Remote sensing aircraft
The installation structure of the sliding mounting block and the limit piece, combined with the rotating motor driving the rotating shaft, simplifies the installation and disassembly of the remote sensing aircraft optical camera, solves the problem of complex operation in the existing technology, improves efficiency and extends the service life of the propeller.
Patent Information
- Application Number
- CN202422735413.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-11
- Publication Date
- 2025-09-19
- Estimated Expiration
- 2034-11-11
AI Technical Summary
The installation and disassembly of optical cameras for existing remote sensing aircraft are complicated, resulting in low efficiency and consuming a lot of time and manpower.
The installation structure adopts a sliding mounting block and a limiter, combined with a rotating motor to drive the shaft, which simplifies the installation and removal process of the optical camera. The propeller is protected by a protective ring and a buffer device to avoid collision damage.
It improves the installation and disassembly efficiency of the optical camera, extends the service life of the propeller, reduces maintenance and repair costs, and ensures the stable operation of the aircraft.
Smart Images
Figure CN223355928U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of geographical surveying and mapping, in particular to a remote sensing aircraft. Background Art
[0002] Remote sensing aircraft are aircraft that use remote sensing technology for detection and observation. Equipped with various sensors, such as optical cameras, radar, and infrared sensors, they conduct long-range, non-contact detection of the ground, ocean, or atmosphere from the air. These sensors receive electromagnetic wave signals reflected, emitted, or scattered from target objects, convert them into electrical or digital signals, and transmit them back to ground receiving stations for processing and analysis.
[0003] Existing remote sensing aircraft usually need to install optical cameras for detection, but the existing installation structure is relatively complicated to operate, which makes the installation and disassembly of the optical camera more complicated and requires a lot of time and manpower, thereby reducing the installation and disassembly efficiency and thus causing the problem of reduced work efficiency. Utility Model Content
[0004] The purpose of this utility model is to solve the problem in the prior art that the existing installation structure is relatively complicated to operate, which makes the installation and disassembly of the optical camera relatively complicated, requires a lot of time and manpower, and thus reduces the installation and disassembly efficiency, thereby reducing work efficiency. A remote sensing aircraft is proposed.
[0005] In order to achieve the above-mentioned purpose, the present invention adopts the following technical solution: a remote sensing aircraft, including an aircraft component, a protective component is provided on the outside of the aircraft component, a mounting component is provided on the bottom of the aircraft component, the aircraft component includes an aircraft body, the mounting component includes a fixing plate and an optical camera, the fixing plate is installed at the bottom of the aircraft body, a mounting groove is installed at the bottom of the fixing plate, a mounting block is slidably installed inside the mounting groove, a support frame is installed at the bottom of the mounting block, a limiting member is passed through the interior of the mounting groove, and a fixing nail is passed through the interior of one end of the limiting member.
[0006] Preferably, the protective assembly includes a plurality of protective rings, a plurality of ventilation holes are opened inside the protective rings, a plurality of buffer dampers and buffer springs are distributed on the outside of the protective rings, and a mounting plate is installed at one end of the buffer dampers and buffer springs.
[0007] Preferably, a rotating shaft passes through both sides of the support frame, a rotating motor is installed at one end of a single rotating shaft, and one end of the rotating shaft is connected to the optical camera.
[0008] Preferably, a plurality of connecting rods are distributed on the outside of the aircraft body, and the bottom of the protective ring is connected to the top of the connecting rod.
[0009] Preferably, an electric motor is installed at one end of the connecting rod, and a propeller is distributed on the outer side of the top of the electric motor.
[0010] Preferably, a landing gear is symmetrically installed on the bottom of the aircraft body.
[0011] Compared with the prior art, the advantages and positive effects of the present invention are:
[0012] 1. In the present invention, the mounting block is slidably mounted inside the mounting groove, and a limiting member is used to pass through the inside of the mounting groove when the installation is completed, thereby limiting the mounting block, ensuring the stability and reliability of the mounting block installation, and the operation is convenient and fast, which facilitates the installation and disassembly of the optical camera, improves the convenience of operation, and thus facilitates the maintenance and repair of the optical camera, shortens the installation and disassembly time, thereby improving the installation and disassembly efficiency, and finally utilizes the fixing nail to pass through the inside of the limiting member, thereby facilitating the limiting member to limit the position, thereby ensuring the stability and reliability of the limiting member in limiting the mounting block.
[0013] 2. In the present invention, when the propeller rotates, the protective ring is conducive to providing protection, avoiding the propeller from being damaged by collision with external objects, providing a physical barrier for the propeller, reducing the possibility of propeller damage, extending the service life of the propeller, and thus ensuring the stable use of the aircraft components. A ventilation hole is provided inside the protective ring to ensure the normal circulation of air. When the propeller accidentally collides with an object during rotation, the buffer damper and the buffer shrapnel are conducive to absorbing and dispersing the impact force, reducing the impact force directly received by the propeller, thereby reducing the maintenance and repair cost of the propeller and extending the service life of the propeller. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 A schematic diagram of the three-dimensional structure of a remote sensing aircraft is provided for the utility model;
[0015] Figure 2 This is a schematic structural diagram of a remote sensing aircraft from another angle proposed by the utility model;
[0016] Figure 3 The utility model provides a schematic diagram of the structure of a protection component of a remote sensing aircraft;
[0017] Figure 4 A schematic diagram of the partial structure of a remote sensing aircraft is provided for the utility model;
[0018] Figure 5 The utility model provides a schematic diagram of the exploded structure of the installation components of a remote sensing aircraft.
[0019] Legend: 1. Aircraft assembly; 101. Aircraft body; 102. Landing gear; 103. Connecting rod; 104. Propeller; 105. Motor; 2. Protective assembly; 201. Protective ring; 202. Buffer damper; 203. Buffer spring; 204. Mounting plate; 3. Mounting assembly; 301. Fixing plate; 302. Mounting slot; 303. Mounting block; 304. Limiting piece; 305. Fixing pin; 306. Optical camera; 307. Rotating motor; 308. Rotating shaft; 309. Support frame. DETAILED DESCRIPTION
[0020] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described below with reference to the accompanying drawings and embodiments. It should be noted that the embodiments of the present application and the features therein can be combined with each other without conflict.
[0021] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. Therefore, the present invention is not limited to the specific embodiments disclosed in the following specification.
[0022] Example 1: Figure 1-Figure 5 As shown, the utility model provides a technical solution: a remote sensing aircraft, including an aircraft component 1, a protective component 2 is provided on the outside of the aircraft component 1, a mounting component 3 is provided at the bottom of the aircraft component 1, the aircraft component 1 includes an aircraft body 101, the mounting component 3 includes a fixing plate 301 and an optical camera 306, the fixing plate 301 is installed at the bottom of the aircraft body 101, a mounting groove 302 is installed at the bottom of the fixing plate 301, a mounting block 303 is slidably installed inside the mounting groove 302, a support frame 309 is installed at the bottom of the mounting block 303, a limiting member 304 is passed through the interior of the mounting groove 302, a fixing nail 305 is passed through the interior of one end of the limiting member 304, a rotating shaft 308 is passed through both sides of the support frame 309, a rotating motor 307 is installed at one end of the single rotating shaft 308, and one end of the rotating shaft 308 is connected to the optical camera 306.
[0023] In this embodiment, the mounting block 303 is slidably mounted inside the mounting groove 302, and the limiting member 304 is used to pass through the inside of the mounting groove 302 after the installation is completed, thereby limiting the mounting block 303, ensuring the stability and reliability of the installation of the mounting block 303, and the operation is convenient and fast, which facilitates the installation and disassembly of the optical camera 306, improves the convenience of operation, and facilitates the maintenance and repair of the optical camera 306, shortens the installation and disassembly time, and thus improves the installation and disassembly efficiency. Finally, the fixing nail 305 is used to pass through the inside of the limiting member 304, which is conducive to limiting the limiting member 304, ensuring the stability and reliability of the limiting member 304 in limiting the mounting block 303, and the rotating shaft 308 is driven by the rotating motor 307 to rotate, thereby causing the rotating shaft 308 to drive the optical camera 306 to rotate, which is conducive to improving the shooting range of the optical camera 306.
[0024] Example 2: Figure 1-Figure 5 As shown, the protective assembly 2 includes a plurality of protective rings 201, a plurality of ventilation holes are opened inside the protective rings 201, a plurality of buffer dampers 202 and buffer springs 203 are distributed on the outside of the protective rings 201, and a mounting plate 204 is installed at one end of the buffer dampers 202 and the buffer springs 203. A plurality of connecting rods 103 are distributed on the outside of the aircraft body 101, the bottom of the protective ring 201 is connected to the top of the connecting rod 103, and an electric motor 105 is installed at one end of the connecting rod 103. A propeller 104 is distributed on the outside of the top of the electric motor 105, and a landing gear 102 is symmetrically installed on the bottom of the aircraft body 101.
[0025] In this embodiment, the propeller 104 is electrically driven to rotate by the motor 105, thereby driving the aircraft assembly 1 to fly. When the propeller 104 rotates, the protective ring 201 is conducive to providing protection, avoiding the propeller 104 from being damaged by collision with external objects, providing a physical barrier for the propeller 104, reducing the damage to the propeller 104, and extending the service life of the propeller 104, thereby ensuring the stable use of the aircraft assembly 1. A ventilation hole is opened inside the protective ring 201 to ensure the normal circulation of air. When the propeller 104 accidentally collides with an object during rotation, the buffer damper 202 and the buffer spring 203 are conducive to absorbing and dispersing the impact force, reducing the impact force directly received by the propeller 104, thereby reducing the maintenance and repair cost of the propeller 104 and extending the service life of the propeller 104.
[0026] The working principle of this embodiment is as follows: when in use, first slide the mounting block 303 into the inside of the mounting groove 302. When the installation is completed, use the limiting piece 304 to pass through the inside of the mounting groove 302 to limit the mounting block 303. Finally, use the fixing nail 305 to pass through the inside of the limiting piece 304, which facilitates the installation and disassembly of the optical camera 306. When the aircraft assembly 1 is working, the motor 105 electrically drives the propeller 104 to rotate, thereby driving the aircraft assembly 1 to fly. When the propeller 104 rotates, the protective ring 201 is helpful in providing protection, preventing the propeller 104 from being damaged by collision with external objects. When the propeller 104 accidentally collides with an object during rotation, the buffer damper 202 and the buffer spring 203 are helpful in absorbing and dispersing the impact force, reducing the impact force directly received by the propeller 104, thereby reducing the maintenance and repair cost of the propeller 104 and extending the service life of the propeller 104.
[0027] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any other form. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes for application in other fields. However, any simple modification, equivalent change and modification of the above embodiment made according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall still fall within the scope of protection of the technical solution of the present invention.
Claims
1. A remote sensing aircraft, comprising an aircraft assembly (1), characterized in that: A protective component (2) is provided on the outside of the aircraft component (1), and a mounting component (3) is provided at the bottom of the aircraft component (1). The aircraft component (1) includes an aircraft body (101), and the mounting component (3) includes a fixing plate (301) and an optical camera (306). The fixing plate (301) is installed at the bottom of the aircraft body (101), and a mounting groove (302) is installed at the bottom of the fixing plate (301). A mounting block (303) is slidably installed inside the mounting groove (302), and a support frame (309) is installed at the bottom of the mounting block (303). A limiting member (304) is passed through the inside of the mounting groove (302), and a fixing nail (305) is passed through the inside of one end of the limiting member (304).
2. The remote sensing aircraft according to claim 1, characterized in that: The protective assembly (2) comprises a plurality of protective rings (201), a plurality of ventilation holes are provided inside the protective rings (201), a plurality of buffer dampers (202) and buffer springs (203) are distributed outside the protective rings (201), and a mounting plate (204) is installed at one end of the buffer dampers (202) and buffer springs (203).
3. The remote sensing aircraft according to claim 1, characterized in that: Rotating shafts (308) are passed through both sides of the support frame (309), a rotating motor (307) is installed at one end of a single rotating shaft (308), and one end of the rotating shaft (308) is connected to an optical camera (306).
4. The remote sensing aircraft according to claim 2, characterized in that: A plurality of connecting rods (103) are distributed on the outside of the aircraft body (101), and the bottom of the protective ring (201) is connected to the top of the connecting rod (103).
5. The remote sensing aircraft according to claim 4, characterized in that: An electric motor (105) is installed at one end of the connecting rod (103), and a propeller (104) is distributed on the outer side of the top of the electric motor (105).
6. The remote sensing aircraft according to claim 1, characterized in that: A landing gear (102) is symmetrically installed at the bottom of the aircraft body (101).