A protective device for a drone

Abstract

This invention discloses a protective device for unmanned aerial vehicles (UAVs), specifically relating to the field of UAV technology. It includes a fuselage protection mechanism 1 and a propeller protection mechanism 2. The fuselage protection mechanism comprises an H-shaped frame with staggered through-grooves on both sides. Fixed shafts are welded to the interior of each end of the staggered through-grooves. An upper protective arm and a lower protective arm are respectively mounted on the two fixed shafts within the same staggered through-grooves. The upper protective arm has an arc-shaped cross-section, and an upper rotating hole is provided at the end of the upper protective arm closest to the H-shaped frame. By incorporating the fuselage protection mechanism and the propeller protection mechanism, this invention can promptly detect whether the UAV is in a state of accidental fall and activate the protective structure in a timely manner. Upon impact with the ground, it effectively protects the UAV's propeller and fuselage, thus ensuring the UAV's flight safety.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a protective device for UAVs. Background Technology

[0002] Drones are devices that perform aerial operations through remote control or automatic flight systems. They are widely used in fields such as aerial photography, surveying, inspection, agriculture, and rescue. During flight, drones may lose control and crash if they encounter situations such as insufficient battery power, signal interruption, strong wind interference, mechanical failure, sensor malfunction, operational errors, or bird strikes. In addition, complex flight environments, exceeding load limits, or failure to conduct sufficient checks can also increase the risk of crashes.

[0003] Therefore, there is an urgent need for a protective device for drones to solve the above problems. Summary of the Invention

[0004] To overcome the aforementioned deficiencies of the prior art, embodiments of the present invention provide a protective device for unmanned aerial vehicles (UAVs). By incorporating a fuselage protection mechanism and a propeller protection mechanism, the present invention can promptly detect whether the UAV is in an accidental crash state and promptly activate the protective structure. Upon crashing to the ground, it effectively protects the UAV's propeller and fuselage, thereby effectively ensuring the flight safety of the UAV and solving the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a protective device for unmanned aerial vehicles (UAVs), comprising a fuselage protection mechanism 1 and a propeller protection mechanism 2; The fuselage protection mechanism includes an H-shaped frame with staggered through slots on both sides. Fixed shafts are welded to the inside of both ends of each staggered through slot. An upper protective arm and a lower protective arm are respectively mounted on the two fixed shafts within the same staggered through slot. The upper protective arm has an arc-shaped cross-section. An upper rotating hole is provided through the end of the upper protective arm near the H-shaped frame, and an upper insertion hole is provided at the top of the upper protective arm. An upper spring is welded to the outer wall of the bottom end of the upper protective arm on the side away from the H-shaped slot. An upper fall protection electric actuator is provided at the bottom of the top of the upper protective arm. The lower protective arm also has an arc-shaped cross-section. A lower rotating hole is provided through the end of the lower protective arm near the H-shaped frame, and a lower insertion hole is provided at the bottom of the lower protective arm. A lower spring is welded to the outer wall of the top end of the lower protective arm on the side away from the H-shaped slot. A lower fall protection electric actuator is provided at the top of the bottom of the lower protective arm. The lower fall protection electric actuator outputs... A top rod is fixedly installed at both the shaft end and the output shaft end of the upper fall protection electric actuator. A protective spring is welded to the end of the top rod away from the H-shaped frame. A connecting seat is welded to the end of the protective spring away from the H-shaped frame. An insert rod is welded to the side of the connecting seat away from the H-shaped frame. Two transmission rods are welded to the outer wall of the H-shaped frame near the top rod. The two transmission rods are symmetrically arranged on the H-shaped frame at corresponding positions. A protective ejection electric actuator is installed at the end of the transmission rod away from the H-shaped frame. The input ends of the lower fall protection electric actuator, the upper fall protection electric actuator, and the protective ejection electric actuator are connected to the same protection controller. The protection controller is a microcontroller. A barometer, a gyroscope, an accelerometer, a GPS locator, and a power supply unit are connected to the input end of the protection controller. The propeller protection mechanism includes a connecting core, and a plurality of first protective arc frames are welded to the outside of the connecting core. A second protective arc frame is provided on one side of each first protective arc frame. Each second protective arc frame is welded to the outside of the connecting core. The plurality of second protective arc frames are evenly distributed in a ring on the outside of the connecting core, and the plurality of first protective arc frames are evenly distributed in a ring on the outside of the connecting core. The barometer is used to detect changes in the drone's altitude and transmits the detection results to the protection controller for processing. The accelerometer is used to measure the linear acceleration of the UAV in three axes, as well as to sense the direction of gravity, and transmit the detection results to the protection controller for processing. The gyroscope is used to measure the angular velocity of the UAV around three axes and transmits the detection results to the protection controller for processing. The GPS locator is used to detect the drone's position, horizontal speed, and vertical speed information, and transmits the detection results to the protection controller for processing.

[0006] In a preferred embodiment, a fixed shaft located at the top of the H-shaped frame passes through the upper rotating hole at the corresponding position, and the upper protective arm is rotatably connected to the fixed shaft at the corresponding position through the upper rotating hole.

[0007] In a preferred embodiment, the width of the upper spring piece is adapted to the width of the misaligned through groove, and the thickness of the upper protective arm is adapted to the width of the misaligned through groove.

[0008] In a preferred embodiment, a fixed shaft located at the bottom of the H-shaped frame passes through a lower rotating hole at a corresponding position, and the lower protective arm is rotatably connected to the fixed shaft at the corresponding position through the lower rotating hole.

[0009] In a preferred embodiment, the width of the lower spring piece is adapted to the width of the misaligned through groove, and the thickness of the lower protective arm is adapted to the width of the misaligned through groove.

[0010] In a preferred embodiment, the output shafts of the fall protection electric actuator and the upper fall protection electric actuator are respectively connected to the corresponding push rods via transmission.

[0011] In a preferred embodiment, the lower insertion hole and the upper insertion hole are collinear with the corresponding insertion rod, and the size of the lower insertion hole and the upper insertion hole matches that of the corresponding insertion rod.

[0012] In a preferred embodiment, the transmission rod is fixedly installed at the end of the output shaft of the protective ejector electric push rod at a corresponding position, and the transmission rod is drivingly connected to the output shaft of the protective ejector electric push rod.

[0013] The technical effects and advantages of this invention are as follows: This invention, by incorporating a fuselage protection mechanism and a propeller protection mechanism, enables it to promptly detect whether a drone is in an accidental crash state and to activate the protective structure in a timely manner. This effectively protects the drone's propeller and fuselage upon impact with the ground, thus ensuring the drone's flight safety. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0015] Figure 2 This is a three-dimensional structural diagram of the connecting core of the present invention.

[0016] Figure 3 This is a schematic diagram of the three-dimensional structure of the push rod of the present invention.

[0017] Figure 4 This is a schematic diagram of the three-dimensional structure of the H-shaped frame of the present invention.

[0018] Figure 5 This is a schematic diagram of the three-dimensional structure of the upper spring sheet of the present invention.

[0019] Figure 6 This is a three-dimensional structural diagram of the upper protective arm of the present invention.

[0020] Figure 7 This is a three-dimensional structural diagram of the lower protective arm of the present invention.

[0021] Figure 8 This is a three-dimensional structural diagram of the fixed shaft of the present invention.

[0022] Figure 9 This is a schematic diagram of the system of the present invention.

[0023] The attached figures are labeled as follows: 1. Fuselage protection mechanism; 101. H-shaped frame; 102. Misaligned through groove; 103. Fixed shaft; 104. Upper protective arm; 105. Upper rotating hole; 106. Upper insertion hole; 107. Upper spring piece; 108. Upper fall protection electric actuator; 109. Lower protective arm; 110. Lower rotating hole; 111. Lower insertion hole; 112. Lower spring piece; 113. Lower fall protection electric actuator; 114. Top rod. ; 115. Protective spring; 116. Connecting seat; 117. Insert rod; 118. Transmission rod; 119. Protective ejector electric push rod; 120. GPS locator; 121. Accelerometer; 122. Gyroscope; 123. Barometer; 124. Protection controller; 125. Power supply unit; 2. Propeller protection mechanism; 201. Connecting core; 202. First protective arc frame; 203. Second protective arc frame. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] As attached Figure 1 Appendix Figure 2 Appendix Figure 3 Appendix Figure 4 Appendix Figure 5 Appendix Figure 6 Appendix Figure 7 Appendix Figure 8 and attached Figure 9 As shown, the present invention provides a protective device for a drone, including a fuselage protection mechanism 1 and a propeller protection mechanism 2; The fuselage protection mechanism 1 includes an H-shaped frame 101. Both sides of the H-shaped frame 101 are provided with staggered through grooves 102. Fixed shafts 103 are welded to the inside of both ends of each staggered through groove 102. An upper protective arm 104 and a lower protective arm 109 are respectively provided on the two fixed shafts 103 within the same staggered through groove 102. The upper protective arm 104 has an arc-shaped cross-section. An upper rotating hole 105 is provided through the end of the upper protective arm 104 closest to the H-shaped frame 101. An upper insertion hole 106 is provided through the top of the upper protective arm 104. An upper spring piece 107 is welded to the outer wall of the bottom end of the upper protective arm 104 away from the H-shaped groove 101. 4. An upper fall protection electric actuator 108 is provided at the top and bottom. The lower protective arm 109 has an arc-shaped cross-section. A lower rotation hole 110 is provided through the end of the lower protective arm 109 near the H-shaped frame 101. A lower insertion hole 111 is provided through the bottom end of the lower protective arm 109. A lower spring piece 112 is welded to the outer wall of the side of the lower protective arm 109 away from the H-shaped groove 101. A lower fall protection electric actuator 113 is provided at the top of the bottom end of the lower protective arm 109. A top rod 114 is fixedly installed at the output shaft end of the lower fall protection electric actuator 113 and the output shaft end of the upper fall protection electric actuator 108. A protective spring is welded to the end of the top rod 114 away from the H-shaped frame 101. A protective spring 115 is provided with a connecting seat 116 welded to one end away from the H-shaped frame 101. A plug rod 117 is welded to the side of the connecting seat 116 away from the H-shaped frame 101. Two transmission rods 118 are welded to the outer wall of the H-shaped frame 101 near the top rod 114. The two transmission rods 118 are symmetrically arranged on the H-shaped frame 101 at corresponding positions. A protective ejection electric push rod 119 is provided at the end of each transmission rod 118 away from the H-shaped frame 101. The input ends of the fall protection electric push rod 113, the fall protection electric push rod 108, and the protective ejection electric push rod 119 are connected to the same protection controller 124, which is configured as a microcontroller. A microcontroller is an integrated circuit chip that uses very large-scale integrated circuit technology to integrate a central processing unit (CPU) with data processing capabilities, random access memory (RAM), read-only memory (ROM), various I / O ports, an interrupt system, timers / counters, and other functions onto a single silicon chip, forming a small but complete microcomputer system. The protection controller 124 has a barometer 123 connected to its input terminal. The barometer measures changes in atmospheric pressure and calculates relative altitude based on the principle that air pressure decreases with increasing altitude. The protection controller 124 also has a gyroscope 122 connected to its input terminal. The gyroscope, also based on MEMS technology, detects the angular velocity generated when the drone rotates around the X, Y, and Z axes using the Coriolis effect. Finally, the protection controller 124 has an accelerometer 121 connected to its input terminal. The accelerometer operates using a microelectromechanical system (MEMS) structure.The system detects the displacement changes of a tiny mass block inside the chip when it moves or is subjected to force, thereby obtaining the acceleration in the X, Y, and Z directions. The input terminal of the protection controller 124 is connected to a GPS locator 120. The GPS locator works by receiving time and orbit information from multiple navigation satellites, calculating the distance from the UAV to each satellite based on the signal propagation time, and then using triangulation or polygonal positioning methods to calculate latitude, longitude, altitude, speed, and time information. The input terminal of the protection controller 124 is connected to a power supply unit 125. The propeller protection mechanism 2 includes a connecting core 201. A plurality of first protective arc frames 202 are welded to the outside of the connecting core 201. A second protective arc frame 203 is provided on one side of each first protective arc frame 202. Each second protective arc frame 203 is welded to the outside of the connecting core 201. The plurality of second protective arc frames 203 are evenly distributed in a ring on the outside of the connecting core 201. The plurality of first protective arc frames 202 are evenly distributed in a ring on the outside of the connecting core 201. The barometer 123 is used to detect changes in the altitude of the UAV and transmits the detection results to the protection controller 124 for processing. The accelerometer 121 is used to measure the linear acceleration of the UAV in three axes, as well as to sense the direction of gravity, and transmit the detection results to the protection controller 124 for processing. The gyroscope 122 is used to measure the angular velocity of the UAV around three axes and transmit the detection results to the protection controller 124 for processing; The GPS locator 120 is used to detect the position, horizontal speed and vertical speed information of the UAV, and transmits the detection results to the protection controller 124 for processing.

[0026] The fixed shaft 103 located at the top of the H-shaped frame 101 passes through the upper rotating hole 105 at the corresponding position, and the upper protective arm 104 is rotatably connected to the fixed shaft 103 at the corresponding position through the upper rotating hole 105.

[0027] The width of the upper spring piece 107 is adapted to the width of the misaligned through groove 102, and the thickness of the upper protective arm 104 is adapted to the width of the misaligned through groove 102.

[0028] The fixed shaft 103 located at the bottom of the H-shaped frame 101 passes through the lower rotating hole 110 at the corresponding position, and the lower protective arm 109 is rotatably connected to the fixed shaft 103 at the corresponding position through the lower rotating hole 110.

[0029] The width of the lower spring piece 112 is adapted to the width of the misaligned through groove 102, and the thickness of the lower protective arm 109 is adapted to the width of the misaligned through groove 102.

[0030] The output shafts of the lower fall protection electric actuator 113 and the upper fall protection electric actuator 108 are respectively connected to the corresponding push rods 114 for transmission.

[0031] The lower insertion hole 111 and the upper insertion hole 106 are collinear with the corresponding insertion rod 117, and the size of the lower insertion hole 111 and the upper insertion hole 106 matches that of the corresponding insertion rod 117.

[0032] The transmission rod 118 is fixedly installed at the end of the output shaft of the protective ejection electric push rod 119 at the corresponding position, and the transmission rod 118 is connected to the output shaft of the protective ejection electric push rod 119 in a transmission connection.

[0033] The barometer 123 is model MS5611, the accelerometer 121 is model ICM-20602, the gyroscope 122 is model BMI088, the GPS locator 120 is model ZED-F9P, and the microcontroller is model M68HC16.

[0034] The specific implementation method is as follows: When using this invention, in the initial state, the upper protective arm 104 and the lower protective arm 109 are in a folded state, and the upper spring 107 and the lower spring 112 are in a deformed state. During the flight of the drone, the barometer 123 can detect the drone's altitude change, the accelerometer 121 can measure the drone's linear acceleration in three axes and sense the direction of gravity, the gyroscope 122 can measure the drone's angular velocity around three axes, the GPS locator 120 can detect the drone's position, horizontal velocity, and vertical velocity information, and the protection controller 124 integrates the above... The information measured by the four detection elements can determine whether the drone has crashed accidentally. When it is determined to be an accidental crash, the protection controller 124 controls the protection ejection actuator 119 to perform a complete extension and retraction action, that is, the output shaft of the protection ejection actuator 119 extends and then retracts. During this process, the upper protective arm 104 and the lower protective arm 109 will leave the outer wall of the drone. At this time, the upper protective arm 104 and the lower protective arm 109 lose their limit, and the upper spring 107 and the lower spring 112 will eject the upper protective arm 104 and the lower protective arm 109 respectively, so that the upper protective arm 104 and the lower protective arm 109 are ejected. 9. When the upper protective arm 104 and lower protective arm 109 are fully extended, the protective ejector rod 119 has retracted its output shaft. At the same time, the output shaft ends of the lower fall protection electric actuator rod 113 and the upper fall protection electric actuator rod 108 push out the push rod 114, so that each insert rod 117 is inserted into the lower insertion hole 111 and the upper insertion hole 106 respectively, thereby achieving limiting and combination. At this time, the upper protective arm 104 and lower protective arm 109 form an arc shape. When falling and colliding with the ground, the connecting core 201, combined with the first protective arc frame 202 and the second protective arc frame 203, forms an all-round protective structure. The structure effectively protects the propeller and prevents it from being damaged. Then, the upper protective arm 104 and the lower protective arm 109 collide and rotate, causing the protective spring 115, upper spring 107 and lower spring 112 to deform. This can dissipate force and reduce the impact of the fall on the drone, thus effectively protecting the drone's fuselage. This invention allows the drone to detect in time whether it is in an accidental fall and to open the protective structure in time, effectively protecting the drone's propeller and fuselage when it falls to the ground, thus effectively ensuring the drone's flight safety.

[0035] Working principle of this invention: Refer to the instruction manual appendix Figure 1 Appendix Figure 2 Appendix Figure 3 Appendix Figure 4 Appendix Figure 5 Appendix Figure 6 Appendix Figure 7 Appendix Figure 8 and attached Figure 9When using this invention, by providing a fuselage protection mechanism 1 and a propeller protection mechanism 2, the invention can detect in a timely manner whether the drone is in an accidental crash state and open the protection structure in time, effectively protecting the drone's propeller and fuselage when it crashes to the ground, thus effectively ensuring the drone's flight safety.

[0036] Finally, the following points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection", and "linkage" should be interpreted broadly, and can be mechanical or electrical connections, or internal connections between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may change. Secondly: The accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other. In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A protective device for unmanned aerial vehicles (UAVs), characterized in that, Including fuselage protection mechanism (1) and propeller protection mechanism (2): The fuselage protection mechanism (1) includes an H-shaped frame (101). Both sides of the H-shaped frame (101) are provided with staggered through slots (102). Fixed shafts (103) are welded to the inside of both ends of the staggered through slots (102). An upper protective arm (104) and a lower protective arm (109) are respectively provided on the two fixed shafts (103) within the same staggered through slot (102). The upper protective arm (104) has an arc-shaped cross-section. An upper rotating hole (105) is provided through the end of the upper protective arm (104) closest to the H-shaped frame (101). An upper insertion hole (106) is provided through the top of the upper protective arm (104). The bottom end of the upper protective arm (104) is away from the H-shaped frame. An upper spring sheet (107) is welded to one side of the outer wall of the groove (101). An upper fall protection electric actuator (108) is provided at the bottom of the top of the upper protective arm (104). The lower protective arm (109) has an arc-shaped cross-section. A lower rotating hole (110) is provided through the end of the lower protective arm (109) near the H-shaped frame (101). A lower insertion hole (111) is provided through the bottom of the lower protective arm (109). A lower spring sheet (112) is welded to the outer wall of the top of the lower protective arm (109) away from the H-shaped groove (101). A fall protection electric actuator (113) is provided at the top of the bottom of the lower protective arm (109). The output shaft end of the fall protection electric actuator (113) A top rod (114) is fixedly installed at the end of the output shaft of the fall protection electric actuator (108). A protective spring (115) is welded to the end of the top rod (114) away from the H-shaped frame (101). A connecting seat (116) is welded to the end of the protective spring (115) away from the H-shaped frame (101). A plug rod (117) is welded to the side of the connecting seat (116) away from the H-shaped frame (101). Two transmission rods (118) are welded to the outer wall of the H-shaped frame (101) near the top rod (114). The two transmission rods (118) are symmetrically arranged on the H-shaped frame (101) at corresponding positions. The transmission rods (118) away from the H-shaped frame (101) are... The device is equipped with a protective ejection actuator (119). The input ends of the fall protection actuator (113), the fall protection actuator (108), and the protective ejection actuator (119) are connected to the same protection controller (124). The protection controller (124) is a microcontroller. The input end of the protection controller (124) is connected to a barometer (123), a gyroscope (122), an accelerometer (121), a GPS locator (120), and a power supply unit (125). The propeller protection mechanism (2) includes a connecting core (201). A plurality of first protective arc frames (202) are welded to the outside of the connecting core (201). A second protective arc frame (203) is provided on one side of each first protective arc frame (202). Each second protective arc frame (203) is welded to the outside of the connecting core (201). The plurality of second protective arc frames (203) are evenly distributed in a ring on the outside of the connecting core (201). The plurality of first protective arc frames (202) are evenly distributed in a ring on the outside of the connecting core (201). The barometer (123) is used to detect changes in the altitude of the UAV and transmits the detection results to the protection controller (124) for processing; The accelerometer (121) is used to measure the linear acceleration of the UAV in three axes, as well as to sense the direction of gravity, and transmit the detection results to the protection controller (124) for processing; The gyroscope (122) is used to measure the angular velocity of the UAV around three axes and transmit the detection results to the protection controller (124) for processing; The GPS locator (120) is used to detect the position, horizontal speed and vertical speed information of the UAV, and transmit the detection results to the protection controller (124) for processing.

2. The protective device for unmanned aerial vehicles according to claim 1, characterized in that: The fixed shaft (103) located at the top of the H-shaped frame (101) passes through the upper rotating hole (105) at the corresponding position, and the upper protective arm (104) is rotatably connected to the fixed shaft (103) at the corresponding position through the upper rotating hole (105).

3. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The width of the upper spring piece (107) is adapted to the width of the misaligned through groove (102), and the thickness of the upper protective arm (104) is adapted to the width of the misaligned through groove (102).

4. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The fixed shaft (103) located at the bottom of the H-shaped frame (101) passes through the lower rotating hole (110) at the corresponding position, and the lower protective arm (109) is rotatably connected to the fixed shaft (103) at the corresponding position through the lower rotating hole (110).

5. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The width of the lower spring piece (112) is adapted to the width of the misaligned through groove (102), and the thickness of the lower protective arm (109) is adapted to the width of the misaligned through groove (102).

6. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The output shafts of the fall protection electric actuator (113) and the upper fall protection electric actuator (108) are respectively connected to the corresponding push rods (114) for transmission.

7. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The lower insertion hole (111) and the upper insertion hole (106) are arranged collinearly with the corresponding insertion rod (117), and the size of the lower insertion hole (111) and the upper insertion hole (106) matches that of the corresponding insertion rod (117).

8. A protective device for unmanned aerial vehicles according to claim 1, characterized in that: The transmission rod (118) is fixedly installed at the end of the output shaft of the protective ejection electric push rod (119) at the corresponding position, and the transmission rod (118) is connected to the output shaft of the protective ejection electric push rod (119) in a transmission connection.

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