Aircraft with lifting obstacle avoidance structure
By designing a lifting and obstacle avoidance structure on the aircraft, and using the servo and swing arm to control the extension and storage of the obstacle avoidance device, the problem of exposed and damaged obstacle avoidance device is solved, which improves service life and enhances the fun and ornamentality.
Patent Information
- Application Number
- CN202421451338.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-24
- Publication Date
- 2025-07-22
- Estimated Expiration
- 2034-06-24
AI Technical Summary
The obstacle avoidance devices of existing aircraft are exposed to the outside when not in use, which is prone to bumps and damage, affecting the service life.
An aircraft with a lifting and obstacle avoidance structure is designed. By installing a lift box in the housing cavity on the fuselage, the extension and accommodation of the obstacle avoidance device are controlled by using the servo and swing arm to achieve selective exposure and protection of the obstacle avoidance device.
It improves the service life of the obstacle avoidance device, enhances the fun and ornamentality of the aircraft, and avoids damage caused by long-term exposure of the obstacle avoidance device.
Smart Images
Figure CN223132388U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft, in particular to an aircraft with a lifting and obstacle avoidance structure. Background Art
[0002] Aircraft are popular among consumers because of their advantages of maneuverability, quick response, unmanned flight, and low operating requirements. Aircraft are usually equipped with obstacle avoidance devices, which obtain information such as the direction and distance of obstacles in the surrounding environment so as to perform autonomous flight and prevent the aircraft from colliding with obstacles during flight. In the prior art, the obstacle avoidance device of the aircraft is usually exposed when not in use. If it is left for a long time, it is easy to bump into it, causing damage to the obstacle avoidance device of the aircraft. Therefore, those skilled in the art provide an aircraft with a lifting obstacle avoidance structure to solve the problems raised in the above background technology. Utility Model Content
[0003] The utility model aims to solve the shortcomings in the prior art and proposes an aircraft with a lifting and obstacle avoidance structure.
[0004] In order to achieve the above-mentioned purpose, the utility model provides an aircraft with a lifting and obstacle avoidance structure, including a body, a housing cavity is opened on the body, and a clearance hole is opened on the side wall of the housing cavity along the depth direction; a lifting box is adapted to be connected in the housing cavity, and the lifting box is used to install an obstacle avoidance device, and a connecting hole is provided on the lifting box, and the connecting hole is arranged corresponding to the clearance hole; a lifting device is fixed outside the housing cavity, and the lifting device includes a steering gear and a swing arm, and the swing arm is movably inserted into the clearance hole and connected to the connecting hole, and the swing arm is controlled by the steering gear to swing back and forth to drive the lifting box to move and extend out of the housing cavity, or to move and be accommodated in the housing cavity.
[0005] Preferably, a receiving groove is further provided on the lifting box, the receiving groove is communicated with the connecting hole and the two are arranged in a vertical direction, and the bottom wall of the receiving groove and the hole wall of the connecting hole are respectively connected to the swing arm in a contactable manner.
[0006] Preferably, the receiving groove is sunken on the bottom wall of the lifting box, and the bottom wall of the accommodating cavity is sunken with a positioning groove at a position corresponding to the receiving groove, and the receiving groove can be accommodated in the positioning groove.
[0007] Preferably, the lifting box includes an upper cover body and a lower cover body connected to each other, the thickness of the upper cover body is equal to or slightly smaller than the moving distance of the lifting box, and at least one concave cavity is provided on the side wall where the upper cover body and the lower cover body are connected; the lower cover body is provided with a guide block and the connecting hole, and the guide block is movably inserted into the side wall of the accommodating cavity.
[0008] Preferably, a wiring hole is further provided on the lower cover body, and a through hole is provided on the bottom wall of the accommodating cavity at a position corresponding to the wiring hole, and the through hole and the wiring hole are used to connect the lifting box and the inside of the body.
[0009] Preferably, the servo comprises a motor and a gear set, the gear set is transmission-connected between the motor and the swing arm, and the gear set is used to drive the swing arm to swing at a reduced speed.
[0010] Preferably, the body comprises an upper shell and a lower shell connected to each other, the upper shell is provided with the accommodating cavity, the lower shell is equipped with a rotor and a camera device, and the lifting device, positioning device and main control device are installed between the upper shell and the lower shell.
[0011] Preferably, the camera device comprises a camera body and a bird's-eye view lens, the camera body is rotatably connected to the outside of the lower shell, and the auxiliary lens is fixed to the outer side of the bottom wall of the lower shell.
[0012] Preferably, the positioning device comprises a decorative frame fixed to the inner wall of the upper shell, and a positioner fixed to the decorative frame, and a portion of the decorative frame passes through the upper shell and is exposed on the machine body.
[0013] Preferably, the rotor includes a rotor body and an anti-collision guardrail, the rotor body is rotatably connected to the lower shell, the rotor body is provided with a supporting foot, the anti-collision guardrail is provided with a fixing hole and a flip buckle, the supporting foot can be inserted into the fixing hole, and the flip buckle can be fastened and connected to the rotor body.
[0014] Compared with the prior art, the advantages and positive effects of the utility model are as follows: the aircraft with a lifting and obstacle avoidance structure provided by the utility model is provided with a accommodating cavity on the fuselage, and a lifting box for installing the obstacle avoidance device is movably connected in the accommodating cavity. The lifting box is controlled to move by the swing arm of the lifting device, and can drive the obstacle avoidance device to move and extend out of the body or be accommodated in the accommodating cavity, so that the obstacle avoidance device can be selectively exposed to the outside, which can not only realize the normal use of the obstacle avoidance device during the flight of the aircraft, but also avoid the obstacle avoidance device from being damaged by being exposed to the outside for a long time, and can improve the service life of the obstacle avoidance device. Moreover, the way in which the lifting box drives the obstacle avoidance device to move up and down simulates the process of cartoon characters exploring, shrinking their heads, and opening and closing their eyes, which can also improve the fun and viewing of the aircraft to a certain extent. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 It is a schematic diagram of a lifting box of an aircraft contained in a receiving cavity according to an embodiment of the utility model.
[0016] Figure 2 is Figure 1 The schematic diagram of the lifting box of the aircraft extending out of the accommodating cavity in
[0017] Figure 3 is Figure 1 The schematic diagram of the fuselage in
[0018] Figure 4 is Figure 3 The exploded schematic diagram of the fuselage in
[0019] Figure 5 is Figure 4 The exploded schematic diagram of the lifting box in
[0020] Figure 6 is Figure 4 The exploded schematic diagram of the servo in
[0021] Figure 7 is Figure 1 The sectional schematic diagram of the fuselage in
[0022] Figure 8 is Figure 2 The sectional schematic diagram of the fuselage in
[0023] Figure 9 is Figure 1 The exploded schematic diagram of the rotor in
[0024] In the figure: 10 - fuselage; 11 - upper housing; 110 - accommodating cavity; 111 - relief hole; 112 - guiding hole; 113 - through hole; 114 - positioning groove; 12 - lower housing; 20 - lifting box; 21 - upper cover body; 211 - concave cavity; 22 - lower cover body; 221 - connecting hole; 222 - guiding block; 223 - wiring hole; 224 - receiving groove; 30 - lifting device; 31 - servo; 311 - motor; 312 - gear set; 3121 - first - stage gear; 3122 - second - stage gear; 3123 - third - stage gear; 3124 - fourth - stage gear; 3125 - fifth - stage gear; 3126 - sixth - stage gear; 32 - swing arm; 40 - positioning device; 41 - decorative frame; 42 - locator; 50 - main control device; 51 - battery box; 52 - battery; 53 - control circuit board; 54 - switch; 55 - male plug; 56 - female plug; 60 - rotor; 61 - rotor main body; 611 - support leg; 62 - anti - collision guardrail; 621 - fixing hole; 622 - flip - cover buckle; 70 - camera device; 71 - camera main body; 72 - downward - looking lens. Detailed implementation manners
[0025] The preferred implementation manners of the present utility model will be further described in detail below in conjunction with the accompanying drawings.
[0026] Embodiments of the present utility model will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present utility model and should not be construed as limiting the present utility model.
[0027] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. These are only for the convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
[0028] In addition, the terms "first", "second", etc. are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features.
[0029] In the present utility model, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0030] In the present utility model, unless otherwise clearly defined and limited, the first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but in contact through other features therebetween. Moreover, the first feature being "above", "over" and "on" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "under" the second feature includes the first feature being directly below and obliquely below the second feature, or merely indicating that the first feature has a lower horizontal height than the second feature.
[0031] Please refer to Figures 1 to 9, this embodiment provides an aircraft with a lifting obstacle avoidance structure, which includes a fuselage 10. A receiving cavity 110 is formed on the fuselage 10, and the receiving cavity 110 is used to install the lifting obstacle avoidance structure.
[0032] It can be understood that the fuselage 10 includes a connected upper shell 11 and a lower shell 12. A lifting device 30, a positioning device 40, and a main control device 50 are installed in the cavity between the upper shell 11 and the lower shell 12. A receiving cavity 110 is formed on the upper shell 11, and rotors 60 and a camera device 70 are installed on the lower shell 12.
[0033] A lifting box 20 is adaptively connected in the receiving cavity 110, and the lifting box 20 is used to install the obstacle avoidance device. In this embodiment, the receiving cavity 110 is formed on the top side of the fuselage 10, which can reduce the probability of false alarms or misreports of the obstacle avoidance device and improve the flight safety of the aircraft. A relief hole 111 and a guiding hole 112 are formed in the side wall of the receiving cavity 110 along the depth direction. The relief hole 111 is used for the lifting device 30 to pass through movably to connect the lifting box 20, and the guiding hole 112 is used for sliding connection and cooperation with the lifting box 20 to play a role in guiding and preventing displacement. A through hole 113 and a positioning groove 114 are formed in the bottom wall of the receiving cavity 110. The through hole 113 is used to communicate the receiving cavity 110 with the inside of the fuselage 10, and the positioning groove 114 is recessed in the bottom wall of the receiving cavity 110 and is used for cooperation with the lifting box 20 to play a role in positioning and quickly installing the lifting box 20.
[0034] In other embodiments of the present invention, the guiding hole 112 and / or the positioning groove 114 may not be provided in the receiving cavity 110, and other structures that can cooperate with the lifting box 20 to play the same role as the guiding hole 112, such as guiding ribs, may also be provided in the receiving cavity 110.
[0035] The lifting box 20 includes a connected upper cover 21 and a lower cover 22. At least one concave cavity 211 is formed on the side wall where the upper cover 21 and the lower cover 22 are connected. The concave cavity 211 is used as the radar port and / or lens port of the obstacle avoidance device, so that the radar and / or lens of the obstacle avoidance device can be exposed on the lifting box 20. In this embodiment, concave cavities 211 are formed on each side wall of the upper cover 21. It can be understood that the thickness of the upper cover 21 is equal to or slightly less than the moving distance of the lifting box 20, so that when the lifting box 20 moves to the first limit position, the upper cover 21 can completely extend out of the receiving cavity 110, and the radar and / or lens on the concave cavity 211 can work normally. Moreover, when the lifting box 20 moves to the second limit position, the upper cover 21 can be completely received in the receiving cavity 110 to protect the obstacle avoidance device from damage.
[0036] The lower cover 22 is provided with a connecting hole 221, which is arranged corresponding to the clearance hole 111, and the length of the connecting hole 221 is smaller than the length of the clearance hole 111. The connecting hole 221 is used to connect with the lifting device 30, so that the lifting device 30 can be started to drive the lifting box 20 to move up and down in the accommodating cavity 110.
[0037] In this embodiment, the lower cover 22 is further provided with a guide block 222, a wiring hole 223 and a receiving groove 224. The guide block 222 is moved and inserted into the guide hole 112 one by one, and the two cooperate to guide and limit the lifting box 20 from rotating during the movement. The wiring hole 223 is arranged corresponding to the through hole 113, and the two cooperate to connect the lifting box 20 and the inside of the body 10 to realize the layout of the conductive wire. The receiving groove 224 is sunken and arranged on the bottom wall of the lifting box 20. The receiving groove 224 is arranged corresponding to the positioning groove 114, and the receiving groove 224 can be accommodated in the positioning groove 114. It can be understood that the receiving groove 224 is connected to the connecting hole 221 and the two are arranged in the vertical direction. The bottom wall of the receiving groove 224 and the hole wall of the connecting hole 221 are respectively connected to the swing arm of the lifting device 30 in a contactable manner, so as to contact the swing arm and be driven to move up or down during the swing of the swing arm of the lifting device 30.
[0038] In other embodiments of the present invention, the lower cover 22 may not be provided with the guide block 222 and / or the receiving groove 224, and the lifting box 20 may also be provided with other structures outside the accommodating cavity 110 that can cooperate with the accommodating cavity 110 to play the same role as the guide block 222, such as a guide groove.
[0039] The lifting device 30 is fixed outside the accommodating chamber 110, and includes a steering gear 31 and a swing arm 32. The steering gear 31 is used to control the swing arm 32 to swing back and forth by a certain amplitude. It can be understood that the steering gear 31 includes a motor 311 and a gear set 312, and the gear set 312 is transmission-connected between the motor 311 and the swing arm 32, and the gear set 312 is used to drive the swing arm 32 to swing at a reduced speed.
[0040] In this embodiment, the gear set 312 includes a first gear 3121, a second gear 3122, a third gear 3123, a fourth gear 3124, a fifth gear 3125 and a sixth gear 3126 that are meshed and connected in sequence. Among them, the first gear 3121 is fixed to the rotating shaft of the motor 311, the second gear 3122, the third gear 3123, the fourth gear 3124 and the fifth gear 3125 are all double gears, the third gear 3123 is coaxially connected to the fifth gear 3125, the fourth gear 3124 is coaxially connected to the sixth gear 3126, and the sixth gear 3126 is fixed to the swing arm 32. In other embodiments of the utility model, the gear set 312 can also be set to other gear meshing structures that achieve the same or similar effects.
[0041] The swing arm 32 movably passes through the relief hole 111 and is connected to the connection hole 221. The swing arm 32 is reciprocally swung under the control of the servo 31 to drive the lifting box 20 to move up and down. As Figure 8 shown, when the swing arm 32 swings upward, the swing arm 32 abuts against the hole wall of the connection hole 221 to push the lifting box 20 to move upward therewith, so that the lifting box 20 can move out of the accommodating cavity 110. As Figure 7 shown, when the swing arm 32 swings downward, the swing arm 32 gradually rotates to abut against the receiving groove 224 to push the lifting box 20 to move downward therewith, so that the lifting box 20 can move and be received in the accommodating cavity 110.
[0042] The positioning device 40 is used to provide positioning information of the aircraft. The positioning device 40 includes a decorative frame 41 fixed to the inner wall of the upper housing 11 and a locator 42 fixed to the decorative frame 41. Among them, a part of the decorative frame 41 passes through the upper housing 11 and is exposed on the airframe 10, playing a role in decorating the appearance of the airframe 10. It can be understood that the decorative frame 41 can not only improve the aesthetics of the aircraft, but also compactly connect the locator 42 inside the fuselage 10.
[0043] The main control device 50 is used to analyze and control each function on the aircraft. The main control device 50 includes a battery box 51 detachably connected inside the fuselage 10, a battery 52 installed in the battery box 52, a control circuit board 53 fixed to the lower housing 12, and a switch 54 exposed on the upper housing 11. Among them, a conductive structure is provided between the battery box 51 and the control circuit board 53. The conductive structure includes a male plug 55 and a female plug 56 that are detachably connected, so as to facilitate the maintenance and replacement of the battery 52.
[0044] The number of the rotors 60 is four. The four rotors 60 are arranged on both sides of the airframe 10 in a staggered manner in pairs, and are used to realize the flight function of the aircraft. In this embodiment, each rotor 60 includes a rotor main body 61 and an anti-collision guardrail 62. The rotor main body 61 is rotatably connected to the lower housing 12, and flight wings are arranged thereon. The flight wings are used to rotate and drive the airframe 10 to fly. A support leg 611 is also provided on the rotor main body 61, and the airframe 10 can be suspended on a plane to reduce the probability of being damaged by touching. Fixing holes 621 and flip covers 622 are provided on the anti-collision guardrail 62. The support leg 611 can be passed through the fixing holes 621, and the flip covers 622 can be detachably connected to the rotor main body 61.
[0045] It can be understood that the above settings of the anti-collision guardrail 62 facilitate the detachable connection with the rotor main body 61. When it is necessary to install the anti-collision guardrail 62 on the rotor main body 61, the fixing hole 621 is sleeved on the support leg 611. At this time, the opening of the flip cover buckle 622 faces the rotor main body 61 directly. By flipping and buckling the flip cover buckle 622, the anti-collision guardrail 62 can be fixed on the rotor main body 61. Operating the above process in reverse can detach the anti-collision guardrail 62 from the rotor main body 61. In other embodiments of the present invention, the rotor 60 may also only include the rotor main body 61.
[0046] The camera device 70 is used to provide the camera and video information of the aircraft. The camera device 70 includes a camera main body 71 and a downward lens 72. The camera main body 71 is rotatably connected to the outside of the lower housing 12, and rotating the camera main body 71 can adjust the camera angle. The secondary lens 72 is fixed to the outer side of the bottom wall of the lower housing 12 to facilitate shooting a downward perspective lens when the aircraft is flying.
[0047] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various modifications and changes; any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.
Claims
1. An aircraft with a lifting obstacle avoidance structure, comprising a fuselage, characterized in that, A accommodating cavity is provided on the body, and a clearance hole is provided on the side wall of the accommodating cavity along the depth direction; a lifting box is adapted to be connected in the accommodating cavity, and the lifting box is used to install an obstacle avoidance device. A connecting hole is provided on the lifting box, and the connecting hole is arranged corresponding to the clearance hole; a lifting device is fixed outside the accommodating cavity, and the lifting device includes a steering gear and a swing arm, and the swing arm is movably arranged in the clearance hole and connected to the connecting hole, and the swing arm is controlled by the steering gear to swing back and forth to drive the lifting box to move and extend out of the accommodating cavity, or to move and be accommodated in the accommodating cavity.
2. The aircraft with a lifting obstacle avoidance structure according to claim 1, wherein, The lifting box is also provided with a receiving groove, which is communicated with the connecting hole and the two are arranged in a vertical direction, and the bottom wall of the receiving groove and the hole wall of the connecting hole are respectively connected to the swing arm so as to be able to contact each other.
3. The aircraft with a lifting obstacle avoidance structure according to claim 2, wherein, The receiving groove is sunken on the bottom wall of the lifting box, and the bottom wall of the accommodating cavity is sunken with a positioning groove at a position corresponding to the receiving groove, and the receiving groove can be accommodated in the positioning groove.
4. The aircraft with a lifting obstacle avoidance structure as claimed in claim 1, wherein, The lifting box includes an upper cover body and a lower cover body connected to each other, the thickness of the upper cover body is equal to or slightly smaller than the moving distance of the lifting box, and at least one concave cavity is opened on the side wall where the upper cover body and the lower cover body are connected; the lower cover body is provided with a guide block and the connecting hole, and the guide block is movably inserted into the side wall of the accommodating cavity.
5. The aircraft with a lifting obstacle avoidance structure according to claim 4, characterized in that, The lower cover body is also provided with a wiring hole, and the bottom wall of the accommodating cavity is provided with a through hole at a position corresponding to the wiring hole, and the through hole and the wiring hole are used to connect the lifting box and the inside of the body.
6. The aircraft with a lifting obstacle avoidance structure as claimed in claim 1, wherein, The steering gear includes a motor and a gear set, wherein the gear set is transmission-connected between the motor and the swing arm, and the gear set is used to drive the swing arm to swing at a reduced speed.
7. The aircraft with a lifting obstacle avoidance structure according to any one of claims 1-6, characterized in that, The machine body comprises an upper shell and a lower shell connected to each other. The upper shell is provided with the accommodating cavity, the lower shell is provided with a rotor and a camera device, and the lifting device, a positioning device and a main control device are installed between the upper shell and the lower shell.
8. The aircraft with a lifting obstacle avoidance structure according to claim 7, characterized in that, The camera device comprises a camera body and a bird's-eye view lens. The camera body is rotatably connected to the outside of the lower shell, and the bird's-eye view lens is fixed on the outer side of the bottom wall of the lower shell.
9. The aircraft with a lifting obstacle avoidance structure according to claim 7, wherein, The positioning device comprises a decorative frame fixed to the inner wall of the upper shell, and a positioner fixed to the decorative frame. A portion of the decorative frame passes through the upper shell and is exposed on the machine body.
10. The aircraft with a lifting obstacle avoidance structure according to claim 7, characterized in that, The rotor includes a rotor body and an anti-collision guardrail, the rotor body is rotatably connected to the lower shell, the rotor body is provided with a supporting foot, the anti-collision guardrail is provided with a fixing hole and a flip cover buckle, the fixing hole can be inserted into the supporting foot, and the flip cover buckle can be connected to the rotor body by snapping.