Aircraft and landing gear thereof and retraction and extension control method

Abstract

The present invention relates to the field of aircraft technology, and discloses a landing gear of an aircraft, comprising a landing gear body, a retracting mechanism, a supporting mechanism and a limiting mechanism, wherein the supporting mechanism comprises a first fuselage fixing seat and a second fuselage fixing seat, the retracting mechanism comprises an electric push rod, a control device and a current detection device, the landing gear body is rotatably connected to the first fuselage fixing seat, the limiting mechanism is used to limit the rotation angle of the landing gear body, one end of the electric push rod is connected to the second fuselage fixing seat, and the other end is connected to the landing gear body, the electric push rod is provided with a self-locking device, the current detection device is used to detect the current of the electric push rod, the control device controls the power on and off of the electric push rod, and the electric push rod drives the rotation of the landing gear body to realize the opening and closing of the landing gear, and the shape can be maintained when the action reaches the target position, and the reliability and safety are high. The present invention also provides an aircraft provided with the above-mentioned landing gear and a retracting and releasing control method of the landing gear.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to an aircraft and a landing gear thereof and a retraction and extension control method. Background Art

[0002] The landing gear is an important part of the aircraft that has both load-bearing and maneuverability. It plays an extremely important role in the safe take-off and landing of the aircraft. The landing gear is a necessary support system for the aircraft to take off, land, taxi, move on the ground and park. It is one of the main parts of the aircraft. Its performance is directly related to the use and safety of the aircraft.

[0003] With the continuous development of emerging technologies such as 5G and industrial Internet, the market demand for industrial application-level drones is growing rapidly. Industrial-level drones are expected to be widely used in surveying and mapping, security inspection, emergency response, agriculture, logistics and other fields, so they are also in urgent need of technological innovation. The common industrial application-level drones in the current market generally have fixed landing gear. When the mission mount is placed under the middle of the landing gear, it occupies a certain space under the fuselage, which will cause a certain obstruction to the field of view of the camera module or optoelectronic pod mounted on the mission, resulting in the execution field of view generally not exceeding ±90°. Moreover, when storing and transporting drones, special disassembly and assembly tools are usually required, separate maintenance work is required, and the operation of the operators requires certain training, which is time-consuming and labor-intensive.

[0004] The prior art discloses a structure of a fixed landing gear unmanned aerial vehicle, which structure includes a protective cover, a propeller, an electric motor, a heat dissipation port, an aircraft body, a flight arm, an LED flash light, a battery, a fixed landing gear device, a camera, an SD card, and a connecting frame. The lower end of the protective cover is fitted with the upper end of the propeller, the LED flash light is electrically connected to a PCB board in the aircraft body, the battery is embedded and connected in the aircraft body, the aircraft body is connected to the fixed landing gear device by bolts, the camera is welded to the connecting frame, the SD card is embedded and connected in the camera, the fixed landing gear device consists of a bolt hole, a landing gear, a tripod shock-absorbing cotton, a shock-absorbing spring, and a connecting platform, the bolt hole and the connecting platform are an integrated structure, the lower end of the landing gear is provided with a tripod shock-absorbing cotton, the shock-absorbing spring is embedded and connected in the landing gear, and the landing gear is welded to the connecting platform. The landing gear of this patent is fixedly connected to the main body of the aircraft, and the camera is mounted on the bottom of the main body of the aircraft. The landing gear cannot be retracted when the aircraft is flying, resulting in obstruction of the field of view when the camera is working, which is inconvenient to use, and the landing gear also needs to be disassembled when the drone is transported. Summary of the invention

[0005] The object of the present invention is to provide an aircraft which can be retracted and deployed with high safety, and its landing gear and a retraction and deployment control method.

[0006] In order to achieve the above-mentioned purpose, the present invention provides a landing gear of an aircraft, including a landing gear body, a retracting and extending mechanism, a supporting mechanism and a limiting mechanism, wherein the supporting mechanism includes a first fuselage fixing seat and a second fuselage fixing seat, the retracting and extending mechanism includes an electric push rod, a control device and a current detection device, the landing gear body is rotatably connected to the first fuselage fixing seat, the limiting mechanism is used to limit the rotation angle of the landing gear body, one end of the electric push rod is connected to the second fuselage fixing seat, and the other end of the electric push rod is connected to the landing gear body, the control device, the current detection device and the electric push rod are electrically connected, the electric push rod is provided with a self-locking device, the current detection device is used to detect the current of the electric push rod, and the control device controls the on and off of the electric push rod.

[0007] As a preferred embodiment, the retracting and extending mechanism also includes a first connecting rod and a second connecting rod, one end of the first connecting rod is rotatably connected to the second fuselage fixing seat, the other end of the first connecting rod is rotatably connected to one end of the second connecting rod, the other end of the second connecting rod is rotatably connected to the landing gear body, one end of the electric push rod is connected to the first connecting rod, the other end of the electric push rod is connected to the landing gear body, and the connection between the electric push rod and the landing gear body is closer to the connection between the landing gear body and the first fuselage fixing seat than the connection between the second connecting rod and the landing gear body.

[0008] As a preferred embodiment, the first connecting rod is connected to the second connecting rod through a first rotating shaft, and the end of the first connecting rod away from the second fuselage fixing seat is provided with two parallel and spaced ear plates, the ear plate is provided with a first connecting hole, the end of the second connecting rod is located between the two ear plates, the end of the second connecting rod is provided with a second connecting hole, the first rotating shaft passes through the second connecting hole and the first connecting holes of the two ear plates, the limiting mechanism includes a limiting block, the limiting block is connected to one side of the second connecting rod, the width direction of the limiting block is parallel to the axial direction of the first rotating shaft, and the end of the second connecting rod where the second connecting hole is set is located between the two ends of the limiting block, and the width of the limiting block is greater than the distance between the two ear plates.

[0009] As a preferred solution, a plug is provided at one end of the first rotating shaft, and a plug hole is provided at the other end of the first rotating shaft, and a latch is inserted into the plug hole.

[0010] As a preferred solution, two first fuselage fixing seats are provided, the connection between the electric push rod and the landing gear body is located between the two first fuselage fixing seats, the landing gear body is provided with an anti-interference notch, and the anti-interference notch is located between the two first fuselage fixing seats.

[0011] As a preferred solution, the landing gear main body is connected to the first fuselage fixing seat through a second rotating shaft. An installation seat is provided on the landing gear main body. The installation seat includes two installation seat plates arranged in parallel at intervals. The installation seat plates are provided with third connection holes. The first fuselage fixing seat is located between the two installation seat plates. The first fuselage fixing seat is provided with fourth connection holes. The second rotating shaft passes through the fourth connection holes and the third connection holes of the two installation seat plates.

[0012] As a preferred solution, the landing gear main body includes a first frame body and a second frame body. One end of the first frame body is connected to the middle of the second frame body, making the landing gear main body in a T-shaped structure. The first fuselage fixing seat and the electric push rod are both connected to the first frame body.

[0013] As a preferred solution, supports are provided at both ends of the second frame body, and the supports and the first frame body are located on opposite sides of the second frame body.

[0014] The present invention also provides an aircraft, including a fuselage and the above landing gear. The first fuselage fixing seat and the second fuselage fixing seat are connected to the fuselage. The landing gear is provided with two, and the two landing gears are symmetrically arranged on both sides of the fuselage.

[0015] As a preferred solution, a receiving groove for the landing gear to be embedded is provided at the bottom of the fuselage.

[0016] In addition, the present invention also provides a method for controlling the retraction and extension of the landing gear of an aircraft, including:

[0017] When the landing gear is opened, the electric push rod is powered on, the push rod of the electric push rod retracts, driving the landing gear main body to rotate downward around its connection with the first fuselage fixing seat until the landing gear main body is deployed to the target position. When the current of the electric push rod exceeds the threshold, the electric push rod is powered off and self-locked;

[0018] When the landing gear is closed, the electric push rod is powered on, the push rod of the electric push rod extends, driving the landing gear main body to rotate upward around its connection with the first fuselage fixing seat until the landing gear main body is in close contact with the fuselage of the aircraft. When the current of the electric push rod exceeds the threshold, the electric push rod is powered off and self-locked.

[0019] As a preferred solution, when the landing gear is opened, the push rod of the electric push rod retracts, driving the first connecting rod to rotate downward around its connection with the second fuselage fixing seat, and driving the second connecting rod to rotate downward around its connection with the first connecting rod, so that when the landing gear main body reaches the target position, the connection between the electric push rod and the first connecting rod, the connection between the electric push rod and the landing gear main body, and the connection between the second connecting rod and the landing gear main body form the three corner points of a triangle;

[0020] When the landing gear is closed, the push rod of the electric push rod extends, driving the first connecting rod to rotate upward around the connection with the remaining second fuselage fixing seat, and driving the second connecting rod to rotate upward around the connection with the first connecting rod and retract.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] The present invention connects the landing gear body to the first fuselage fixing seat in rotation, connects one end of the electric push rod to the second fuselage fixing seat, and connects the other end to the landing gear body, and the first fuselage fixing seat and the second fuselage fixing seat are used to connect to the fuselage of the aircraft. The rotation of the landing gear body can be realized by retracting the push rod of the electric push rod, so as to realize the retraction and extension of the landing gear body, which can prevent the landing gear body from blocking the field of vision when other devices of the aircraft are working, and does not need to be disassembled when the aircraft is transported, so it is easy to use. In addition, the retracting and extending mechanism of the present invention also includes a control device and The current detection device and the electric push rod are provided with a self-locking device. When the landing gear body rotates into position, the limit mechanism prevents the landing gear body from continuing to rotate, so that the resistance of the electric push rod to continue to retract or extend increases, thereby increasing the current of the electric push rod. When the current detection device detects that the current of the electric push rod increases, the control device cuts off the power of the electric push rod, and the electric push rod self-locks after power is cut off, maintaining its state before power is cut off, so that the landing gear body can be kept in the target position, ensuring that the landing gear will not be closed due to impact when the aircraft lands, thereby achieving reliability and safety of landing gear retraction and extension. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic structural diagram of the landing gear of an embodiment of the present invention when it is opened.

[0024] Figure 2 It is a schematic structural diagram of a landing gear when it is closed according to an embodiment of the present invention.

[0025] Figure 3 is an exploded view of a landing gear according to an embodiment of the present invention.

[0026] Figure 4 Schematic diagram of the structure of the landing gear body according to an embodiment of the present invention.

[0027] Figure 5 It is a schematic structural diagram of an aircraft when the landing gear is closed according to an embodiment of the present invention.

[0028] Figure 6 It is a schematic structural diagram of an aircraft with the landing gear opened according to an embodiment of the present invention.

[0029] In the figure, 1-landing gear body; 101-anti-interference notch; 102-first frame; 103-second frame; 104-support; 2-first fuselage fixing seat; 201-fourth connecting hole; 3-second fuselage fixing seat; 4-electric push rod; 401-sixth connecting hole; 5-second rotating shaft; 6-mounting seat; 601-mounting seat plate; 602-third connecting hole; 7-first connecting rod; 8-second connecting rod; 801-second connecting hole; 802-eighth connecting hole; 9-first rotating shaft; 901-plug; 902-jack; 10-ear plate; 1001-first connecting hole; 11-limiting block; 12-latch pin; 13-push rod connecting seat; 1301-push rod connecting seat plate; 1302-fifth connecting hole; 14-connecting shaft; 15-nut; 16-connecting rod connecting seat; 1601-connecting rod connecting seat plate; 1602-seventh connecting hole; 17-third rotating shaft; 18-fourth rotating shaft; 19-body; 1901-accommodating slot. DETAILED DESCRIPTION

[0030] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0031] In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0032] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] Embodiment 1

[0034] like Figures 1 to 6As shown, a landing gear of an aircraft according to a preferred embodiment of the present invention comprises a landing gear body 1, a retracting and extending mechanism, a supporting mechanism and a limiting mechanism, wherein the supporting mechanism comprises a first fuselage fixing seat 2 and a second fuselage fixing seat 3, the retracting and extending mechanism comprises an electric push rod 4, a control device and a current detecting device, the landing gear body 1 is rotatably connected to the first fuselage fixing seat 2, the limiting mechanism is used for limiting the rotation angle of the landing gear body 1, one end of the electric push rod 4 is connected to the second fuselage fixing seat 3, and the other end of the electric push rod 4 is connected to the landing gear body 1, the control device, the current detecting device and the electric push rod 4 are electrically connected, the electric push rod 4 is provided with a self-locking device, the current detecting device is used for detecting the current of the electric push rod 4, and the control device controls the on and off of the electric push rod 4. In this embodiment, the landing gear body 1 is rotatably connected to the first fuselage fixing seat 2, one end of the electric push rod 4 is connected to the second fuselage fixing seat 3, and the other end is connected to the landing gear body 1, and the first fuselage fixing seat 2 and the second fuselage fixing seat 3 are used to be connected to the fuselage of the aircraft. The push rod extension of the electric push rod 4 can realize the rotation of the landing gear body 1, thereby realizing the retraction and extension of the landing gear body 1, which can prevent the landing gear body 1 from blocking the field of vision when other devices of the aircraft are working, and does not need to be disassembled when the aircraft is transported, which is convenient to use. In addition, the retracting and extending mechanism of this embodiment also includes a control device The electric push rod 4 is provided with a self-locking device. When the landing gear body 1 rotates into place, the limit mechanism prevents the landing gear body 1 from continuing to rotate, so that the resistance of the electric push rod 4 to continue to retract or extend increases, thereby increasing the current of the electric push rod 4. When the current detection device detects that the current of the electric push rod 4 increases, the control device cuts off the power of the electric push rod 4. The electric push rod 4 self-locks after power is cut off and maintains its state before power is cut off, so that the landing gear body 1 can be kept in the target position, ensuring that the landing gear will not be closed due to impact when the aircraft lands, thereby achieving the reliability and safety of the landing gear retraction and extension.

[0035] In this embodiment, two first fuselage fixing seats 2 are provided, and the connection between the electric push rod 4 and the landing gear body 1 is located between the two first fuselage fixing seats 2. The landing gear body 1 is provided with an anti-interference notch 101, and the anti-interference notch 101 is located between the two first fuselage fixing seats 2. The landing gear body 1 is connected to the fuselage of the aircraft through the two first fuselage fixing seats 2, so that the landing gear body 1 can be connected to the fuselage of the aircraft more firmly. The connection between the electric push rod 4 and the landing gear body 1 is located between the two first fuselage fixing seats 2, so that the landing gear body 1 can rotate smoothly. The anti-interference notch 101 can avoid other components to avoid hindering the rotation of the landing gear body 1.

[0036] In addition, the landing gear body 1 of the present embodiment is connected to the first fuselage fixing seat 2 via the second rotating shaft 5. A mounting seat 6 is provided on the landing gear body 1. The mounting seat 6 includes two mounting seat plates 601 arranged in parallel and spaced apart. The mounting seat plates 601 are provided with a third connecting hole 602. The first fuselage fixing seat 2 is located between the two mounting seat plates 601. The first fuselage fixing seat 2 is provided with a fourth connecting hole 201. The second rotating shaft 5 passes through the fourth connecting hole 201 and the third connecting holes 602 of the two mounting seat plates 601.

[0037] In addition, the main body of the electric push rod 4 of this embodiment is connected to the second fuselage fixing seat 3, and the push rod of the electric push rod 4 is connected to the landing gear body 1. When the push rod of the electric push rod 4 is extended, the landing gear is driven to close, and when the push rod of the electric push rod 4 is retracted, the landing gear is driven to open.

[0038] The retracting and extending mechanism of this embodiment further includes a stroke detection device, which includes a transmitter and a receiver, wherein the transmitter is arranged at one end of the push rod of the electric push rod 4 away from the main body thereof, and the receiver is arranged on the main body of the electric push rod 4. The stroke detection device can detect the length of the push rod of the electric push rod 4 exposed outside the main body thereof, thereby realizing monitoring of the extension and retraction of the push rod, and further realizing closed-loop control of the action of the electric push rod 4.

[0039] Embodiment 2

[0040] The difference between this embodiment and the first embodiment is that, based on the first embodiment, this embodiment further illustrates the retracting and extending mechanism and the limiting mechanism.

[0041] In this embodiment, the retracting and extending mechanism further includes a first connecting rod 7 and a second connecting rod 8, one end of the first connecting rod 7 is rotatably connected to the second fuselage fixing seat 3, the other end of the first connecting rod 7 is rotatably connected to one end of the second connecting rod 8, the other end of the second connecting rod 8 is rotatably connected to the landing gear body 1, one end of the electric push rod 4 is connected to the first connecting rod 7, the other end of the electric push rod 4 is connected to the landing gear body 1, and the connection between the electric push rod 4 and the landing gear body 1 is closer to the connection between the landing gear body 1 and the first fuselage fixing seat 2 than the connection between the second connecting rod 8 and the landing gear body 1. When the push rod of the electric push rod 4 is extended or retracted, it will drive the first connecting rod 7 and the second connecting rod 8 to rotate, thereby pulling the landing gear body 1 to rotate, so as to realize the rapid retraction and extension of the landing gear.

[0042] Specifically, the first connecting rod 7 is connected to the second connecting rod 8 through the first rotating shaft 9, and two parallel and spaced ear plates 10 are provided at one end of the first connecting rod 7 away from the second fuselage fixing seat 3, and the ear plate 10 is provided with a first connecting hole 1001, and the end of the second connecting rod 8 is located between the two ear plates 10, and the end of the second connecting rod 8 is provided with a second connecting hole 801. The first rotating shaft 9 passes through the second connecting hole 801 and the first connecting holes 1001 of the two ear plates 10, and the limiting mechanism includes a limiting block 11, which is connected to one side of the second connecting rod 8, and the width direction of the limiting block 11 is parallel to the axial direction of the first rotating shaft 9, and the end of the second connecting rod 8 with the second connecting hole 801 is located between the two ends of the limiting block 11, and the width of the limiting block 11 is greater than the distance between the two ear plates 10. When the landing gear is opened, after the second link 8 rotates to be in the same straight line with the first link 7, the limit block 11 abuts against the first link 7 to limit the second link 8 from continuing to rotate. When the electric push rod 4 continues to retract, the resistance received by the electric push rod 4 increases, thereby increasing the current of the electric push rod 4. The current detection device detects the increase in the electric push rod 4, cuts off the power to the electric push rod 4 and self-locks, thereby keeping the landing gear body 1 in this position.

[0043] In addition, a plug 901 is provided at one end of the first rotating shaft 9 of the present embodiment, and a plug hole 902 is provided at the other end of the first rotating shaft 9, and a plug pin 12 is inserted into the plug hole 902. The plug pin 12 of the present embodiment is a U-shaped structure, and one side of the plug pin 12 is a straight arm, and the other side is an arc-shaped curved arm. When in use, the straight arm of the plug pin 12 is inserted into the plug hole 902, and the arc-shaped curved arm of the plug pin 12 is against the side wall of the first rotating shaft 9, which is convenient for installation and disassembly and is not easy to fall off. The structure of the second rotating shaft 5 of the present embodiment is the same as that of the first rotating shaft 9, and the second rotating shaft 5 is also connected with a plug pin 12.

[0044] In addition, a push rod connection seat 13 is provided on the landing gear body 1, and the electric push rod 4 is connected to the push rod connection seat 13 through a connecting shaft 14. The push rod connection seat 13 includes two parallel and opposite push rod connection seat plates 1301, and the push rod connection seat plates 1301 are provided with a fifth connection hole 1302. The push rod of the electric push rod 4 is provided with a sixth connection hole 401, and the connecting shaft 14 passes through the sixth connection hole 401 and the fifth connection holes 1302 of the two push rod connection seat plates 1301. In addition, one end of the connecting shaft 14 of this embodiment is provided with a bolt head, and the outer wall of the end of the other end is provided with an external thread, and the end of the connecting shaft 14 provided with the external thread is also connected to a nut 15. Similarly, the main body of the electric push rod 4 of this embodiment is also connected to the first connecting rod 7 through a connecting shaft 14 and a nut 15.

[0045] The landing gear body 1 is provided with a connecting rod connection seat 16, and the second connecting rod 8 is rotatably connected to the connecting rod connection seat 16 through a third rotating shaft 17. The connecting rod connection seat 16 includes two connecting rod connection seat plates 1601 arranged in parallel and opposite to each other, and the connecting rod connection seat plates 1601 are provided with a seventh connecting hole 1602, and the end of the second connecting rod 8 is provided with an eighth connecting hole 802. The third rotating shaft 17 passes through the eighth connecting hole 802 and the seventh connecting holes 1602 of the two connecting rod connection seat plates 1601, and the structure of the third rotating shaft 17 is the same as that of the first rotating shaft 9, and the third rotating shaft 17 is also connected to the latch 12. The first connecting rod 7 is rotatably connected to the second fuselage fixing seat 3 through a fourth rotating shaft 18, and the fourth rotating shaft 18 is the same as the structure of the first rotating shaft 9, and the third rotating shaft 17 is also connected to the latch 12.

[0046] In this embodiment, the landing gear body 1 is made of a carbon fiber glass fiber composite material, and the first connecting rod 7 and the second connecting rod 8 are made of 7075 series aluminum alloy material, which achieves lightweight while ensuring reliable structural strength, and has extremely high durability and maintenance-free performance.

[0047] The other structures of this embodiment are the same as those of the first embodiment and will not be described again here.

[0048] Embodiment 3

[0049] The difference between this embodiment and the second embodiment is that, based on the second embodiment, this embodiment further illustrates the landing gear body 1 .

[0050] In this embodiment, the landing gear body 1 includes a first frame 102 and a second frame 103, one end of the first frame 102 is connected to the middle of the second frame 103, so that the landing gear body 1 is a T-shaped structure, and the first fuselage fixing seat 2 and the electric push rod 4 are both connected to the first frame 102. Setting the landing gear body 1 to a T-shaped structure can ensure stable support for the aircraft and reduce resistance when the landing gear is opened.

[0051] Furthermore, in this embodiment, the two ends of the second frame 103 are provided with supports 104, and the supports 104 and the first frame 102 are located on opposite sides of the second frame 103. When the landing gear is opened, the supports 104 land first, which can be the main structure of the landing gear, and can be supported in places where the landing point is limited. Optionally, the two supports 104 can be connected to the second frame 103 close to or far from each other.

[0052] In addition, the second frame 103 of the present embodiment is an arc-shaped structure, and when the landing gear is closed, a space for accommodating the retractable mechanism and the supporting mechanism can be formed between the landing gear body 1 and the fuselage of the aircraft.

[0053] The other structures of this embodiment are the same as those of the second embodiment and will not be described again here.

[0054] Embodiment 4

[0055] This embodiment provides an aircraft, including a fuselage 19 and the landing gear of the first, second or third embodiment, the first fuselage fixing seat 2 and the second fuselage fixing seat 3 are connected to the fuselage 19, and two landing gears are provided, and the two landing gears are symmetrically arranged on both sides of the fuselage 19. The two symmetrically arranged landing gears can provide stable support for the aircraft.

[0056] Furthermore, a receiving groove 1901 for the landing gear to be embedded is provided at the bottom of the fuselage 19, which can protect the landing gear when the landing gear is retracted.

[0057] Embodiment 5

[0058] This embodiment provides a method for controlling the retraction and extension of a landing gear of an aircraft, comprising:

[0059] When the landing gear is opened, the electric push rod 4 is energized, and the push rod of the electric push rod 4 is retracted, driving the landing gear body to rotate downward around the connection between it and the first fuselage fixing seat 2 until the landing gear body 1 is deployed to the target position. When the current of the electric push rod 4 exceeds the threshold, the electric push rod 4 is powered off and self-locked;

[0060] When the landing gear is closed, the electric push rod 4 is energized, and the push rod of the electric push rod 4 extends, driving the landing gear body 1 to rotate upward around the connection between it and the first fuselage fixing seat 2 until the landing gear body 1 is tightly attached to the fuselage 16 of the aircraft. When the current of the electric push rod 4 exceeds the threshold, the electric push rod 4 is powered off and self-locked.

[0061] By detecting the current of the electric push rod 4, when the current of the electric push rod 4 increases, the movement of the landing gear body 1 is blocked, that is, it reaches the target position. At this time, the electric push rod is powered off and self-locked, so that the electric push rod 4 can maintain its state, and then the landing gear body 1 can be kept in the target position, and the landing gear will not move when it is impacted, thereby ensuring the reliability and safety of the landing gear.

[0062] Further, based on the landing gear of the second embodiment and the third embodiment, the retraction and extension control method of this embodiment further includes:

[0063] When the landing gear is opened, the push rod of the electric push rod 4 is retracted, driving the first link 7 to rotate downward around the connection between the electric push rod 4 and the second fuselage fixing seat 3, and driving the second link 8 to rotate downward around the connection between the electric push rod 4 and the first link 7, so that when the landing gear body 1 reaches the target position, the connection between the electric push rod 4 and the first link 7, the connection between the electric push rod 4 and the landing gear body 1, and the connection between the second link 8 and the landing gear body 1 form three corner points of a triangle;

[0064] When the landing gear is closed, the push rod of the electric push rod 4 extends, driving the first link 7 to rotate upward around the connection with the second fuselage fixing seat 3, and driving the second link 8 to rotate upward and retract around its connection with the first link 7.

[0065] In summary, the embodiment of the present invention provides a landing gear for an aircraft. By rotatably connecting the landing gear main body 1 with the first fuselage fixing seat 2, connecting one end of the electric push rod 4 with the second fuselage fixing seat 3 and the other end with the landing gear main body 1, and the first fuselage fixing seat 2 and the second fuselage fixing seat 3 are used to connect with the fuselage of the aircraft. Through the telescopic movement of the push rod of the electric push rod 4, the rotation of the landing gear main body 1 can be realized, thereby realizing the retraction and extension of the landing gear main body 1. It can prevent the landing gear main body 1 from blocking the view when other devices of the aircraft are working, and there is no need to disassemble it during the transportation of the aircraft, which is convenient to use. Moreover, the retraction and extension mechanism of this embodiment further includes a control device and a current detection device. The electric push rod 4 is provided with a self-locking device. When the landing gear main body 1 rotates in place, the limiting mechanism prevents the landing gear main body 1 from continuing to rotate, increasing the resistance for the electric push rod 4 to continue to retract or extend, thereby increasing the current of the electric push rod 4. When the current detection device detects that the current of the electric push rod 4 increases, the control device cuts off the power supply of the electric push rod 4. After the electric push rod 4 is powered off, it self-locks and maintains its state before power-off, so that the landing gear main body 1 can be kept in the target position, ensuring that the landing gear will not close due to impact when the aircraft lands, and realizing the reliability and safety of the landing gear retraction and extension. In addition, the embodiment of the present invention further provides an aircraft, including a fuselage 16 and the above landing gear. Two landing gears are symmetrically arranged on both sides of the fuselage 16. In addition, the embodiment of the present invention further provides a method for controlling the retraction and extension of the landing gear of an aircraft.

[0066] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the technical principle of the present invention, several improvements and replacements can be made, and these improvements and replacements should also be regarded as the protection scope of the present invention.

Claims

1. A landing gear for an aircraft, It is characterized in that The invention comprises a landing gear body (1), a retractable mechanism, a support mechanism and a limit mechanism, wherein the support mechanism comprises a first fuselage fixing seat (2) and a second fuselage fixing seat (3), the retractable mechanism comprises an electric push rod (4), a control device and a current detection device, the landing gear body (1) is rotatably connected to the first fuselage fixing seat (2), the limit mechanism is used to limit the rotation angle of the landing gear body (1), the control device, the current detection device and the electric push rod (4) are electrically connected, the electric push rod (4) is provided with a self-locking device, the current detection device is used to detect the current of the electric push rod (4), and the control device controls the on and off of the electric push rod (4); The retracting and extending mechanism further comprises a first connecting rod (7) and a second connecting rod (8); one end of the first connecting rod (7) is rotatably connected to the second fuselage fixing seat (3); the other end of the first connecting rod (7) is rotatably connected to one end of the second connecting rod (8); the other end of the second connecting rod (8) is rotatably connected to the landing gear body (1); one end of the electric push rod (4) is connected to the first connecting rod (7); the other end of the electric push rod (4) is connected to the landing gear body (1); and the connection between the electric push rod (4) and the landing gear body (1) is closer to the connection between the landing gear body (1) and the first fuselage fixing seat (2) than the connection between the second connecting rod (8) and the landing gear body (1); When the push rod of the electric push rod (4) is retracted, the landing gear is driven to open; when the push rod of the electric push rod (4) is extended, the landing gear is driven to close.

2. The landing gear of an aircraft according to claim 1, It is characterized in that The first connecting rod (7) is connected to the second connecting rod (8) via a first rotating shaft (9); one end of the first connecting rod (7) away from the second fuselage fixing seat (3) is provided with two parallel and spaced ear plates (10); the ear plates (10) are provided with a first connecting hole (1001); the end of the second connecting rod (8) is located between the two ear plates (10); the end of the second connecting rod (8) is provided with a limiting second connecting hole (801); the first rotating shaft (9) passes through the second connecting hole (801) and the first connecting holes (1001) of the two ear plates (10); The limiting mechanism comprises a limiting block (11), the limiting block (11) being connected to one side of the second connecting rod (8), the width direction of the limiting block (11) being parallel to the axial direction of the first rotating shaft (9), and the end of the second connecting rod where the second connecting hole (801) is provided is located between the two ends of the limiting block (11), and the width of the limiting block (11) is greater than the distance between the two ear plates (10).

3. The landing gear of an aircraft according to claim 2, It is characterized in that A plug (901) is provided at one end of the first rotating shaft (9), and a plug hole (902) is provided at the other end of the first rotating shaft (9), wherein a latch pin (12) is inserted into the plug hole (902).

4. The landing gear of an aircraft according to claim 1, It is characterized in that The first fuselage fixing seats (2) are provided in two numbers, the connection between the electric push rod (4) and the landing gear body (1) is located between the two first fuselage fixing seats (2), the landing gear body (1) is provided with an anti-interference notch (101), and the anti-interference notch (101) is located between the two first fuselage fixing seats (2).

5. The landing gear of an aircraft according to claim 1, It is characterized in that The landing gear body (1) is connected to the first fuselage fixing seat (2) via a second rotating shaft (5); a mounting seat (6) is provided on the landing gear body (1); the mounting seat (6) comprises two mounting seat plates (601) arranged in parallel and spaced apart; the mounting seat plates (601) are provided with a third connecting hole (602); the first fuselage fixing seat (2) is located between the two mounting seat plates (601); the first fuselage fixing seat (2) is provided with a fourth connecting hole (201); and the second rotating shaft (5) passes through the fourth connecting hole (201) and the third connecting holes (602) of the two mounting seat plates (601).

6. The landing gear of an aircraft according to claim 1, It is characterized in that The landing gear body (1) comprises a first frame (102) and a second frame (103); one end of the first frame (102) is connected to the middle of the second frame (103), so that the landing gear body (1) has a T-shaped structure; the first fuselage fixing seat (2) and the electric push rod (4) are both connected to the first frame (102).

7. The landing gear of an aircraft according to claim 6, It is characterized in that Supports (104) are provided at both ends of the second frame (103), and the support (104) and the first frame (102) are located on two opposite sides of the second frame (103).

8. An aircraft, It is characterized in that The invention comprises a fuselage (19) and the landing gear according to any one of claims 1 to 7, wherein the first fuselage fixing seat (2) and the second fuselage fixing seat (3) are connected to the fuselage (19), and the number of the landing gears is two, and the two landing gears are symmetrically arranged on both sides of the fuselage (19).

9. The aircraft according to claim 8, It is characterized in that The bottom of the fuselage (19) is provided with a receiving groove (1901) into which the landing gear can be embedded.

10. A method for controlling the retraction and extension of a landing gear of an aircraft, It is characterized in that include: When the landing gear is opened, the electric push rod (4) is energized, the push rod of the electric push rod (4) is retracted, and the landing gear body (1) is driven to rotate downward around the connection between the electric push rod (4) and the first fuselage fixing seat (2), until the landing gear body (1) is deployed to the target position, and when the current of the electric push rod (4) exceeds the threshold value, the electric push rod (4) is powered off and self-locked; when the landing gear is opened, the push rod of the electric push rod (4) is retracted, and the first connecting rod (7) is driven to rotate downward around the connection between the electric push rod (4) and the second fuselage fixing seat (3), and the second connecting rod (8) is driven to rotate downward around the connection between the electric push rod (4) and the first connecting rod (7), and when the landing gear body (1) reaches the target position, the connection between the electric push rod (4) and the first connecting rod (7), the connection between the electric push rod (4) and the landing gear body (1), and the connection between the second connecting rod (8) and the landing gear body (1) form three corner points of a triangle; When the landing gear is closed, the electric push rod (4) is energized, the push rod of the electric push rod (4) extends, driving the landing gear body (1) to rotate upward around the connection between the landing gear body (1) and the first fuselage fixing seat (2) until the landing gear body (1) is tightly attached to the fuselage (19) of the aircraft. When the current of the electric push rod (4) exceeds a threshold value, the electric push rod (4) is powered off and self-locked. When the landing gear is closed, the push rod of the electric push rod (4) extends, driving the first connecting rod (7) to rotate upward around the connection with the remaining second fuselage fixing seat (3), and driving the second connecting rod (8) to rotate upward around the connection with the first connecting rod (7) and retract.

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