Protection mechanism for electric eVTOL vertical take-off and landing aircraft based on abnormal weather

Abstract

The utility model relates to the technical field of aircrafts, in particular to a protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather, which comprises an aircraft body, a mounting box is arranged at the top of the aircraft body, a mounting plate is arranged in the mounting box, an electronic device is arranged on the mounting plate, and the electronic device is connected with the aircraft body. The mounting box is provided with a mounting groove allowing the mounting plate to ascend and descend, a first rotating shaft and a second rotating shaft are symmetrically arranged on the mounting box, a first cover plate is arranged on the first rotating shaft, and a second cover plate is arranged on the second rotating shaft; the aircraft body is provided with a first cover plate and a second cover plate, one side of the first cover plate and one side of the second cover plate are inclined relative to the aircraft body, the mounting box is further provided with a secondary sealing mechanism, and the secondary sealing mechanism can seal the mounting box again, so that the mounting box has better sealing performance, and the service life of the aircraft body is prolonged. Therefore, the electronic device on the mounting plate can be better protected.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and in particular to a protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather. Background Art

[0002] The electric vertical take-off and landing aircraft is a new type of multi-purpose drone that can carry various mission payloads according to needs to complete different work tasks. In addition to being used for private flights, it can also be used for commercial flights, and is widely used in freight, short-distance aviation, express delivery, fire rescue, agricultural plant protection and other fields.

[0003] Chinese patent CN218967208U discloses a logistics drone with a sensing device protection mechanism, including a drone body assembly, an ultrasonic integrated protection assembly arranged at the center of the drone body assembly, and an aircraft assembly connected to the drone body assembly, wherein the drone body assembly includes a body, a visual monitoring assembly arranged at the front lower end of the body, and a battery storage compartment arranged at the rear lower end of the body, and the two sides of the body are symmetrically provided with body vertical brackets, and the other end of each of the body vertical brackets is connected to the body horizontal bracket, and the body is provided with a telescopic rod compartment, the telescopic rod compartment is connected to one end of the telescopic rod, and the other end of the telescopic rod is connected to the aircraft assembly. The utility model adopts a logistics drone with a sensing device protection mechanism of the above structure, and proposes a drone with a high degree of protection, which can still perform operations better under adverse weather conditions and has a sensing function.

[0004] This kind of logistics drone with a sensing device protection mechanism mainly protects the ultrasonic integrated protection assembly on the drone in abnormal weather conditions by cooperating with the integrated protection device baffle and the integrated protection device cover. However, the integrated protection device cover may not be sealed tightly after working for a long time, which will still affect the ultrasonic integrated protection assembly. In addition, when the drone is flying, the integrated protection device cover is in a vertical shape, which will cause greater wind resistance for the drone during flight, thereby increasing power consumption. Utility Model Content

[0005] In view of the above problems, a protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather is provided. The secondary sealing mechanism can form a re-sealing effect on the mounting box, thereby better protecting the electronic equipment on the mounting plate.

[0006] To solve the problems of the prior art, the utility model provides a protective mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather, including an aircraft body, a mounting box is arranged on the top of the aircraft body, a sensor is arranged on the mounting box, a mounting plate that can be raised and lowered is arranged in the mounting box, a plurality of electronic devices are arranged on the mounting plate, the mounting box is provided with a mounting groove for raising and lowering the mounting plate, a first rotating shaft and a second rotating shaft that can rotate are symmetrically arranged on the mounting box, a first cover plate is arranged on the first rotating shaft, and the first cover plate can be abutted against the mounting box, a second cover plate is arranged on the second rotating shaft, and the second cover plate can be abutted against the mounting box, the first cover plate and the second cover plate can also be abutted against the aircraft body respectively, and one side of the first cover plate and the second cover plate has an inclination with the aircraft body, and a secondary sealing mechanism is also arranged on the mounting box.

[0007] Preferably, the secondary sealing mechanism comprises a sealing plate, and the sealing plate is movably arranged on the installation box, and a limiting groove for movement of the sealing plate is arranged on the installation box.

[0008] Preferably, a driving assembly is provided on the aircraft body, and the driving assembly includes a first rotating motor, a rotating screw and a connecting block; the first rotating motor is provided on the aircraft body, and a first bevel gear is provided on the output end of the first rotating motor; the rotating screw is provided on the aircraft body through a bearing seat, and a second bevel gear is provided on the rotating screw, and the second bevel gear is meshingly connected with the first bevel gear; the connecting block is movably provided on the rotating screw, and the connecting block is connected to the sealing plate.

[0009] Preferably, the installation box is provided with a flipping and lifting mechanism, and the flipping and lifting mechanism includes a connecting plate and a rack; there are at least two connecting plates, and the two connecting plates are symmetrically arranged on the sealing plate, and the connecting plate is slidingly connected to the installation box, and the installation box is provided with a positioning groove for the connecting plate to move; the number of the racks is the same as the number of the connecting plates and is arranged on the connecting plates in a one-to-one correspondence, and the first rotating shaft and the second rotating shaft are both provided with toothed grooves that mesh with the racks.

[0010] Preferably, a power assembly is provided on the aircraft body, and the power assembly includes a second rotating motor, a limiting shaft, a third pulley and a fourth pulley; the second rotating motor is provided on the aircraft body, and the output ends of the second rotating motor are respectively provided with a first pulley and a first gear; the limiting shaft is provided on a side of the aircraft body close to the second rotating motor through a fixed seat, and a second pulley and a second gear are respectively provided on the limiting shaft, and the second gear is meshingly connected with the first gear; the third pulley is provided on an extension end of the first rotating shaft, and the third pulley is rotatably connected with the second pulley through a first belt; the fourth pulley is provided on an extension end of the second rotating shaft, and the fourth pulley is rotatably connected with the first pulley through a second belt.

[0011] Preferably, the mounting plate is provided with a guide assembly, the guide assembly comprises a guide block, at least one of the guide blocks is arranged on the mounting plate, and the mounting box is provided with a guide groove for the guide block to move.

[0012] Preferably, a guide wheel is further provided on the guide block, and the guide wheel is rotatably connected to the installation box.

[0013] Preferably, sealing gaskets are provided on both the first cover plate and the second cover plate.

[0014] Compared with the prior art, the utility model has the following beneficial effects:

[0015] 1. The utility model can form a re-sealing effect on the installation box through the secondary sealing mechanism, so that the installation box has better sealing performance, thereby being able to better protect the electronic device on the installation board.

[0016] 2. The utility model adopts a design in which the first cover plate and the second cover plate are in an inclined manner when they abut against the aircraft body, so that the wind resistance of the aircraft body can be reduced when the aircraft body is flying horizontally, thereby reducing energy consumption. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional structural schematic diagram of a protective mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather.

[0018] Figure 2 This is a partial three-dimensional structure diagram of the protection mechanism for electric eVTOL vertical take-off and landing aircraft based on abnormal weather Figure 1 .

[0019] Figure 3 This application Figure 2 A local enlarged schematic diagram of point A in the middle.

[0020] Figure 4 This is a partial three-dimensional structure diagram of the protection mechanism for electric eVTOL vertical take-off and landing aircraft based on abnormal weather Figure 2 .

[0021] Figure 5 This is a partial three-dimensional structural cross-sectional view of the protection mechanism for the electric eVTOL vertical take-off and landing aircraft based on abnormal weather.

[0022] Figure 6 This application Figure 5 A local enlarged schematic diagram of point B in the middle.

[0023] Figure 7 This is a partial three-dimensional structure diagram of the protection mechanism for electric eVTOL vertical take-off and landing aircraft based on abnormal weather Figure 3 .

[0024] The numbers in the figure are: 1, aircraft body; 2, mounting box; 21, mounting groove; 22, first rotating shaft; 23, second rotating shaft; 24, first cover plate; 25, second cover plate; 26, sealing gasket; 27, magnetic suction assembly; 28, guide assembly; 281, guide block; 2811, guide wheel; 282, guide groove; 3, sensor; 4, mounting plate; 41, electronic device; 5, secondary sealing mechanism; 51, sealing plate; 52, limit groove; 53, driving assembly; 531, first rotating motor; 5311, first protective cover; 53 2. First bevel gear; 533. Second bevel gear; 534. Rotating screw; 535. Connecting block; 6. Flipping and lifting mechanism; 61. Rack; 62. Toothed groove; 63. Connecting plate; 631. Positioning groove; 64. Power assembly; 641. Second rotating motor; 6411. Second protective cover; 6412. First gear; 6413. First pulley; 642. Limiting shaft; 6421. Second gear; 6422. Second pulley; 643. First belt; 644. Third pulley; 645. Second belt; 646. Fourth pulley. DETAILED DESCRIPTION

[0025] In order to further understand the features, technical means, specific objectives and functions of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0026] Reference Figures 1 to 7As shown, a protective mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather includes an aircraft body 1, a mounting box 2 is arranged on the top of the aircraft body 1, a sensor 3 is arranged on the mounting box 2, a mounting plate 4 that can be raised and lowered is arranged in the mounting box 2, a plurality of electronic devices 41 are arranged on the mounting plate 4, the mounting box 2 is provided with a mounting groove 21 for raising and lowering the mounting plate 4, a first rotating shaft 22 and a second rotating shaft 23 that can rotate are symmetrically arranged on the mounting box 2, a first cover plate 24 is arranged on the first rotating shaft 22, and the first cover plate 24 can be abutted against the mounting box 2, a second cover plate 25 is arranged on the second rotating shaft 23, and the second cover plate 25 can be abutted against the mounting box 2, the first cover plate 24 and the second cover plate 25 can also be abutted against the aircraft body 1 respectively, and one side of the first cover plate 24 and the second cover plate 25 has an inclination with the aircraft body 1, and a secondary sealing mechanism 5 is also arranged on the mounting box 2.

[0027] When the aircraft body 1 is in abnormal weather, the sensor 3 will detect the abnormal weather and start to issue signals and alarms, thereby driving the mounting plate 4 to descend in the mounting slot 21 of the mounting box 2, thereby driving the installed electronic device 41 to descend synchronously, and then through the setting of the first rotating shaft 22 and the second rotating shaft 23, the first cover plate 24 and the second cover plate 25 are driven to flip, and then the first cover plate 24 and the second cover plate 25 are abutted against the top of the mounting box 2, thereby closing the top of the mounting box 2, thereby forming a sealed space inside the mounting box 2, and then driving the secondary sealing mechanism 5 to work, thereby forming a re-sealing effect on the inside of the mounting box 2, and when the electronic device 41 works better, the secondary sealing mechanism 5 is first driven to open, and then the first cover plate 24 and the second cover plate 25 are driven to flip. 4 and the second cover plate 25 are rotated to abut against the aircraft body 1, and the first cover plate 24 and the second cover plate 25 are both provided with a magnetic attraction component 27, so that the first cover plate 24 and the second cover plate 25 have a fixed limit function when abutting against the aircraft body 1, and then the mounting plate 4 is driven to rise in the mounting groove 21, and then the electronic device 41 is moved out of the mounting box 2, so as to perform better work, and the secondary sealing mechanism 5 can form a re-sealing effect on the mounting box 2, so that the mounting box 2 has better sealing, so as to better protect the electronic device 41 on the mounting plate 4, and the first cover plate 24 and the second cover plate 25 are designed with an inclination when abutting against the aircraft body 1, so that the wind resistance of the aircraft body 1 can be reduced when it is flying horizontally, thereby reducing energy consumption.

[0028] Reference Figure 2 As shown, the secondary sealing mechanism 5 includes a sealing plate 51 , and the sealing plate 51 is movably arranged on the installation box 2 . The installation box 2 is provided with a limiting groove 52 for the sealing plate 51 to move.

[0029] By driving the sealing plate 51 to move in the limiting groove 52 of the installation box 2, when the sealing plate 51 is inserted into the limiting groove 52 of the installation box 2, a secondary sealing effect is formed on the installation box 2. When it is necessary to drive the electronic device 41 to move toward the top of the installation box 2, it is only necessary to drive the sealing plate 51 to move out of the limiting groove 52 of the installation box 2, so that the mechanism is simpler, thereby making it more stable during operation.

[0030] Reference Figure 5 and Figure 7 As shown, a driving assembly 53 is provided on the aircraft body 1, and the driving assembly 53 includes a first rotating motor 531, a rotating screw 534 and a connecting block 535; the first rotating motor 531 is provided on the aircraft body 1, and a first bevel gear 532 is provided on the output end of the first rotating motor 531; the rotating screw 534 is provided on the aircraft body 1 through a bearing seat, and a second bevel gear 533 is provided on the rotating screw 534, and the second bevel gear 533 is meshingly connected with the first bevel gear 532; the connecting block 535 is movably provided on the rotating screw 534, and the connecting block 535 is connected to the sealing plate 51.

[0031] By driving the first rotating motor 531 to work, a first protective cover 5311 is arranged on the outer side of the first rotating motor 531. When the output end of the first rotating motor 531 rotates, the first bevel gear 532 is synchronously driven to rotate, and then the rotating screw rod 534 is synchronously driven to rotate through the setting of the second bevel gear 533, so that the connecting block 535 will move on the rotating screw rod 534, and then the sealing plate 51 can be synchronously driven to move in the limiting groove 52 of the mounting box 2, so that the sealing plate 51 can be directly driven to move by the operation of the first rotating motor 531, thereby reducing manual operation.

[0032] Reference Figure 3As shown, the installation box 2 is provided with a flipping and lifting mechanism 6, and the flipping and lifting mechanism 6 includes a connecting plate 63 and a rack 61; the connecting plate 63 has at least two, and the two connecting plates 63 are symmetrically arranged on the sealing plate 51, and the connecting plate 63 is slidingly connected to the installation box 2, and the installation box 2 is provided with a positioning groove 631 for the connecting plate 63 to move; the number of the racks 61 is the same as the number of the connecting plates 63 and is arranged on the connecting plates 63 in a one-to-one correspondence, and the first rotating shaft 22 and the second rotating shaft 23 are both provided with a toothed groove 62 that meshes with the rack 61.

[0033] When the first cover plate 24 and the second cover plate 25 are driven to flip over and abut against the mounting box 2, the first rotating shaft 22 and the second rotating shaft 23 will be driven to rotate in opposite directions respectively. When the first rotating shaft 22 and the second rotating shaft 23 rotate, the toothed groove 62 will synchronously drive the rack 61 to descend in the mounting box 2, and then the connecting plate 63 will directly drive the mounting plate 4 to descend in the mounting box 2. When the first cover plate 24 and the second cover plate 25 are flipped over and abut against the aircraft body 1, the rack 61 will synchronously rise in the mounting box 2, and then directly drive the mounting plate 4 to rise in the mounting box 2.

[0034] Reference Figure 4 and Figure 5 As shown, the aircraft body 1 is provided with a power assembly 64, and the power assembly 64 includes a second rotating motor 641, a limiting shaft 642, a third pulley 644 and a fourth pulley 646; the second rotating motor 641 is provided on the aircraft body 1, and the output end of the second rotating motor 641 is provided with a first pulley 6413 and a first gear 6412 respectively; the limiting shaft 642 is provided on a side of the aircraft body 1 close to the second rotating motor 641 through a fixing seat, and the limiting shaft 642 A second pulley 6422 and a second gear 6421 are respectively provided on it, and the second gear 6421 is meshingly connected with the first gear 6412; the third pulley 644 is provided on the extension end of the first rotating shaft 22, and the third pulley 644 is rotatably connected with the second pulley 6422 through the first belt 643; the fourth pulley 646 is provided on the extension end of the second rotating shaft 23, and the fourth pulley 646 is rotatably connected with the first pulley 6413 through the second belt 645.

[0035] Through the operation of the second rotating motor 641, a second protective cover 6411 is provided on the outer side of the second rotating motor 641. When the output end of the second rotating motor 641 rotates counterclockwise, the first pulley 6413 and the first gear 6412 are synchronously driven to rotate counterclockwise. In this way, through the setting of the second belt 645, the fourth pulley 646 is synchronously driven to rotate counterclockwise, and then the second rotating shaft 23 is driven to rotate counterclockwise, so that the second cover plate 25 is rotated to abut against the installation box 2, and the When the first gear 6412 rotates counterclockwise, it will synchronously drive the second gear 6421 to rotate clockwise, so that through the setting of the limiting shaft 642, it will also synchronously drive the second pulley 6422 to rotate clockwise, and then through the setting of the first belt 643, it will synchronously drive the third pulley 644 to rotate clockwise, and then drive the first rotating shaft 22 to rotate clockwise, thereby driving the first cover plate 24 to rotate and abut against the installation box 2, and will synchronously drive the installation plate 4 to descend, which can further reduce manual operations.

[0036] Reference Figure 5 and Figure 6 As shown, the mounting plate 4 is provided with a guide assembly 28, and the guide assembly 28 includes a guide block 281, at least one of the guide blocks 281 is arranged on the mounting plate 4, and the mounting box 2 is provided with a guide groove 282 for the guide block 281 to move.

[0037] The guide block 281 can only move in the guide groove 282 of the installation box 2, so as to guide and limit the installation plate 4 when it moves in the installation box 2, so that the installation plate 4 is more stable when moving.

[0038] Reference Figure 6 As shown, a guide wheel 2811 is also provided on the guide block 281 , and the guide wheel 2811 is rotatably connected to the installation box 2 .

[0039] By setting the guide wheel 2811, the friction between the guide block 281 and the installation box 2 can be reduced, so that the stability of the installation plate 4 can be further improved when the installation box 2 moves, and the power consumption can also be reduced.

[0040] Reference Figure 4 and Figure 5 As shown, sealing gaskets 26 are disposed on both the first cover plate 24 and the second cover plate 25 .

[0041] Because the first cover plate 24 and the second cover plate 25 are in hard contact with the installation box 2 , the sealing gasket 26 can provide a better sealing effect when the first cover plate 24 and the second cover plate 25 are in contact with the installation box 2 .

[0042] The above embodiments only express one or several implementation methods of the present invention, and the description is relatively specific and detailed, but it cannot be understood as limiting the scope of the present invention. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the attached claims.

Claims

1. A protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather, comprising an aircraft body (1), characterized in that: A mounting box (2) is arranged on the top of the aircraft body (1), a sensor (3) is arranged on the mounting box (2), a mounting plate (4) capable of being raised and lowered is arranged inside the mounting box (2), a plurality of electronic devices (41) are arranged on the mounting plate (4), the mounting box (2) is provided with a mounting groove (21) for raising and lowering the mounting plate (4), a first rotating shaft (22) and a second rotating shaft (23) capable of being rotated are symmetrically arranged on the mounting box (2), a first cover plate (24) is arranged on the first rotating shaft (22), and The first cover plate (24) can be arranged in abutment with the installation box (2); a second cover plate (25) is arranged on the second rotating shaft (23), and the second cover plate (25) can be arranged in abutment with the installation box (2); the first cover plate (24) and the second cover plate (25) can also be arranged in abutment with the aircraft body (1), respectively; one side of the first cover plate (24) and the second cover plate (25) are inclined with respect to the aircraft body (1); and a secondary sealing mechanism (5) is also arranged on the installation box (2).

2. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 1, characterized in that: The secondary sealing mechanism (5) comprises a sealing plate (51), the sealing plate (51) being movably arranged on the installation box (2), and a limiting groove (52) for the sealing plate (51) to move is arranged on the installation box (2).

3. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 2, characterized in that: The aircraft body (1) is provided with a driving assembly (53), wherein the driving assembly (53) comprises a first rotating motor (531), a rotating screw rod (534) and a connecting block (535); The first rotating motor (531) is arranged on the aircraft body (1), and a first bevel gear (532) is arranged on the output end of the first rotating motor (531); The rotating screw (534) is arranged on the aircraft body (1) via a bearing seat, and a second bevel gear (533) is arranged on the rotating screw (534), and the second bevel gear (533) is meshingly connected with the first bevel gear (532); The connecting block (535) is movably arranged on the rotating screw (534), and the connecting block (535) is connected to the sealing plate (51).

4. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 2, characterized in that: The installation box (2) is provided with a flipping and lifting mechanism (6), and the flipping and lifting mechanism (6) comprises a connecting plate (63) and a rack (61); There are at least two connecting plates (63), the two connecting plates (63) are symmetrically arranged on the sealing plate (51), and the connecting plates (63) are slidably connected to the installation box (2), and the installation box (2) is provided with a positioning groove (631) for the connecting plates (63) to move; The number of the racks (61) is the same as the number of the connecting plates (63) and they are arranged on the connecting plates (63) in a one-to-one correspondence, and the first rotating shaft (22) and the second rotating shaft (23) are both provided with toothed grooves (62) that mesh with the racks (61).

5. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 4, characterized in that: The aircraft body (1) is provided with a power assembly (64), and the power assembly (64) comprises a second rotating motor (641), a limit shaft (642), a third pulley (644) and a fourth pulley (646); The second rotating motor (641) is arranged on the aircraft body (1), and the output end of the second rotating motor (641) is respectively provided with a first pulley (6413) and a first gear (6412); The limiting shaft (642) is arranged on a side of the aircraft body (1) close to the second rotating motor (641) through a fixing seat, and a second pulley (6422) and a second gear (6421) are respectively arranged on the limiting shaft (642), and the second gear (6421) is meshedly connected with the first gear (6412); The third pulley (644) is arranged on the extended end of the first rotating shaft (22), and the third pulley (644) is rotatably connected to the second pulley (6422) via the first belt (643); The fourth pulley (646) is arranged on the extended end of the second rotating shaft (23), and the fourth pulley (646) is rotatably connected to the first pulley (6413) through the second belt (645).

6. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 1, characterized in that: The mounting plate (4) is provided with a guide assembly (28), the guide assembly (28) comprising a guide block (281), at least one of the guide blocks (281) is arranged on the mounting plate (4), and the mounting box (2) is provided with a guide groove (282) for the guide block (281) to move.

7. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 6, characterized in that: The guide block (281) is also provided with a guide wheel (2811), and the guide wheel (2811) is rotatably connected to the installation box (2).

8. The protection mechanism for an electric eVTOL vertical take-off and landing aircraft based on abnormal weather according to claim 1, characterized in that: A sealing gasket (26) is provided on both the first cover plate (24) and the second cover plate (25).

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