CN117465669A

CN117465669A - Submersible aircraft

Info

Publication number: CN117465669A
Application number: CN202311444514.1A
Authority: CN
Inventors: 陈希; 陈永杰; 招启军; 朱清华; 杨帆; 费钟阳; 任斌武; 赵国庆; 马砾
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2023-11-01
Filing date: 2023-11-01
Publication date: 2024-01-30

Abstract

The invention provides a submersible aircraft, which comprises a fuselage and foldable wings, wherein the foldable wings are arranged on two sides of the fuselage, any one of the foldable wings comprises a fixed section connected with the fuselage and a folding section connected with the fixed section, the fixed section is provided with a first propeller, the tail of the fuselage is provided with an annular tail wing, a second propeller is arranged in the annular tail wing, the belly of the fuselage is provided with an booster which provides boosting force for the aircraft when the aircraft is in transit in the air by water, the first propeller is connected with the fixed section through a tilting mechanism, and/or the annular tail wing is provided with a vertical control surface and a horizontal control surface which can adjust angles, when the aircraft is switched from an underwater submersible mode to an air flight mode, the aircraft is in an overhead state under water, the second propeller and the booster provide power for the aircraft, and the aircraft can reach a take-off speed under water, so that the underwater submersible aircraft can realize quick take-off.

Description

Submersible aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a submersible aircraft.

Background

The cross-medium aircraft is influenced by the physical characteristics of two different mediums of water and air, the appearance structures of the aircraft and the aircraft are obviously different, the cross-medium aircraft is required to complete preset tasks in different medium environments such as adjacent space, high-low altitude, water-air crossing medium, underwater space and the like, therefore, the appearance structure is required to consider the flight performance in different medium environments, and the realization of autonomous deformation in different medium environments through a variable design is one of important ways for solving the problem;

when the existing known medium-crossing aircraft is submerged under water, water is stored in a water tank at the belly of a fuselage, the weight of the aircraft is increased to enable the aircraft to be submerged, when the aircraft is converted from a submerged state to a flying state, the water in the water tank is required to be released firstly, wings are adjusted to be in a flying state, the aircraft is enabled to gradually float out of the water surface, and then the aircraft is accelerated on the water surface and gradually reaches a take-off speed through the acceleration of a propeller, so that take-off is completed, the submerged aircraft in the prior art needs to undergo two processes of floating out of the water surface and accelerating on the water surface from the submerged state to the take-off state, and the process of switching the aircraft from the submerged state to the take-off state is very slow;

patent document CN106986023a discloses a submersible vehicle, comprising a fuselage, fin pontoons are arranged on two sides of the belly of the fuselage, a weight box is arranged at the front part of the fuselage, rotatable wings are arranged at the back part of the fuselage, duck wings are arranged at the front part of the fuselage, each duck wing consists of a first stabilizer and a first control surface, butterfly tails consisting of a second stabilizer and a second control surface are arranged on two sides of the tail part of the fuselage, when the submersible vehicle is changed into a state of a water vehicle, the weight of the weight box is reduced, the vehicle floats upwards, the wings are perpendicular to the longitudinal axis of the vehicle, the duck wings are rotated to a horizontal state orientation, the butterfly tails are rotated to a large dihedral orientation, the aircraft propellers of the wing tips of the butterfly tails work, the vehicle accelerates on the water surface, the wings can generate lift like the wings of a common vehicle, the aircraft can complete take-off, however, the aircraft still gradually floats out, the water surface accelerates again, the take-off of the vehicle can complete the take-off from the submersible state, and the process of the vehicle switched from the state to the state is still very slow.

Disclosure of Invention

The invention aims to provide a submersible vehicle so as to solve the problems in the prior art and enable the submersible vehicle to realize quick take-off.

In order to achieve the above object, the present invention provides the following solutions: the utility model provides a submersible vehicle, including fuselage and collapsible wing, collapsible wing sets up the fuselage both sides, arbitrary including on the collapsible wing with the fixed section of fuselage connection and with the folding section that the fixed section is connected, the fixed section is provided with first screw, the fuselage afterbody is provided with the annular fin, be provided with the second screw in the annular fin, the belly of fuselage is provided with by water transfer in the sky for the booster of aircraft provides the boost force, wherein, first screw through tilting mechanism with the fixed section is connected, and/or the annular fin is provided with vertical control surface and the horizontal control surface that can angle regulation.

Preferably, a semicircular duct is formed on one side, facing the front, of the fixed section of the foldable wing, and the first propeller is arranged in the semicircular duct.

Preferably, the connecting shaft is installed in the semicircular duct, the end part of the connecting shaft is connected with an output shaft of a propeller angle adjusting motor, the propeller angle adjusting motor is arranged inside the fixed section, the first propeller is fixedly connected with a driving motor which drives the first propeller to rotate, the driving motor is fixed on a support, the support is fixedly connected with the connecting shaft, and the propeller angle adjusting motor can drive the first propeller to tilt in the front-back direction of the aircraft.

Preferably, the end of the folded section remote from the fixed section is further provided with a wing tip winglet.

Preferably, a connecting section is installed between the fixed section and the folding section, the connecting section is hinged with the fixed section, and the connecting section is hinged with the folding section.

Preferably, the fixing section is hinged to the connecting section through a first hinge device, the first hinge device comprises a first protrusion arranged inside the fixing section and a first groove base arranged on one side of the connecting section, the first protrusion is connected with the first groove base through a first hinge, the first protrusion can be embedded into the first groove base, and when the first protrusion is embedded into the first groove base, the end part of the fixing section is attached to the end part of the connecting section.

Preferably, a first motor is arranged on one side of the fixing section, which is close to the end part of the connecting section, the first motor is arranged inside the fixing section, and an output shaft of the first motor is connected with the rotation center of the first groove base.

Preferably, the connecting section is hinged with the folding section through a second hinge device, the second hinge device comprises a second protrusion arranged inside the connecting section and a second groove base arranged on one side of the folding section, the second protrusion is connected with the second groove base through a second hinge, the second protrusion can be embedded into the second groove base, and when the second protrusion is embedded into the second groove base, the end part of the connecting section is attached to the end part of the folding section.

Preferably, a second motor is arranged on one side, close to the end part of the folding section, of the connecting section, the second motor is arranged inside the folding section, and an output shaft of the second motor is connected with the rotation center of the second groove base.

Preferably, a telescopic device is arranged in the machine body, and the telescopic device can drive the booster to stretch and retract into the machine body.

Compared with the prior art, the invention has the following technical effects:

when the aircraft is switched from the underwater diving mode to the air flight mode, the angle of the vertical control surface of the annular tail wing is adjusted, or the tilting angle of the first propeller is adjusted, or the vertical control surface of the annular tail wing and the tilting angle of the first propeller are adjusted at the same time, so that the aircraft can adjust the pitching direction under the water until the aircraft is in a pitching state under the water, the second propeller provides power for the aircraft, at the moment, the booster jets back to provide power for the aircraft, the annular tail wing can slow down the resistance of the aircraft diving under the water, the aircraft can accelerate rapidly under the water, the aircraft can reach the take-off speed under the water, and therefore, the underwater diving aircraft can directly enter the air flight mode when the aircraft is flushed out of the water, and the underwater diving aircraft can realize rapid take-off.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of the overall structure of the present invention;

FIG. 2 is a schematic view of a foldable wing of the present invention;

FIG. 3 is a schematic view of the ring tail and a second propeller of the present invention;

FIG. 4 is a schematic view of a first propeller mounting structure according to the present invention;

fig. 5 is a schematic view of a second hinge device according to the present invention.

The novel wing-mounted aircraft comprises a 1-fuselage, a 2-foldable wing, a 21-fixed section, a 22-folding section, a 23-wing tip winglet, a 24-connecting section, a 3-first propeller, a 31-connecting shaft, a 32-bracket, a 4-annular tail wing, a 5-booster, a 6-second propeller, a 71-second bulge, a 72-second groove base and a 73-second motor.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

The invention aims to provide a quick response aircraft, which solves the problems in the prior art and can enable an underwater submerged aircraft to realize quick take-off.

In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.

Referring to fig. 1, in this embodiment, a fast response aircraft is provided, including a fuselage 1 and foldable wings 2, the foldable wings 2 are symmetrically installed at two sides of the fuselage 1, the foldable wings 2 include a fixed section 21 and a folding section 22, the folding section 22 can be turned to the lower part of the fixed section 21, a first propeller 3 is provided at the fixed section 21, specifically, the first propeller 3 can be embedded in the fixed section, or can be directly provided at the outside of the fixed section, as a preferred mode, the first propeller 3 is embedded in the inside of the fixed section, the rotating part of the first propeller is exposed, referring to fig. 1, an annular tail wing 4 is provided at the tail of the fuselage 1, a second propeller 6 is provided in the inside of the annular tail wing 4, the annular tail wing 4 includes a vertical rudder surface and a horizontal rudder surface, and the first propeller 3 can also be connected with the fixed section 21 through a tilting mechanism, when the aircraft is submerged under water, pitch of the aircraft is controlled by controlling the angle of the vertical rudder surface, or by adjusting the angle of the first propeller 3 to make a sudden pitch angle of the first propeller 5, or by adjusting the angle of the first propeller 3 to make a sudden pitch of the aircraft and the second propeller 5 is provided by the aircraft under water, and the condition of the aircraft is advanced by the aircraft under water, and the plane is a small power of the aircraft is provided in the state of the nose aircraft, and the aircraft is advanced in the state of the second propeller is a thrust aircraft is a thrust of the aircraft, and the second aircraft is a small nose plane is a thrust of a lower than is a thrust aircraft, and can is a lower nose aircraft, and can is a thrust aircraft is a lower nose aircraft is a thrust aircraft is a lower thrust aircraft is a thrust aircraft;

when the aircraft switches from underwater creep mode to air flight mode: firstly, the aircraft is in a face upward flushing state, the folding section 22 is unfolded, the booster 5 starts to work, the booster 5 and the second propeller 6 provide power for the aircraft, the aircraft is accelerated rapidly under water, and when the aircraft flushes out of the water, the take-off speed is reached, so that the underwater submerged aircraft can take off rapidly.

The ring-shaped tail 4 has no influence of mutual interference of the conventional tail, the conventional tail layout can form complex airflow interaction at the tail, the efficiency and the instability can be reduced, and the design of the ring-shaped tail 4 can eliminate the interference and keep the stability of the tail airflow.

The booster 5 is a propeller which can be applied under water, in particular a propeller or an air pump, and the accelerating effect of the aircraft can be obviously improved through the action of the booster 5; the fuselage is preferably water-drop-shaped structure, and the annular tail wing of cooperation makes the aircraft whole be streamlined design, can show the resistance that reduces the aircraft and receive by itself when accelerating under water.

The first propeller 3 is a variable pitch propeller that can increase the pulling force by reducing the pitch angle of the rotor blades when the aircraft is taking off vertically.

A semicircular duct is arranged on one side, facing the front, of the fixed section of the foldable wing 2, and the first propeller 3 is arranged in the semicircular duct in a specific installation mode: install connecting axle 31 in semicircle form duct, end connection at connecting axle 31 has screw angle adjustment motor, screw angle adjustment motor sets up inside fixed section 21, screw angle adjustment motor's output shaft is connected with connecting axle 31, still include driving motor, driving motor and first screw 3 fixed connection, driving motor can drive first screw 3 self rotations, this driving motor fixed mounting is on support 32, support 32 is fixed on connecting axle 31, at screw angle adjustment motor during operation, screw angle adjustment motor is as the power take off of tilting mechanism, can drive connecting axle 31 rotation, because first screw 3 is fixed on connecting axle 31, thereby realize that first screw 3 is tilted along the aircraft fore-and-aft direction.

At the end of the folded section 22 is mounted a winglet 23, which winglet 23 is adjustable in the range-30 ° -45 °, by means of which winglet 23 the tip vortex of the folded section 22 can be reduced when the aircraft is in an airborne mode.

A connecting section 24 is arranged between the fixed section 21 and the folding section 22, which connecting section 24 is articulated to the fixed section 21, while the connecting section 24 is also articulated to the folding section 22.

The fixing section 21 is specifically hinged to the connecting section 24 through a first hinge device, and in one embodiment, the first hinge device includes a first protrusion disposed inside the fixing section, and a first groove base disposed on one side of the connecting section, and a first hinge is disposed between the first protrusion and the first groove base, and the first protrusion can be embedded into the first groove base, so that when the first protrusion is embedded into the first groove base, an end portion of the fixing section 21 is attached to an end portion of the connecting section 24.

The fixed section 21 is provided with first motor near one side of connecting section 24 tip, and first motor sets up in the inside of fixed section 21, and the output shaft of first motor is connected with the rotation center of first recess base.

The connecting section 24 is hinged to the folding section 22 by a second hinge means, which in one embodiment comprises a second protrusion 71 arranged inside the connecting section 24, a second groove seat 72 arranged at one side of the folding section 22, a second hinge being arranged between the second protrusion 71 and the second groove seat 72, the second protrusion 71 being capable of being embedded inside the second groove seat 72, and when the second protrusion 71 is embedded inside the second groove seat 72, the end of the connecting section 24 is in abutment with the end of the folding section 22.

A second motor 73 is arranged on one side of the connecting section 24, which is close to the end part of the folding section 22, the second motor 73 is arranged inside the connecting section 24, an output shaft of the second motor 73 is connected with the rotation center of the second groove base 72, and when the second motor 73 works, the second motor 73 drives the second groove base 72 to rotate, so that the second groove base 72 can move close to or far away from the second protrusion 71, and the connecting section 24 is attached to or detached from the folding section 22.

The contraction device is arranged in the fuselage and can drive the booster 5 to contract into the fuselage, and the principle of the contraction device is the same as that of a landing gear of the jet aircraft.

A method of cross-medium operation of a submersible vehicle comprising the steps of:

s1, a vertical take-off mode: the angle of forward tilting of the first propeller 3 to the front of the aircraft is 0 degrees, the pitch angle of the first propeller 3 is adjusted to be minimum, and the first propeller 3 is controlled to work so that the aircraft vertically takes off;

s2, an air flight mode: the first propeller 3 is made to tilt forward of the aircraft, the tilting angle can be 30 degrees, the booster 5 is contracted into the fuselage 1, the vertical control surface of the annular tail wing 4 is controlled, the aircraft is made to pitch, the horizontal control surface is controlled, the aircraft is made to yaw, meanwhile, the rotation speed difference of the left rotor wing and the right rotor wing of the first propeller 3 of the aircraft can be controlled, and the aircraft is further controlled to fly leftwards or rightwards, so that the yaw of the aircraft is realized;

s3, switching an air flight mode to an underwater diving mode: the forward tilting angle of the first propeller 3 is adjusted to be 0 degree, the vertical control surface angle is adjusted, the aircraft is in a diving state, then the folding section 22 of the wing and the wing tip winglet 23 are controlled to be folded, the aircraft is enabled to dive into water, and therefore the rapid water entering of the aerial aircraft is completed, the aircraft is enabled to be in a streamline design as a whole due to the design of the water drop of the aircraft body 1 and the design of the annular tail wing 4, the impact area of the aircraft when the aircraft enters water is reduced through the folding of the foldable wing, the aircraft can be enabled to dive into water rapidly, and the impact force born by the aircraft is small.

S4, underwater diving mode: the second propeller 6 operates to provide forward power to the aircraft and the first propeller 3 controls the ascent and descent of the aircraft.

S5, switching the underwater forward mode to an air flight mode: the booster 5 extends out of the aircraft body, the angle of the vertical control surface is adjusted, the aircraft is in a face-up state, the folding section 22 and the wing tip winglet 23 are unfolded, the booster 5 starts to work, the booster 5 and the second propeller 6 provide power for the aircraft, the aircraft is accelerated suddenly under water, and when the aircraft is flushed out of the water, the aircraft reaches a take-off speed, and quick take-off of the aircraft is completed.

The co-operation of the first propeller 3, the foldable wing 2 and the booster 5 enables the aircraft to be quickly switched between flight in the air, vertical take-off and landing, underwater creep, which enables the aircraft to have quick maneuvering capability when required to take-off and landing vertically or when no runway is required and when tasks are required to be performed in a complex environment in the ocean, and which is very effective in applications requiring quick deployment such as emergency rescue, fire rescue and search tasks due to the fact that the aircraft is not required to have complex take-off and landing facilities, the design of the fuselage 1 in the form of a water droplet, the shrinkage of the foldable wing 2 and the design of the annular tail 4 reduces the radar scattering area of the aircraft, reducing the probability that external details of the aircraft are detected.

It should be noted that it will be apparent to those skilled in the art that the present invention is not limited to the details of the above-described exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.

Claims

1. The utility model provides a submersible vehicle, its characterized in that, includes fuselage and collapsible wing, collapsible wing sets up the fuselage both sides, arbitrary including on the collapsible wing with the fixed section of fuselage connection and with the folding section that the fixed section is connected, the fixed section is provided with first screw, the fuselage afterbody is provided with the annular fin, be provided with the second screw in the annular fin, the belly of fuselage is provided with by water transfer when being aerial for the booster that the aircraft provided thrust, wherein, first screw through tilting mechanism with the fixed section is connected, and/or the annular fin is provided with vertical rudder face and the horizontal rudder face that can angle regulation.

2. The submersible vehicle of claim 1, wherein a side of the fixed section of the collapsible wing that faces forward is provided with a semicircular duct, the first propeller being disposed within the semicircular duct.

3. The submersible vehicle according to claim 2, wherein a connecting shaft is installed in the semicircular duct, the end of the connecting shaft is connected with an output shaft of a propeller angle adjusting motor, the propeller angle adjusting motor is arranged inside the fixed section, the first propeller is fixedly connected with a driving motor for driving the first propeller to rotate, the driving motor is fixed on a support, the support is fixedly connected with the connecting shaft, and the propeller angle adjusting motor can drive the first propeller to tilt in the front-rear direction of the vehicle.

4. The submersible vehicle of claim 1, wherein an end of the folded section remote from the stationary section is further provided with a winglet.

5. The submersible vehicle of claim 4, wherein a connecting section is mounted between the stationary section and the folding section, the connecting section being hinged to the stationary section, the connecting section being hinged to the folding section.

6. The submersible vehicle of claim 5, wherein the fixed segment is hinged to the connecting segment by a first hinge device, the first hinge device comprises a first protrusion disposed inside the fixed segment, and a first groove base disposed on one side of the connecting segment, the first protrusion is connected with the first groove base by a first hinge, the first protrusion can be embedded inside the first groove base, and when the first protrusion is embedded inside the first groove base, an end of the fixed segment is attached to an end of the connecting segment.

7. The submersible vehicle of claim 6, wherein a first motor is disposed on a side of the stationary segment adjacent the end of the connecting segment, the first motor being disposed within the stationary segment, an output shaft of the first motor being coupled to a center of rotation of the first recess base.

8. The submersible vehicle of claim 5, wherein the connecting section is hinged to the folding section by a second hinge device, the second hinge device comprises a second protrusion arranged inside the connecting section and a second groove base arranged on one side of the folding section, the second protrusion is connected with the second groove base by a second hinge, the second protrusion can be embedded inside the second groove base, and when the second protrusion is embedded inside the second groove base, the end of the connecting section is attached to the end of the folding section.

9. The submersible vehicle of claim 8, wherein a second motor is disposed on a side of the connecting section adjacent to the end of the folding section, the second motor being disposed inside the folding section, and an output shaft of the second motor being connected to a center of rotation of the second groove base.

10. The submersible vehicle of claim 1, wherein a telescoping device is provided within the fuselage, the telescoping device being capable of telescoping the booster into the fuselage interior.