A portable, telescoping folding aircraft

Abstract

The application relates to aircraft technology and aims to solve the problems that a rotating arm occupies a large space, is easy to cause damage to propeller blades, lacks a protective structure for other components of a unmanned aerial vehicle, and the protective structure increases wind resistance and affects normal flight of the unmanned aerial vehicle, in particular to a portable telescopic folding aircraft. The telescopic design between a rotating main arm and a rotating branch arm makes the rotating arm with installed propeller blades retractable and the occupying space reduced, the propeller blades are stored in the inner side of a storage groove, the possibility of collision with objects is reduced, the possibility of damage to the propeller blades is reduced, the traction spring buffers the impact force when the protective frame is impacted, the damage to the protective frame and the propeller blades caused by the impact force is reduced, the buffer spring buffers the impact force on the adjusting rod and the support frame, the damage to the unmanned aerial vehicle caused by the impact force is reduced, and the protective structure composed of the adjusting rod, the electrified spring and the support frame can be retracted to reduce wind resistance.

Description

TECHNICAL FIELD

[0001] The present application relates to aircraft technology, in particular to a portable telescopic folding aircraft. BACKGROUND

[0002] An unmanned aircraft, commonly known as a "drone", is a pilotless aircraft that is controlled by radio control equipment and self-programmed control devices, or is completely or intermittently operated by an on-board computer;

[0003] In the prior art, the connection between the propeller blades of the unmanned aerial vehicle and the unmanned aerial vehicle is mostly fixed connection, and the propeller blades are directly exposed to the external environment, occupying a large space, and when carrying the unmanned aerial vehicle, the propeller blades are more likely to collide with other objects in the external environment, causing damage to the propeller blades, and when flying, the damaged propeller blades cannot provide normal driving force for the unmanned aerial vehicle, affecting the normal use of the unmanned aerial vehicle. The patent with application number "CN202110173888.9" sets up a protective frame to protect the propeller blades to prevent damage to the unmanned aerial vehicle caused by collision. The protective frame is only installed by sleeving, and is easy to deviate in direction when encountering external forces, reducing the protection effect of the propeller blades. The protective frame occupies a large space and is not convenient to fold and store, and the rotating arm after storage does not have a fixing structure and is easy to expand again, which is not convenient to carry.

[0004] In view of the above technical problems, the present application provides a solution. SUMMARY

[0005] The purpose of the present application is to make the rotating arm with installed propeller blades retractable to reduce the occupied space, the propeller blades are stored inside the storage slot, reducing the possibility of collision with objects, reducing the possibility of damage to the propeller blades, buffering the impact force on the protective frame when the protective frame is impacted by the traction spring, reducing the damage to the protective frame and the propeller blades caused by the impact force, buffering the force acting on the adjusting rod and the support frame by the buffer spring, reducing the damage to the unmanned aerial vehicle caused by the force, and the protective structure composed of the adjusting rod, the power spring and the support frame can be retracted to reduce the wind resistance. The problem of large space occupied by the rotating arm, easy damage to the propeller blades, no protective structure for other components of the unmanned aerial vehicle, and the problem of increasing wind resistance affecting the normal flight of the unmanned aerial vehicle are solved, and a portable telescopic folding aircraft is provided.

[0006] The purpose of the present application can be achieved by the following technical solutions:

[0007] The utility model provides a portable telescopic folding aircraft, including unmanned aerial vehicle, folding assembly, protection assembly and monitoring assembly are arranged on the unmanned aerial vehicle, folding assembly includes storage groove, the unmanned aerial vehicle two diagonal positions are all set up storage groove, the unmanned aerial vehicle four corner positions are all rotatably connected with rotating main arm, the rotating main arm is internally provided with sliding cavity no.

[0008] As a preferred embodiment of the utility model, the protection assembly includes a main protection frame, the rotating arm lower surface middle position is installed with the main protection frame, the main protection frame upper surface and lower surface are all installed with secondary protection frame, the main protection frame is close to the rotating arm one side and is provided with fixed hole, the main protection frame outer wall is close to the rotating arm one side and is installed with sliding frame on both sides.

[0009] As a preferred embodiment of the utility model, the two secondary protection frame outer wall is close to the main protection frame one side and is all provided with limiting sliding groove no., the two secondary protection frame outer wall corresponding limiting sliding groove no. one end position is all provided with limiting sliding groove two, limiting sliding groove two and limiting sliding groove no. are perpendicular, the main protection frame inside corresponding sliding frame position is provided with sliding cavity two, the sliding frame inside one end corresponding limiting sliding groove no. position is integrally formed with sliding block, the sliding frame outer wall is installed with limiting spring.

[0010] As a preferred embodiment of the utility model, the protection assembly further includes a support frame, the unmanned aerial vehicle lower surface both sides are installed with rotating seat, the rotating seat is in the shape of N, the rotating seat inside is rotatably connected with support frame through rotating shaft, the support frame outer wall both sides are provided with a group of adjusting barrels.

[0011] As a preferred embodiment of the present application, the adjusting cylinder comprises a cylinder body, an adjusting rod is slidably connected inside the cylinder body, a power supply box one is installed at one end of the cylinder body close to the support frame, a plurality of power supply boxes two are evenly distributed and installed on the outer wall of the cylinder body in six directions, a limiting block one is slidably connected to the inner wall of the cylinder body at a position corresponding to the power supply box two, a power-on spring one is installed inside the cylinder body through a mounting plate, one end of the power-on spring one is installed on the limiting plate, one end of the adjusting rod is installed on the limiting disc inside the cylinder body, grooves are formed on the outer side of the limiting disc at positions corresponding to the limiting block one, a buffer spring is installed on the outer wall of the limiting disc at a position corresponding to the limiting plate, and a power-on spring two is installed inside the power supply box two at a position corresponding to the limiting block one.

[0012] As a preferred embodiment of the present application, the monitoring assembly comprises a measurement module, a processing module and an execution module.

[0013] The measurement module detects the vertical height data between the unmanned aerial vehicle and the ground, the flight speed data of the unmanned aerial vehicle and the angle data between the flight direction and the vertical line, and transmits the detected vertical height data, flight speed data and angle data to the processing module.

[0014] The processing module processes the vertical height data, flight speed data and angle data transmitted from the measurement module, generates an alarm signal or a fall-prevention protection signal according to the processing result, and transmits the alarm signal or the fall-prevention protection signal to the execution module.

[0015] The data processing steps of the processing module are as follows:

[0016] Step one: the vertical height data transmitted by the measurement module is subjected to extreme value removal and average value calculation to obtain the vertical height average value at each collection time point, and coordinate points are plotted in a two-dimensional coordinate system with the collection time point and the vertical height average value as the x-axis and y-axis, adjacent coordinate points are connected, the slope of each line segment is calculated and counted to obtain the slope value L.

[0017] Step two: the absolute value of the slope value L is compared with the set slope value SL, the set slope value SL is the corresponding slope value in the two-dimensional coordinate system when the falling speed of the unmanned aerial vehicle reaches the dangerous value, if |L|>SL, it indicates that the falling speed of the unmanned aerial vehicle is too fast and danger is easy to occur, then the slope value L is compared with the set slope value SL, if L>SL, it indicates that the ascending speed of the unmanned aerial vehicle is too fast, an alarm signal is generated and transmitted to the execution module, and if L<SL, it indicates that the descending speed of the unmanned aerial vehicle is too fast, the vertical height distance is compared.

[0018] Step three: the vertical direction falling speed data is calculated according to the flight speed data and the included angle data, and the time T required for vertical falling to the ground is calculated, the time ST is set as the reaction time of the protection component opening when the unmanned aerial vehicle falls, if T> ST, it is determined that the opening of the protection component affects the flight of the unmanned aerial vehicle, and no operation is performed; when T = ST, a fall protection signal is generated, and the fall protection signal is transmitted to the executive module;

[0019] The executive module receives the warning signal or the fall protection signal transmitted by the processing module, and performs a buzzer warning or a protection execution operation according to the type of the received signal.

[0020] As a preferred embodiment of the application, the operation steps performed by the executive module are as follows:

[0021] Step one: after receiving the warning signal transmitted by the processing module, the executive module controls the buzzer warning;

[0022] Step two: after receiving the fall protection signal transmitted by the processing module, the executive module controls the unmanned aerial vehicle to rotate horizontally, so that the cylinder is thrown out under the action of centrifugal force, and then the limiting block one pops out to limit the mounting plate, stops the rotation operation of the unmanned aerial vehicle, and after the unmanned aerial vehicle is stable, the energized spring one is de-energized, so that the energized spring one quickly pops out, and the limiting block one at the other end clamps the limiting plate, so that the exposed length reaches the maximum, so that when the unmanned aerial vehicle collides, the adjusting rod can buffer the impact force under the action of the buffer spring, reducing the damage to the unmanned aerial vehicle.

[0023] Compared with the prior art, the application has the following advantages:

[0024] 1. The telescopic design between the rotating main arm and the rotating branch arm allows the rotating arm with the installed propeller blades to be retracted to reduce the occupied space, and after the rod is retracted, the rotating main arm is rotated to the inside of the storage slot, so that the rotating arm is completely stored in the storage slot, further reducing the occupied space of the rotating arm, the propeller blades are stored inside the storage slot, reducing the possibility of collision with other objects outside, reducing the possibility of damage to the propeller blades, and reducing the influence of propeller blade damage on the flight of the unmanned aerial vehicle;

[0025] 2. The traction spring buffers the impact force when the protection frame is impacted, reducing the damage to the protection frame and the propeller blades caused by the impact force, the buffer spring buffers the impact force on the adjusting rod and the support frame, reducing the damage to the unmanned aerial vehicle caused by the impact force, and the protection structure composed of the adjusting rod, the energized spring one and the support frame can be retracted to reduce wind resistance and prevent adverse effects on the flight of the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0026] For the convenience of those skilled in the art to understand, the present application will be further described below in conjunction with the drawings.

[0027] Figure 1 is the aircraft storage state structure diagram of the present application;

[0028] Figure 2 is the aircraft deployment state structure diagram of the present application;

[0029] Figure 3 is the storage state rotating arm structure diagram of the present application;

[0030] Figure 4 is the deployment state rotating arm structure diagram of the present application;

[0031] Figure 5 is the bottom structure diagram of the present application Figure 2 ;

[0032] Figure 6 is the A part enlarged structure diagram of the present application Figure 5 ;

[0033] Figure 7 is the inside structure diagram of the adjusting cylinder of the present application;

[0034] In the figure: 1, unmanned aerial vehicle; 2, propeller blade; 31, rotating main arm; 32, rotating arm; 33, storage slot; 34, adjusting frame; 35, limiting hole; 36, adjusting sliding slot; 4, protection assembly; 41, main protection frame; 42, support frame; 43, adjusting cylinder; 431, cylinder body; 432, limiting block one; 433, power supply box two; 434, power supply box one; 435, power-on spring one; 436, limiting plate; 437, groove; 438, adjusting rod; 44, secondary protection frame; 45, rotating seat; 46, fixed hole; 47, sliding frame. DETAILED DESCRIPTION

[0035] The technical solutions of the present application will be described below in conjunction with the embodiments, obviously, the described embodiments are only part of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the present application.

[0036] Embodiment 1:

[0037] Please refer to Figures 1-4As shown, a portable telescopic folding aircraft includes a unmanned aerial vehicle 1, the unmanned aerial vehicle 1 is provided with a folding assembly, a protection assembly 4 and a monitoring assembly, the folding assembly includes a storage groove 33, the storage groove 33 is provided at two diagonal positions of the unmanned aerial vehicle 1, the storage groove 33 is in a right angle shape, and the length and width of the two sides are the same, the unmanned aerial vehicle 1 is rotationally connected with a rotating main arm 31 at four corner positions, the rotating main arm 31 is provided with two insertion holes, the included angle between the two insertion holes and the rotating shaft of the rotating main arm 31 is 45 degrees, an elastic groove is formed in the inner upper surface of the storage groove 33, an insertion rod is installed in the elastic groove through a power spring, the insertion rod can be inserted into the insertion hole to limit the rotation of the rotating main arm 31 after the rotating main arm 31 is stored inward or unfolded outward, a sliding cavity one is formed in the rotating main arm 31, a rotating branch arm 32 is slidingly connected to the side of the sliding cavity one away from the rotating main arm 31, a traction spring is installed in the sliding cavity one corresponding to the position of the rotating branch arm 32, the traction spring is in a normal state when the rotating branch arm 32 is retracted in the sliding cavity one, and the traction spring is in a stretched state after the rotating branch arm 32 slides outward, a propeller blade 2 is rotationally connected to the upper surface of the rotating branch arm 32, two limiting holes 35 are formed in the upper surface of the rotating main arm 31 corresponding to the two sides of the sliding cavity one, an adjusting sliding groove 36 is formed in one side of the outer wall of the rotating main arm 31, an adjusting frame 34 is installed in the adjusting sliding groove 36, the adjusting frame 34 pulls the traction spring when sliding in the adjusting sliding groove 36, the limiting block two on the adjusting frame 34 is clamped in the limiting hole 35 to limit the adjusting frame 34 when sliding to the position of the limiting hole 35 on one side of the rotating main arm 31, and the limiting block two on the adjusting frame 34 is clamped in the limiting hole 35 to limit the adjusting frame 34 when sliding to the position of the limiting hole 35 on the other side of the rotating main arm 31, and the limiting block two is integrally formed on the upper surface of the adjusting frame 34 corresponding to the position of the limiting hole 35;

[0038] In the prior art, the connection between the propeller blade 2 of the unmanned aerial vehicle 1 and the unmanned aerial vehicle 1 is mostly fixed connection, the propeller blade 2 is directly exposed to the external environment, occupies a large space, and is easy to collide with other objects in the external environment when carrying the unmanned aerial vehicle 1, causing damage to the propeller blade 2, and the damaged propeller blade 2 cannot provide normal driving force for the unmanned aerial vehicle 1 during flight, affecting the normal use of the unmanned aerial vehicle 1;

[0039] When the unmanned aerial vehicle 1 is carried, the adjusting frame 34 is slid in the adjusting sliding groove 36 by pressing, and the sliding process causes the extrusion and contraction of the traction spring in the sliding cavity. During the movement of the adjusting frame 34, the downward pressing of the limiting block 2 at the position of the limiting hole 35 is required, so that the limiting block 2 does not affect the normal position movement of the adjusting frame 34. When the adjusting frame 34 moves inward, the rotating branch arm 32 is driven to slide into the rotating main arm 31. After the adjusting frame 34 moves inward to the inside of the other limiting hole 35 on the rotating main arm 31, the power supply spring 3 on the unmanned aerial vehicle 1 is controlled by the control button on the unmanned aerial vehicle 1 to supply power, so that the plug rod inserted into the rotating main arm 31 is driven to shrink into the inside of the elastic groove on the unmanned aerial vehicle 1 when the power supply spring 3 shrinks. After the rotating main arm 31 is rotated to the inside of the storage groove 33, the control button is pressed again to disconnect the power supply of the power supply spring 3. The plug rod is inserted into the other plug hole on the rotating main arm 31 under the driving of the rebounding power supply spring 3 to limit the position of the rotating main arm 31 again. Through the telescopic design between the rotating main arm 31 and the rotating branch arm 32, the rotating arm with the installed propeller blade 2 can be contracted and reduced to occupy the space. After the plug rod is contracted, the rotating main arm 31 is rotated to the inside of the storage groove 33, so that the rotating arm is completely stored in the inside of the storage groove 33, and the occupied space of the rotating arm is reduced again. The propeller blade 2 is stored in the inside of the storage groove 33, the possibility of collision with other objects in the outside is reduced, the possibility of damage to the propeller blade 2 is reduced, and the influence of the damage of the propeller blade 2 on the flight of the unmanned aerial vehicle 1 is reduced.

[0040] Example 2:

[0041] Please refer to Figures 1-7As shown, the protection assembly 4 comprises a main protection frame 41, which is installed at the middle position of the lower surface of the rotating support arm 32. The upper and lower surfaces of the main protection frame 41 are both provided with a secondary protection frame 44. The main protection frame 41 and the secondary protection frame 44 are both in T shape, and the end of the T shape is arc-shaped. The shape and size of the main protection frame 41 and the two secondary protection frames 44 are the same. A fixing hole 46 is formed on the side of the main protection frame 41 close to the rotating main arm 31. The main protection frame 41 can be fixed on the rotating support arm 32 through the fixing hole 46, so that the protection frame will not deviate from the position when subjected to external force. The two sides of the outer side wall of the main protection frame 41 close to the rotating support arm 32 are both provided with a sliding frame 47. Limiting sliding grooves one are formed on the outer side wall of the two secondary protection frames 44 close to the main protection frame 41. Limiting sliding grooves two are formed on the outer side wall of the two secondary protection frames 44 corresponding to the position of the limiting sliding grooves one. The limiting sliding grooves two are perpendicular to and communicate with the limiting sliding grooves one. A sliding cavity two is formed in the main protection frame 41 corresponding to the position of the sliding frame 47. A sliding block is integrally formed on the end of the sliding frame 47 in the sliding cavity two corresponding to the position of the limiting sliding groove one. When the secondary protection frame 44 rotates around one end of the main protection frame 41, the sliding blocks on the two sliding frames 47 in the main protection frame 41 slide in the limiting sliding grooves one. In the sliding process, the limiting springs connected to the sliding frames 47 are in a stretched state. The limiting springs are installed on the outer side wall of the sliding frame 47. The protection assembly 4 further comprises a support frame 42, which can support the unmanned aerial vehicle 1 when the unmanned aerial vehicle 1 lands. The two sides of the lower surface of the unmanned aerial vehicle 1 are provided with rotating seats 45, which are in the shape of a n. The lower surface of the unmanned aerial vehicle 1 is provided with a power spring four corresponding to the position of the support frame 42. When the power spring four is tightened, it drives the support frame 42 to rotate to a state parallel to the lower surface of the unmanned aerial vehicle 1. When the power spring four is expanded, it drives the support frame 42 to rotate to a state forming an obtuse angle with the lower surface of the unmanned aerial vehicle 1. The support frame 42 is rotatably connected to the rotating seat 45 through a rotating shaft. One group of adjusting barrels 43 is arranged on the outer side wall of the support frame 42;

[0042] In the prior art, the patent with the application number "CN202110173888.9" is provided to prevent damage to the unmanned aerial vehicle 1 caused by collision. The protection frame is used to protect the propeller blades 2. The protection frame is only installed by sleeving. When subjected to external force, it is easy to deviate from the direction, reducing the protection effect on the propeller blades 2. The protection frame occupies a large space and is not convenient to fold and store. Moreover, the rotating arm after storage is not provided with a fixing structure and is easy to be unfolded again, which is not convenient to carry.

[0043] The protection of the propeller blade 2 is composed of a main protection frame 41 and two secondary protection frames 44, when stored, the secondary protection frames 44 are retracted to completely coincide with the main protection frame 41, reducing the occupied space, when in use, the two secondary protection frames 44 are rotated to expand, during the expansion process, the sliding blocks on the sliding frame 47 inside the sliding cavities two on both sides of the main protection frame 41 slide inside the limiting sliding grooves one, after the secondary protection frames 44 are completely expanded, the sliding blocks on the sliding frame 47 slide inside the limiting sliding grooves one to the intersection position of the limiting sliding grooves one and the limiting sliding grooves two, under the pulling action of the limiting spring, the sliding blocks on the sliding frame 47 slide inside the limiting sliding grooves two, the limiting sliding grooves two are perpendicular to the limiting sliding grooves one, so that the sliding blocks on the sliding frame 47 are limited in position after sliding inside the limiting sliding grooves two, the positions of the two secondary protection frames 44 and the main protection frame 41 are limited, so that they will not deviate in position when subjected to external forces, so that the propeller blade 2 can be stably protected, the position of the main protection frame 41 is limited through the fixing hole 46, so that the main protection frame 41 will not deviate in position when subjected to external forces, the secondary protection frames 44 are opened inside the limiting sliding grooves two through the sliding blocks on the main protection frame 41, so that the positions of the secondary protection frames 44 and the main protection frame 41 are limited, so that they will not deviate in direction when subjected to external forces, improving the stability of the protection of the propeller blade 2.

[0044] The monitoring assembly comprises a measurement module, a processing module and an execution module;

[0045] The processing module performs extreme value removal and average value processing on the vertical height data transmitted by the measurement module, obtains the vertical height average value of each collection time point, and draws coordinate points in a two-coordinate system formed by the collection time point and the vertical height average value as the x-axis and y-axis, connects adjacent coordinate points, calculates and counts the slope of each line segment, and obtains the slope value;

[0046] The absolute value of the slope value L is compared with the set slope value SL, which is the corresponding slope value in the binary coordinate system when the falling speed of the UAV 1 reaches the dangerous value. If |L|>SL, it indicates that the falling speed of the UAV 1 is too fast and is prone to danger. Then the comparison between the slope value L and the set slope value SL is performed. If L>SL, it indicates that the rising speed of the UAV 1 is too fast, a warning signal is generated, and the warning signal is transmitted to the number execution module. If L<SL, it indicates that the falling speed of the UAV 1 is too fast, and the vertical height distance is compared. The number execution module detects the real-time speed data of the UAV 1, the number processing module calculates the speed average and the included angle in the vertical direction at the corresponding time point, and the falling speed data in the vertical direction is calculated according to the Pythagorean theorem. Through the calculation of the vertical distance average and the falling speed data in the vertical direction, the time T required for vertical falling to the ground is obtained. The set time ST is the reaction time of the protection assembly 4 when the UAV 1 falls. If T>ST, it is determined that the opening of the protection assembly 4 affects the flight of the UAV 1, and no operation is performed. When T=ST, a fall protection signal is generated, and the fall protection signal is transmitted to the number execution module.

[0047] The adjusting cylinder 43 comprises a cylinder body 431, an adjusting rod 438 is slidably connected inside the cylinder body 431, a power supply box one 434 is installed at one end of the cylinder body 431 close to the support frame 42, the power supply box one 434 supplies power to and controls the power-on spring one 435, a plurality of power supply boxes two 433 are uniformly distributed and installed in six directions on the outer side wall of the cylinder body 431, the power supply boxes two 433 supply power to and control the power-on spring two connected with the limiting block one 432, the power supply boxes two 433 on the same circle of the outer side wall of the cylinder body 431 are synchronously controlled and powered on and off, the limiting block one 432 is slidably connected at the position corresponding to the power supply box two 433 on the inner side wall of the cylinder body 431, the power-on spring one 435 is installed inside the cylinder body 431 close to one end of the support frame 42 through the mounting plate, one end of the power-on spring one 435 is connected to the mounting plate, and the other end is connected to the limiting plate 436, the mounting plate is installed at one end of the support frame 42 inside the cylinder body 431, the mounting plate has the same shape and size as the limiting plate 436, the support frame 42 and the cylinder body 431 keep a relative sliding state, the limiting plate 436 is installed at the end of the power-on spring one 435 away from the support frame 42, the limiting disc is installed at one end of the adjusting rod 438 inside the cylinder body 431, grooves 437 are formed at positions corresponding to the limiting block one 432 on the outer side of the limiting disc, buffer springs are installed on the side of the outer side wall of the limiting disc corresponding to the limiting plate 436, and power-on springs two are installed at positions corresponding to the limiting block one 432 inside the power supply box two 433.

[0048] In the prior art, when only the propeller blades 2 are protected and other parts of the unmanned aerial vehicle 1 are damaged, the normal use of the unmanned aerial vehicle 1 is still affected. The protection of other positions of the unmanned aerial vehicle 1 leads to an increase in the volume of the unmanned aerial vehicle 1, an increase in the wind resistance in the flight process, an increase in the power resources consumed by the unmanned aerial vehicle 1 for flying the same distance, an increase in the generated heat, and an easy overheating of the internal equipment of the unmanned aerial vehicle 1, which affects the service life of the unmanned aerial vehicle 1.

[0049] When the unmanned aerial vehicle 1 is flying, the measurement module positions the position of the limiting plate 436 and transmits the positioning data to the control module, so that the control module keeps the limiting block one 432 on one side of the limiting plate 436 protruding outward, and the remaining limiting block one 432 is retracted into the inside of the power supply box two 433 under the action of the energized spring two. The power supply box one 434 performs energization operation on the energized spring one 435, so that the energized spring one 435 is retracted. After the energized spring one 435 is retracted, the energized spring two inside the barrel 431 closest to the mounting plate side is de-energized, so that the limiting block one 432 is ejected and clamped on one side of the mounting plate under the action of the energized spring two. The mounting plate, the energized spring one 435 and the limiting plate 436 are clamped between the two adjacent limiting block one 432, reducing the length of the support frame 42 and the adjusting rod 438 exposed to the outside environment. The energized spring four is energized and tightened, so that the support frame 42 and the lower surface of the unmanned aerial vehicle 1 are kept in a horizontal state, reducing the wind resistance. When protecting the unmanned aerial vehicle 1, the energized spring one 435 is first energized, and then all the limiting block one 432 is retracted into the inside of the power supply box two 433. Then the unmanned aerial vehicle 1 is controlled to rotate horizontally, so that the barrel 431 is thrown out under the action of the centrifugal force in the rotating process. After the measurement module detects that the mounting plate is attached to the inner wall of one side of the barrel 431, the limiting block one 432 closest to the mounting plate position is ejected to limit the mounting plate. Then the energized spring one 435 is de-energized, so that the energized spring one 435 is quickly ejected. The time of the energized spring one 435 ejected to the other end and the time of the limiting block one 432 ejected are calculated. The limiting plate 436 is controlled to be clamped by the limiting block one 432 at the other end, that is, the distance between the limiting plate 436 and the mounting plate reaches the maximum, the distance between the support frame 42 and the adjusting rod 438 also reaches the maximum, and the exposed length also reaches the maximum. When the unmanned aerial vehicle 1 is impacted, the adjusting rod 438 can buffer the force generated by the impact under the action of the buffer spring, reducing the damage to the unmanned aerial vehicle 1.

[0050] The application is used, when the unmanned aerial vehicle 1 is flying, the position of the limiting plate 436 is positioned by the measurement module, and the positioning data is transmitted to the control module, so that the control module keeps the limiting block one 432 on one side of the limiting plate 436 protruding outward, and the rest of the limiting block one 432 is retracted into the inside of the power supply box two 433 under the action of the power spring two, the power supply box one 434 is powered on to the power spring one 435, so that the power spring one 435 is retracted, after the power spring one 435 is retracted, the power spring two closest to the inside of the cylinder 431 on the side of the mounting plate is powered off, so that the limiting block one 432 is ejected and clamped on the side of the mounting plate under the action of the power spring two, so that the mounting plate, the power spring one 435 and the limiting plate 436 are clamped between the two adjacent limiting block one 432, the length of the supporting frame 42 and the adjusting rod 438 exposed to the outside environment is reduced, the power spring four is powered on to tighten, so that the supporting frame 42 and the lower surface of the unmanned aerial vehicle 1 keep horizontal, and the wind resistance is reduced;

[0051] During the flight of the unmanned aerial vehicle 1, the monitoring assembly calculates and counts the slope of each line segment in a two-dimensional coordinate system formed by the average of the collection time point and the vertical height as the x-axis and the y-axis, and after comparison, the state of the unmanned aerial vehicle is determined, if the ascending speed of the unmanned aerial vehicle 1 is too fast, an alarm signal is generated, and a buzzer is sounded as a warning; if the descending speed of the unmanned aerial vehicle 1 is too fast, when the falling impact time T is equal to the reaction time ST, a fall protection signal is generated, and a protection operation is performed;

[0052] When the unmanned aerial vehicle 1 is protected, the power spring one 435 is powered on first, then all the limiting block one 432 is retracted into the inside of the power supply box two 433, then the unmanned aerial vehicle 1 is controlled to rotate horizontally, so that the cylinder 431 is thrown out under the action of centrifugal force during rotation, after the measurement module detects that the mounting plate is attached to the inner wall on one side of the cylinder 431, the limiting block one 432 closest to the mounting plate position is ejected to limit the mounting plate, then the power spring one 435 is powered off, so that the power spring one 435 is quickly ejected, and the time of the power spring one 435 ejected to the other end and the time of the limiting block one 432 ejected are calculated, the limiting plate 436 is controlled to be clamped by the limiting block one 432 on the other end, that is, the distance between the limiting plate 436 and the mounting plate reaches the maximum, the distance between the supporting frame 42 and the adjusting rod 438 also reaches the maximum, and the exposed length also reaches the maximum, so that when the unmanned aerial vehicle 1 is impacted, the adjusting rod 438 can buffer the force generated by the impact under the action of the buffer spring, reducing the damage to the unmanned aerial vehicle 1;

[0053] When the unmanned aerial vehicle 1 is carried, the adjusting frame 34 is slid in the adjusting sliding groove 36 by pressing, and the sliding process causes the extrusion and contraction of the traction spring in the sliding cavity, and during the movement of the adjusting frame 34, the downward pressing of the limiting block two at the position of the limiting hole 35 is required, so that the limiting block two does not affect the normal position movement of the adjusting frame 34, and when the adjusting frame 34 moves inward, the rotating branch arm 32 is driven to slide into the rotating main arm 31, and after the adjusting frame 34 moves inward to the inside of the other limiting hole 35 on the rotating main arm 31, the power supply spring three on the unmanned aerial vehicle 1 is controlled by the control button on the unmanned aerial vehicle 1, so that the plug rod inserted into the rotating main arm 31 is driven to shrink into the inside of the elastic groove of the unmanned aerial vehicle 1 when the power supply spring three shrinks, and then the rotating main arm 31 is rotated to the inside of the storage groove 33, and the control button is pressed again to disconnect the power supply of the power supply spring three, and the plug rod is inserted into the other plug hole on the rotating main arm 31 under the driving of the rebound power supply spring three to limit the position of the rotating main arm 31 again.

[0054] The preferred embodiments disclosed above are only used to help explain the present application. The preferred embodiments do not describe all the details and limit the present application to the specific embodiments. Obviously, according to the content of the present application, many modifications and changes can be made. The present application is selected and described in detail, in order to better explain the principles and practical application of the present application, so that those skilled in the art can well understand and utilize the present application. The present application is limited by the claims and their full scope and equivalents.

Claims

1. A portable, telescoping folding aircraft comprising a drone (1), characterized in that, The unmanned plane (1) is provided with a folding assembly, a protection assembly (4) and a monitoring assembly, the folding assembly comprises a storage groove (33), the unmanned plane (1) is provided with the storage groove (33) at two diagonal positions, the unmanned plane (1) is rotationally connected with a rotating main arm (31) at four corner positions, a sliding cavity one is formed in the rotating main arm (31), a rotating branch arm (32) is slidably connected to the side of the rotating main arm (31) away from the sliding cavity one, a traction spring is installed in the sliding cavity one corresponding to the position of the rotating branch arm (32), a propeller blade (2) is rotationally connected to the upper surface of the rotating branch arm (32), two limiting holes (35) are formed in the upper surface of the rotating main arm (31) corresponding to the two sides of the sliding cavity one, an adjusting sliding groove (36) is formed in the outer side wall of the rotating main arm (31), an adjusting frame (34) is installed in the sliding cavity one corresponding to the position of the adjusting sliding groove (36), and a limiting block two is integrally formed on the upper surface of the adjusting frame (34) corresponding to the position of the limiting hole (35). The protection assembly (4) further comprises a support frame (42), the lower surface of the unmanned plane (1) is provided with a rotating seat (45) on both sides, the rotating seat (45) is in the shape of a n, the support frame (42) is rotationally connected to the inner side of the rotating seat (45) through a rotating shaft, and the outer side wall of the support frame (42) is provided with a group of adjusting barrels (43) on both sides. The adjusting barrel (43) comprises a barrel body (431), an adjusting rod (438) is slidably connected in the barrel body (431), a power supply box one (434) is installed at one end of the barrel body (431) close to the support frame (42), a plurality of power supply boxes two (433) are evenly distributed and installed on the outer side wall of the barrel body (431) in six directions, a limiting block one (432) is slidably connected to the inner side wall of the barrel body (431) corresponding to the position of the power supply box two (433), a power-on spring one (435) is installed in the barrel body (431) through the mounting plate close to the support frame (42), a limiting plate (436) is installed at the end of the power-on spring one (435) away from the support frame (42), a limiting disc is installed at one end of the adjusting rod (438) in the barrel body (431), recesses (437) are formed in the outer side of the limiting disc corresponding to the positions of the limiting block one (432), a buffer spring is installed on the outer side wall of the limiting disc corresponding to the side of the limiting plate (436), and a power-on spring two is installed in the power supply box two (433) corresponding to the position of the limiting block one (432).

2. A portable, collapsible aircraft as in claim 1, wherein, The protection assembly (4) comprises a main protection frame (41), the main protection frame (41) is installed on the lower surface of the rotating branch arm (32) at the middle position, the upper surface and the lower surface of the main protection frame (41) are provided with a secondary protection frame (44), a fixing hole (46) is formed in the side of the main protection frame (41) close to the rotating main arm (31), and the two sides of the outer side wall of the main protection frame (41) close to the rotating branch arm (32) are provided with a sliding frame (47).

3. A portable, collapsible aircraft as in claim 2, wherein: Two outer side walls of the secondary protection frame (44) are provided with a limiting sliding groove one on one side close to the main protection frame (41), and the other end of the limiting sliding groove one is provided with a limiting sliding groove two corresponding to the limiting sliding groove one, and the limiting sliding groove two is perpendicular to the limiting sliding groove one, the main protection frame (41) is provided with a sliding cavity two corresponding to the sliding frame (47) inside, and the sliding frame (47) is integrally formed with a sliding block at one end inside the sliding cavity two corresponding to the limiting sliding groove one, and the sliding frame (47) is provided with a limiting spring outside the wall.

4. A portable, collapsible aircraft as in claim 1, wherein, The monitoring assembly comprises a measurement module, a processing module and an execution module; The measurement module detects vertical height data between the unmanned aerial vehicle (1) and the ground, flight speed data of the unmanned aerial vehicle (1) and angle data between the flight direction and the vertical line, and transmits the detected vertical height data, flight speed data and angle data to the processing module; The processing module processes the vertical height data, flight speed data and angle data transmitted by the measurement module, generates an alarm signal or a fall protection signal according to the processing result, and transmits the alarm signal or the fall protection signal to the execution module; The data processing steps of the processing module are as follows: Step one: the vertical height data transmitted by the measurement module is processed by removing extreme values and averaging, the vertical height average of each collection time point is obtained, and the coordinate points are drawn in the two-coordinate system formed by the collection time point and the vertical height average as the x-axis and y-axis, the adjacent coordinate points are connected, the slope of each line segment is calculated and counted, and the slope value L is obtained; Step two: compare the absolute value of the slope value L with the set slope value SL, the set slope value SL is the corresponding slope value in the two-coordinate system when the falling speed of the unmanned aerial vehicle (1) reaches the dangerous value, if |L|>SL, it indicates that the falling speed of the unmanned aerial vehicle (1) is too fast and is easy to be dangerous, compare the slope value L with the set slope value SL, if L>SL, it indicates that the rising speed of the unmanned aerial vehicle (1) is too fast, an alarm signal is generated, and the alarm signal is transmitted to the execution module; L<SL, it indicates that the falling speed of the unmanned aerial vehicle (1) is too fast, and the vertical height distance is compared; Step three: the processing module calculates the falling speed data in the vertical direction according to the flight speed data and the angle data, and calculates the time T required for vertical falling to the ground, the set time ST is the reaction time when the protection assembly is opened when the unmanned aerial vehicle (1) falls, if T>ST, it is determined that the opening of the protection assembly affects the flight of the unmanned aerial vehicle (1), and no operation is performed; when T=ST, a fall protection signal is generated, and the fall protection signal is transmitted to the execution module; The execution module receives the alarm signal or the fall protection signal transmitted by the processing module, and performs a buzzer warning or a protection operation according to the type of the received signal.

5. A portable, collapsible aircraft as in claim 4, wherein, The operation steps performed by the execution module are as follows: Step one: the execution module controls the buzzer warning after receiving the alarm signal transmitted by the processing module; Step two: the number of modules in receiving the number of modules passed anti-drop protection signal, control unmanned aerial vehicle (1) horizontal rotation, so that the cylinder (431) under the action of centrifugal force to the outside, and then through the limit block one (432) pop-up installation plate limiting, stop the rotation of unmanned aerial vehicle (1) operation, after the unmanned aerial vehicle (1) stable again to the power spring one (435) power operation, make the power spring one (435) pop out, and use the other end of the limit block one (432) will limit the plate (436) stuck, so that the exposed length to the maximum, when the unmanned aerial vehicle (1) impact, adjusting rod (438) under the action of the buffer spring can produce the force of impact buffering, reduce the damage to the unmanned aerial vehicle (1).

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