Figure 10 As shown, the lower port of the duct 11 is equipped with an automatically opening and closing fairing 10. Similarly, during vertical takeoff, the fairing 10 is in the open state, and the rear propeller 7 acts as the rotor, generating vertical upward lift; when the fairing 10 is closed, the rear propeller 7 becomes part of the rear wing, and has little impact on the aerodynamic characteristics of the aircraft.

[0027] Furthermore, one side of the fairing 10 is hinged to the side wall of the duct 11 via a hinge shaft 28. A hinge gear 29 is mounted at one end of the hinge shaft 28, meshing with a drive gear 30. The drive gear 30 is mounted on the motor shaft of the fairing-closing motor 31, which is mounted on the rear wing 5. The other side of the fairing 10 is provided with a locking block 32, and the side wall of the duct 11 is provided with a locking pin mechanism 33 that engages with the locking block 32 for locking. The fairing 10 is directly driven to open and close by the fairing-closing motor 31. After closing, it is automatically locked by the locking pin mechanism 33 to prevent the fairing 10 from opening during forward flight.

[0028] Furthermore, such as Figure 9As shown, the pin mechanism 33 includes a pin 34, a limiting permanent magnet block 35, a limiting plate 36, a stop block 37, a pin spring 38, and a pin winding iron core 39. The pin 34 is inserted into the insertion hole of the limiting plate 36. The limiting permanent magnet block 35 is located at the end of the pin 34 that contacts the limiting plate 36. The stop block 37 is located on the pin 34. The pin spring 38 is fitted onto the pin 34 between the stop block 37 and the limiting plate 36 and pushes the end of the pin 34 into the insertion hole of the pin block 32. The pin winding iron core 39 is installed on the rear wing 5 outside the limiting permanent magnet block 35. When the coil of the pin winding iron core 39 is energized, the magnetic attraction generated pulls the pin 34 out of the insertion hole of the locking block 32.

[0029] Furthermore, the rear power unit 6 and the rear propeller 8 mounted thereon are integrated with the rear wing 5 via a mounting bracket 40. During forward flight, the rear propeller 8, under the cover of the fairing 9 and the fairing 10, becomes part of the rear wing 5, reducing its impact on airflow.

[0030] Furthermore, the front power unit 3 and the rear power unit 6 are both equipped with external rotor brushless DC motors. Alternatively, the power units can also use gasoline or diesel engines, or a hybrid power system. The advantages of using electric motors include fast response and ease of control.

[0031] Working principle: During takeoff and landing, the front propeller 4 is perpendicular to the fuselage 1, and the fairing 9 and fairing 10 of the rear wing 5 are opened, at which point the aircraft becomes a quadcopter and can achieve vertical takeoff and landing; when the flight is stable, the front propeller 4 is adjusted to rotate 90 degrees so that it is parallel to the fuselage 1, and the fairing 9 and fairing 10 of the rear wing 5 are closed and become part of the rear wing 5. At this time, the aircraft becomes a fixed-wing aircraft with two propellers, and the front propeller 4 provides horizontal thrust to achieve greater payload and longer distance flight.

[0032] This specific embodiment is merely an explanation of the present utility model and is not intended to limit the present utility model. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of the claims of the present utility model, they are protected by patent law.

Claims

1. A quadcopter and two-propeller tandem adjustable flight vehicle, comprising a fuselage (1) and a wing assembly, characterized in that: The wing assembly includes a front wing group and a rear wing group; The forward wing assembly includes forward wings (2) mounted on both sides of the front of the fuselage (1); each end of the forward wing (2) is equipped with a forward power unit (3); each forward power unit (3) is equipped with a forward propeller (4). The rear wing assembly includes rear wings (5) mounted on both sides of the rear of the fuselage (1); a rear power unit (6) is mounted on the rear wings (5); and a rear propeller (7) is mounted on the rear power unit (6). The front power unit (3) is connected to the outer end of the forewing (2) through a steering mechanism (8) that can turn 90 degrees. The steering mechanism (8) drives the front power unit (3) and the front propeller (4) on the front power unit (3) to rotate within the range of 0-90 degrees, so that the front propeller (4) switches back and forth between the two working directions of vertical and horizontal.

2. The adjustable quadcopter and dual-propeller tandem-wing flight vehicle according to claim 1, characterized in that: The steering mechanism (8) includes a rotating shaft (12), a transmission block (13), a mounting plate (14), a steering motor (15), and a positioning structure. The outer end of the rotating shaft (12) is fixedly connected to the housing of the front power unit (3), and the other end of the rotating shaft (12) is fixedly connected to the transmission block (13) installed inside the front wing (2). The transmission block (13) is connected to the steering motor (15) installed on the mounting plate (14). The positioning structure includes a positioning block (16), a positioning groove (17), a guide rod (18), a positioning spring (19), and a positioning winding core (20). The four positioning grooves (17) are evenly distributed on the transmission block (13) at one end facing the steering motor (15). The two positioning blocks (16) are respectively inserted into the two guide rods (18) on the outside of the transmission block (13). The positioning spring (19) is fitted on the guide rod (18) and pushes the positioning block (16) into the positioning groove (17) for positioning. The two positioning winding cores (20) are installed on the mounting plate (14). After the positioning winding core (20) is energized, the magnetic attraction generated attracts the positioning block (16) to compress the positioning spring (19), so that the positioning block (16) is disengaged from the positioning groove (17).

3. The adjustable quadcopter and dual-propeller tandem-wing flight vehicle according to claim 2, characterized in that: The upper port of the duct (11) on the rear wing (5) where the rear power unit (6) is installed is equipped with an automatically opening and closing rectifier baffle (9).

4. The adjustable quadcopter and two-propeller tandem-wing flight vehicle according to claim 3, characterized in that: The number of rectifier baffles (9) is multiple. Multiple rectifier baffles (9) form a circular rectifier cover that can cover the duct (11). The two ends of each rectifier baffle (9) are connected to the rear wing (5) through the mounting shaft (21) and bearing. A small gear (22) is installed on the shaft end of the mounting shaft (21) on one side of the rectifier baffle (9). The small gear (22) meshes with the rack (23) installed in the slide groove (24). The rack (23) can slide relative to the slide groove (24). One end of the rack (23) is connected to the side wall of one end of the slide groove (24) through the tension spring (27). A permanent magnet block (25) is fixedly installed on the other end of the rack (23). A wound iron core (26) that attracts the rack (23) to slide is installed on the other end of the slide groove (24).

5. The adjustable quadcopter and two-propeller tandem-wing flight vehicle according to claim 3, characterized in that, The lower port of the duct (11) is equipped with an automatically opening and closing fairing (10).

6. The adjustable quadcopter and dual-propeller tandem-wing flight vehicle according to claim 5, characterized in that: One side of the fairing (10) is hinged to the side wall of the duct (11) via a hinge shaft (28). A hinge gear (29) is installed at one end of the hinge shaft (28). The hinge gear (29) meshes with a drive gear (30). The drive gear (30) is installed on the motor shaft of the fairing motor (31). The fairing motor (31) is installed on the rear wing (5). A locking block (32) is provided on the other side of the fairing (10). A pin mechanism (33) that engages with the locking block (32) to lock the fairing (11) is provided on the side wall of the duct (11).

7. The adjustable quadcopter and two-propeller tandem-wing flight vehicle according to claim 6, characterized in that: The pin mechanism (33) includes a pin (34), a limiting permanent magnet block (35), a limiting plate (36), a stop block (37), a pin spring (38), and a pin winding iron core (39). The pin (34) is inserted into the insertion hole of the limiting plate (36). The limiting permanent magnet block (35) is located at the end of the pin (34) that contacts the limiting plate (36). The stop block (37) is located on the pin (34). The pin spring (38) is fitted onto the pin (34) between the stop block (37) and the limiting plate (36), and pushes the end of the pin (34) into the insertion hole of the locking block (32). The pin winding iron core (39) is installed on the rear wing (5) outside the limiting permanent magnet block (35). After the coil of the pin winding iron core (39) is energized, the magnetic attraction force generated pulls the pin (34) out of the insertion hole of the locking block (32).

8. The adjustable quadcopter and dual-propeller tandem-wing flight vehicle according to claim 1, characterized in that: The rear power unit (6) and the rear propeller (7) mounted thereon are connected to the rear wing (5) by a mounting bracket (40).

9. A quadcopter and two-propeller tandem adjustable flight vehicle according to claim 8, characterized in that, The front power unit (3) and the rear power unit (6) are both external rotor brushless DC motors.

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