A remote-controlled aircraft with a crash protection structure

Abstract

This invention relates to a remote-controlled aircraft with a crash protection structure. The fuselage includes a cavity housing a crash protection component, which is located within the fuselage and communicates with a component cavity. A parachute outlet, communicating with the cavity, is located at the tail end of the fuselage. An electromagnetic opening and closing mechanism includes an electromagnet and an armature. A connector at one end of a connecting rod is detachably connected to the electromagnetic opening and closing mechanism. The other end of the connecting rod is connected to a parachute, which covers the connecting rod and is displaced into the parachute storage cavity through the outlet. This invention utilizes a connecting rod within the fuselage, with the parachute connected to its end. The other end of the connecting rod is secured by the engagement of the electromagnet and the armature. The electromagnet is powered by a power source. When the power source fails to provide power, the electromagnet disengages from the armature, releasing its grip on the connecting rod, allowing the parachute to deploy. This enables the remote-controlled aircraft to descend slowly under the deceleration of the parachute, reducing the descent force and preventing damage.

Description

Technical Field

[0001] This invention belongs to the field of toy remote control aircraft technology, specifically relating to a remote control aircraft with a crash protection structure. Background Technology

[0002] With the increasing variety of toys, remote-controlled airplanes have become a popular toy for all ages. They use built-in batteries to power motors that drive the propellers, allowing them to fly in the sky with high thrust and the balancing effect of the wings.

[0003] Because the propeller needs to rotate rapidly to generate sufficient thrust to power the remote-controlled aircraft for takeoff, this high-speed propeller drive consumes a lot of electrical energy. If the battery inside the remote-controlled aircraft is too large, it will be too heavy, resulting in insufficient lift and making it difficult to take off. If the battery is too small, it will result in insufficient driving force and range, making it difficult to play for a long time. Therefore, in order to enable the remote-controlled aircraft to take off smoothly, on the one hand, the fuselage has been made lighter. By reducing the weight of the fuselage, the excess load can be used to increase the battery capacity, thereby maximizing the power and range of the remote-controlled aircraft.

[0004] However, lightweight remote-controlled aircraft and batteries that can run out of power at any time can cause them to lose power and crash in the air when the power is insufficient or even cut off. Once a remote-controlled aircraft loses power and crashes, there is no way to provide power again; one can only watch it accelerate downwards. Under such a falling force, its lightweight fuselage cannot withstand the impact. Once it is hit, it will be severely damaged or even unusable. Although current program control can reduce power output and slow down the descent when the battery is low, it is still impossible to completely prevent remote-controlled aircraft from crashing due to low power or losing power completely and crashing. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a remote-controlled aircraft with a crash protection structure. A connecting rod is installed inside the fuselage, with a parachute connected to one end. The other end of the connecting rod is fixed by an electromagnet and an armature. The electromagnet is powered by a power source. When the power source fails to provide power, the electromagnet disengages from the armature, releasing its grip on the connecting rod. This allows the aircraft to disengage from the connecting rod and deploy the parachute, enabling the remote-controlled aircraft to descend slowly under the deceleration of the parachute, reducing the descent force and preventing damage.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] A remote-controlled aircraft with a crash protection structure includes a fuselage, a motor-driven propeller mounted on the fuselage, symmetrical wings on the left and right sides of the fuselage, a tail fin at the tail end of the fuselage, a component cavity inside the fuselage containing a circuit board and a power supply, the circuit board being electrically connected to the motor and the power supply respectively, and a crash protection assembly including a parachute, a connecting rod, an electromagnetic opening and closing device, and a receiving cavity.

[0008] The receiving cavity is located inside the fuselage and is connected to the component cavity. The tail end of the fuselage is provided with an umbrella outlet that is connected to the receiving cavity. The limiting part provided inside the receiving cavity divides the receiving cavity into a movable cavity and an umbrella storage cavity.

[0009] The electromagnetic opening and closing component is located inside the component cavity and electrically connected to the power supply. One end of the connecting rod has a connector, which is detachably connected inside the electromagnetic opening and closing component. The connection between the connector and the connecting rod can abut against the limiting part. The other end of the connecting rod is connected to the parachute. The parachute covers the connecting rod and is inserted into the parachute storage cavity through the parachute outlet along with the connecting rod. The connector is located inside the movable cavity and is movably connected between the electromagnetic opening and closing component and the limiting part. The electromagnetic opening and closing component includes an electromagnet and an armature. The electromagnet is fixedly connected inside the component cavity and electrically connected to the power supply. The armature is located inside the component cavity and can abut against the electromagnet. Both the electromagnet and the armature are provided with limiting semi-cylinders. When the electromagnet and the armature abut against each other, the two sets of limiting semi-cylinders abut against each other and form a limiting cylinder. The openings at both ends of the limiting cylinder are chamfered. The connecting rod is fitted inside the limiting cylinder, and the connection between the connecting head and the connecting rod abuts against the chamfer. The electromagnetic opening and closing component also includes two sets of first screws. The machine body is provided with two sets of first screw holes that connect to the element cavity. The armature is provided with two sets of first through holes that are symmetrical about the limiting half cylinder. The electromagnet is provided with two sets of second screw holes that are symmetrical about the limiting half cylinder. The first screws are screwed into the first screw holes, pass through the first through holes, and then screwed into the second screw holes from bottom to top. The armature is movably connected to the first screws through the first through holes. The two sets of first screws approach the limiting half cylinder but do not communicate with it. The first screws are made of insulating material. The lower opening edge of the first through hole is provided with a downwardly extending fitting part, and the upper opening edge of the first screw hole is provided with a fitting hole. The fitting part fits into the fitting hole.

[0010] The fall arrestor also includes a switch button and a contact piece. The body has a switch hole connecting to the component cavity. The switch button is formed by a pressing part, a movable column, a limiting platform, a connecting column, a clamping part, and a metal plate connected sequentially from bottom to top. The limiting platform and the pressing part surround the switch hole vertically and are engaged within the switch hole via the movable column. The clamping part is a C-shaped structure formed by connecting an upper clamping plate and a lower clamping plate, which together form a fixed cavity. The side opening of the fixed cavity is an elastic opening. The connector is engaged within the fixed cavity. The metal plate is connected to the upper end of the upper clamping plate. The contact piece is disposed within the component cavity and is receptively connected to the metal plate. The contact piece is electrically connected to the circuit board. The elastic opening is an inwardly constricted structure formed by the ends of the upper and lower clamping plates approaching each other. The fixed cavity has a straight groove shape, with the upper and lower clamping plates facing the fixed cavity. The inner wall of the cavity is provided with grooves, and the outer contour of the connector fits into the grooves; the contact piece includes two sets, which are located at the upper end of the metal plate and are respectively connected to the metal plate; during the left and right lateral movement of the pressing part, the connector moves from the groove near the bottom of the fixed cavity to the groove near the elastic opening, and the metal piece abuts against the first set of contact pieces; during the continued lateral movement of the pressing part, the connector moves out of the elastic opening after being squeezed out, and the metal piece abuts against the second set of contact pieces; the switch hole is a T-shaped hole structure composed of a horizontal hole and a vertical hole, and the pressing part passes through the horizontal hole and is fitted into the vertical hole through the movable column. The body is also provided with a third screw hole communicating with the horizontal hole. The anti-fall component also includes a second screw, which is screwed into the third screw hole from the outside to the inside and abuts against the switch button in the horizontal hole.

[0011] Furthermore, the limiting part is provided with a second through hole that extends laterally. The diameter of the second through hole is larger than the diameter of the outer contour of the connector. Both the front and rear openings of the second through hole are chamfered. The body is also provided with a fourth screw hole that communicates with the second through hole. The fall arrestor assembly also includes a third screw. The third screw is screwed into the fourth screw hole from the outside to the inside and then extends into the second through hole. The end of the third screw is connected to the connecting rod in abutment. The body is also provided with a fourth through hole that communicates with the parachute chamber. The fourth through hole is inclined along the front end of the body towards the rear end of the body. A circular plate is provided at the connection between the connecting rod and the parachute. The circular plate opens / closes the parachute outlet during the lateral displacement of the connecting rod. The parachute can be covered by the circular plate.

[0012] Furthermore, the power source is a battery, which is electrically connected to and supplies power to the circuit board, the motor, and the electromagnet.

[0013] Furthermore, the power source includes a battery and a magnet generator. The battery is electrically connected to and supplies power to the circuit board and the motor. The magnet generator is disposed between the motor and the propeller and is electrically connected to an electromagnet. The magnet generator supplies power to the electromagnet during the rotation of the propeller.

[0014] Compared with the prior art, the advantages of the present invention are as follows:

[0015] 1. If the electromagnet's electrical energy is obtained from a power source, then when the remote-controlled aircraft loses power or shuts down in the air, the electromagnet will stop generating magnetism and maintain its attraction to the armature, thereby detaching from the attraction to the connecting rod. The un-clamped connecting rod will move towards the tail end of the fuselage, thereby deploying the parachute at the end of the connecting rod, thus slowing down the descent speed of the remote-controlled aircraft and preventing it from being damaged during the high-speed descent.

[0016] 2. The clamping part holds the connector in three states. When the pressing part is displaced in the first stage, the connector is still clamped in the groove of the fixing cavity. However, the entire remote control aircraft has completed the initial power-on of the motor, which causes the electromagnet to generate magnetism and attract the armature, thus clamping the connecting rod. After the pressing part is displaced in the second stage, the connector is squeezed out of the elastic opening, which makes the connector loosen the fixation. At this time, the remote control aircraft can take off normally for fun. Once the aircraft loses power and crashes, the armature can be released in time to open the parachute for slow descent.

[0017] 3. After deploying the parachute and recovering the remote-controlled aircraft, the parachute can be wrapped around the connecting rod, and the connecting rod can be reinserted into the receiving cavity. Push the connector to open the fixing cavity and fix the connector in the groove.

[0018] 4. After using the remote control airplane, turn off the switch button so that the clamping part re-clamps the connector, but the electromagnet still attracts the armature, keeping the connecting rod fixed. Push the pressing part again, and the metal piece will disengage from the contact piece, thus completely cutting off the power. Release the electromagnet from the armature, but the clamping part still keeps the connector fixed, thus ensuring that the parachute will not open by itself when the remote control airplane is not in use. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a perspective view of the parachute in the deployed state of the present invention;

[0021] Figure 2 This is a top view of the parachute in the deployed state according to the present invention;

[0022] Figure 3 For the present invention Figure 2 AA section view;

[0023] Figure 4 For the present invention Figure 3 A magnified view of section B;

[0024] Figure 5 This is a top view of the parachute in its retracted state according to the present invention;

[0025] Figure 6 For the present invention Figure 5 CC section view;

[0026] Figure 7 For the present invention Figure 6 A magnified view of a portion of point P;

[0027] Figure 8 For the present invention Figure 5 JJ sectional view;

[0028] Figure 9 For the present invention Figure 5 KK sectional view;

[0029] Figure 10 This is a bottom-view explosion diagram of the present invention;

[0030] Figure 11 For the present invention Figure 10 A magnified view of a portion at point D;

[0031] Figure 12 For the present invention Figure 10 A magnified view of a portion at point E;

[0032] Figure 13 For the present invention Figure 10 A magnified view of a portion at point F;

[0033] Figure 14 This is a top-view explosion diagram of the present invention;

[0034] Figure 15 For the present invention Figure 14 A magnified view of a portion of point G;

[0035] Figure 16 This is a perspective cross-sectional view of the lower half of the fuselage of the present invention and a schematic diagram of the first positional relationship.

[0036] Figure 17 This is a schematic diagram of the second positional relationship and displacement direction of the present invention;

[0037] Figure 18 This is a schematic diagram of the third positional relationship and displacement direction of the present invention.

[0038] The components include: 1. Fuselage; 11. Motor; 12. Propeller; 13. Component cavity; 131. Circuit board; 132. Power supply; 133. Magnet generator; 14. Parachute outlet; 15. First screw hole; 151. Fitting hole; 16. Switch hole; 161. Horizontal hole; 162. Vertical hole; 163. Third screw hole; 17. Fourth screw hole; 18. Fourth through hole; 2. Fall arrestor assembly; 21. Parachute; 22. Connecting rod; 221. Connector; 222. Circular plate; 23. Electromagnetic opening and closing component; 231. Electromagnet; 2311. Second screw hole; 232. Armature; 2321. First 2322. Through hole; 233. Fitting part; 234. Limiting half cylinder; 235. Limiting cylinder; 236. First screw; 24. Receiving cavity; 241. Limiting part; 242. Movable cavity; 243. Storage cavity; 244. Second through hole; 25. Switch button; 251. Pressing part; 252. Movable column; 253. Limiting platform; 254. Connecting column; 255. Clamping part; 2551. Upper clamping plate; 2552. Lower clamping plate; 2553. Fixed cavity; 2554. Elastic opening; 2555. Groove; 256. Metal plate; 26. Contact piece; 27. Second screw; 28. Third screw. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this invention.

[0040] The specific embodiments of the present invention will now be described with reference to the accompanying drawings:

[0041] like Figure 1-18 As shown in Embodiment 1, a remote-controlled aircraft with a crash protection structure includes a fuselage 1, a propeller 12 driven by a motor 11 on the fuselage 1, symmetrical wings on the left and right sides of the fuselage 1, a tail fin at the tail end of the fuselage 1, a component cavity 13 inside the fuselage 1, a circuit board 131 and a power supply 132 inside the component cavity 13, the circuit board 131 being electrically connected to the motor 11 and the power supply 132 respectively, and a crash protection assembly 2, which includes a parachute 21, a connecting rod 22, an electromagnetic opening and closing element 23 and a receiving cavity 24;

[0042] The receiving cavity 24 is disposed inside the fuselage 1 and connected to the component cavity 13. The tail end of the fuselage 1 is provided with an umbrella outlet 14 connected to the receiving cavity 24. The limiting part 241 provided inside the receiving cavity 24 divides the receiving cavity 24 into a movable cavity 242 and an umbrella storage cavity 243.

[0043] The electromagnetic opening and closing component 23 is located inside the component cavity 13 and electrically connected to the power supply 132. One end of the connecting rod 22 is provided with a connector 221, which is detachably connected to the electromagnetic opening and closing component 23. The connection between the connector 221 and the connecting rod 22 can abut against the limiting part 241. The other end of the connecting rod 22 is connected to the parachute 21. The parachute 21 covers the connecting rod 22 and is disposed from the parachute outlet 14 into the parachute storage cavity 243 along with the connecting rod 22. The connector 221 is located inside the movable cavity 242 and is movably connected to the electromagnetic opening and closing component. Between component 23 and limiting part 241; the electromagnetic opening and closing component 23 includes an electromagnet 231 and an armature 232. The electromagnet 231 is fixedly connected inside the component cavity 13 and electrically connected to the power supply 132. The armature 232 is located inside the component cavity 13 and is in contact with the electromagnet 231. Both the electromagnet 231 and the armature 232 are provided with limiting semi-cylinders 233. When the electromagnet 231 and the armature 232 abut against each other, the two sets of limiting semi-cylinders 233 abut against each other and form a limiting cylinder 234. The openings at both ends of the limiting cylinder 234 are chamfered. The connecting rod 22 is fitted inside the limiting cylinder 234, and the connection between the connecting head 221 and the connecting rod 22 abuts against the chamfer; the electromagnetic opening and closing component 23 also includes two sets of first screws 235, the body 1 is provided with two sets of first screw holes 15 connecting the element cavity 13, the armature 232 is provided with two sets of first through holes 2321 symmetrical about the limiting half cylinder 233 as the center of symmetry, the electromagnet 231 is provided with two sets of second screw holes 2311 symmetrical about the limiting half cylinder 233 as the center of symmetry, and the first screws 235 are screwed sequentially from bottom to top to the first The screw hole 15 passes through the first through hole 2321 and is screwed onto the second screw hole 2311. The armature 232 is movably connected to the first screw 235 through the first through hole 2321. The two sets of first screws 235 approach the limiting half cylinder 233 but do not communicate with the limiting half cylinder 233. The first screw 235 is made of insulating material. The lower opening edge of the first through hole 2321 is provided with a downwardly extending fitting part 2322. The upper opening edge of the first screw hole 15 is provided with a fitting hole 151. The fitting part 2322 fits into the fitting hole 151.

[0044] The fall arrestor assembly 2 also includes a switch button 25 and a contact piece 26. The body 1 has a switch hole 16 connecting to the component cavity 13. The switch button 25 is formed by a pressing part 251, a movable column 252, a limiting platform 253, a connecting column 254, a clamping part 255, and a metal plate 256 connected sequentially from bottom to top. The limiting platform 253 and the pressing part 251 are vertically enclosed on the switch hole 16 and are engaged within the switch hole 16 by the movable column 252. The clamping part 255 is a C-shaped structure formed by connecting an upper clamping plate 2551 and a lower clamping plate 2552. A fixed cavity 2553 is formed by the enclosure of 52. The side opening of the fixed cavity 2553 is an elastic opening 2554. The connector 221 is fitted inside the fixed cavity 2553. The metal plate 256 is connected to the upper end of the upper clamping plate 2551. The contact piece 26 is disposed in the component cavity 13 and is in contact with the metal plate 256. The contact piece 26 is electrically connected to the circuit board 131. The elastic opening 2554 is an inwardly narrowing structure formed by the ends of the upper clamping plate 2551 and the lower clamping plate 2552 approaching each other. The fixed cavity 2553 has a straight groove shape. The upper clamping plate 2551 and the lower clamping plate 2552 form a straight groove shape. The inner wall of plate 2552 facing the fixing cavity 2553 is provided with grooves 2555, and the outer contour of the connector 221 fits into the grooves 2555; the contact pieces 26 include two sets, the two sets of contact pieces 26 are located at the upper end of the metal plate 256 and are respectively abuttingly connected to the metal plate 256; during the left and right lateral movement of the pressing part 251, the connector 221 moves from the groove 2555 near the bottom of the fixing cavity 2553 to the groove 2555 near the elastic opening 2554, and the metal piece abuts against the first set of contact pieces 26; the pressing part 251 continues to move laterally... During the process, the connector 221 is displaced outside the elastic opening 2554 after being extruded from the elastic opening 2554, and the metal sheet abuts against the second set of contact pieces 26; the switch hole 16 is a T-shaped hole structure composed of a horizontal hole 161 and a vertical hole 162, and the pressing part 251 passes through the horizontal hole 161 and is fitted into the vertical hole 162 through the movable column 252. The body 1 is also provided with a third screw hole 163 communicating with the horizontal hole 161. The anti-fall component 2 also includes a second screw 27, which is screwed into the third screw hole 163 from the outside to the inside and abuts against the switch button 25 in the horizontal hole 161.

[0045] Furthermore, the limiting part 241 is provided with a second through hole 244 that extends laterally. The diameter of the second through hole 244 is larger than the diameter of the outer contour of the connector 221. Both the front and rear openings of the second through hole 244 are chamfered. The body 1 is also provided with a fourth screw hole 17 that communicates with the second through hole 244. The fall arrestor 2 also includes a third screw 28. The third screw 28 is screwed into the fourth screw hole 17 from the outside to the inside and then extends into the second through hole 244. The end of the third screw 28 is connected to the connecting rod 22 in abutment. The body 1 is also provided with a fourth through hole 18 that communicates with the parachute storage cavity 243. The fourth through hole 18 is inclined along the front end of the body 1 towards the rear end of the body 1. A circular plate 222 is provided at the connection between the connecting rod 22 and the parachute 21. The circular plate 222 opens / closes the parachute outlet 14 during the lateral displacement of the connecting rod 22. The parachute 21 can be covered by the circular plate 222.

[0046] Furthermore, the power source 132 is a battery, which is electrically connected to and supplies power to the circuit board 131, the motor 11 and the electromagnet 231 respectively.

[0047] Furthermore, the power source 132 includes a battery and a magnet generator 133. The battery is electrically connected to and supplies power to the circuit board 131 and the motor 11. The magnet generator 133 is disposed between the motor 11 and the propeller 12. The magnet generator 133 is electrically connected to the electromagnet 231. The magnet generator 133 supplies power to the electromagnet 231 during the rotation of the propeller 12.

[0048] Description of the working principle of this invention:

[0049] The remote-controlled aircraft with a crash protection structure using this design must first meet its own flight requirements. Therefore, a propeller 12 driven by a motor 11 is installed on the fuselage 1, and the wings on both sides are used for balance. At the same time, a tail fin is installed at the tail of the fuselage 1. Power is supplied by the power supply 132 in the component cavity 13 inside the fuselage 1, and the circuit board 131 provides the control program. When the propeller 12 rotates and lifts the remote-controlled aircraft into the air, the flight trajectory of the remote-controlled aircraft can be changed by adjusting the guide plates on the wings and tail fin. The propeller 12 can be set on the nose or on the fuselage 1 and point backward, which can provide power for the flight of the remote-controlled aircraft. This structure is existing technology, so the take-off method and structure of the remote-controlled aircraft will not be described in detail here.

[0050] To slow the descent of the remote-controlled aircraft in the event of a power loss, thus preventing damage from a high-speed impact, a receiving cavity 24 communicating with the component cavity 13 is provided inside the fuselage 1. The connecting rod 22 extends into the receiving cavity 24 and is embedded in the electromagnetic opening and closing component 23 inside the component cavity 13 through the connector 221 at its end. The electromagnetic opening and closing component 23 is electrically connected to the power supply 132, and the other end of the connecting rod 22 is connected to the parachute 21. Therefore, when the electromagnetic opening and closing component 23 is energized, it engages with the connector 221, thereby fixing the connecting rod 22. When the power supply 132 of the remote-controlled aircraft is depleted or disconnected, the electromagnetic opening and closing component 23 disengages from the connector 221, thereby releasing the connecting rod 22 and allowing the parachute 21 to extend from the tail end of the fuselage 1 and deploy in the air.

[0051] However, without a structure to restrain the connecting rod 22 within the receiving cavity 24, the connecting rod 22 would fall directly out from the umbrella outlet 14, losing its deceleration and descent function. Therefore, a limiting part 241 is added within the receiving cavity 24, dividing the receiving cavity 24 into a movable cavity 242 and an umbrella storage cavity 243. The function of the limiting part 241 is to prevent the connecting head 221 from crossing the limiting part 241 and entering the umbrella storage cavity 243. Therefore, under the action of the limiting part 241, the connecting head 221 can only move within the movable cavity 242 between the electromagnetic opening and closing member 23 and the limiting part 241, while the connecting rod 22... When the connector 221 abuts against the limiting part 241, the end of the connecting rod 22 extends out of the parachute opening 14 and smoothly deploys the parachute 21 in the air, pulling the fuselage 1, thereby slowing down the descent speed of the remote-controlled aircraft. After the remote-controlled aircraft is recovered, the parachute 21 is wrapped around the connecting rod 22 and inserted into the parachute storage cavity 243. During the displacement of the connecting rod 22, the connector 221 also moves into the electromagnetic opening and closing part 23, which is in a disconnected state due to lack of power. Recharging the remote-controlled aircraft again can maintain the engagement of the connector 221 until the next flight.

[0052] To achieve the engagement and clamping of the electromagnetic opening / closing component 23 with the connector 221, an opening and closing mechanism is achieved through a combination of electromagnet 231 and armature 232. Electromagnet 231 generates magnetism by being energized, thereby attracting armature 232. Electromagnet 231 and armature 232 are existing technologies, so their principles of energization-based attraction and de-energization-based disconnection will not be elaborated upon here. Both electromagnet 231 and armature 232 are equipped with limiting semi-cylinders 233. When electromagnet 231 is energized and attracts armature 232, they abut against each other. The two sets of limiting semi-cylinders 233 combine to form a limiting cylinder 234. The limiting cylinder 234 cooperates with the connecting rod 22. Therefore, when electromagnet 231 is energized, it can attract and clamp armature 232 to the connecting rod 22. The chamfer on the limiting cylinder 234 is used to abut against the connection point of connector 221 and connecting rod 22, thus fixing the position of connector 221.

[0053] Since the two sets of limiting half-cylinders 233 can only form a complete limiting cylinder 234 by abutting each other without any misalignment, it is difficult to guarantee that the armature 232 attracted by the electromagnet 231, which has no position restriction, can form a complete limiting cylinder 234 by abutting each other. In order to limit the displacement direction of the armature 232 and to fix the position of the electromagnet 231, a first screw 235 is added. The first screw 235 is screwed into the first screw hole 15 on the machine body 1 from bottom to top, then passes through the first through hole 2321 on the armature 232, and finally screwed into the second screw hole 2311 on the electromagnet 231, thereby fixing the electromagnet 231 and restricting the armature 232 to move up and down only on the first screw 235.

[0054] The first screw 235 includes two sets, which are symmetrical about the left and right with the limiting sleeve 234 as the center of symmetry. Therefore, after the two sets of first screws 235 are screwed together, the position of the electromagnet 231 can be fixed. In addition to screwing the first screw 235 into the first screw hole 15, the first screw hole 15 can also be changed to a through hole. The first screw 235 passes through the through hole and is screwed into the second screw hole 2311. The lower end of the first screw 235 is fixed in position by means of external pressure cap, welding, adhesive, etc., which can also keep the electromagnet 231 relatively fixed.

[0055] Since the two sets of first screws 235 are screwed into the first screw hole 15 and the second screw hole 2311 for connection, the left and right twisting of the electromagnet 231 alone cannot loosen the screw connection of the first screw 235. Therefore, the structure is relatively stable. However, since there is an armature 232 that can move up and down in the middle of the first screw 235, the electromagnet 231 will still twist left and right without any other restraint. In order to avoid this situation, a downwardly extending fitting part 2322 is provided at the lower end opening edge of the first through hole 2321, and a fitting hole 151 is provided at the upper end opening edge of the first screw hole 15. The fitting part 2322 fits into the fitting hole 151. Therefore, the armature 232 is restricted by the fitting hole 151 on the fitting part 2322 during the up and down movement, and its displacement direction can be better restricted. Moreover, the left and right twisting of the electromagnet 231 can be reduced.

[0056] When the electromagnet 231 is not energized, the connecting rod 22 and the armature 232 will fall to the bottom due to gravity. When the electromagnet 231 is energized, it will re-attract the armature 232, thereby pulling the armature 232 upward. If the connecting rod 22 does not enter the limiting half-cylinder 233 during its fall, but falls onto the upper surface of the armature 232, the armature 232 will clamp the connecting rod 22 between the armature 232 and the electromagnet 231 when it moves upward, thus losing the clamping function of the limiting half-cylinder 233. Therefore, the first screw 235 that is close to the limiting half-cylinder 233 can prevent the connecting rod 22 from falling onto the upper surface of the armature 232, ensuring that the connecting rod 22 is always inside the limiting half-cylinder 233. The first screw 235 that is not connected to the limiting half-cylinder 233 can avoid abutting the connecting rod 22 inside the limiting half-cylinder 233.

[0057] In addition, it is important that the first screw 235 is made of insulating material. Since the electromagnet 231 generates magnetism when energized, if the first screw 235 is made of iron, it will also generate magnetism when the electromagnet 231 is energized. After the power is turned off, there may be residual magnetism, which will cause the armature 232 to remain attracted and not fall off on its own. Therefore, using an insulating material for the first screw 235 can effectively avoid this problem.

[0058] If the connecting rod 22 is held in place solely by the attraction between the electromagnet 231 and the armature 232, then it needs to be kept energized throughout the entire process. However, when the remote-controlled aircraft is not in use, it will definitely be in a de-energized state. Once the power is cut off, the holding force on the connecting rod 22 will be lost, causing the connector 221 to lose its limit and move freely in the movable cavity 242. The parachute 21 will also fall out as a result, causing the connecting rod 22 to need to be repositioned for the next time the aircraft is used.

[0059] To avoid this situation, a switch button 25 and a contact piece 26 are added. The switch button 25 is fitted into the switch hole 16 through the limiting platform 253 and the pressing part 251. The clamping part 255 on the connecting post 254 clamps the connector 221 in the fixing cavity 2553 enclosed between the upper clamping plate 2551 and the lower clamping plate 2552. The distance between the upper clamping plate 2551 and the lower clamping plate 2552 is slightly smaller than the outer diameter of the connector 221. However, the groove 2555 in the upper clamping plate 2551 and the lower clamping plate 2552 is the same size as the outer diameter of the connector 221. Therefore, the connector 221 can be fixed after being embedded in the groove 2555.

[0060] Both the upper clamping plate 2551 and the lower clamping plate 2552 of the clamping part 255 are deformable plastics. The positional relationship between the clamping part 255 and the connector 221 is one of three types: one is the groove 2555 close to the bottom of the fixing cavity 2553, such as... Figure 16As shown; the second is the groove 2555 that is close to the elastic opening 2554, as shown. Figure 17 As shown; thirdly, after being extruded from the elastic opening 2554, it is displaced outside the elastic opening 2554, as shown. Figure 18 As shown, the first two positional relationships can fix the connector 221, while the third positional relationship can loosen the fixation of the connector 221.

[0061] When the connector 221 approaches the groove 2555 at the bottom of the fixed cavity 2553, the metal piece does not contact any of the contact pieces 26, and is therefore in a de-energized state. At this time, the electromagnet 231 is not energized and therefore does not attract the armature 232. When the pressing part 251 is pressed and moved laterally, the connector 221 moves from the groove 2555 at the bottom of the fixed cavity 2553 to the groove 2555 at the elastic opening 2554. At this time, the metal piece contacts the first set of contact pieces 26, and initial energization is achieved. In addition to the motor 11, the electromagnet 231, the lights on the fuselage 1, the circuit board 131, the barometer, and other electronic devices are energized first. At this time, the remote-controlled aircraft has no power and cannot take off. The energized electromagnet 231... The armature 232 is initially attracted, thus engaging the connecting rod 22 and fixing it in place. As the pressing part 251 continues to move laterally, the upper clamping plate 2551 and the lower clamping plate 2552 are pushed by the connecting head 221. After the connecting head 221 is squeezed out of the elastic opening 2554, it moves outside the elastic opening 2554, releasing the fixation on the connecting head 221. The metal sheet abuts against the second set of contact pieces 26, thereby starting the motor 11, causing the propeller 12 to rotate and generate power, thus enabling remote control aircraft operation. At this time, the connecting head 221 has been released from its fixed position. When the remote control aircraft crashes due to power failure, the attraction of the electromagnet 231 to the armature 232 is released, and the parachute 21 can be quickly opened for a slow descent.

[0062] When the recovered remote-controlled aircraft is held in hand, first press the pressing part 251 to restore the power-off position 132. Then, cover the parachute 21 onto the connecting rod 22, insert the connecting rod 22 and the parachute 21 into the parachute storage cavity 243, and press the connector 221 against and through the fixing cavity 2553, embedding it into the groove 2555 to fix the connector 221. If the aircraft lands normally, press the pressing part 251 and move it horizontally. At the same time, the motor 11 is initially turned off, and the connector 221 passes through the elastic opening 2554 and enters the fixing cavity 2553, where it is held by the groove 2555. Continue to move the pressing part 251 horizontally to completely cut off the power, releasing the electromagnet 231 from the armature 232, thereby releasing the clamp on the connecting rod 22. Ideally, the connecting rod 22 is made of high-strength steel. Even if it is attracted by the electromagnet 231 and becomes residually magnetized, its lateral displacement will not be affected when there is no magnetic force after the electromagnet 231 is de-energized. The top of the connector 221 is a pointed structure, and the axes of the fixing cavity 2553, the limiting cylinder 234 and the limiting part 241 are coincident. Therefore, when the connecting rod 22 is pushed, it can be inserted and fixed into the groove 2555 in the direction of the coincident axis. Moreover, when the electromagnet 231 releases its grip on the connecting rod 22, the connecting rod 22 can also move without much resistance.

[0063] The switch hole 16 is configured as a T-shaped hole structure formed by connecting the horizontal hole 161 and the vertical hole 162. The pressing part 251 can be rotated after passing through the horizontal hole 161, thereby embedding the movable column 252 into the vertical hole 162, so that the movable column 252 can move laterally along the direction of the vertical hole 162. In order to prevent the movable column 252 from falling out of the horizontal hole 161 and causing the switch button 25 to malfunction, a third screw hole 163 is provided on the body 1. By screwing in the second screw 27 and abutting against the switch button 25, the movable column 252 is prevented from re-entering the horizontal hole 161, thus ensuring the normal operation of the switch button 25.

[0064] Because the connecting rod 22 exerts a great force when it displaces and abuts the connector 221 against the limiting part 241 to deploy the parachute 21, the connecting rod 22 needs to be replaced after wear and tear. If the hole in the limiting part 241 is smaller than the connector 221, this part will also suffer continuous wear. Once the wear is severe, subsequent replacement will involve replacing the fuselage 1, which will drastically increase the cost. Therefore, a second through hole 244 is provided in the limiting part 241, and the diameter of the second through hole 244 is larger than the diameter of the outer contour of the connector 221. Therefore, without obstruction, the connector 221 can pass smoothly through the second through hole 244. In order to prevent the connector 221 from passing through the second through hole 244, a fourth screw hole 17 connected to the second through hole 244 is added to the body 1. By screwing in the third screw 28, a gap is left between the end of the third screw 28 and the second through hole 244, which is only wide enough for the connector 22 to pass through. Therefore, even if the connector 221 hits the third screw 28, the third screw 28, a very low-cost replacement part, can be replaced periodically, reducing subsequent material costs.

[0065] Since the deployment of the parachute 21 is achieved by releasing the clamps of the connector 221 and the connecting rod 22, leaving the connecting rod 22 in a free-clamped state, but the parachute 21 is wrapped around the connecting rod 22 and stored in the parachute storage cavity 243, although the connecting rod 22 is not clamped, there is a lack of external force to actively push the connecting rod 22 and the parachute 21 to move. Although an external force could be added by adding a spring, this would increase the number of structures and parts required to achieve this function. In order to achieve the effect of external force propulsion with minimal cost and optimal effect, a fourth passage communicating with the parachute storage cavity 243 is provided on the fuselage 1. The fourth through hole 18 is inclined along the front end of the fuselage 1 towards the rear end of the fuselage 1. Therefore, during the flight or descent of the remote-controlled aircraft, wind pressure is generated around the fuselage 1 towards the rear end of the fuselage 1. The wind pressure flows into the parachute storage cavity 243 along the fourth through hole 18, pushing the parachute 21 towards the exit 14, thus providing the conditions for external force. In the daily flight of the remote-controlled aircraft, the connecting rod 22 is clamped and fixed. Even with the wind pressure flowing into the fourth through hole 18, the connecting rod 22 will not be forcibly displaced. The function of the fourth through hole 18 is to play an auxiliary role when the parachute 21 needs to be deployed.

[0066] To enhance the auxiliary effect of the fourth through hole 18, a circular plate 222 is installed at the connection between the connecting rod 22 and the parachute 21. When the parachute 21 is covered, the circular plate 222 is enclosed inside. When the parachute 21 needs to be deployed, the wind enters through the fourth through hole 18 and flows through the gap between the circular plate 222 and the parachute outlet 14. Due to the narrow gap, the wind speed is increased, so the parachute 21 can be deployed in an extreme time, thus slowing down the descent speed of the remote-controlled aircraft in advance. At the same time, the circular plate 222 can provide some decorative effect at the parachute outlet 14.

[0067] The power supply 132 uses a battery to power the circuit board 131, motor 11 and electromagnet 231. When the battery is depleted or disconnected, the electromagnet 231 is de-energized, thereby releasing the clamp on the connecting rod 22 and deploying the parachute 21.

[0068] Example 2 differs from Example 1 in that the power supply 132 includes a battery and a magnet generator 133. The power supply 132 powers the circuit board 131 and the motor 11. The magnet generator 133 is positioned between the motor 11 and the propeller 12. During the rotation of the propeller 12, with the propeller's rotating shaft as the rotor and the magnet generator 133 encased outside the rotating shaft as the stator, the propeller 12 can cut magnetic field lines, generating current to power the electromagnet 231. This arrangement ensures that, despite the high power consumption of the motor 11 and the battery's potential failure to power it after depletion, the remaining electrical energy can still power the electromagnet 231. Powering the electromagnet 231 would prevent it from being de-energized in time, thus failing to deploy the parachute 21 to prevent the remote-controlled aircraft from crashing. However, if the power supply for the electromagnet 231 is provided by the rotation of the propeller 12, the criterion for determining whether the electromagnet 231 is disconnected becomes whether the propeller 12 is rotating. When the aircraft runs out of power in the air and the propeller 12 stops rotating, the electromagnet 231 is de-energized in an instant, releasing the connecting rod 22 and injecting wind pressure through the fourth through hole 18. The parachute 21 will then deploy in a very short time. Even if the aircraft falls and drives the propeller 12 to reverse and generate electricity, it will no longer be able to attract the armature 232 through the electromagnet 231 and hold the connecting rod 22. Therefore, the judgment effect will be better.

[0069] The beneficial effects of this invention are as follows:

[0070] 1. The electromagnet 231 obtains its electrical energy from the power source 132. When the remote control aircraft loses power or shuts down in the air, the electromagnet 231 will no longer generate magnetism and will maintain its attraction to the armature 232. This will cause it to break away from the attraction to the connecting rod 22. The un-clamped connecting rod 22 will move towards the tail end of the fuselage 1, thereby deploying the parachute 21 at the end of the connecting rod 22. This will slow down the descent speed of the remote control aircraft and prevent the remote control aircraft from being damaged during the high-speed descent.

[0071] 2. The electromagnet 231 can also obtain electrical energy through the rotation of the propeller 12. The rotating shaft of the propeller 12 is used as the rotor, and the magnet generator 133 covering the outside of the rotating shaft is used as the stator. Therefore, the propeller 12 can cut magnetic field lines during rotation, thereby generating current to power the electromagnet 231. This allows for better power failure judgment and timely deployment of the parachute 21.

[0072] 3. The clamping part 255 clamps the connector 221 in three states. When the pressing part 251 is displaced in the first stage, the connector 221 is still clamped in the groove 2555 of the fixing cavity 2553. However, the entire remote control aircraft has completed the initial power-on except for the motor 11, which causes the electromagnet 231 to generate magnetism and attract the armature 232, clamping the connecting rod 22. After the pressing part 251 is displaced in the second stage, the connector 221 is squeezed out of the elastic opening 2554, so that the connector 221 is released from the fixation. At this time, the remote control aircraft can take off normally for fun. Once the aircraft loses power and crashes, the armature 232 can be released in time to open the parachute 21 for slow descent.

[0073] 4. After deploying the parachute 21 and recovering the remote-controlled aircraft, the parachute 21 can be wrapped around the connecting rod 22, and the connecting rod 22 can be reinserted into the receiving cavity 24. The connector 221 is pushed to open the fixing cavity 2553, and the connector 221 is fixed in the groove 2555.

[0074] 5. After using the remote control airplane, turn off the switch button 25, so that the clamping part 255 re-clamps the connector 221, but the electromagnet 231 still attracts the armature 232, keeping the connecting rod 22 fixed. Push the pressing part 251 again, and the metal piece disengages from the contact piece 26, thus completely cutting off the power. Release the electromagnet 231 from the armature 232, but the clamping part 255 still keeps the connector 221 fixed, thus ensuring that the parachute 21 will not open by itself when the remote control airplane is not in use.

[0075] 6. Electromagnet 231 is electrically connected to battery or magnet generator 133 to determine whether the power is low or cut off. All structures for the deployment and retraction of parachute 21 are mechanical structures. Compared with program control, mechanical structures have better operational stability.

[0076] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A remote control aircraft with anti-falling protection structure, comprising a fuselage, a motor-driven propeller is arranged on the fuselage, the left and right sides of the fuselage are provided with mutually symmetrical wings, the tail end of the fuselage is provided with a tail wing, an element cavity is arranged in the fuselage, a circuit board and a power supply are arranged in the element cavity, the circuit board is electrically connected with the motor and the power supply respectively, characterized in that: The anti-falling assembly comprises a parachute, a connecting rod, an electromagnetic opening and closing element and a containing cavity; ​ The containing cavity is arranged in the fuselage and communicates with the element cavity, the tail end of the fuselage is provided with a parachute outlet communicating with the containing cavity, and a limiting part is arranged in the containing cavity to divide the containing cavity into an active cavity and a parachute storage cavity. The electromagnetic opening and closing element is located in the element cavity and electrically connected with the power supply, one end of the connecting rod is provided with a connecting head which is detachably connected in the electromagnetic opening and closing element, the connecting head and the connecting rod are abuttingly connected on the limiting part, the other end of the connecting rod is connected with the parachute, the parachute is wrapped on the connecting rod and is placed into the parachute storage cavity from the parachute outlet, the connecting head is located in the active cavity and is movably connected between the electromagnetic opening and closing element and the limiting part. The electromagnetic opening and closing element comprises an electromagnet and an armature, the electromagnet is fixedly connected in the element cavity and electrically connected with the power supply, the armature is located in the element cavity and abuttingly connected with the electromagnet, limiting half cylinders are arranged on the electromagnet and the armature, when the electromagnet and the armature abut against each other, the two groups of limiting half cylinders abut against each other and form a limiting cylinder, chamfers are arranged at the front and rear ends of the limiting cylinder, the connecting rod is matched in the limiting cylinder, and the connecting head and the connecting rod are abuttingly connected on the chamfers.

2. The remote control aircraft having a crash protection structure according to claim 1, characterized in that: The electromagnetic opening and closing element further comprises two groups of first screw rods, the fuselage is provided with two groups of first screw holes communicating with the element cavity, the armature is provided with two groups of first through holes which are left-right symmetrical with the limiting half cylinder as the center of symmetry, the electromagnet is provided with two groups of second screw holes which are left-right symmetrical with the limiting half cylinder as the center of symmetry, the first screw rods are sequentially screwed into the first screw holes, pass through the first through holes and are screwed into the second screw holes, the armature is movably connected on the first screw rods through the first through holes, the two groups of first screw rods are close to the limiting half cylinder but do not communicate with the limiting half cylinder, and the first screw rods are made of insulating materials.

3. The remote control aircraft having a crash protection structure according to claim 2, characterized in that: The edge of the lower end opening of the first through hole is provided with a downward extending fitting part, and the edge of the upper end opening of the first screw hole is provided with a fitting hole, and the fitting part is matched in the fitting hole.

4. The RC aircraft with crash protection according to claim 3, characterized in that: The anti-falling assembly further comprises a switch button and a contact sheet, the fuselage is provided with a switch hole communicating with the element cavity, the switch button is sequentially connected by a pressing part, a movable column, a limiting table, a connecting column, a clamping part and a metal plate from bottom to top, the limiting table and the pressing part are enclosed on the switch hole and matched in the switch hole through the movable column, the clamping part is a C-shaped structure connected by an upper clamping plate and a lower clamping plate, the upper clamping plate and the lower clamping plate enclose a fixed cavity, the side opening of the fixed cavity is an elastic opening, the connecting head is matched in the fixed cavity, the metal plate is connected to the upper end of the upper clamping plate, the contact sheet is arranged in the element cavity and abuttingly connected with the metal plate, and the contact sheet is electrically connected with the circuit board.

5. The RC aircraft with crash protection according to claim 4, characterized in that: The elastic mouth is a structure of inwardly tapering formed by the mutual approaching of the ends of the upper and lower clamping plates, the fixing cavity is in the shape of a straight slot, the upper and lower clamping plates are each provided with a groove on the inner side wall facing the fixing cavity, and the outer contour of the connecting head is fitted in the groove; the contact pieces include two groups, and the two groups of contact pieces are located at the upper end of the metal plate and are respectively in abutting connection with the metal plate; in the process of horizontal movement of the pressing part, the connecting head is displaced from the groove near the bottom of the fixing cavity to the groove near the elastic mouth, the metal plate is in abutting connection with the first group of contact pieces; in the process of continued horizontal movement of the pressing part, the connecting head is displaced to the outside of the elastic mouth after being extruded out of the elastic mouth, and the metal plate is in abutting connection with the second group of contact pieces.

6. The RC aircraft with crash protection according to claim 5, characterized in that: The switch hole is a T-shaped hole structure composed of a horizontal hole and a vertical hole, the pressing part is embedded in the vertical hole through the horizontal hole, the machine body is further provided with a third screw hole in communication with the horizontal hole, and the anti-falling assembly further includes a second screw rod, which is screwed into the third screw hole from the outside to the inside and is in abutting connection with the switch button in the horizontal hole.

7. The RC aircraft with crash protection according to claim 6, characterized in that: The limiting part is provided with a second through hole penetrating in the transverse direction, the diameter of the second through hole is greater than the diameter of the outer contour of the connecting head, chamfers are arranged at the front and rear openings of the second through hole, the machine body is further provided with a fourth screw hole in communication with the second through hole, the anti-falling assembly further includes a third screw rod, which is screwed into the fourth screw hole from the outside to the inside and extends into the second through hole, and the end of the third screw rod is in abutting connection with the connecting rod; The machine body is further provided with a fourth through hole in communication with the storage cavity, the fourth through hole is arranged obliquely along the direction from the front end of the machine body to the tail end of the machine body, the connecting rod is provided with a circular plate at the connection position with the parachute, the circular plate opens / closes the ejection opening in the process of horizontal displacement of the connecting rod, and the parachute can be wrapped on the circular plate.

8. The RC aircraft with crash protection according to claim 7, characterized in that: The power supply is a battery, and the battery is electrically connected with the circuit board, the motor and the electromagnet and supplies power for them.

9. The RC aircraft with crash protection according to claim 7, characterized in that: The power supply includes a battery and a magnet generator, the battery is electrically connected with the circuit board and the motor and supplies power for them, the magnet generator is arranged between the motor and the propeller, the magnet generator is electrically connected with the electromagnet, and the magnet generator supplies power for the electromagnet in the rotation of the propeller.

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