Modularized nose of rotorcraft

Abstract

The modular nose is installed on the front portion of a cabin body of the rotorcraft and comprises an equipment cabin, a balance weight cabin, a nose expansion cabin and a nose pod, the balance weight cabin is fixedly connected to the front portion of the equipment cabin, the equipment cabin is arranged in the cabin body of the rotorcraft in a sleeved mode, and the nose expansion cabin and the nose pod are arranged on the upper portion and the lower portion of the front end of the balance weight cabin respectively; the front part of the balance weight cabin is provided with a mounting notch for embedding the nose expansion cabin; and the tops of the balance weight cabin and the nose expansion cabin and the top of the rotorcraft cabin body jointly form a flat top surface. The counterweight cabin is arranged at the nose position, so that the gravity center distribution of the rotorcraft can be adjusted, and the rotorcraft is more stable in the flying process. And moreover, the modular nose design is adopted, the equipment cabin, the counterweight cabin, the nose expansion cabin and the nose pod are concentrated at the front part of the rotorcraft at an extremely high space utilization rate, and the rotorcraft is greatly convenient to assemble and overhaul while the top is kept flat.

Description

Technical Field

[0001] The invention relates to the field of autogyro aviation technology, in particular to a modular nose of a gyroplane. Background Art

[0002] An autogyro (or gyroplane for short) is a rotorcraft that uses its own rotating rotor as a lifting surface and propeller push / pull or other energy supply methods as forward propulsion. It has the characteristics of simple structure, high safety and low cost. The rotor of the autogyro relies on the forward flow during flight to achieve self-rotation to provide lift.

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

[0004] The Chinese invention with patent number 202222664395.8 proposes an aircraft with a foldable nose. The Chinese invention with patent number 202011593768.6 proposes a new multi-purpose autogyro. The avionics system of this type of design is relatively scattered. In addition, the center of gravity of the autogyro needs to be adjusted before flight. The traditional method is to add a heavy object to the nose. The pre-flight preparation of this method is more cumbersome. Summary of the invention

[0005] In order to solve the above problems, an object of the present invention is to provide a modular nose of a rotorcraft, in which an avionics system and components for center of gravity adjustment are modularly integrated into the nose of the rotorcraft.

[0006] The following scheme is adopted in the embodiment of the present invention: a modular nose of a rotorcraft is installed at the front part of the rotor cabin body, including an equipment cabin, a counterweight cabin, a nose expansion cabin and a nose pod, the counterweight cabin is fixedly connected to the front part of the equipment cabin, the equipment cabin is mounted in the rotor cabin body, the nose expansion cabin and the nose pod are respectively arranged at the upper and lower parts of the front end of the counterweight cabin; an installation notch is provided at the front part of the counterweight cabin for burying the nose expansion cabin, and the top of the counterweight cabin and the nose expansion cabin and the top of the rotor cabin body together form a flat top surface.

[0007] Preferably, the equipment compartment includes an equipment mounting frame, a counterweight connecting plate, a battery compartment shell, avionics equipment, avionics batteries and an equipment compartment shell; the two battery compartment shells are arranged in parallel, the front sides of the two battery compartment shells are connected to one side of the counterweight connecting plate, and the other side of the counterweight connecting plate is fixedly connected to the counterweight compartment, and the inner sides of the two battery compartment shells are provided with slide rails for the installation of the equipment mounting frame, the avionics equipment is placed on the equipment mounting frame, and the avionics batteries are arranged in the battery compartment shell, and several parallel slide rails are arranged on the outer sides of the two battery compartment shells, and the equipment mounting frame, the counterweight connecting plate and the battery compartment shell together constitute a whole and slide inside the equipment compartment shell, and the equipment compartment shell is arranged inside the rotor cabin body.

[0008] Preferably, a ballast water tank is arranged in the ballast cabin, a water inlet and a water outlet are respectively arranged at the top and bottom of the ballast water tank, a wiring groove is recessed at the front of the ballast water tank, a circular notch is opened at the bottom of the ballast cabin, a circular mounting plate is arranged in the circular notch, and the bottom of the circular mounting plate is provided for the installation of the nose pod.

[0009] Preferably, there are two parallel wiring grooves on the top of the counterweight water tank.

[0010] Preferably, a keel notch is recessed on the top of the equipment compartment shell and is used to limit the internal keel of the rotorcraft.

[0011] Preferably, the nose pod is an optoelectronic pod.

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

[0013] The present invention provides a modular nose of a rotorcraft. Compared with the prior art, the present invention has at least the following technical effects: the present invention sets a counterweight compartment at the nose position, which is conducive to adjusting the center of gravity distribution of the rotorcraft and making it more stable during flight. When loading different cargoes, a cargo unmanned autorotor often needs to adjust the position of the weight center of gravity through a counterweight compartment so that it meets the flight requirements.

[0014] In addition, the present invention adopts a modular nose design, which concentrates the equipment compartment, counterweight compartment, nose expansion compartment and nose pod at the front of the rotorcraft with extremely high space utilization, while keeping the top flat, greatly facilitating the assembly and maintenance of the rotorcraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a front view of the present invention;

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

[0017] Figure 3 is a structural exploded view of the present invention;

[0018] Figure 4 It is a front view of the counterweight water tank of the present invention;

[0019] Figure 5 It is a bottom view of the photoelectric pod installed in the present invention;

[0020] Figure 6 It is a bottom view of the present invention installing the pan-tilt camera.

[0021] Explanation of reference numbers: Equipment compartment-1, counterweight compartment-2, nose expansion compartment-3, nose pod-4, installation gap-30, equipment mounting frame-11, counterweight connecting plate-12, battery compartment shell-13, avionics equipment-14, avionics battery-15, equipment compartment shell-16, counterweight water tank-21, water inlet-22, water outlet-23, circular mounting plate-40, keel gap-10, optoelectronic pod-41, gimbal camera-42. DETAILED DESCRIPTION

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

[0023] See also Figures 1 to 6 A modular nose of a rotorcraft is installed at the front of a rotorcraft cabin body, and includes an equipment cabin 1, a counterweight cabin 2, a nose expansion cabin 3 and a nose pod 4. The counterweight cabin 2 is fixedly connected to the front of the equipment cabin 1, and the equipment cabin 1 is set in the rotorcraft cabin body. The nose expansion cabin 3 and the nose pod 4 are respectively arranged at the upper and lower parts of the front end of the counterweight cabin 2; an installation notch 30 for burying the nose expansion cabin 3 is provided at the front of the counterweight cabin 2, and the top of the counterweight cabin 2 and the nose expansion cabin 3 and the top of the rotorcraft cabin body together form a flat top surface.

[0024] The present invention arranges the ballast compartment 2 at the nose position, which is beneficial to adjusting the center of gravity distribution of the rotorcraft, making it more stable during flight. When loading different cargoes, the cargo unmanned autogyro often needs to adjust the position of the weight center of gravity through the ballast compartment 2 so that it meets the flight requirements.

[0025] In addition, the present invention adopts a modular nose design, which concentrates the equipment compartment 1, the counterweight compartment 2, the nose expansion compartment 3 and the nose pod 4 at the front of the rotorcraft with extremely high space utilization, while keeping the top flat, greatly facilitating the assembly and maintenance of the rotorcraft.

[0026] Different mission requirements may have different requirements on the capacity, material, etc. of the counterweight cabin 2. The counterweight cabin 2 can be quickly disassembled and replaced, and the counterweight cabin module can be upgraded according to technological development without the need for large-scale transformation of the entire UAV. For example, for artificial rainmaking models, the counterweight cabin 2 is not needed, and air defense radar and other components can be installed in the counterweight cabin 2, which has excellent scalability.

[0027] The equipment compartment 1 comprises 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; two battery compartment shells 13 are arranged in parallel, the front sides of the two battery compartment shells 13 are connected to one side of the counterweight connecting plate 12, and the other side of the counterweight connecting plate 12 is fixedly connected to the counterweight compartment 2, and the inner sides of the two battery compartment shells 13 are 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, and the avionics battery 15 is arranged in the battery compartment shell 13. Several parallel slide rails are arranged on the outer sides of the two battery compartment shells 13, and the equipment mounting frame 11, the counterweight connecting plate 12 and the battery compartment shell 13 together constitute an integral sliding arrangement inside the equipment compartment shell 16, and the equipment compartment shell 16 is sleeved in the rotorcraft cabin body. The equipment compartment 1 is highly integrated, and the equipment compartment 1 is sleeved in the rotorcraft body as a whole, and expensive electronic devices such as the avionics equipment 14 can have a more stable working environment, extending the service life of the avionics equipment 14.

[0028] The counterweight tank 2 is provided in the counterweight cabin 2. A water inlet 22 and a water outlet 23 are provided at the top and bottom of the counterweight tank 21, respectively. A wiring groove is provided at the front of the counterweight tank 21. A circular notch is provided at the bottom of the counterweight cabin 2. A circular mounting plate 40 is provided in the circular notch. The bottom of the circular mounting plate 40 is provided for the nose pod 4 to be installed. By adding water / waterproofing the counterweight tank 21, the center of gravity of the rotorcraft can be quickly adjusted. In winter, antifreeze can be added to the water.

[0029] There are two parallel wiring grooves on the top of the counterweight water tank 21. The wiring grooves are for facilitating the wiring of different expansion modules.

[0030] The top of the equipment compartment shell 16 is concavely provided with a keel notch 10 for limiting the keel inside the rotorcraft.

[0031] The nose pod 4 can be rotatably installed with an optoelectronic pod 41, a gimbal camera 42, a night vision device and other equipment according to the flight mission.

[0032] Several points should be explained: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, and can be mechanical or electrical connections, or internal connectivity between two components, or direct connections. "Up", "down", "left", "right", etc. are only used to indicate relative position relationships. When the absolute position of the object being described changes, the relative position relationship may change.

[0033] Secondly: In the drawings of the embodiments disclosed in the present invention, only the structures related to the embodiments disclosed in the present invention are involved, and other structures can refer to the usual design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

[0034] Finally, the above is only a preferred implementation of the present invention. The protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention.

Claims

1. A modular nose of a rotorcraft, mounted at the front of a rotorcraft cabin, characterized in that: The invention comprises an equipment cabin (1), a counterweight cabin (2), a nose expansion cabin (3) and a nose pod (4); the counterweight cabin (2) is fixedly connected to the front of the equipment cabin (1); the equipment cabin (1) is sleeved in a rotor cabin body; the nose expansion cabin (3) and the nose pod (4) are respectively arranged at the upper and lower parts of the front end of the counterweight cabin (2); a mounting notch (30) for burying the nose expansion cabin (3) is provided at the front of the counterweight cabin (2); the tops of the counterweight cabin (2) and the nose expansion cabin (3) and the top of the rotor cabin body together form a flat top surface.

2. The modular nose of a rotorcraft according to claim 1, characterized in that: The equipment compartment (1) comprises an equipment mounting frame (11), a counterweight connecting plate (12), a battery compartment shell (13), avionics equipment (14), avionics batteries (15) and an equipment compartment shell (16); the two battery compartment shells (13) are arranged in parallel, the front sides of the two battery compartment shells (13) are connected to one side of the counterweight connecting plate (12), and the other side of the counterweight connecting plate (12) is fixedly connected to the counterweight compartment (2); the inner sides of the two battery compartment shells (13) are 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 batteries (15) are arranged in the battery compartment shell (13), and a plurality of parallel slide rails are arranged 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 shell (13) together constitute an integral body slidably arranged inside the equipment compartment shell (16), and the equipment compartment shell (16) is sleeved in the rotor cabin body.

3. The modular nose of a rotorcraft according to claim 1, characterized in that: A counterweight water tank (21) is arranged in the counterweight cabin (2), a water inlet (22) and a water outlet (23) are arranged at the top and bottom of the counterweight water tank (21), a wiring groove is arranged in the front of the counterweight water tank (21), a circular notch is arranged at the bottom of the counterweight cabin (2), a circular mounting plate (40) is arranged in the circular notch, and the bottom of the circular mounting plate (40) is used for mounting the nose pod (4).

4. The modular nose of a rotorcraft according to claim 3, characterized in that: The top of the counterweight water tank (21) is also provided with two parallel wiring grooves.

5. The modular nose of a rotorcraft according to claim 2, characterized in that: The top of the equipment compartment shell (16) is concavely provided with a keel notch (10) for limiting the keel inside the rotorcraft.

6. The modular nose of a rotorcraft according to claim 1, characterized in that: The nose pod (4) is a photoelectric pod (41).

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

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