Transportation rotor unmanned aerial vehicle
By designing rollover devices and material racks in transport rotor drones, the function of automatic airdropping of materials in special environments is realized, the problem that traditional rotor aircraft cannot airdrop materials is solved, and transportation efficiency and flexibility are improved.
Patent Information
- Application Number
- CN202322925524.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2023-10-31
- Publication Date
- 2024-12-13
- Estimated Expiration
- 2033-10-31
AI Technical Summary
Traditional rotor aircraft cannot transport airdrop materials in special battlefield environments, and cannot expand capacity, and cannot automatically complete material transportation and unloading in environments without landing conditions.
A transport rotor UAV was designed, using a rollover device and a material rack. By combining a rollover electric cylinder and a material rack, the automatic airdrop of materials can be achieved, ensuring that the safe transportation of materials can be completed at target points that do not meet the conditions for landing. and airdrop.
It realizes unmanned flight and automatic material airdrop, solves the problem that traditional rotor aircraft cannot airdrop materials in special environments, improves transportation efficiency and flexibility, and can safely complete material transportation and airdrop in environments without landing conditions. .
Smart Images
Figure CN222157820U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of transport rotor UAVs, in particular to a transport rotor UAV. Background Art
[0002] In the existing technology, traditional gyroplanes are usually manned, and when performing material transportation tasks, the materials can only be unloaded manually after arriving at the target point.
[0003] The defects of the prior art are: in a special battlefield environment, there is no condition for the gyroplane to land, and the gyroplane is required to airdrop the transported materials. And the capacity cannot be expanded.
[0004] In view of the fact that this patent has the key feature of a rollover device, a search was conducted in the Chinese Patent Publication Database using "rollover and drone and load" as abstract keywords, and a document was found that was unrelated to this patent. Utility Model Content
[0005] Purpose of the utility model: to provide a transport rotor drone with better effect. The specific purpose can be seen in the multiple substantial technical effects in the specific implementation part.
[0006] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0007] A transport rotor UAV, characterized in that the UAV comprises an aircraft main beam 1, an I-shaped beam body is connected below the aircraft main beam 1, a material rack mounting beam 14 is hingedly connected above the I-shaped beam body, a rollover electric cylinder 15 is hingedly installed below the I-shaped beam body, the rollover electric cylinder 15 is installed at an angle and the end of the cylinder shaft at its end is hingedly connected to the material rack mounting beam 14, and a material rack 11 is fixed on the material rack mounting beam 14.
[0008] A further technical solution of the utility model is that the aircraft main beam 1 is inverted T-shaped, and the three landing gears 2 are arranged in a triangle, wherein one landing gear 2 is installed at the bottom of the front end of the crossbeam of the aircraft main beam 1, and two landing gears 2 are installed at the bottom surface of the middle part of the crossbeam of the aircraft main beam 1.
[0009] A further technical solution of the utility model is that the tail 3 is installed on the tail of the horizontal beam of the main beam 1, the engine 4 is installed in the middle of the vertical beam of the aircraft main beam 1 through a switching mounting structure, the output shaft of the engine 4 is equipped with a forward propeller 5, the rotor head 6 is installed at the top of the vertical beam of the aircraft main beam 1, and the rotor 7 is installed in the propeller clamp of the rotor head 6.
[0010] A further technical solution of the utility model is that the fuel tank 8 is installed on the aircraft main beam 1 through the fuel tank support beam, the flight control equipment box 9 is installed on the aircraft main beam 1 through the fuel tank support beam, and the optoelectronic pod 10 is installed at the front end bottom of the crossbeam of the aircraft main beam 1.
[0011] A further technical solution of the utility model is that two electric cylinder mounting beams 13 are mounted on the middle part of the cross beam of the aircraft main beam 1 by screws and welding, and are installed front and back respectively. The fixed end of the rollover electric cylinder 15 is mounted in the electric cylinder mounting slot at the bottom of the electric cylinder mounting beam 13 by a latch, and the rotating shaft end of the material rack mounting beam 14 is mounted in the latch slot at the top of the electric cylinder mounting beam 13 by a latch, and the telescopic end of the rollover electric cylinder 15 is connected to the electric cylinder mounting slot in the middle of the material rack mounting beam 14 by a latch.
[0012] A further technical solution of the utility model is that the material rack 11 is fixed to the material rack mounting beam 14 by rivets, the material safety lock 12 is fixed to the middle part of the crossbeam of the aircraft main beam 1 by screws, and the fuselage shell 16 is fixed to the aircraft main beam 1 by a shell mounting support.
[0013] A further technical solution of the present invention is that the housing 16 includes a space for placing items.
[0014] The utility model adopting the above technical solution has the following beneficial effects compared with the prior art: the gyroplane is an aircraft with a long history and mature technology, and the transport rotor UAV is formed by unmanned design of the gyroplane through the structure and control system, and designing material transportation and automatic material airdrop devices, so as to form an unmanned flight, material transportation and automatic material airdrop transport rotor UAV. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] In order to further illustrate the present invention, the following is further described in conjunction with the accompanying drawings:
[0016] Figure 1 It is a lower shaft side view of the structure of the utility model.
[0017] Figure 2 The internal structure of the utility model is shown in FIG. Figure 1 .
[0018] Figure 3 The internal structure of the utility model is shown in FIG. Figure 2 .
[0019] Figure 4 The internal structure of the cargo rack of the utility model is in a rollover state.
[0020] Figure 5 This is a cargo transport view of the utility model structure.
[0021] Figure 6The product structure of the utility model is Figure 1 .
[0022] Figure 7 The product structure of the utility model is Figure 2 .
[0023] Figure 8 The product structure of the utility model is Figure 3 .
[0024] The markings therein are: aircraft main beam 1, landing gear 2, tail wing 3, engine 4, forward propeller 5, rotor head 6, rotor 7, fuel tank 8, flight control equipment box 9, optoelectronic pod 10, material rack 11, material safety lock 12, electric cylinder mounting beam 13, material rack mounting beam 14, rollover electric cylinder 15, and fuselage shell 16. DETAILED DESCRIPTION
[0025] The present invention is further explained below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are only used to illustrate the present invention and are not used to limit the scope of the present invention. In the description of the present invention, it should be noted that the orientation or position relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", "top", "bottom", etc. is based on the orientation or position relationship shown in the accompanying drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be a connection between the two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0026] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.
[0027] This patent provides a variety of parallel solutions. The different expressions are improved solutions or parallel solutions based on the basic solution. Each solution has its own unique characteristics. In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other. The fixing method not described in the text can be any fixing method such as thread fixing, bolt fixing or glue bonding.
[0028] The aircraft main beam 1 is inverted T-shaped, and the three landing gears 2 are arranged in a triangular shape, one of which is installed at the bottom of the front end of the crossbeam of the aircraft main beam 1, and two are installed on the bottom surface of the middle part of the crossbeam of the aircraft main beam 1. The tail 3 is installed on the tail of the crossbeam of the main beam 1, and the engine 4 is installed in the middle of the vertical beam of the aircraft main beam 1 through a transfer installation structure. The output shaft of the engine 4 is equipped with a forward propeller 5, the rotor head 6 is installed at the top of the vertical beam of the aircraft main beam 1, and the rotor 7 is installed in the propeller clamp of the rotor head 6. The fuel tank 8 is installed on the aircraft main beam 1 through the fuel tank bracket beam, the flight control equipment box 9 is installed on the aircraft main beam 1 through the fuel tank bracket beam, and the optoelectronic pod 10 is installed on the aircraft main beam 1. At the bottom of the front end of the beam, two electric cylinder mounting beams 13 are installed in the middle of the crossbeam of the aircraft main beam 1 by screws and welding, and are installed front and back. The fixed end of the rollover electric cylinder 15 is installed in the electric cylinder mounting slot at the bottom of the electric cylinder mounting beam 13 by a pin, and the rotating shaft end of the material rack mounting beam 14 is installed in the pin slot at the top of the electric cylinder mounting beam 13 by a pin. The telescopic end of the rollover electric cylinder 15 is connected to the electric cylinder mounting slot in the middle of the material rack mounting beam 14 by a pin. The material rack 11 is fixed to the material rack mounting beam 14 by rivets, and the material safety lock buckle 12 is fixed to the middle of the crossbeam of the aircraft main beam 1 by screws. The body shell 16 is fixed to the aircraft main beam 1 by a shell mounting support.
[0029] Before the plane takes off, the remote control is used to control the rollover electric cylinder to keep the material rack horizontal, the materials are placed on the material rack, and the material safety buckles are locked in the material safety locks of the plane. The plane takes off and transports the materials to the destination. The destination does not have the conditions for landing, and the materials need to be airdropped. The flight control equipment controls the rollover electric cylinder to shorten according to the ground airdrop command, and the telescopic end of the electric cylinder drives the material rack to tilt downward. When the material rack tilts to the angle that meets the sliding angle of the materials, it stops tilting, and the flight control controls the material safety lock to unlock. The materials slide down along the slope of the material rack, and the materials reach the ground by parachuting or other means to complete the airdrop.
[0030] The two electric cylinder mounting beams are installed in the middle part of the crossbeam of the aircraft main beam by screws and welding, and are installed front and back. The fixed end of the rollover electric cylinder is installed in the electric cylinder mounting slot at the bottom of the electric cylinder mounting beam by a pin, and the rotating shaft end of the material rack mounting beam is installed in the pin slot at the top of the electric cylinder mounting beam by a pin. The telescopic end of the rollover electric cylinder is connected to the electric cylinder mounting slot in the middle part of the material rack mounting beam by a pin. The material rack is fixed to the material rack mounting beam by rivets, and the material safety lock is fixed to the middle part of the crossbeam of the aircraft main beam by screws.
[0031] The transport rotor UAV has a set of material loading, transport and airdrop devices on each side of the aircraft's main beam. The material rack is used to carry and transport materials. The transport rotor UAV can carry materials for takeoff and landing, and can also airdrop materials at target points that do not have landing conditions. When the aircraft is loaded with materials for takeoff, flight transportation, and landing, the material rack is in a normal horizontal state, and the material safety rope is locked by the aircraft's material safety lock. Materials need to be loaded and unloaded manually. When the aircraft encounters an emergency airdrop that does not meet the landing conditions, the flight control equipment controls the rollover electric cylinder to drive the material rack to tilt downward according to the ground airdrop command, and the material safety lock is unlocked. The materials slide down along the slope of the material rack to complete the airdrop.
[0032] The basic principle, main features and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, and these changes and improvements all fall within the scope of the protection required.
Claims
1. A transport rotor drone, It is characterized in that The unmanned aerial vehicle comprises an aircraft main beam (1), an I-shaped beam body is connected below the aircraft main beam (1), a material rack mounting beam (14) is hingedly connected above the I-shaped beam body, a rollover electric cylinder (15) is hingedly mounted below the I-shaped beam body, the rollover electric cylinder (15) is tiltedly mounted and the end of the cylinder shaft at its end is hingedly connected to the material rack mounting beam (14), and a material rack (11) is fixed on the material rack mounting beam (14).
2. A transport rotor drone as claimed in claim 1, It is characterized in that The aircraft main beam (1) is in an inverted T-shape, and the three landing gears (2) are arranged in a triangular shape, wherein one landing gear (2) is installed at the bottom of the front end of the crossbeam of the aircraft main beam (1), and two landing gears (2) are installed at the bottom surface of the middle part of the crossbeam of the aircraft main beam (1).
3. A transport rotor drone as claimed in claim 2, It is characterized in that The tail wing (3) is mounted on the tail of the crossbeam of the main beam (1), the engine (4) is mounted on the middle of the vertical beam of the aircraft main beam (1) through a transfer mounting structure, the output shaft of the engine (4) is mounted with a forward propeller (5), the rotor head (6) is mounted on the top of the vertical beam of the aircraft main beam (1), and the rotor (7) is mounted in the propeller clamp of the rotor head (6).
4. A transport rotor drone as claimed in claim 3, It is characterized in that The fuel tank (8) is mounted on the aircraft main beam (1) via a fuel tank support beam, the flight control equipment box (9) is mounted on the aircraft main beam (1) via a fuel tank support beam, and the optoelectronic pod (10) is mounted at the bottom of the front end of the crossbeam of the aircraft main beam (1).
5. A transport rotor drone as claimed in claim 4, It is characterized in that Two electric cylinder mounting beams (13) are mounted on the middle of the crossbeam of the aircraft main beam (1) by screws and welding, and are mounted front and rear respectively. The fixed end of the rollover electric cylinder (15) is mounted in the electric cylinder mounting slot at the bottom of the electric cylinder mounting beam (13) by a latch, and the rotating shaft end of the material rack mounting beam (14) is mounted in the latch slot at the top of the electric cylinder mounting beam (13) by a latch. The telescopic end of the rollover electric cylinder (15) is connected to the electric cylinder mounting slot in the middle of the material rack mounting beam (14) by a latch.
6. A transport rotor drone as claimed in claim 5, It is characterized in that The material rack (11) is fixed to the material rack mounting beam (14) by rivets, the material safety lock buckle (12) is fixed to the middle part of the crossbeam of the aircraft main beam (1) by screws, and the fuselage shell (16) is fixed to the aircraft main beam (1) by shell mounting struts.
7. A transport rotor drone as claimed in claim 6, It is characterized in that The housing (16) includes a space for placing items.