CN108583875B

CN108583875B - General aircraft overall arrangement of diving

Info

Publication number: CN108583875B
Application number: CN201810486892.9A
Authority: CN
Inventors: 吴文华; 胡星志; 余雷; 段焰辉; 赵鹏; 杨伟
Original assignee: Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
Current assignee: Computational Aerodynamics Institute of China Aerodynamics Research and Development Center
Priority date: 2018-05-21
Filing date: 2018-05-21
Publication date: 2021-09-14
Anticipated expiration: 2038-05-21
Also published as: CN108583875A

Abstract

The invention discloses a submerged general aircraft layout, which comprises an aircraft body, wherein the aircraft body comprises an aircraft body front section and an aircraft body rear section, two folding fixed wings are symmetrically arranged on two side surfaces of the aircraft body front end respectively, vertical lifting devices are arranged on the folding fixed wings, a rotor wing for parallel propulsion is arranged right in front of the aircraft body front section, a horizontal tail and a vertical tail are arranged at the aircraft body rear end, and watertight compartments for floating up and sinking down in water are arranged on the aircraft body. The watertight compartment at the lower part of the engine room is beneficial to realizing the functions of repeated submergence and upward floating; the larger dihedral angle of the wings can enable the propeller of the vertical take-off and landing device to be separated from the water surface before starting, simultaneously provides rolling stability, can give consideration to high-speed and low-speed flight in the air, reduces the underwater impact load and underwater navigation resistance, can increase the water outlet speed, and completes the conversion of various motion states.

Description

General aircraft overall arrangement of diving

Technical Field

The invention relates to the field of cross-medium aircrafts, in particular to a general submerged aircraft layout.

Background

The submerged general aircraft (flying vehicle) is a new equipment capable of simultaneously meeting the requirements of flying or navigating in air, under water and on water, and has the characteristics of quick maneuvering of aircraft and high concealment of submarine, and has important significance for national economy, national defense science and technology and military application. The layout design of the general submerged aircraft is crucial, and the requirement of the general submerged aircraft for the design has better underwater performance and air performance at the same time, and the requirement is a new problem to be solved by fluid mechanics. The density difference between water and air is 800 times, the viscosity coefficient difference is about 100 times, the Reynolds numbers differ by one magnitude, the buoyancy difference is 800 times, and the density, speed, Reynolds number and viscosity differences enable the layout of the general submerged aircraft to comprehensively consider the requirements of underwater navigation and air flight. However, with a good flight performance, the underwater navigation resistance may be too large; the layout with good underwater navigation performance may have poor air performance, so the layout scheme needs to solve the contradiction, and mainly solves the design problems of wing and fuselage configuration and layout mode.

In addition, when the submerged general aircraft enters the air from the water or enters the water from the air, the submerged general aircraft can encounter the problems of more complex two-phase flow, free surface and the like in the processes of taking off and landing, thereby influencing the attitude of the aircraft. When the submerged general aircraft is partially underwater and partially enters the air, the force and the moment acting on the submerged general aircraft are very complex and variable, and the attitude of the aircraft needs to be controlled well, so that not only is the exquisite design layout and the control surface controlled, but also a strong and ingenious control system is needed. The stress and moment of the submerged general aircraft in the process need to be comprehensively and accurately evaluated, which is always the difficult problem of computational fluid dynamics processing of the cross-medium aircraft, and the research through experiments is also very complex.

At present, documents about the layout of a submerged unmanned aerial vehicle disclosed at home and abroad are few, and a submerged unmanned aerial vehicle concept is provided, but the submerged unmanned aerial vehicle can only be a low-fusion submerged unmanned aerial vehicle, the submerged unmanned aerial vehicle does not have the underwater navigation capability, can only be launched from the water under water, is launched by a buoy, and basically does not contact with the water. Like cormorant submarine-launched unmanned aerial vehicle developed in the United states, the cormorant submarine-launched unmanned aerial vehicle is the most similar technical scheme reported at present, and the cormorant submarine-launched unmanned aerial vehicle adopts catapulting launching and vertical takeoff, can be folded on wings, can only leave water once, adopts a parachute to recover, does not have the function of repeatedly entering water, and does not have the function of navigating underwater or on the water surface.

Disclosure of Invention

One purpose of the invention is to provide a novel layout scheme of a general unmanned aerial vehicle for diving, which develops a controllable-motion and feasible-layout repeatable submerged general aircraft for diving, so that the aircraft has a more flexible medium-crossing flight/navigation mode;

the invention also aims to provide a submerged general aircraft layout which can ensure that the aircraft body keeps stable posture in the water inlet and outlet processes;

still another object of the present invention is to provide a general-purpose aircraft layout for diving which combines functions of vertical take-off and landing, air flight and underwater navigation. The hybrid power system is an oil-electricity integrated hybrid power system and comprises an aircraft engine (a turbojet engine or a piston type aircraft engine), a generator, a battery, a motor and a propeller.

In order to achieve the purpose, the invention adopts the following technical scheme:

the utility model provides a general aircraft overall arrangement of diving in air, includes the fuselage, the fuselage includes fuselage anterior segment and fuselage back end, the symmetry is provided with a folding stationary vane separately on the both sides face of fuselage front end, be provided with vertical lift device on the folding stationary vane, the dead ahead of fuselage anterior segment is provided with and is used for parallel propulsive rotor, the fuselage back end is provided with horizontal tail and vertical tail, be provided with the watertight bulkhead that is used for floating up and dive in aqueous on the fuselage.

In the above technical solution, the watertight compartment is disposed at a front section of the fuselage.

In the above technical solution, the front section of the body includes two independent cabin bodies, an instrument cabin disposed at an upper portion of the front section of the body, and a watertight compartment disposed at a lower portion of the front end of the body.

In the technical scheme, the rear section of the fuselage is of a tubular structure and plays a role in connection and support.

In the technical scheme, the rear section of the machine body is provided with a propeller device for underwater propulsion.

In the above technical solution, the folding fixed wing is an upper single wing with a dihedral angle.

In the technical scheme, the folding fixed wing comprises a wingtip winglet, a main wing and a wing root, and the wingtip winglet and the main wing are connected with the front section of the fuselage through the wing root.

In the above-described aspect, the winglet is folded inward of the main wing in the extending direction of the main wing.

In the above technical solution, a flap is provided on a trailing edge of the main wing.

In above-mentioned technical scheme, vertical lift device sets up between winglet, and vertical lift device includes the horizontal installed part and sets up the rotor of arranging at installed part both ends symmetry.

In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:

according to the general submerged aircraft layout, the aircraft body adopts a streamline design suitable for water flow and air flow, and resistance of air flight and underwater navigation can be reduced. The upper part of the cabin is isolated from water, so that the working reliability of parts, sensors and the like is better ensured, and the watertight compartment at the lower part of the cabin is favorable for realizing the functions of repeated submergence and upward floating;

according to the layout of the submerged general aircraft provided by the invention, the propellers of the vertical take-off and landing device can be separated from the water surface before being started by the aid of the larger dihedral angle of the wings, and meanwhile, rolling stability is provided. The underwater vehicle can not only give consideration to high-speed and low-speed flight in the air, reduce the underwater impact load and underwater navigation resistance, but also increase the water outlet speed and complete the conversion of various motion states;

according to the layout of the submerged general aircraft, the rotary wing type vertical take-off and landing device arranged on the wing generates pulling force, so that the aircraft body and the wing can be lifted off the water surface, and the submerged general aircraft can rapidly reach the take-off speed. The device can also be matched with a flap, a horizontal tail and a vertical tail to provide control force, and particularly, the device can keep the posture stability in the water inlet and outlet processes;

according to the general submerged aircraft layout provided by the invention, under the conditions of vertical take-off and landing, air flight and underwater navigation functions, the hybrid power system can provide good power and energy guarantee, so that the general submerged aircraft has a more flexible flight mode, and can further improve the flight efficiency and the energy utilization rate.

Drawings

The invention will now be described, by way of example, with reference to the accompanying drawings, in which:

FIG. 1 is a schematic layout view of a submerged general aircraft according to the present invention;

FIG. 2 is a central cross-sectional view of the configuration of the submerged general purpose aircraft of the present invention;

in the figure, 1, a fuselage, 11 is a front fuselage section, 12 is a rear fuselage section, 111 is an instrument cabin, and 112 is a watertight compartment; 2. wings, 21 wingtip winglet, 22 main wing, 23 flap and 24 wing root; 3. flattening the tail; 4. hanging a tail; 5. an underwater propeller; 6. the vertical lifting device is a rotor 61 and a mounting part 62; 7. a front end rotor.

Detailed Description

All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.

Example one

As shown in fig. 1 and 2, the overall layout of the aircraft is that the aircraft has a nearly cylindrical fuselage 1 which is streamline overall, wings 2 which are folded backwards and inwards on the outer side, a horizontal tail 3 and a vertical tail 4 which play a control role, an underwater propeller 5, a vertical take-off and landing device 6 and a front rotor 7.

The whole fuselage is divided into a fuselage front section and a fuselage rear section, the whole fuselage is linear, the fuselage front section is in a streamline design suitable for water flow and air flow, the fuselage front section comprises an instrument cabin and a watertight compartment, the instrument cabin isolated from water is used for installing onboard electronic equipment such as a power supply, a communication device and a sensor, and the watertight compartment can absorb water or drain water to complete submergence and floatation operations of the whole fuselage. The rear section of the body is a long tubular connecting and supporting piece, a lead and a signal wire can be laid in the connecting and supporting piece, and a horizontal tail, a vertical tail and an underwater propeller are arranged at the tail part of the connecting and supporting piece; the fuselage is also equipped with a front rotor to assist horizontal propulsion.

The design of the watertight compartment is adopted in the embodiment in a breakthrough manner, so that the floating and submerging of the whole aircraft in water are realized through the operation of the watertight compartment, and the mode that the traditional aircraft cannot freely lift underwater is changed; and through the underwater propeller arranged at the tail part of the aircraft body, the whole aircraft can move forward underwater, so that the aircraft can work in an underwater environment more concealably, and the defect that the existing aircraft cannot be concealed is increased.

In this embodiment, the wings are thin-walled wings with the outer sides folded backwards and inwards, are symmetrically arranged on two sides of the rear part of the front section of the fuselage, are upper single wings with large dihedral angles, and are composed of wingtips winglets, main wings and wing roots folded inwards, and are provided with trailing edge flaps, and the whole wing is connected with the fuselage through the wing roots. A vertical lifting device is arranged between the flap and the wingtip winglet and consists of symmetrically arranged rotors and a horizontal mounting piece. The vertical lifting device can work with the horizontal tail and the vertical tail in a coordinated mode to further achieve the effect of stabilizing the posture, and the horizontal tail and the vertical tail are provided with control surfaces.

In order to ensure that the aircraft can repeatedly enter water, go out water and be latent in water, a sealing design is adopted for two cabin bodies at the front section of the aircraft body, particularly an instrument cabin, the determined sealing of the instrument cabin is ensured, and the whole control system cannot be failed due to water entering; the design of watertight compartments not only needs to meet the requirements of submergence and floating, but also can deal with the water impact force.

In the embodiment, as the vertical upgrading and diving operations of the aircraft are realized, the main wing and the fuselage in the vertical lifting device are provided with larger dihedral angles, and the wingtip winglet is arranged by folding towards the horizontal position of the main wing, so that the rotor wing is ensured to be separated from the water surface before starting, the rolling stability is provided, the high-speed and low-speed flight in the air is considered, the underwater impact load and the underwater navigation resistance are reduced, and the conversion of the moving states of the flight and the underwater navigation is realized.

The control system which can be installed on the instrument cabin in the embodiment can realize the stability of pitching and yawing directions by controlling the control surfaces on the horizontal tail and the vertical tail, and can control the underwater propeller, the vertical take-off and landing device and the front-end rotor wing to form a hybrid power system, so that the whole machine has a more flexible flight mode, and the flight efficiency and the energy utilization rate can be further improved.

The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.

Claims

1. The layout of the submerged general aircraft is characterized by comprising an aircraft body, wherein the aircraft body comprises an aircraft body front section and an aircraft body rear section;

the front section of the fuselage comprises two mutually independent cabin bodies, an instrument cabin arranged at the upper part of the front section of the fuselage and a watertight bulkhead arranged at the lower part of the front end of the fuselage and used for floating and submerging in water, two folding fixed wings with dihedral angles are symmetrically arranged on two side surfaces of the front end of the fuselage respectively, and a rotor wing used for parallel propulsion is arranged right in front of the front section of the fuselage;

the folding fixed wing comprises a wingtip winglet, a main wing and a wing root, the wingtip winglet and the main wing are connected with the front section of the fuselage through the wing root, a vertical lifting device is arranged between the wingtip winglet and the wing flap, and the vertical lifting device comprises a horizontal mounting piece and rotor wings which are symmetrically arranged at two ends of the mounting piece;

the rear section of the machine body is of a tubular structure and plays a role in connection and support, and the rear end of the machine body is provided with a horizontal tail, a vertical tail and a propeller device for underwater propulsion.

2. A submerged general aircraft arrangement according to claim 1, characterised in that the winglet folds towards the inside of the main wing in the direction of extension of the main wing.

3. A submerged general-purpose aircraft arrangement according to claim 2, characterised in that the trailing edge of the main wing is provided with a flap.