A forced landing protection mechanism for unmanned aerial vehicle

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles, and discloses a forced landing protection mechanism for unmanned aerial vehicle aircraft. The forced landing protection mechanism for unmanned aerial vehicle aircraft comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body is an annular structure with a hole in the middle, an annular cavity is provided inside the unmanned aerial vehicle body for installing batteries and control panels, an arm is fixedly installed on the outer wall of the unmanned aerial vehicle body, a driving motor is fixedly installed on the end of the arm away from the unmanned aerial vehicle body through a mounting sleeve, and a plurality of landing gears are provided on the lower surface of the unmanned aerial vehicle body. The forced landing protection mechanism for unmanned aerial vehicle aircraft, by utilizing the design of the forced landing mechanism and the arm protection mechanism, can reduce the falling speed by utilizing the forced landing mechanism and provide buffer protection for the equipment shell and the camera equipment during the falling process of the unmanned aerial vehicle, and can also reduce the damage to the unmanned aerial vehicle body by utilizing the arm protection mechanism, thereby reducing economic losses, and solving the problems raised in the background technology.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a forced landing protection mechanism for unmanned aerial vehicle aircraft. Background Art

[0002] Drones can be divided into military and civilian applications according to their application areas. The civilian application area has many uses, including aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, creating romance, etc., which greatly expands the use of drones themselves.

[0003] For multi-rotor aerial photography drones, in addition to their own value, the professional photography equipment mounted on the bottom gimbal often exceeds the value of the drone. This type of equipment is usually installed at the bottom of the drone. When the drone fails, such as the drive motor overloads and burns out, or the drone loses power, the drone needs to make an emergency landing. In addition to the landing gear, the impact force generated by the high-speed fall will first act on the camera equipment. The existing drone protection mechanism for camera equipment is not perfect and mainly relies on the landing gear support, but its protection effect is limited. Therefore, we propose a forced landing protection mechanism for drone aircraft. Summary of the invention

[0004] The purpose of the invention is to provide a forced landing protection mechanism for unmanned aerial vehicle aircraft, which can use the forced landing protection mechanism to fully protect high-value equipment on the unmanned aerial vehicle, absorb the impact during the fall, maintain the integrity of the unmanned aerial vehicle, reduce economic losses, and avoid data loss.

[0005] To achieve the above objectives, the present invention is implemented through the following technical solutions: a forced landing protection mechanism for a UAV aircraft, comprising a UAV body, the UAV body is an annular structure with a hole in the middle, an annular cavity is provided inside the UAV body for installing a battery and a control panel, an arm is fixedly installed on the outer wall of the UAV body, a drive motor is fixedly installed on one end of the arm away from the UAV body through a mounting sleeve, a plurality of landing gears are provided on the lower surface of the UAV body, a forced landing mechanism is provided on the inner side of the UAV body, and an arm protection mechanism is provided at the arm position;

[0006] The forced landing mechanism includes a cover, a parachute bag for forced landing, micropores, a device shell, a pull rope, a gimbal assembly, an electric push rod, a slot, a ventilator, a closed hole, a closed plate, a push rod, a fixing ring and a tension spring. The cover is fixed to the upper surface of the drone body by magnetic attraction to close the central hole. The outer side of the parachute bag for forced landing is bonded to the inner side of the drone body. The inner side of the parachute bag for forced landing is provided with evenly distributed micropores, and the opening of the parachute bag for forced landing points to the lower side of the drone body. The device shell is located on the inner side of the parachute bag for forced landing, and the top of the device shell is connected to the inner wall of the parachute bag for forced landing by a pull rope. The bottom of the device shell is provided with a gimbal assembly, and an electric push rod is fixedly installed on the inner wall of the annular cavity. The output end of the electric push rod runs through the drone body. The side wall of the body and the forced landing parachute bag are inserted into the slot at the corresponding position of the outer wall of the equipment shell. The control system of the electric push rod is independent of the flight control system of the drone. When the flight control system of the drone fails, the electric push rod can be controlled to release the equipment shell to ensure the effectiveness of the forced landing mechanism. The ventilation pipe is arranged in the equipment shell, and the openings at both ends of the ventilation pipe are respectively located at the upper and lower ends of the equipment shell. A closed hole is opened on the side of the ventilation pipe close to the slot, and a closed plate is inserted in the closed hole. A push rod is fixedly connected to one end of the closing plate close to the slot. The push rod penetrates the equipment shell and is inserted in the slot and contacts the electric push rod. The position of the push rod in the equipment shell is fixedly connected to a fixing ring, and the fixing ring is connected to the inner wall of the equipment shell by a tension spring.

[0007] The arm protection mechanism includes a connecting bag, a support rod, a support sheet and a protection bag. Two support rods are symmetrically provided on the side wall of the drone body and on the lower side of the arm. One end of the support rod away from the drone body is fixedly connected to the mounting sleeve, and the support rod and the arm are fixedly connected via the support sheet. The protection bag is arranged on the lower side of the arm and bonded to the support rod and the support sheet. The connecting bag is bonded to the drone body for connecting the protection bag and the parachute-shaped bag for forced landing.

[0008] Preferably, the cross section of the ventilation pipe is rectangular, and the closing plate can be inserted into the ventilation pipe to close it.

[0009] Preferably, the edge of the lower surface of the device shell is chamfered, and the forced landing parachute-shaped bag is provided with folds at the chamfered position of the device shell, which can expand inward after being inflated. When the forced landing parachute-shaped bag is inflated, the inner side thereof pulls the device shell into the forced landing parachute-shaped bag through a pull rope, and the camera equipment installed on the gimbal assembly also follows it in. The folds are inflated to shrink the opening of the forced landing parachute-shaped bag, thereby providing protection for the equipment.

[0010] Preferably, the top wall of the forced landing parachute-shaped bag is folded between the cover and the equipment shell, and after the ventilation pipe is opened and air enters the inside of the forced landing parachute-shaped bag, it can be propped up to form a parachute shape, thereby reducing the descent speed of the drone body and protecting the equipment shell and the camera equipment on the gimbal assembly.

[0011] Preferably, an annular airbag is sleeved on the position where the mounting sleeve extends from the bottom of the driving motor, and the annular airbag is connected to the protective bag. The bottom of the annular airbag is provided with air outlet holes arranged in a ring, and the number of the air outlet holes is not less than three. After the airflow fills the protective bag, it can be discharged downward through the air outlet holes, providing a recoil force to reduce the falling speed, and cooperating with the parachute-shaped bag in the middle for forced landing, it can maintain the stability of the drone body and avoid rolling in the air.

[0012] Preferably, the number of the electric push rods is not less than four and they are arranged in a ring with reference to the central axis of the drone body, and the number of the electric push rods is the same as the number of the ventilation pipes.

[0013] Preferably, the micropores are located at a position where the forced landing parachute-shaped bag is opposite to the top of the equipment shell, and the pore size range of the micropores is 0.1-1mm. When the UAV falls, air enters between the equipment shell and the forced landing parachute-shaped bag through the ventilation tube. While the forced landing parachute-shaped bag is propped up into a parachute shape, high-speed airflow can also enter the forced landing parachute-shaped bag through the micropores to expand it and wrap the equipment shell to provide protection, and supply air to the protection bag and the connecting bag.

[0014] Preferably, the bottom cross-section of the protection bag is wavy and can expand downward after being inflated to provide protection for the arm. The protection bag and the connecting bag can provide a buffer for the drone body. When the landing gear becomes ineffective due to a high-speed fall, the two can be used to provide protection for the drone body, avoiding direct impact on internal components and reducing damage to them.

[0015] By adopting the above technical solution, the beneficial effects of the present invention are:

[0016] The forced landing protection mechanism for the UAV aircraft utilizes the design of the forced landing mechanism and the arm protection mechanism. During the falling process of the UAV, the forced landing mechanism can be used to reduce the falling speed and provide buffer protection for the equipment shell and the camera equipment. The arm protection mechanism can also reduce the damage to the UAV body and reduce economic losses, thereby solving the problems raised in the background technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the present invention from a top view perspective;

[0018] Figure 2 It is a front cross-sectional view of the structure of the present invention;

[0019] Figure 3 For the present invention Figure 2 The enlarged view of point A in the middle;

[0020] Figure 4 For the present invention Figure 2 The enlarged view of point B in the middle;

[0021] Figure 5 It is a schematic diagram of the present invention from a bottom-up perspective.

[0022] In the figure: 1 UAV body, 2 annular cavity, 3 machine arm, 4 mounting sleeve, 5 drive motor, 6 landing gear,

[0023] 7 forced landing mechanism, 71 cover, 72 forced landing parachute bag, 73 micro hole, 74 equipment shell, 75 pull rope, 76 pan / tilt assembly, 77 electric push rod, 78 slot, 79 ventilation pipe, 710 closed hole, 711 closed plate, 712 push rod, 713 fixed ring, 714 tension spring,

[0024] 8 machine arm protection mechanism, 81 connecting bag, 82 support rod, 83 support plate, 84 protection bag, 9 wrinkles, 10 annular airbag, 11 air outlet. DETAILED DESCRIPTION

[0025] See also Figure 1-5 The present invention provides a technical solution: a forced landing protection mechanism for a UAV aircraft, comprising a UAV body 1, the UAV body 1 is a ring structure with a hole in the middle, an annular cavity 2 is provided inside the UAV body 1 for installing a battery and a control panel, an arm 3 is fixedly installed on the outer wall of the UAV body 1, a driving motor 5 is fixedly installed at one end of the arm 3 away from the UAV body 1 through a mounting sleeve 4, a plurality of landing gears 6 are provided on the lower surface of the UAV body 1, a forced landing mechanism 7 is provided on the inner side of the UAV body 1, and an arm protection mechanism 8 is provided at the position of the arm 3;

[0026] The forced landing mechanism 7 includes a cover 71, a parachute-shaped capsule 72, micropores 73, a device shell 74, a pull rope 75, a gimbal assembly 76, an electric push rod 77, a slot 78, a vent 79, a closed hole 710, a closed plate 711, a push rod 712, a fixing ring 713 and a tension spring 714. The cover 71 is fixed to the upper surface of the drone body 1 by magnetic attraction to close the central hole. The outer side of the parachute-shaped capsule 72 is bonded to the inner side of the drone body 1. The inner side of the parachute-shaped capsule 72 is provided with uniformly distributed micropores 73, and the opening of the parachute-shaped capsule 72 points to the lower side of the drone body 1. The device shell 74 is located on the inner side of the parachute-shaped capsule 72, and the top of the device shell 74 is connected to the inner wall of the parachute-shaped capsule 72 by a pull rope 75. The bottom of the device shell 74 is provided with a gimbal assembly 76. The annular cavity 2 An electric push rod 77 is fixedly installed on the inner wall, and the output end of the electric push rod 77 penetrates the side wall of the drone body 1 and the forced landing parachute bag 72 and is inserted into the slot 78 at the corresponding position of the outer wall of the equipment shell 74. The ventilation pipe 79 is arranged in the equipment shell 74, and the two end openings of the ventilation pipe 79 are respectively located at the upper and lower ends of the equipment shell 74. A closed hole 710 is opened on the side of the ventilation pipe 79 close to the slot 78, and a closed plate 711 is inserted in the closed hole 710. A push rod 712 is fixedly connected to one end of the closing plate 711 close to the slot 78. The push rod 712 penetrates the equipment shell 74 and is inserted into the slot 78 and contacts the electric push rod 77. The position of the push rod 712 in the equipment shell 74 is fixedly connected to a fixing ring 713, and the fixing ring 713 is connected to the inner wall of the equipment shell 74 through a tension spring 714.

[0027] The arm protection mechanism 8 includes a connecting bag 81, a support rod 82, a support sheet 83 and a protection bag 84. Two support rods 82 are symmetrically provided on the side wall of the drone body 1 and on the lower side of the arm 3. The end of the support rod 82 away from the drone body 1 is fixedly connected to the mounting sleeve 4. The support rod 82 and the arm 3 are fixedly connected through the support sheet 83. The protection bag 84 is arranged on the lower side of the arm 3 and is bonded to the support rod 82 and the support sheet 83. The connecting bag 81 is bonded to the drone body 1 for connecting the protection bag 84 and the forced landing parachute bag 72.

[0028] The cross section of the vent pipe 79 is rectangular, and the closing plate 711 is inserted into the vent pipe 79 to close it.

[0029] The edge of the lower surface of the equipment shell 74 is chamfered, and the forced landing parachute-shaped bag 72 is provided with folds 9 at the chamfered position of the equipment shell 74, which can expand inward after being inflated. When the forced landing parachute-shaped bag 72 is inflated, the inner side thereof pulls the equipment shell 74 into the forced landing parachute-shaped bag 72 through the pull rope 75, and the camera equipment installed on the gimbal assembly 76 also follows it in. The folds are inflated to shrink the opening of the forced landing parachute-shaped bag 72, thereby providing protection for the equipment.

[0030] The top wall of the forced landing parachute-shaped bag 72 is folded between the cover 71 and the equipment shell 74. When the vent 79 is opened and air enters the inside of the forced landing parachute-shaped bag 72, it can be propped up to form a parachute shape, thereby reducing the descent speed of the drone body 1 and protecting the equipment shell 74 and the camera equipment on the gimbal assembly 76.

[0031] An annular airbag 10 is mounted on the position where the mounting sleeve 4 is extended from the bottom of the driving motor 5. The annular airbag 10 is connected to the protective bag 84. The bottom of the annular airbag 10 is provided with an annularly arranged air outlet holes 11. The number of the air outlet holes 11 is not less than three. After the airflow is filled into the protective bag 84, it can be discharged downward through the air outlet holes 11, providing a recoil force to reduce the falling speed. In conjunction with the central forced landing parachute bag 72, the drone body 1 can be kept stable to prevent rolling in the air.

[0032] The number of the electric push rods 77 is not less than four and they are arranged in a ring with the central axis of the drone body 1 as a reference. The number of the electric push rods 77 is the same as the number of the ventilation pipes 79.

[0033] The micropores 73 are located at a position opposite to the top of the forced landing parachute bag 72 and the equipment shell 74. The aperture range of the micropores 73 is 0.1-1 mm. When the drone falls, air enters between the equipment shell 74 and the forced landing parachute bag 72 through the ventilation tube 79. While propping up the forced landing parachute bag 72 into a parachute shape, high-speed airflow can also enter the forced landing parachute bag 72 through the micropores 73 to expand it and wrap the equipment shell 74 to provide protection, and supply air to the protection bag 84 and the connecting bag 81.

[0034] The bottom cross-section of the protection bag 84 is wavy and can expand downward after being inflated to provide protection for the arm 3. The protection bag 84 and the connecting bag 81 can provide a buffer for the drone body 1. When the landing gear is ineffective due to a high-speed fall, the two can be used to provide protection for the drone body 1, avoiding direct impact on internal components and reducing damage to them.

[0035] Various modifications to these embodiments will be apparent to those skilled in the art. The general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A forced landing protection mechanism for an unmanned aerial vehicle, comprising an unmanned aerial vehicle body (1), the unmanned aerial vehicle body (1) being an annular structure with a hole in the middle, an annular cavity (2) being provided inside the unmanned aerial vehicle body (1) for installing a battery and a control panel, an arm (3) being fixedly installed on the outer wall of the unmanned aerial vehicle body (1), a drive motor (5) being fixedly installed on one end of the arm (3) away from the unmanned aerial vehicle body (1) through an installation sleeve (4), a plurality of landing gears (6) being provided on the lower surface of the unmanned aerial vehicle body (1), characterized in that: A forced landing mechanism (7) is provided on the inner side of the drone body (1), and an arm protection mechanism (8) is provided at the position of the arm (3); The forced landing mechanism (7) comprises a cover (71), a forced landing parachute bag (72), a micro hole (73), a device shell (74), a pull rope (75), a pan / tilt assembly (76), an electric push rod (77), a slot (78), a vent pipe (79), a closed hole (710), a closed plate (711), a push rod (712), a fixing ring (713) and a tension spring (714). The cover (71) is fixed to the upper surface of the drone body (1) by magnetic attraction to seal the central hole. The outer side of the forced landing parachute bag (72) is bonded to the inner side of the drone body (1), the inner side of the forced landing parachute bag (72) is provided with uniformly distributed micropores (73), and the opening of the forced landing parachute bag (72) points to the lower side of the drone body (1), the equipment shell (74) is located on the inner side of the forced landing parachute bag (72), and the top of the equipment shell (74) is connected to the inner wall of the forced landing parachute bag (72) by a pull rope (75), and the bottom of the equipment shell (74) is provided with a gimbal assembly (76), An electric push rod (77) is fixedly mounted on the inner wall of the annular cavity (2). The output end of the electric push rod (77) penetrates the side wall of the drone body (1) and the forced landing parachute bag (72) and is then inserted into a slot (78) at a corresponding position on the outer wall of the device shell (74). The ventilation pipe (79) is arranged in the device shell (74), and the openings at both ends of the ventilation pipe (79) are respectively located at the upper and lower ends of the device shell (74). A closed hole (710) is provided on one side of the ventilation pipe (79) close to the slot (78). ), a closing plate (711) is inserted into the closing hole (710), a push rod (712) is fixedly connected to one end of the closing plate (711) close to the slot (78), the push rod (712) passes through the device shell (74) and is inserted into the slot (78) and contacts the electric push rod (77), a fixing ring (713) is fixedly connected to the position of the push rod (712) in the device shell (74), and the fixing ring (713) is connected to the inner wall of the device shell (74) via a tension spring (714); The arm protection mechanism (8) comprises a connection bag (81), a support rod (82), a support sheet (83) and a protection bag (84); two support rods (82) are symmetrically arranged on the side wall of the drone body (1) and on the lower side of the arm (3); one end of the support rod (82) away from the drone body (1) is fixedly connected to the mounting sleeve (4); the support rod (82) and the arm (3) are fixedly connected via the support sheet (83); the protection bag (84) is arranged on the lower side of the arm (3) and is bonded to the support rod (82) and the support sheet (83); the connection bag (81) is bonded to the drone body (1) for connecting the protection bag (84) and the parachute bag (72) for forced landing.

2. The forced landing protection mechanism for an unmanned aerial vehicle according to claim 1, characterized in that: The cross section of the ventilation pipe (79) is rectangular, and the closing plate (711) is inserted into the ventilation pipe (79) to close it.

3. The forced landing protection mechanism for an unmanned aerial vehicle according to claim 2, characterized in that: The edge of the lower surface of the device shell (74) is chamfered, and the parachute-shaped bag (72) is provided with wrinkles (9) at the position corresponding to the chamfer of the device shell (74) so ​​as to expand inwards after being inflated.

4. The forced landing protection mechanism for an unmanned aerial vehicle according to claim 3, characterized in that: The top wall of the forced landing parachute bag (72) is folded between the cover (71) and the equipment shell (74).

5. The forced landing protection mechanism for a UAV according to claim 4, characterized in that: The bottom of the driving motor (5) extends out of the mounting sleeve (4) and is sleeved with an annular airbag (10), the annular airbag (10) is connected to the protective bag (84), and the bottom of the annular airbag (10) is provided with annularly arranged air outlet holes (11), and the number of the air outlet holes (11) is not less than three.

6. The forced landing protection mechanism for an unmanned aerial vehicle according to claim 5, characterized in that: The number of the electric push rods (77) is not less than four and they are arranged in a ring with the central axis of the drone body (1) as a reference. The number of the electric push rods (77) is the same as the number of the ventilation pipes (79).

7. The forced landing protection mechanism for an unmanned aerial vehicle according to claim 6, characterized in that: The micropore (73) is located at a position where the parachute-shaped bag (72) is opposite to the top of the equipment shell (74), and the aperture range of the micropore (73) is 0.1-1 mm.

8. The forced landing protection mechanism for a UAV according to claim 7, characterized in that: The bottom cross-section of the protective bag (84) is wavy and can expand downward after being inflated to provide protection for the machine arm (3).

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