Self-locking device of folding arm of aircraft and aircraft

Abstract

The utility model discloses a self-locking device of a folding arm of an aircraft and the aircraft. According to the self-locking device, a gear transmission mechanism is arranged to be in transmission connection with a folding arm, the gear transmission mechanism is provided with an unfolding locking hole and a folding locking hole, a locking structure comprises an electromagnet and a ferromagnetic locking pin capable of being attracted by the electromagnet to move back and forth, and the output end of a driving motor is in transmission connection with the gear transmission mechanism. The power of the driving motor can be transmitted to the folding arm through the gear transmission mechanism, so that the folding arm is driven to rotate, the locking pin made of the ferromagnetic material is controlled to be inserted into the unfolding locking hole to be locked when the folding arm rotates to the position of the unfolding locking hole in the first direction by arranging an electromagnet to be powered on and powered off, and otherwise, the locking pin is inserted into the unfolding locking hole to be locked. When the folding arm reversely rotates to the position of the folding locking hole in the first direction, the folding arm is inserted into the folding locking hole to be unlocked, automatic locking and unlocking are achieved, manual intervention is not needed, operation is easy and convenient, the error probability is reduced, reliability is improved, and safety accidents are avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, specifically, a folding arm's self-locking device of aircraft and aircraft. BACKGROUND

[0002] With the rapid development of aircraft technology, multi-rotor aircraft has been widely used in military reconnaissance, disaster rescue, agricultural plant protection, logistics distribution and other fields due to its vertical take-off and landing, hovering flight and flexible control. However, the folding arm of the multi-rotor aircraft usually needs to be folded up to save space during transportation and storage.

[0003] The existing locking device of the folding arm of the aircraft mainly relies on manual operation or simple mechanical structure, which needs manual intervention during the locking and unlocking of the folding arm, increasing the operation difficulty and error probability. In addition, the reliability of the existing locking device is difficult to guarantee, especially in harsh environmental conditions such as vibration, impact, etc., which may cause locking failure and further cause safety accidents. SUMMARY

[0004] The utility model provides a folding arm's self-locking device of aircraft and aircraft, can automatically lock and unlock, need not manual intervention, operation is simple, reduces error probability, and improves reliability, avoids causing safety accidents. The specific technical scheme is as follows:

[0005] In the first aspect, the utility model provides a folding arm's self-locking device of aircraft, comprising:

[0006] Gear transmission mechanism, gear transmission mechanism is connected with folding arm transmission, and gear transmission mechanism is equipped with unfolding locking hole and folding locking hole;

[0007] Locking structure, the locking structure includes electromagnet and the ferromagnetic material locking pin that can be attracted to and fro by electromagnet;

[0008] Drive motor, the output end of drive motor is connected with gear transmission mechanism transmission;

[0009] Before the aircraft takes off, the electromagnet is electrified, the ferromagnetic material locking pin is extracted from the folding locking hole, the electromagnet is powered off, the drive motor drives the gear transmission mechanism to drive the folding arm to rotate to the first direction, when rotating to the position of the unfolding locking hole, the ferromagnetic material locking pin is inserted into the unfolding locking hole and locks;

[0010] After the aircraft lands, the electromagnet is powered on, the ferromagnetic material locking pin is extracted from the unfolding locking hole, the electromagnet is powered off, the driving motor drives the gear transmission mechanism to drive the folding arm to rotate in the reverse direction of the first direction, and when the folding arm rotates to the position of the folding locking hole, the ferromagnetic material locking pin is inserted into the folding locking hole to be unlocked.

[0011] Optionally, the gear transmission mechanism comprises a driving gear and a driven gear which are externally meshed with each other, and the output end of the driving motor is fixedly connected with the driving gear.

[0012] The driven gear is fixedly installed at one end of the folding arm, and the part of the outer periphery of the driven gear which is not meshed with the driving gear is provided with the unfolding locking hole and the folding locking hole.

[0013] Optionally, the gear transmission mechanism comprises a first gear, a second gear and a third gear, the first gear is externally meshed with the second gear, and the second gear is externally meshed with the third gear.

[0014] The third gear is fixedly installed at one end of the folding arm, the part of the outer periphery of the third gear which is not meshed with the second gear is provided with the unfolding locking hole and the folding locking hole, and the output end of the driving motor is fixedly connected with the first gear.

[0015] Optionally, the included angle between the unfolding locking hole and the folding locking hole is an acute angle.

[0016] Optionally, the self-locking device of the folding arm of the aircraft further comprises a connector.

[0017] The connector comprises a folding arm connecting part and a fixed arm connecting part which are connected with each other.

[0018] The third gear is fixedly installed at the folding arm connecting part, and the fixed arm connecting part is fixedly connected with the fixed arm of the aircraft.

[0019] Optionally, the diameter of the third gear is greater than the diameter of the second gear, and the diameter of the second gear is greater than the diameter of the first gear.

[0020] Optionally, the locking structure further comprises a non-ferromagnetic material spring and a pressure sensor.

[0021] The lower outer periphery of the ferromagnetic material locking pin is provided with an annular groove, one end of the non-ferromagnetic material spring is embedded in the annular groove, the other end of the non-ferromagnetic material spring is fixedly installed on the fixed arm of the aircraft, and the pressure sensor is fixedly installed between the other end of the non-ferromagnetic material spring and the fixed arm.

[0022] The electromagnet is fixedly installed on the fixed arm of the aircraft, and is located below the ferromagnetic locking pin.

[0023] Before the aircraft takes off, the electromagnet is powered on, the ferromagnetic locking pin compresses the non-ferromagnetic spring, the ferromagnetic locking pin is extracted from the folding locking hole, the pressure sensor detects pressure, and the electromagnet is powered off.

[0024] After the aircraft lands, the electromagnet is powered on, the ferromagnetic locking pin compresses the non-ferromagnetic spring, the ferromagnetic locking pin is extracted from the folding locking hole, the pressure sensor detects pressure, and the electromagnet is powered off.

[0025] Optionally, the self-locking device of the folding arm of the aircraft further comprises a controller.

[0026] The pressure sensor, the driving motor and the electromagnet are all signal-connected with the controller.

[0027] Optionally, the self-locking device of the folding arm of the aircraft further comprises an angle sensor and an alarm device, and the angle sensor and the alarm device are both signal-connected with the controller.

[0028] The angle sensor and the alarm device are both fixedly installed on the folding arm, when the driving motor acts for a preset time period, the angle sensor detects that the rotation angle of the folding arm is 0, and the alarm device sends a fault alarm indicating that the self-locking device is faulty.

[0029] In a second aspect, the utility model provides a kind of aircraft, including folding arm, and the folding arm is equipped with the self-locking device as any described in first aspect.

[0030] From the above, the self-locking device of the folding arm of the aircraft provided by the embodiments of the utility model comprises a gear transmission mechanism, a locking structure and a driving motor. The gear transmission mechanism is in transmission connection with the folding arm, and the gear transmission mechanism is provided with an unfolding locking hole and a folding locking hole; the locking structure comprises an electromagnet and a ferromagnetic material locking pin which can be attracted by the electromagnet to move back and forth; the output end of the driving motor is in transmission connection with the gear transmission mechanism; before the aircraft takes off, the electromagnet is powered on, the ferromagnetic material locking pin is pulled out from the folding locking hole, the electromagnet is powered off, the driving motor drives the gear transmission mechanism to drive the folding arm to rotate in the first direction, when rotating to the position of the unfolding locking hole, the ferromagnetic material locking pin is inserted into the unfolding locking hole to lock; after the aircraft lands, the electromagnet is powered on, the ferromagnetic material locking pin is pulled out from the unfolding locking hole, the electromagnet is powered off, the driving motor drives the gear transmission mechanism to drive the folding arm to rotate in the reverse direction of the first direction, when rotating to the position of the folding locking hole, the ferromagnetic material locking pin is inserted into the folding locking hole to unlock. Thus, by means of the gear transmission mechanism in transmission connection with the folding arm, the gear transmission mechanism provided with the unfolding locking hole and the folding locking hole, the locking structure comprising the electromagnet and the ferromagnetic material locking pin which can be attracted by the electromagnet to move back and forth, and the output end of the driving motor in transmission connection with the gear transmission mechanism, the power of the driving motor can be transmitted to the folding arm through the gear transmission mechanism, so as to drive the folding arm to rotate, and by means of the power-on and power-off mode of the electromagnet, the ferromagnetic material locking pin is inserted into the unfolding locking hole to lock when the folding arm rotates in the first direction to the position of the unfolding locking hole, and vice versa, the ferromagnetic material locking pin is inserted into the folding locking hole to unlock when the folding arm rotates in the reverse direction of the first direction to the position of the folding locking hole, automatic locking before the aircraft takes off and automatic unlocking after the aircraft lands are realized, manual intervention is not needed, the operation is simple, the error probability is reduced, and the mechanical locking mode of the locking pin and the locking hole in cooperation makes the locking stable, even in harsh environmental conditions, the locking will not fail, the reliability is improved, and a safety accident is avoided.

[0031] The innovation points of the embodiments of the utility model include:

[0032] 1. The gear transmission mechanism is in transmission connection with the folding arm, and the gear transmission mechanism is provided with an unfolding locking hole and a folding locking hole, the locking structure includes an electromagnet and a ferromagnetic locking pin which can be attracted by the electromagnet to move back and forth, the output end of the driving motor is in transmission connection with the gear transmission mechanism, so that the power of the driving motor can be transmitted to the folding arm through the gear transmission mechanism, thereby driving the folding arm to rotate, and the ferromagnetic locking pin is inserted into the unfolding locking hole to lock when the folding arm rotates to the position of the unfolding locking hole in the first direction, and vice versa, the ferromagnetic locking pin is inserted into the folding locking hole to unlock when the folding arm rotates to the position of the folding locking hole in the opposite direction of the first direction, thereby achieving automatic locking before takeoff of the aircraft and automatic unlocking after landing of the aircraft, without manual intervention, simple operation, reduced error probability, and the mechanical locking mode of the locking pin and the locking hole makes the locking stable, even in harsh environmental conditions, the locking will not fail, improving the reliability and avoiding safety accidents.

[0033] 2. The gear transmission mechanism includes a driving gear and a driven gear which are in external meshing with each other, so that the driving motor can transmit power to the folding arm through the gear transmission mechanism composed of two gears, improving the transmission efficiency.

[0034] 3. The gear transmission mechanism includes a first gear, a second gear and a third gear which are in external meshing in sequence, so that the driving motor can transmit power to the folding arm through the gear transmission mechanism composed of three gears, the transmission direction can be changed according to the demand, the space layout can be optimized, the gear transmission mechanism is more compact, the limited space is fully utilized, and the reliability and stability of transmission are ensured.

[0035] 4. The third gear is fixedly installed at one end of the folding arm, the third gear is fixed to a connector, and the connector is fixed to the fixed arm, thereby realizing stable connection of the folding arm and ensuring stable rotation of the folding arm.

[0036] 5. The locking structure further includes a non-ferromagnetic spring and a pressure sensor, so that the power supply of the electromagnet is controlled by the pressure sensor, and the ferromagnetic locking pin can be driven to move back and forth by the non-ferromagnetic spring, which is simple and reliable, and easy to manufacture and maintain.

[0037] 6. The controller controls the power supply of the electromagnet and the action of the driving motor, thereby improving the intelligent level and reducing the demand for manual operation.

[0038] 7. The angle sensor and the alarm device are provided, so that when the angle sensor detects that the rotation angle of the folding arm is 0 after the driving motor acts for a preset period of time, the alarm device issues a fault alarm indicating that the self-locking device is faulty, reminding the user to check and maintain.

[0039] 8. The aircraft of the utility model embodiment provides a folding arm, the folding arm is equipped with the self locking device like any one of embodiment one. The self locking device is transmission connection with the folding arm through the gear transmission mechanism, and the gear transmission mechanism is equipped with unfolding locking hole and folding locking hole, the locking structure includes electromagnet and ferromagnetic material locking pin that can be attracted to move back and forth by the electromagnet, the output end of the driving motor is transmission connection with the gear transmission mechanism, so that the power of the driving motor can be transmitted to the folding arm through the gear transmission mechanism, thereby driving the folding arm to rotate, and the ferromagnetic material locking pin is inserted into the unfolding locking hole and locked when the folding arm rotates to the position of the unfolding locking hole in the first direction through the mode of controlling the on-off electricity of the electromagnet, on the contrary, it is inserted into the folding locking hole and unlocked when the folding arm rotates to the position of the folding locking hole in the reverse direction of the first direction, realize automatic locking before the aircraft takes off and automatic unlocking after the aircraft lands, without manual intervention, simple operation, reduce the error probability, and the mechanical locking mode of the locking pin and the locking hole cooperation makes the locking stable, even in harsh environmental conditions, the locking will not fail, improve the reliability, avoid causing safety accidents.

[0040] 9. The folding arm is folded after the aircraft lands automatically, reduces the occupied space, and is convenient for carrying and transporting.

[0041] 10. In the process of aircraft flight, the mechanical locking mode of the locking pin and the locking hole cooperation makes the locking stable, ensures that the folding arm will not loosen during flight, thereby guaranteeing the stability and safety of the aircraft.

[0042] 11. The self locking device of the folding arm of the aircraft of the utility model embodiment includes gear transmission mechanism, locking structure and driving motor three modules, this modular design is convenient for maintenance and upgrading, at the same time, it is also convenient for users to replace corresponding modules according to different aircraft types, without replacing the whole self locking device, reduce the cost at the same time also realize the customized service.

[0043] 12. The self locking device of the folding arm of the aircraft of the utility model embodiment adopts gear transmission mechanism to drive, because the gear transmission mechanism has enough strength and rigidity, so as to ensure the stability and reliability in the process of locking and unlocking.

[0044] 13. The self locking device of the folding arm of the aircraft of the utility model embodiment is suitable for various types of aircraft with folding arms, and has wide application prospect.

[0045] Of course, implementing any product or method of the utility model does not necessarily need to achieve all the advantages described above at the same time. BRIEF DESCRIPTION OF DRAWINGS

[0046] In order to more clearly illustrate the technical solutions of the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application. For those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0047] Figure 1 A structural schematic view of the self-locking device of the folding arm of the aircraft provided by the embodiments of the present application is shown in the figure.

[0048] Figure 2 A structural schematic view of the unfolding locking hole and the folding locking hole provided by the embodiments of the present application is shown in the figure.

[0049] Figure 3 A schematic view of the folding arm of the aircraft provided with the self-locking device in an unfolded state is shown in the figure.

[0050] Figure 4 A schematic view of the folding arm of the aircraft provided with the self-locking device in a moving state is shown in the figure.

[0051] Figures 1-4 In the figure, 1 is a gear transmission mechanism, 11 is an unfolding locking hole, 12 is a folding locking hole, 13 is a first gear, 14 is a second gear, 15 is a third gear, 2 is a driving motor, 3 is a folding arm, 4 is an electromagnet, 5 is a ferromagnetic material locking pin, 6 is a connector, 61 is a folding arm connecting part, 62 is a fixed arm connecting part, 7 is a fixed arm, and 8 is a non-ferromagnetic material spring. DETAILED DESCRIPTION

[0052] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0053] It should be noted that the terms "include" and "have" and any variations thereof in the embodiments of the present application and the drawings are intended to cover non-exclusive inclusion. For example, the processes, methods, systems, products or devices including a series of steps or units are not limited to the listed steps or units, but can optionally further include steps or units not listed or can optionally further include other steps or units inherent to these processes, methods, products or devices.

[0054] The utility model embodiment discloses a self locking device of folding arm of aircraft and aircraft, can automatically lock and unlock, need not manual intervention, simple operation reduces the probability of error, and improved reliability, avoid causing safety accident. The utility model embodiment is explained in detail below.

[0055] Embodiment one

[0056] Figure 1 A structural schematic view of the self locking device of folding arm of aircraft provided by the utility model embodiment. Figure 2 A structural schematic view of the unfolding locking hole and folding locking hole provided by the utility model embodiment. Figure 3 A schematic view of the folding arm of aircraft provided with the self locking device of the utility model embodiment in the unfolded state. Figure 4 A schematic view of the folding arm of aircraft provided with the self locking device of the utility model embodiment in the motion state.

[0057] Referring to Figure 1 , the self locking device of folding arm of aircraft provided by the utility model embodiment includes gear transmission mechanism 1, locking structure and drive motor 2, wherein, locking structure is used for locking and unlocking folding arm 3. Gear transmission mechanism 1 is transmissionally connected with folding arm 3, and gear transmission mechanism 1 is equipped with unfolding locking hole 11 and folding locking hole 12 as Figure 2 Indicated.

[0058] The included angle between unfolding locking hole 11 and folding locking hole 12 is set according to actual needs, and the included angle between unfolding locking hole 11 and folding locking hole 12 is an acute angle exemplarily.

[0059] Continuously referring to Figure 1 , locking structure includes electromagnet 4 and ferromagnetic material locking pin 5 that can be attracted to move back and forth by electromagnet 4, and the ferromagnetic material locking pin 5 that can be attracted to move up and down by electromagnet 4 is shown in Figure 1 , wherein, ferromagnetic material can be iron, cobalt, nickel and its alloy, and ferromagnetic material locking pin 5 is used for being used with unfolding locking hole 11 and folding locking hole 12 of gear transmission mechanism 1.

[0060] The output end of drive motor 2 is transmissionally connected with gear transmission mechanism 1, so that the power of drive motor 2 can be transmitted to folding arm 3 through gear transmission mechanism 1.

[0061] After the aircraft lands, the ferromagnetic material locking pin 5 is in the state of being inserted into the folding locking hole 12. Before the aircraft takes off, the folding arm 3 needs to be unfolded for flight, so the electromagnet 4 is powered on to attract the ferromagnetic material locking pin 5 to be pulled out of the folding locking hole 12, then the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the first direction, and when it rotates to the position of the unfolding locking hole 11, the ferromagnetic material locking pin 5 is inserted into the unfolding locking hole 11 to be locked. At this time, the folding arm 3 is in the unfolded state as shown in Figure 3 , and the state of the folding arm 3 in the movement process is as shown in Figure 4 . The first direction can be set according to actual needs, which can be clockwise or counterclockwise.

[0062] Before the aircraft lands, the ferromagnetic material locking pin 5 is in the state of being inserted into the unfolding locking hole 11. After the aircraft lands, the folding arm 3 needs to be folded at this time, so the electromagnet 4 is powered on to attract the ferromagnetic material locking pin 5 to be pulled out of the unfolding locking hole 11, then the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the reverse direction of the first direction, and when it rotates to the position of the folding locking hole 12, the ferromagnetic material locking pin 5 is inserted into the folding locking hole 12 to be unlocked. At this time, the folding arm 3 is in the folded state as shown in Figure 1 .

[0063] The self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model comprises a gear transmission mechanism 1, a locking structure and a driving motor 2. The gear transmission mechanism 1 is in transmission connection with the folding arm 3, and the gear transmission mechanism 1 is provided with an unfolding locking hole 11 and a folding locking hole 12; the locking structure comprises an electromagnet 4 and a ferromagnetic material locking pin 5 which can be attracted by the electromagnet to move back and forth; the output end of the driving motor 2 is in transmission connection with the gear transmission mechanism 1; before the aircraft takes off, the electromagnet 4 is powered on, the ferromagnetic material locking pin 5 is pulled out from the folding locking hole 12, the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the first direction, when rotating to the position of the unfolding locking hole 11, the ferromagnetic material locking pin 5 is inserted into the unfolding locking hole 11 to lock; after the aircraft lands, the electromagnet 4 is powered on, the ferromagnetic material locking pin 5 is pulled out from the unfolding locking hole 11, the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the reverse direction of the first direction, when rotating to the position of the folding locking hole 12, the ferromagnetic material locking pin 5 is inserted into the folding locking hole 12 to unlock. Thus, by means of the gear transmission mechanism 1 in transmission connection with the folding arm 3, the gear transmission mechanism 1 provided with the unfolding locking hole 11 and the folding locking hole 12, the locking structure comprising the electromagnet 4 and the ferromagnetic material locking pin 5 which can be attracted by the electromagnet to move back and forth, and the output end of the driving motor 2 in transmission connection with the gear transmission mechanism 1, the power of the driving motor 2 can be transmitted to the folding arm 3 through the gear transmission mechanism 1 to drive the folding arm 3 to rotate, and by means of the power-on and power-off of the electromagnet 4 to control the ferromagnetic material locking pin 5 to be inserted into the unfolding locking hole 11 to lock when the folding arm 3 rotates in the first direction to the position of the unfolding locking hole 11, and vice versa, to be inserted into the folding locking hole 12 to unlock when the folding arm 3 rotates in the reverse direction of the first direction to the position of the folding locking hole 12, automatic locking before the aircraft takes off and automatic unlocking after the aircraft lands are realized, without manual intervention, the operation is simple, the error probability is reduced, and the mechanical locking mode of the locking pin and the locking hole in cooperation makes the locking stable, even in harsh environmental conditions, the locking will not fail, the reliability is improved, and a safety accident is avoided.

[0064] Meanwhile, the folding arm 3 is folded automatically after the aircraft lands, the occupied space is reduced, and the folding arm 3 is convenient to carry and transport.

[0065] In addition, during the flight of the aircraft, the mechanical locking mode of the locking pin and the locking hole in cooperation makes the locking stable, the folding arm 3 is ensured not to loosen during the flight, and thus the stability and safety of the aircraft are ensured.

[0066] And, the self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model comprises three modules of gear transmission mechanism 1, locking structure and driving motor 2, this modular design is convenient for maintenance and upgrading, and also facilitates users to replace corresponding modules according to different aircraft types, without needing to replace the whole self-locking device, reducing cost while realizing customized service.

[0067] And, the self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model adopts gear transmission mechanism 1 to drive, since the gear transmission mechanism 1 has sufficient strength and rigidity, thereby the stability and reliability in the locking and unlocking process can be ensured.

[0068] And, the self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model is suitable for various types of aircrafts with folding arms, and has wide application prospects.

[0069] In the embodiment of the utility model, the structure of gear transmission mechanism 1 can be set according to actual demand, and the structure of gear transmission mechanism 1 has multiple types, including but not limited to the following two forms:

[0070] The first form is:

[0071] The gear transmission mechanism 1 comprises a driving gear and a driven gear which are mutually externally meshed, and the output end of the driving motor 2 is fixedly connected with the driving gear. The driven gear is fixedly installed at one end of the folding arm 3, and the part of the outer periphery of the driven gear which is not meshed with the driving gear is provided with an unfolding locking hole 11 and a folding locking hole 12.

[0072] That is to say, the part of the outer periphery of the driven gear which is not meshed with the driving gear can be that the diameter of the driven gear is greater than the diameter of the driving gear, so that after the outer periphery of the driven gear is externally meshed with the driving gear, there is still the part which is not meshed with the driving gear, and the setting of the unfolding locking hole 11 and the folding locking hole 12 in this part does not affect the external meshing of the driven gear with the driving gear.

[0073] In use, the driving motor 2 drives the driving gear to rotate, the driving gear drives the driven gear to rotate, and the driven gear drives the folding arm 3 to rotate.

[0074] Therefore, by setting the gear transmission mechanism 1 to comprise the driving gear and the driven gear which are mutually externally meshed, the driving motor 2 can transmit power to the folding arm 3 through the gear transmission mechanism 1 composed of two gears, improving the transmission efficiency.

[0075] The second form is:

[0076] Continuing to refer to Figure 1, the gear transmission mechanism 1 includes a first gear 13, a second gear 14 and a third gear 15, the first gear 13 is externally meshed with the second gear 14, and the second gear 14 is externally meshed with the third gear 15. The third gear 15 is fixedly installed at one end of the folding arm 3, and a part of the outer periphery of the third gear 15 that is not meshed with the second gear 14 is provided with an unfolding locking hole 11 and a folding locking hole 12, and the output end of the driving motor 2 is fixedly connected with the first gear 11. Wherein, the fixed installation mode can be screw connection, welding, or other prior art fixed connection mode, the embodiment of the utility model does not make any limitation to this.

[0077] That is, there is a part of the outer periphery of the third gear 15 that is not meshed with the second gear 14, which can be that the diameter of the third gear 15 is greater than the diameter of the second gear 14, so that after the outer periphery of the third gear 15 is externally meshed with the second gear 14, there is still a part that is not meshed with the second gear 14, and the setting of the unfolding locking hole 11 and the folding locking hole 12 in this part does not affect the external meshing of the third gear 15 and the second gear 14.

[0078] In use, the driving motor 2 drives the first gear 13 to rotate, the first gear 13 drives the second gear 14 to rotate, the second gear 14 drives the third gear 15 to rotate, and the third gear 15 drives the folding arm 3 to rotate.

[0079] Specifically, the diameters of the gears can be set according to actual needs, so that different transmission ratios, torque sizes or transmission directions can be realized, for example, the diameter of the third gear 15 is greater than the diameter of the second gear 14, and the diameter of the second gear 14 is greater than the diameter of the first gear 13.

[0080] Therefore, by setting the gear transmission mechanism 1 to include the first gear 13, the second gear 14 and the third gear 15 which are externally meshed in sequence, the driving motor 2 can transmit power to the folding arm 3 through the gear transmission mechanism 1 composed of three gears, the transmission direction can be changed according to needs, the space layout can be optimized, the gear transmission mechanism 1 is more compact, the limited space is fully utilized, and the reliability and stability of transmission are ensured.

[0081] Continuing to refer to Figure 1 When the gear transmission mechanism 1 includes the first gear 13, the second gear 14 and the third gear 15, the self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model further includes a connector 6.

[0082] The connector 6 comprises a folding arm connecting portion 61 and a fixed arm connecting portion 62 connected with each other, the third gear 13 is fixedly installed on the folding arm connecting portion 61, and the fixed arm connecting portion 62 is fixedly connected with the fixed arm 7 of the aircraft. The fixedly installed mode can be screw connection, welding or other fixed connection modes in the prior art, and the embodiment of the utility model does not make any limitation on this. The fixed arm 7 can be made of aluminum alloy material which is light but high in strength, so that the fixed arm 7 is light and durable in the running process.

[0083] Since the third gear 15 is fixedly installed on one end of the folding arm 3, the folding arm 3 is stably connected by the mode that the third gear 13 is fixed on the connector 6 and the connector 6 is fixed on the fixed arm 7, so that the stable rotation of the folding arm 3 is ensured.

[0084] Similarly, when the gear transmission mechanism 1 comprises a driving gear and a driven gear which are externally meshed with each other, the difference between the gear transmission mechanism 1 with three gears and the gear transmission mechanism 1 with two gears is that the driven gear is fixedly installed on one end of the folding arm 3 and the driven gear is fixedly installed on the folding arm connecting portion 61. The specific description can be referred to the corresponding description of the gear transmission mechanism 1 with three gears, and the description is not repeated here.

[0085] Since the driven gear is fixedly installed on one end of the folding arm 3, the folding arm 3 is stably connected by the mode that the driven gear is fixed on the connector 6 and the connector 6 is fixed on the fixed arm 7, so that the stable rotation of the folding arm 3 is ensured.

[0086] Continuing to refer to Figure 1 The locking structure further comprises a non-ferromagnetic material spring 8 and a pressure sensor.

[0087] The lower part of the ferromagnetic material locking pin 5 is provided with an annular groove, one end of the non-ferromagnetic material spring 8 is embedded in the annular groove, and the other end of the non-ferromagnetic material spring 8 is fixedly installed on the fixed arm 7 of the aircraft, that is, the non-ferromagnetic material spring 8 is fixedly sleeved in the annular groove of the lower part of the ferromagnetic material locking pin 5, and the non-ferromagnetic material spring 8 can drive the ferromagnetic material locking pin 5 to move.

[0088] The pressure sensor is fixedly installed between the other end of the non-ferromagnetic material spring 8 and the fixed arm 7, that is, the other end of the non-ferromagnetic material spring 8 is fixedly installed on the fixed arm 7 of the aircraft so that the non-ferromagnetic material spring 8 cannot move, and the pressure sensor is fixedly installed between the other end of the non-ferromagnetic material spring 8 and the fixed arm 7, so that the pressure sensor can detect the pressure change of the non-ferromagnetic material spring 8. In this way, when the ferromagnetic material locking pin 5 compresses the non-ferromagnetic material spring 8, the pressure sensor is squeezed, so that the pressure sensor detects the pressure.

[0089] The electromagnet 4 is fixedly installed on the fixed arm 7 of the aircraft, and the electromagnet 4 is located below the ferromagnetic material locking pin 5, so that the electromagnet 4 can attract the ferromagnetic material locking pin 5 to move after being powered on. The fixed installation mode can be screw connection, welding or other existing fixed connection modes, and the embodiment of the utility model does not make any limitation on this, and the non-ferromagnetic material is a material other than the ferromagnetic material, which is of course a material with certain hardness.

[0090] Before the aircraft takes off, the electromagnet 4 is powered on to attract the ferromagnetic material locking pin 5, so that the ferromagnetic material locking pin 5 compresses the non-ferromagnetic material spring 8, the ferromagnetic material locking pin 5 is extracted from the folding locking hole 12, and the ferromagnetic material locking pin 5 compresses the non-ferromagnetic material spring 8 when extruding the pressure sensor. The pressure sensor detects the pressure, indicating that the ferromagnetic material locking pin 5 has been extracted from the folding locking hole 12, and the electromagnet is powered off. At this time, the non-ferromagnetic material spring 8 can be stretched, but since the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the first direction, so that the non-ferromagnetic material spring 8 is still in a compressed state, until it is rotated to the position of the unfolding locking hole 11, the non-ferromagnetic material spring 8 is stretched, and the ferromagnetic material locking pin 5 is inserted into the unfolding locking hole 11 to be locked.

[0091] Similarly, after the aircraft lands, the electromagnet 4 is powered on to attract the ferromagnetic material locking pin 5, so that the ferromagnetic material locking pin 5 compresses the non-ferromagnetic material spring 8, the ferromagnetic material locking pin 5 is extracted from the unfolding locking hole 11, and the ferromagnetic material locking pin 5 compresses the non-ferromagnetic material spring 8 when extruding the pressure sensor. The pressure sensor detects the pressure, indicating that the ferromagnetic material locking pin 5 has been extracted from the unfolding locking hole 11, and the electromagnet is powered off. At this time, the non-ferromagnetic material spring 8 can be stretched, but since the electromagnet 4 is powered off, the driving motor 2 drives the gear transmission mechanism 1 to drive the folding arm 3 to rotate in the first direction, so that the non-ferromagnetic material spring 8 is still in a compressed state, until it is rotated to the position of the folding locking hole 12, the non-ferromagnetic material spring 8 is stretched, and the ferromagnetic material locking pin 5 is inserted into the folding locking hole 12 to be unlocked.

[0092] Therefore, by setting the locking structure to further include the non-ferromagnetic material spring 8 and the pressure sensor, the electromagnet 4 is controlled to be powered off through the pressure sensor, and the ferromagnetic material locking pin 5 can be driven to move back and forth through the non-ferromagnetic material spring 8. This structure is simple and reliable, and easy to manufacture and maintain.

[0093] In one implementation mode, the self-locking device of the folding arm of the aircraft provided by the embodiment of the utility model further includes a controller, the pressure sensor, the driving motor 2 and the electromagnet 4 are all signal connected with the controller, the controller controls the on-off of the electromagnet 4, and the controller controls the action of the driving motor 2.

[0094] The controller can be a programmable logic controller (PLC).

[0095] Specifically, the controller controls the electromagnetic iron 4 to be powered on after receiving the signal that the aircraft is ready to take off or the signal that the aircraft lands, and then controls the electromagnetic iron 4 to be powered off when the pressure sensor detects pressure, and controls the driving motor 2 to act.

[0096] Therefore, the controller controls the electromagnetic iron 4 to be powered on and off, and controls the driving motor 2 to act, thereby improving the intelligent level and reducing the need for manual operation.

[0097] In an implementation manner, the self-locking device of the folding arm of the aircraft also includes an angle sensor and an alarm device, and the angle sensor and the alarm device are both in signal connection with the controller.

[0098] The angle sensor and the alarm device are both fixedly installed on the folding arm 3, and when the driving motor 2 acts for a preset time period, the angle sensor detects the rotation angle of the folding arm 3 and sends the rotation angle to the controller, and when the controller detects that the rotation angle of the folding arm 3 is 0, it indicates that the folding arm 3 does not rotate, which indicates that a fault occurs, and the alarm device is controlled to issue a fault alarm indicating that the self-locking device is faulty. The driving motor 2 acts means that the driving gear transmission mechanism 1 drives the folding arm 3 to rotate in a first direction or to rotate in the opposite direction of the first direction.

[0099] The alarm device can be a sound emitting device, such as a loudspeaker, or the alarm device can be a flash lamp, and of course, the alarm device can also be other devices that can alarm, which are not limited herein. The preset time period can be set by the user or can be set according to experience, which is not limited herein.

[0100] Therefore, by means of the angle sensor and the alarm device, when the angle sensor detects that the rotation angle of the folding arm is 0 after the driving motor 2 acts for a preset time period, the alarm device issues a fault alarm indicating that the self-locking device is faulty, thereby reminding the user to check and maintain.

[0101] Embodiment two

[0102] The embodiment of the utility model provides a kind of aircraft, including folding arm 3, folding arm 3 is equipped with as any one of embodiment one self-locking device.

[0103] The folding arm 3 can be made of aluminum alloy material which is light but high in strength, ensuring that it is both light and durable during operation.

[0104] In one implementation, the aircraft further comprises an accelerometer and a gyroscope.

[0105] Thus, the embodiment of the utility model provides a kind of aircraft, including folding arm 3, folding arm 3 is equipped with as any one of embodiment one self-locking device.Self-locking device is driven by gear mechanism 1 and folding arm 3 transmission connection, and gear mechanism 1 is equipped with unfolding locking hole 11 and folding locking hole 12, locking structure includes electromagnet 4 and the ferromagnetic material locking pin 5 that can be attracted to move back and forth by electromagnet, the output end of drive motor 2 and the mode of gear mechanism 1 transmission connection, so that the power of drive motor 2 can be transmitted to folding arm 3 by gear mechanism 1, to drive folding arm 3 rotation, and by setting the mode of electromagnet 4 on-off electricity control ferromagnetic material locking pin 5 is inserted into unfolding locking hole 11 and locks when folding arm 3 rotates to the position of unfolding locking hole 11 in first direction, conversely, when folding arm 3 rotates to the position of folding locking hole 12 in the reverse direction of first direction, insert folding locking hole 12 and unlock, realize automatic locking before aircraft take-off and automatic unlocking after aircraft landing, without manual intervention, easy to operate, reduce error probability, and the mechanical locking mode that locking pin and locking hole cooperate makes locking firm, even in harsh environmental conditions, locking failure will not occur, improve reliability, avoid causing safety accident.

[0106] Those skilled in the art can understand that the drawings are only schematic diagrams of an embodiment, and the modules or flows in the drawings are not necessarily necessary for implementing the utility model.

[0107] Those skilled in the art can understand that the modules in the device in the embodiment can be distributed in the device of the embodiment according to the embodiment description, and can be changed and located in one or more devices different from the embodiment. The modules of the above embodiment can be combined as one module, or can be further split into multiple sub-modules.

[0108] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the utility model, and not to limit them; although the utility model has been described in detail with reference to the foregoing examples, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiment of the utility model.

Claims

1. A self-locking device for a folding arm of an aircraft, characterized in that, Comprise: Gear transmission mechanism, the gear transmission mechanism is driven connection with the folding arm, and the gear transmission mechanism is equipped with unfolding locking hole and folding locking hole; Locking structure, the locking structure includes electromagnet and ferromagnetic material locking pin can be attracted by the electromagnet to move back and forth; Drive motor, the output end of the drive motor is in transmission with the gear transmission mechanism; Before the aircraft takes off, the electromagnet is powered, the ferromagnetic material locking pin is extracted from the folding locking hole, the electromagnet is powered off, the drive motor drives the gear transmission mechanism and drives the folding arm to rotate to the first direction, when rotating to the position of the unfolding locking hole, the ferromagnetic material locking pin is inserted into the unfolding locking hole and locked; After the aircraft lands, the electromagnet is powered, the ferromagnetic material locking pin is extracted from the unfolding locking hole, the electromagnet is powered off, the drive motor drives the gear transmission mechanism and drives the folding arm to rotate to the reverse direction of the first direction, when rotating to the position of the folding locking hole, the ferromagnetic material locking pin is inserted into the folding locking hole and unlocked.

2. The self-locking device of the folding arm of the aircraft according to claim 1, wherein the gear transmission mechanism comprises a driving gear and a driven gear which are externally meshed with each other, and the output end of the drive motor is fixedly connected with the driving gear; The driven gear is fixedly installed at one end of the folding arm, and the part of the outer periphery of the driven gear which is not meshed with the driving gear is provided with the unfolding locking hole and the folding locking hole.

3. The self-locking device of the folding arm of the aircraft according to claim 1, wherein the gear transmission mechanism comprises a first gear, a second gear and a third gear, the first gear is externally meshed with the second gear, and the second gear is externally meshed with the third gear; The third gear is fixedly installed at one end of the folding arm, the part of the outer periphery of the third gear which is not meshed with the second gear is provided with the unfolding locking hole and the folding locking hole, and the output end of the drive motor is fixedly connected with the first gear. The included angle between the unfolding locking hole and the folding locking hole is an acute angle. Further comprising a connector; 4. A self-locking device for a folding arm of an aircraft according to any one of claims 1 to 3, characterized in that, The connector comprises a folding arm connecting part and a fixed arm connecting part which are connected with each other; 5. The self-locking device of a folding arm of an aircraft according to claim 3, characterized in that, The third gear is fixedly installed on the folding arm connecting part, and the fixed arm connecting part is fixedly connected with the fixed arm of the aircraft.

6. The self-locking device of the folding arm of the aircraft according to claim 3, wherein the diameter of the third gear is greater than the diameter of the second gear, and the diameter of the second gear is greater than the diameter of the first gear. The locking structure further comprises a non-ferromagnetic material spring and a pressure sensor; The lower outer periphery of the ferromagnetic material locking pin is provided with an annular groove, one end of the non-ferromagnetic material spring is embedded in the annular groove, the other end of the non-ferromagnetic material spring is fixedly installed on the fixed arm of the aircraft, and the pressure sensor is fixedly installed between the other end of the non-ferromagnetic material spring and the fixed arm. ​ 7. The self-locking device of a folding arm of an aircraft according to claim 1, characterized in that, ​ ​ The electromagnet is fixedly installed on the fixed arm of the aircraft, and is located below the ferromagnetic locking pin; Before the aircraft takes off, the electromagnet is powered on, the ferromagnetic locking pin compresses the non-ferromagnetic spring, the ferromagnetic locking pin is extracted from the folding locking hole, the pressure sensor detects pressure, and the electromagnet is powered off; After the aircraft lands, the electromagnet is powered on, the ferromagnetic locking pin compresses the non-ferromagnetic spring, the ferromagnetic locking pin is extracted from the unfolding locking hole, the pressure sensor detects pressure, and the electromagnet is powered off.

8. The self-locking device of a folding arm of an aircraft according to claim 7, characterized in that, Further comprising a controller; The pressure sensor, the driving motor and the electromagnet are all signal-connected with the controller.

9. The self-locking device of a folding arm of an aircraft according to claim 8, characterized in that, Further comprising an angle sensor and an alarm device, the angle sensor and the alarm device are both signal-connected with the controller; The angle sensor and the alarm device are both fixedly installed on the folding arm, when the angle sensor detects that the rotation angle of the folding arm is 0 after the driving motor acts for a preset period of time, the alarm device issues a fault alarm indicating that the self-locking device is faulty.

10. An aircraft, characterized in that The folding arm is provided with the self-locking device as claimed in any one of claims 1-9.

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