Modular nose of a gyroplane

Abstract

The utility model relates to a kind of modularization nose of gyroplane, install in the front of gyroplane cabin, including equipment cabin, counterweight cabin, nose expansion cabin and nose hanging cabin, counterweight cabin is fixedly connected in the front of equipment cabin, equipment cabin is sleeved in gyroplane cabin, nose expansion cabin and nose hanging cabin are respectively arranged in the upper portion and lower portion of the front end of counterweight cabin;Installation gap for nose expansion cabin embedding is opened in the front of counterweight cabin, the top of counterweight cabin and nose expansion cabin and the top of gyroplane cabin jointly constitute a flat top surface.The utility model sets up counterweight cabin in nose position, it is favorable to adjust the gravity center distribution of gyroplane, so that it is more stable in flight process.Moreover, the utility model uses modularization nose design, equipment cabin, counterweight cabin, nose expansion cabin and nose hanging cabin are concentrated in the front of gyroplane with very high space utilization, while maintaining the top flat, greatly facilitate the assembly and overhaul of gyroplane.

Description

Technical Field

[0001] This utility model relates to the field of autogyro aviation technology, and in particular to a modular nose section for an autogyro. Background Technology

[0002] An autogyro (or simply autogyro) is a type of rotorcraft that uses an autorotating rotor as its lifting surface and propeller thrust / pull or other power sources for forward propulsion. It is characterized by its simple structure, high safety, and low cost. The rotor of an autogyro relies on the airflow in front of it to rotate and generate lift.

[0003] The existing internal structure design of rotorcraft has a relatively decentralized avionics system.

[0004] Chinese utility model patent number 202222664395.8 proposes an aircraft with a foldable nose. Chinese utility model patent number 202011593768.6 proposes a novel multi-purpose autogyro. The avionics systems in these designs are relatively dispersed. Furthermore, autogyros require pre-flight center-of-gravity adjustment, traditionally achieved by adding weight to the nose. This method makes pre-flight preparation quite cumbersome. Utility Model Content

[0005] To address the aforementioned problems, the purpose of this invention is to provide a modular nose section for a rotorcraft, which modularly integrates the avionics system and center-of-gravity adjustment components into the rotorcraft nose section.

[0006] The present invention is implemented using the following scheme: a modular nose section of a rotorcraft is installed at the front of the rotorcraft cabin, including an equipment compartment, a counterweight compartment, a nose extension compartment, and a nose pod. The counterweight compartment is fixedly connected to the front of the equipment compartment, which is fitted inside the rotorcraft cabin. The nose extension compartment and the nose pod are respectively located at the upper and lower parts of the front end of the counterweight compartment. An installation notch for embedding the nose extension compartment is provided at the front of the counterweight compartment. The top of the counterweight compartment and the nose extension compartment together with the top of the rotorcraft cabin form a flat top surface.

[0007] Preferably, the equipment bay includes an equipment mounting frame, a counterweight connecting plate, a battery bay shell, avionics equipment, avionics batteries, and the equipment bay shell itself. Two battery bay shells are arranged in parallel, with their front sides connected to one side of the counterweight connecting plate. The other side of the counterweight connecting plate is used for the fixed connection of the counterweight bay. The inner sides of the two battery bay shells are provided with slide rails for the equipment mounting frame to mount. Avionics equipment is placed on the equipment mounting frame, and avionics batteries are installed inside the battery bay shells. Several parallel slide rails are provided on the outer sides of the two battery bay shells. The equipment mounting frame, counterweight connecting plate, and battery bay shell together form a whole that slides inside the equipment bay shell, which is fitted inside the rotorcraft cabin.

[0008] Preferably, a counterweight water tank is provided inside the counterweight compartment. The top and bottom of the counterweight water tank are respectively provided with a water inlet and a water outlet. A cable routing groove is recessed at the front of the counterweight water tank. A circular notch is opened at the bottom of the counterweight compartment, and a circular mounting plate is provided inside the circular notch. The bottom of the circular mounting plate is used for the installation of the nose pod.

[0009] Preferably, the top of the counterweight water tank also has two parallel cable trays.

[0010] Preferably, the top of the equipment cabin is recessed with a keel notch for limiting its position within the rotorcraft's internal keel.

[0011] Preferably, the nose pod is an electro-optical pod.

[0012] Preferably, the nose pod is a gimbal camera.

[0013] This invention provides a modular nose section for a rotorcraft. Compared to existing technologies, this invention offers at least the following technical advantages: By placing a counterweight compartment at the nose position, this invention facilitates adjustments to the rotorcraft's center of gravity distribution, resulting in greater stability during flight. Cargo unmanned autorotor aircraft often require a counterweight compartment to adjust the center of gravity when loading different cargoes, thereby ensuring the aircraft meets flight requirements.

[0014] Furthermore, this utility model adopts a modular nose design, which concentrates the equipment compartment, counterweight compartment, nose extension compartment and nose pod at the front of the rotorcraft with extremely high space utilization, greatly facilitating the assembly and maintenance of the rotorcraft while keeping the top flat. Attached Figure Description

[0015] Figure 1 This is the front view of this utility model;

[0016] Figure 2 This is a side view of the present invention;

[0017] Figure 3 This is an exploded view of the structure of this utility model;

[0018] Figure 4 This is a front view of the counterweight water tank of this utility model;

[0019] Figure 5 This is a bottom view of the installation of the photoelectric pod in this utility model;

[0020] Figure 6 This is a bottom view of the camera mounted on the gimbal in this utility model.

[0021] Labeling Explanation: Equipment Cabin-1, Counterweight Cabin-2, Nose Extension Cabin-3, Nose Pod-4, Installation Notch-30, Equipment Mounting Rack-11, Counterweight Connecting Plate-12, Battery Cabin Shell-13, Avionics Equipment-14, Avionics Battery-15, Equipment Cabin Shell-16, Counterweight Water Tank-21, Water Inlet-22, Water Outlet-23, Circular Mounting Plate-40, Keel Notch-10, Optoelectronic Pod-41, Gimbal Camera-42. Detailed Implementation

[0022] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0023] Please see Figures 1 to 6 A modular nose section for a rotorcraft is installed at the front of the rotorcraft fuselage. It includes an equipment compartment 1, a counterweight compartment 2, a nose extension compartment 3, and a nose pod 4. The counterweight compartment 2 is fixedly connected to the front of the equipment compartment 1, and the equipment compartment 1 is fitted inside the rotorcraft fuselage. The nose extension compartment 3 and the nose pod 4 are respectively located at the upper and lower parts of the front end of the counterweight compartment 2. An installation notch 30 is provided at the front of the counterweight compartment 2 for the nose extension compartment 3 to be installed. The top of the counterweight compartment 2 and the nose extension compartment 3 together with the top of the rotorcraft fuselage form a flat top surface.

[0024] This invention places the counterweight compartment 2 at the nose position, which facilitates the adjustment of the rotorcraft's center of gravity distribution, making it more stable during flight. When loading different cargo, cargo unmanned autorotor aircraft often need to use the counterweight compartment 2 to adjust the position of the center of gravity to meet flight requirements.

[0025] Furthermore, this utility model adopts a modular nose design, which concentrates the equipment compartment 1, counterweight compartment 2, nose extension compartment 3 and nose pod 4 at the front of the rotorcraft with extremely high space utilization, greatly facilitating the assembly and maintenance of the rotorcraft while maintaining a flat top.

[0026] Different mission requirements may have different requirements for the capacity and materials of the counterweight compartment 2. The counterweight compartment 2 can be quickly disassembled and replaced, and the counterweight compartment module can be upgraded according to technological development without large-scale modification of the entire UAV. For example, in artificial rainmaking models, the counterweight compartment 2 is not required, so components such as air search radar can be installed inside the counterweight compartment 2, which has excellent scalability.

[0027] The equipment bay 1 includes an equipment mounting frame 11, a counterweight connecting plate 12, a battery compartment shell 13, avionics equipment 14, avionics batteries 15, and an equipment bay shell 16. Two battery compartment shells 13 are arranged in parallel, with their front sides connected to one side of the counterweight connecting plate 12. The other side of the counterweight connecting plate 12 is used for the fixed connection of the counterweight bay 2. The inner sides of the two battery compartment shells 13 are provided with slide rails for mounting the equipment mounting frame 11. The avionics equipment 14 is placed on the equipment mounting frame 11, and the avionics batteries 15 are housed inside the battery compartment shells 13. Several parallel slide rails are provided on the outer sides of the two battery compartment shells 13. The equipment mounting frame 11, the counterweight connecting plate 12, and the battery compartment shells 13 together form a whole and slide inside the equipment bay shell 16, which is fitted inside the rotorcraft fuselage. The highly integrated equipment bay 1, and its integral placement within the rotorcraft fuselage, provides a more stable working environment for expensive electronic components such as the avionics equipment 14, extending the service life of the avionics equipment 14.

[0028] The counterweight compartment 2 is equipped with a counterweight water tank 21. The top and bottom of the counterweight water tank 21 are respectively equipped with a water inlet 22 and a water outlet 23. A cable routing groove is recessed at the front of the counterweight water tank 21, and a circular notch is formed at the bottom of the counterweight compartment 2. A circular mounting plate 40 is installed within the circular notch, and the bottom of the circular mounting plate 40 is used for mounting the nose pod 4. By adding / removing water from the counterweight water tank 21, the center of gravity of the rotorcraft can be quickly adjusted. In winter, antifreeze can be added to the water.

[0029] The top of the counterweight water tank 21 also has two parallel cable routing channels. These channels are for facilitating the routing of cables for installing different expansion modules.

[0030] The top of the equipment cabin 16 is recessed with a keel notch 10 for limiting the position of the keel inside the rotorcraft.

[0031] The nose pod 4 can be rotatably equipped with devices such as an optoelectronic pod 41, a gimbal camera 42, and a night vision device during flight missions.

[0032] Several points should be noted: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installation", "connection" and "linkage" should be interpreted broadly, and can be mechanical or electrical connection, or internal connection between two components, or direct connection. "Up", "down", "left", "right", etc. are only used to indicate relative positional relationship. When the absolute position of the described object changes, the relative positional relationship may change.

[0033] Secondly: The accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this utility model can be combined with each other.

[0034] Finally, the above description is only a preferred embodiment of the present utility model. The protection scope of the present utility model is not limited to the above embodiments. All technical solutions that fall within the scope of the present utility model are protected by the present utility model.

Claims

1. A modular nose of a gyroplane, installed in the front part of the cabin of the gyroplane, characterized in that: It includes an equipment compartment (1), a counterweight compartment (2), a nose extension compartment (3), and a nose pod (4). The counterweight compartment (2) is fixedly connected to the front of the equipment compartment (1). The equipment compartment (1) is fitted inside the rotor cabin. The nose extension compartment (3) and the nose pod (4) are respectively located at the upper and lower parts of the front end of the counterweight compartment (2). An installation notch (30) is opened at the front of the counterweight compartment (2) for the nose extension compartment (3) to be installed. The top of the counterweight compartment (2) and the nose extension compartment (3) together with the top of the rotor cabin form a flat top surface.

2. The modular nose section of a rotorcraft according to claim 1, characterized in that: The equipment compartment (1) includes an equipment mounting frame (11), a counterweight connecting plate (12), a battery compartment shell (13), avionics equipment (14), avionics battery (15), and an equipment compartment shell (16). The two battery compartment shells (13) are arranged in parallel, and the front side of each battery compartment shell (13) is connected to one side of the counterweight connecting plate (12). The other side of the counterweight connecting plate (12) is used for the counterweight compartment (2) to be fixedly connected. The inner side of the two battery compartment shells (13) is provided with slide rails for the equipment mounting frame (11) to be installed. The avionics equipment (14) is placed on the equipment mounting frame (11). The avionics battery (15) is installed inside the battery compartment shell (13). Several parallel slide rails are provided on the outer side of the two battery compartment shells (13). The equipment mounting frame (11), the counterweight connecting plate (12), and the battery compartment shell (13) together form an integral part that slides inside the equipment compartment shell (16). The equipment compartment shell (16) is fitted inside the rotor cabin.

3. The modular nose section of a rotorcraft according to claim 1, characterized in that: The counterweight compartment (2) is equipped with a counterweight water tank (21). The top and bottom of the counterweight water tank (21) are respectively equipped with a water inlet (22) and a water outlet (23). A cable tray is recessed at the front of the counterweight water tank (21). A circular notch is opened at the bottom of the counterweight compartment (2). A circular mounting plate (40) is installed in the circular notch. The bottom of the circular mounting plate (40) is used for the installation of the nose pod (4).

4. The modular nose section of a rotorcraft according to claim 3, characterized in that: The top of the counterweight water tank (21) also has two parallel cable trays.

5. The modular nose section of a rotorcraft according to claim 2, characterized in that: The top of the equipment cabin (16) is recessed with a keel notch (10) for limiting the position of the keel inside the rotorcraft.

6. The modular nose section of a rotorcraft according to claim 1, characterized in that: The nose pod (4) is an electro-optical pod (41).

7. The modular nose section of a rotorcraft according to claim 3, characterized in that: The nose pod (4) is a gimbal camera (42).

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