Ducted aircraft cabin cover structure

Abstract

A ducted aircraft cabin cover structure comprises an aircraft body, a plurality of ducted drivers are fixedly connected to the two sides of the aircraft body, an aircraft cabin is arranged in the aircraft body, a cabin cover is hinged to the upper portion of the aircraft cabin in a turnover mode, a blocking cover is detachably arranged on the cabin cover, a goods shelf is detachably arranged in the aircraft cabin, and the blocking cover is in coupling linkage with the upper portion of the goods shelf. The detachable blocking cover is arranged and can be installed on the bin cover frame, when goods are loaded and after the bin cover is opened, the blocking cover is opened at the same time, when the bin cover is closed, the blocking cover covers the upper portion of the goods shelf at the same time, goods can be prevented from flying out of the interior of the goods shelf to be separated, bin cover glass cannot be damaged, meanwhile, the blocking cover does not need to be disassembled at first when the goods are loaded and unloaded every time, and time and labor are saved. And the working efficiency is improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and more specifically to a ducted aircraft canopy structure. Background Technology

[0002] Aircraft can be classified into fixed-wing, rotary-wing, and ducted-wing types according to their functions. Ducted-wing aircraft are currently the most advanced type of aircraft. Most ducted-wing aircraft are currently single-tube ducted-wing aircraft, which are only suitable for low-altitude, low-speed flight. Due to limitations in the power of a single engine and rotational inertia, the load-bearing capacity of single-tube ducted-wing aircraft cannot be significantly improved, and their structure is relatively complex. Multi-body ducted-wing aircraft have a relatively strong load-bearing capacity. Manned ducted-wing aircraft mostly adopt a multi-body ducted-wing design. The applicant has a new technology that allows ducted-wing aircraft to switch between carrying passengers and cargo by changing the seats or racks in the cabin. However, during subsequent research and development, it was discovered that when changing racks to carry cargo, due to the instability of the internal straps, the center of gravity of the racks can easily shift or the cargo can detach from the racks. This could cause the ducted-wing aircraft to tip over and detach during flight maneuvers, or even damage the cabin glass, posing a safety hazard. Utility Model Content

[0003] One advantage of this invention is that it provides a ducted aircraft cargo hold structure with a detachable cover that can be installed on the edge of the cargo hold. When loading cargo, the cover is opened and simultaneously lifted. When closing the cargo hold, the cover covers the upper part of the shelf, preventing goods from flying out of the shelf and damaging the cargo hold glass. It also eliminates the need to remove the cover every time loading or unloading, thus improving work efficiency.

[0004] To achieve at least one of the above advantages of this utility model, this utility model provides a ducted aircraft canopy structure, including a fuselage, several ducted drive units fixedly connected to both sides of the fuselage, a canopy arranged inside the fuselage, a canopy cover hinged to the upper part of the canopy in a folding manner, a cover detachably provided on the canopy cover, and a rack detachably provided inside the canopy, with the cover and the upper part of the rack coupled together.

[0005] According to one embodiment of the present invention, the compartment cover includes a frame that is hinged to the body, and a glass cover is coupled to the frame.

[0006] According to one embodiment of the present invention, the cover includes a frame, a sealing plate is provided inside the frame, a push-button latch is provided between the frame and the frame and is detachably connected by the push-button latch, the lock body of the push-button latch is fixedly installed on the inner side of the frame edge, and the lock core of the push-button latch is fixedly installed at the corresponding position of the frame.

[0007] According to one embodiment of the present invention, four limiting rods are fixedly provided at the lower end of the frame, and limiting grooves are opened at corresponding positions of the shelf. The limiting rods correspond to the limiting grooves and are connected in a detachable manner.

[0008] According to one embodiment of the present invention, the two limiting grooves at the front end of the shelf have a front opening structure, which allows the two limiting rods at the front of the frame to slide in. The two limiting grooves at the rear end of the shelf have an arc-shaped guide groove at the front, and the guide groove is adapted to the travel path of the ends of the two limiting rods at the rear of the frame.

[0009] According to one embodiment of the present invention, the sealing plate is located between the glass cover and the shelf. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the structure of this utility model;

[0011] Figure 2 This is an enlarged schematic diagram of the bin cover of this utility model;

[0012] Figure 3 This is a perspective view of the sealing structure of this utility model;

[0013] Figure 4 This is a bottom view of the sealing structure of this utility model;

[0014] In the attached diagram: 1. Body, 2. Duct drive, 3. Compartment cover, 4. Push-button latch, 5. Cover, 6. Limit bar, 7. Shelf, 8. Limit groove, 9. Guide groove. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of this utility model clearer, the following description will be provided in conjunction with the appendix of this utility model. Figure 1 ~Attached Figure 4 The present invention will be described in more detail below.

[0016] The following description is intended to disclose the present invention so that those skilled in the art can implement it. The preferred embodiments described below are merely examples, and other obvious variations will occur to those skilled in the art. The basic principles of the present invention defined in the following description can be applied to other embodiments, modifications, improvements, equivalents, and other technical solutions that do not depart from the spirit and scope of the present invention.

[0017] Those skilled in the art should understand that, in the disclosure of this specification, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limitations on this utility model.

[0018] It is understood that the term "a" should be understood as "at least one" or "one or more", that is, in one embodiment, the number of an element can be one, while in another embodiment, the number of the element can be multiple, and the term "a" should not be understood as a limitation on the number.

[0019] This utility model provides a ducted aircraft canopy structure 3, including a fuselage 1, with several ducted drive units 2 fixedly connected to both sides of the fuselage 1. A canopy is located inside the fuselage 1, and a canopy 3 is hinged to the upper part of the canopy in a folding manner. A cover 5 is detachably mounted on the canopy 3. A rack 7 is detachably mounted inside the canopy, and the cover 5 is coupled to the upper part of the rack 7. The canopy 3 includes a frame hinged to the fuselage 1, and a glass cover is coupled to the frame. The cover 5 includes a frame, with a sealing plate inside the frame. A push-button latch 4 is provided between the frame and the frame, and the cover 5 is detachably mounted via the push-button latch 4. The frame is connected in a push-button lock 4, with the lock body fixedly installed on the inner side of the frame edge and the lock cylinder fixedly installed on the corresponding position of the frame. Four limiting rods 6 are fixedly installed at the lower end of the frame, and limiting grooves 8 are opened at the corresponding positions of the shelf 7. The limiting rods 6 and the limiting grooves 8 correspond to each other and are detachably connected. The two limiting grooves 8 at the front end of the shelf 7 have a front opening structure, which allows the two limiting rods 6 at the front of the frame to slide in. The two limiting grooves 8 at the rear end of the shelf 7 have an arc-shaped guide groove 9 at the front, which is adapted to the travel path of the ends of the two limiting rods 6 at the rear end of the frame. The sealing plate is located between the glass cover and the shelf 7.

[0020] The first embodiment of this utility model is as follows:

[0021] The ducted jet aircraft canopy structure 3 comprises a fuselage 1, with four fixedly connected mounting positions for ducted drive units 2 on both sides. These mounting positions support a lift drive system arranged in a two-dimensional, planar layout, consisting of four ducted drive units 2. Each ducted drive unit 2 is equipped with at least one permanent magnet synchronous motor and an FOC controller. The FOC controller is responsible for adjusting the flux linkage and torque of the permanent magnet synchronous motor, enabling the ducted drive unit 2 to rotate and thus change the direction of the driving force. This design allows the ducted jet aircraft to perform takeoff, landing, and flight operations. During vertical takeoff, all modules of the lift drive system remain horizontal, with all four modules rotating synchronously on the same horizontal plane, generating lift in a vertically downward direction. During level flight, the modules of the lift drive system are tilted, with all four modules rotating at similar tilt angles, generating lift tilted diagonally backward. Through precise force analysis, the UAV can maintain a constant altitude while flying forward. When the ducted jet aircraft is hovering, the modules of the lift drive system also remain horizontal, with all four modules rotating on the same horizontal plane, generating lift in a vertically downward direction.

[0022] Inside fuselage 1, batteries are configured to power the motors of ducted drive 2 via a power management system. Fuselage 1 also houses a control system, which includes a flight controller and multiple independent control computers. These computers utilize non-volatile computer-readable storage media containing one or more sets of computer instructions executable by the control computers to control the operation of the ducted aircraft.

[0023] The fuselage 1 has a machine compartment inside. The upper part of the machine compartment is hinged to the cover 3 by a folding mechanism. The cover 3 includes a frame that is hinged to the fuselage 1. The rear part of the frame is connected to the fuselage 1 by a hinge. There are latches at the front and middle of the frame that automatically lock after the cover 3 is closed. The latches are existing technology and will not be described in detail here. A glass cover is coupled to the frame.

[0024] A cover 5 is detachably installed on the cover 3. The cover 5 includes a frame, the cross-sectional shape of which is the same as that of the frame. The outer surface of the frame contacts the inner surface of the frame. A push-button latch 4 is installed between the frame and the frame and is detachably connected. The lock body of the push-button latch 4 is fixedly installed on the inner edge of the frame, and the lock cylinder of the push-button latch 4 is fixedly installed at the corresponding position on the frame. During installation, simply align the lock cylinder on the frame with the lock body on the frame, insert the cover 5 completely and press it to install it on the frame. A sealing plate is installed inside the frame. The sealing plate is located between the glass cover and the shelf 7. The sealing plate can be of two types: one is a frame structure with a hollowed-out design made of aluminum alloy, which can effectively achieve a lightweight effect; the second is a single sealing plate without hollowed-out design, which provides better protection.

[0025] The interior of the cabin is equipped with a detachable rack 7. The cover 5 is coupled to the upper part of the rack 7. Four limit rods 6 are fixedly installed at the lower end of the frame. The rack 7 has corresponding limit grooves 8. The limit rods 6 correspond to the limit grooves 8 and are detachably connected. When the cover 3 is closed, the limit rods 6 will slide into the limit grooves 8. At this time, the rear side of the limit rods 6 contacts the inner edge of the limit grooves 8, and the bottom end of the limit rods 6 abuts against the bottom surface of the limit grooves 8. When combined with the fixing device of the rack 7, the rack 7 and the cover 5 can be integrated into one, and the stability of both is stronger.

[0026] Since the movement trajectory of the limit rod 6 is curved when the cover 3 is opened and closed, the two limit grooves 8 at the front end of the shelf 7 are open on the front side, which allows the two limit rods 6 at the front side of the frame to slide in. The two limit grooves 8 at the rear end of the shelf 7 are provided with arc-shaped guide grooves 9 at the front. The guide grooves 9 are connected to the limit grooves 8, and the guide grooves 9 are adapted to the walking path of the ends of the two limit rods 6 at the rear side of the frame.

[0027] The length and depth of the limiting rod 6 and the limiting groove 8 can be changed according to the actual situation. In order not to interfere with the goods loaded in the shelf 7, the length of the limiting rod 6 can be shortened so that its travel trajectory will not affect the loaded goods.

[0028] During the flight of the ducted aircraft, even if the ducted aircraft flips and the cargo detaches, it will only collide with the cover 5 and will not damage the glass cover.

[0029] It should be noted that the terms "first, second, and third" used in this utility model are for descriptive purposes only and do not indicate any order. They should not be construed as indicating or implying relative importance, and can be interpreted as names.

[0030] Those skilled in the art should understand that the embodiments of the present invention described above and shown in the accompanying drawings are merely examples and do not limit the present invention. The advantages of the present invention have been fully and effectively realized. The functional and structural principles of the present invention have been shown and explained in the embodiments. Without departing from the principles, the implementation of the present invention may have any modifications or variations.

Claims

1. A ducted aircraft cabin cover structure comprising a fuselage, the two sides of the fuselage are fixedly connected with a plurality of ducted drives, characterized in that: The machine body is internally provided with a machine compartment, a compartment cover is hingedly connected to the upper portion of the machine compartment in a folding manner, a cover is detachably arranged on the compartment cover, a goods shelf is detachably arranged in the machine compartment, and the cover is coupled and linked to the upper portion of the goods shelf.

2. The nacelle cover structure according to claim 1, characterized in that: The compartment cover comprises a frame connected to the machine body in a hinged manner, and a glass cover body is coupled to the frame.

3. The ducted aircraft bay cover structure of claim 2, wherein: The cover comprises a frame, an enclosing plate is arranged in the frame, a press-type lock is arranged between the frame and the enclosing plate and detachably connects the frame and the enclosing plate, a lock body of the press-type lock is fixedly installed on the inner side of the edge of the frame, and a lock core of the press-type lock is fixedly installed at a corresponding position of the frame.

4. The ducted aircraft bay cover structure of claim 3, wherein: Four limiting rods are fixedly arranged at the lower end of the frame, limiting grooves are formed at corresponding positions of the goods shelf, and the limiting rods are correspondingly and detachably connected to the limiting grooves.

5. The ducted aircraft bay cover structure of claim 4, wherein: Two limiting grooves at the front end of the goods shelf are front-side opening structures, and the two limiting rods at the front side of the frame can slide into the two limiting grooves, arc-shaped guide grooves are formed at the front portion of the two limiting grooves at the rear end of the goods shelf, and the guide grooves are adapted to the running paths of the end portions of the two limiting rods at the rear side of the frame.

6. The ducted aircraft bay cover structure of claim 3, wherein: The enclosing plate is arranged between the glass cover body and the goods shelf.

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