Suspension cabin structure of six-rotor aircraft

Abstract

The utility model discloses a six-rotor aircraft's suspension cabin structure, including aircraft body, undercarriage, fixed column, mounting seat, mounting groove, connecting plate, suspension cabin body, clamping plate and fastening bolt, the lower side of aircraft body is equipped with the support seat, the both sides of support seat are equipped with undercarriage, the fixed column is equipped with the mounting groove, connecting plate, suspension cabin body, clamping plate and fastening bolt. The two undercarriages are symmetrically arranged relative to the aircraft body, two fixing columns are arranged on the lower side of the supporting base, a mounting base is arranged at the ends, away from the supporting base, of the two fixing columns, a mounting groove is formed in the mounting base, a connecting plate is arranged in the mounting groove, and the size of the connecting plate is matched with that of the mounting groove. Two fastening bolts are arranged at the positions, close to the mounting groove, of the mounting base, clamping plates are arranged on the two fastening bolts, and the sizes of the two clamping plates are matched with the sizes of the fastening bolts. The hanging cabin is convenient and fast to mount and dismount, and articles in the hanging cabin are easier to take.

Description

Technical Field

[0001] The utility model relates to the technical field of rotorcraft equipment, and particularly relates to a suspension cabin structure of a six-rotor aircraft. Background Technique

[0002] Rotorcraft have functions such as vertical takeoff and landing and hovering. Compared with other rotorcraft, six-rotor aircraft have the advantages of large load capacity, stable flight, simple operation, and high fault tolerance. At present, they have been widely used in civil fields such as aerial photography and plant protection, and have broad application prospects in the military field.

[0003] During the use of existing rotorcraft, it is necessary to frequently disassemble and install the suspension cabin to take the items inside the suspension cabin, which not only consumes manpower and material resources, but also multiple disassembly and installation may cause damage to the suspension cabin and affect subsequent use. Therefore, the utility model proposes a suspension cabin structure of a six-rotor aircraft to solve the above problems. Content of the Utility Model

[0004] The purpose of the utility model is to provide a suspension cabin structure of a six-rotor aircraft to solve the problems raised in the above background technique.

[0005] To achieve the above purpose, the utility model provides the following technical solution: A suspension cabin structure of a six-rotor aircraft, including an aircraft body, landing gears, fixed columns, mounting seats, mounting grooves, connecting plates, a suspension cabin body, clamping plates, and fastening bolts. A support seat is provided on the lower side of the aircraft body, landing gears are provided on both sides of the support seat, and the two landing gears are symmetrically arranged relative to the aircraft body. Two fixed columns are provided on the lower side of the support seat, and mounting seats are provided at the ends of the two fixed columns away from the support seat. An mounting groove is provided in the mounting seat, a connecting plate is provided in the mounting groove, the size of the connecting plate is adapted to the size of the mounting groove, two fastening bolts are provided at the position of the mounting seat close to the mounting groove, clamping plates are provided on both of the two fastening bolts, and the sizes of the two clamping plates are adapted to the sizes of the fastening bolts.

[0006] Preferably, a fixed block is provided on the lower side of the connecting plate, a suspension cabin body is provided on the side of the fixed block away from the connecting plate, an adjusting frame is provided on one side of the suspension cabin body, a receiving groove is provided in the adjusting frame, a baffle is provided in the receiving groove, and a fixed vertical plate is provided on the lower side of the baffle.

[0007] Preferably, a fixed horizontal plate is provided on the lower side of the fixed vertical plate, the size of the fixed horizontal plate is adapted to the size of the fixed vertical plate, a lifting rod is provided on the fixed horizontal plate, and the end of the lifting rod away from the fixed horizontal plate is fixedly connected to the suspension cabin body.

[0008] Preferably, an electric push rod is provided on the inner wall of the hanging cabin body. One end of the electric push rod away from the hanging cabin body is fixedly connected with a push plate, and the size of the push plate is adapted to the size of the hanging cabin body.

[0009] Compared with the prior art, the beneficial effects of the present utility model are as follows: The installation and disassembly method of the present utility model is convenient and fast, and it is simpler to take the items in the hanging cabin. Through the installation groove and the connecting plate, it is ensured that the disassembly of the hanging cabin body is simpler. Through the baffle and the push plate, it is ensured that it is not necessary to disassemble the hanging cabin body when taking the items in it, which is more convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 is the overall structural schematic diagram of the present utility model;

[0011] Figure 2 is the sectional structural schematic diagram of the present utility model;

[0012] Figure 3 is the partial structural decomposition schematic diagram of the present utility model.

[0013] In the figure: 1, aircraft body; 2, landing gear; 3, fixed column; 4, mounting seat; 5, installation groove; 6, connecting plate; 7, hanging cabin body; 8, clamping plate; 9, fastening bolt; 10, support seat; 11, fixed block; 12, adjustment frame; 13, baffle; 14, fixed vertical plate; 15, fixed horizontal plate; 16, lifting rod; 17, electric push rod; 18, push plate. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0014] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present utility model.

[0015] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "vertical", "upper", "lower", "horizontal", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model 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 should not be construed as a limitation of the present utility model.

[0016] In the description of the present utility model, it should also be noted that unless otherwise clearly defined and limited, the terms "arranged", "installed", "connected", and "coupled" 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, and it can be the communication inside two components. 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.

[0017] Please refer to Figures 1-3 , the present utility model provides a technical solution: a suspension cabin structure of a six-rotor aircraft, including an aircraft body 1, landing gears 2, fixed columns 3, mounting seats 4, mounting grooves 5, connecting plates 6, a suspension cabin body 7, clamping plates 8, and fastening bolts 9. A support seat 10 is provided on the lower side of the aircraft body 1. Landing gears 2 are provided on both sides of the support seat 10. The two landing gears 2 are symmetrically arranged relative to the aircraft body 1. Two fixed columns 3 are provided on the lower side of the support seat 10. Mounting seats 4 are provided at one ends of the two fixed columns 3 away from the support seat 10. Mounting grooves 5 are provided in the mounting seats 4. Connecting plates 6 are provided in the mounting grooves 5. The size of the connecting plates 6 is adapted to the size of the mounting grooves 5. Two fastening bolts 9 are provided at positions of the mounting seats 4 close to the mounting grooves 5. Clamping plates 8 are provided on both of the two fastening bolts 9. The size of the two clamping plates 8 is adapted to the size of the fastening bolts 9.

[0018] In this embodiment, a fixed block 11 is provided on the lower side of the connecting plate 6. A suspension cabin body 7 is provided on one side of the fixed block 11 away from the connecting plate 6. An adjusting frame 12 is provided on one side of the suspension cabin body 7. A receiving groove is provided in the adjusting frame 12. A baffle 13 is provided in the receiving groove. A fixed vertical plate 14 is provided on the lower side of the baffle 13.

[0019] In this embodiment, a fixed horizontal plate 15 is provided on the lower side of the fixed vertical plate 14. The size of the fixed horizontal plate 15 is adapted to the size of the fixed vertical plate 14. A lifting rod 16 is provided on the fixed horizontal plate 15. One end of the lifting rod 16 away from the fixed horizontal plate 15 is fixedly connected to the suspension cabin body 7.

[0020] In this embodiment, an electric push rod 17 is provided on the inner wall of the suspension cabin body 7. A push plate 18 is fixedly connected to one end of the electric push rod 17 away from the suspension cabin body 7. The size of the push plate 18 is adapted to the size of the suspension cabin body 7.

[0021] Working principle: The staff aligns the connecting plate 6 with the installation groove 5 according to the usage, and then installs it. Rotate the fastening bolt 9 so that the clamping plate 8 fastens the connecting plate 6. Then, send the suspension cabin body 7 to the required position through the aircraft body 1, and make the baffle 13 move downward relative to the adjustment frame 12 through the lifting rod 16. Then, make the push plate 18 send out the items in the suspension cabin body 7 through the electric push rod 17.

[0022] It should be noted that: The entire device is controlled through the main control button. Since the devices matched with the control button are common devices and belong to the existing mature technologies, the electrical connection relationship and the specific circuit structure are not described herein again.

[0023] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A suspension cabin structure of a six-rotor aircraft, characterized in that It includes an aircraft body (1), landing gears (2), fixed columns (3), mounting seats (4), mounting grooves (5), connecting plates (6), suspension cabin bodies (7), clamping plates (8) and fastening bolts (9). A support seat (10) is provided on the lower side of the aircraft body (1). Landing gears (2) are provided on both sides of the support seat (10). The two landing gears (2) are symmetrically arranged relative to the aircraft body (1). Two fixed columns (3) are provided on the lower side of the support seat (10). Mounting seats (4) are provided at the ends of the two fixed columns (3) far away from the support seat (10). Mounting grooves (5) are provided in the mounting seats (4). Connecting plates (6) are provided in the mounting grooves (5). The size of the connecting plate (6) is adapted to the size of the mounting groove (5). Two fastening bolts (9) are provided at positions of the mounting seat (4) close to the mounting groove (5). Clamping plates (8) are provided on both of the fastening bolts (9). The size of the two clamping plates (8) is adapted to the size of the fastening bolts (9).

2. The suspension cabin structure of a six-rotor aircraft according to claim 1, characterized in that: A fixed block (11) is provided on the lower side of the connecting plate (6). A suspension cabin body (7) is provided on the side of the fixed block (11) far away from the connecting plate (6). An adjustment frame (12) is provided on one side of the suspension cabin body (7). A receiving groove is provided in the adjustment frame (12). A baffle (13) is provided in the receiving groove. A fixed vertical plate (14) is provided on the lower side of the baffle (13).

3. The suspension cabin structure of a six-rotor aircraft according to claim 2, characterized in that: A fixed horizontal plate (15) is provided on the lower side of the fixed vertical plate (14). The size of the fixed horizontal plate (15) is adapted to the size of the fixed vertical plate (14). A lifting rod (16) is provided on the fixed horizontal plate (15). The end of the lifting rod (16) far away from the fixed horizontal plate (15) is fixedly connected to the suspension cabin body (7).

4. The suspension cabin structure of a six-rotor aircraft according to claim 2, characterized in that: An electric push rod (17) is provided on the inner wall of the suspension cabin body (7). A push plate (18) is fixedly connected to the end of the electric push rod (17) far away from the suspension cabin body (7). The size of the push plate (18) is adapted to the size of the suspension cabin body (7).

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