CN114771830A

CN114771830A - Fuselage structure of cross-medium aircraft

Info

Publication number: CN114771830A
Application number: CN202210436295.1A
Authority: CN
Inventors: 谢炜程; 朱慧宁; 吴俊杰; 江炜; 郑琦; 刘坤; 魏然; 熊怀; 蒋丽丽
Original assignee: Shanghai Ases Spaceflight Technology Ltd
Current assignee: Shanghai Ases Spaceflight Technology Ltd
Priority date: 2022-04-25
Filing date: 2022-04-25
Publication date: 2022-07-22

Abstract

The invention discloses a fuselage structure of a cross-medium aircraft, which comprises a fuselage body, two wings, a connecting assembly and two driving pieces respectively corresponding to the two wings. The fuselage body is provided with two wing accommodating grooves along the length direction of the fuselage body, and the two wing accommodating grooves are respectively used for accommodating two wings. The aircraft body is movably connected with the two wings through the connecting assembly, the driving piece is fixedly connected with the aircraft body, and the output end of the driving piece is connected with the corresponding wing and used for driving the wings to fold or unfold. In a furled state, the wings are accommodated in the corresponding wing accommodating grooves and are used for underwater navigation, and the body and the two wings are matched with each other to form a rotating body shape for reducing water flow resistance. In the unfolded state, the wings are transversely unfolded relative to the fuselage body and are used for flying in the air, and the wings and incoming flow air form a proper attack angle to provide lift force.

Description

Fuselage structure of cross-medium aircraft

Technical Field

The invention belongs to the field of cross-medium aircrafts, and particularly relates to a fuselage structure of a cross-medium aircraft.

Background

The cross-medium aircraft has a unique application background, and can execute an underwater navigation task on one hand and play a role in scientific research and underwater patrol tasks; on the other hand, the flying robot can jump out of the water surface to fly in the air and perform tasks such as air patrol and the like.

The cross-medium aircraft has various purposes and can adapt to two environments, namely underwater environment and aerial environment. In the air flight, besides the power propulsion, the wing with the wing profile is required to generate the lift force. When navigating underwater, the cross-media vehicle preferably has a profile similar to a rotating body to reduce water flow resistance when navigating. However, there is currently no cross-media aircraft that is capable of achieving both air flight and underwater navigation.

Disclosure of Invention

In order to solve the problems, the invention provides a fuselage structure of a cross-medium aircraft.

The technical scheme of the invention is as follows:

a fuselage structure of a cross-medium aircraft comprises a fuselage body, two wings, a connecting assembly and two driving pieces which respectively correspond to the two wings;

the fuselage body is provided with two wing accommodating grooves along the length direction of the fuselage body, and the two wing accommodating grooves are respectively used for accommodating two wings; the fuselage body is movably connected with the two wings through the connecting component respectively, the driving piece is fixedly connected with the fuselage body, and the output end of the driving piece is connected with the corresponding wing and used for driving the wings to fold or unfold;

in a furled state, the wings are accommodated in the corresponding wing accommodating grooves and are used for underwater navigation, and the fuselage body and the two wings are mutually matched to form a rotating body shape and are used for reducing water flow resistance; in the unfolded state, the wings are transversely unfolded relative to the fuselage body and are used for flying in the air, and the wings and incoming flow air form a proper attack angle to provide lift force.

Preferably, a locking and unlocking mechanism is arranged between the fuselage body and the wings and used for locking the relative positions of the wings and the fuselage body in the unfolding state.

Preferably, the locking and unlocking mechanism includes:

the groove is arranged on the wing, and a clamping groove is arranged on the inner wall of the groove;

the convex block is arranged on the machine body, and a clamping block is connected to the convex block in a sliding manner; in the furled state, the convex block is accommodated in the groove, and the clamping block is clamped and locked with the groove;

an electric control part is arranged between the convex block and the clamping block and is used for controlling the sliding of the clamping block relative to the convex block.

Preferably, the connection assembly includes:

the rotating base is connected with the machine body in a sliding manner, and the sliding direction is the length direction of the machine body;

the two rotating pieces are respectively connected with the rotating base in a rotating mode, the two rotating axes are parallel to each other, and the plane where the two rotating pieces are located is perpendicular to the length direction of the fuselage body; the rotating pieces are rotatably connected with the corresponding wings, and the rotating axes of the rotating pieces are parallel to the length direction of the wings.

Preferably, the rotating base is connected with the machine body in a sliding manner through a limiting piece, the limiting piece is connected with the machine body in a sliding manner, and the sliding direction of the limiting piece is the same as the length direction of the machine body;

the limiting part is provided with a sliding block, the rotating base is provided with a sliding groove, the sliding block is connected in the sliding groove in a sliding mode, and the sliding direction is the same as the length direction of the machine body.

Preferably, the rotation axes of the rotating piece and the rotating base are positioning axes, and the plane where the two positioning axes are located is a positioning plane;

the rotating part is provided with a movable shaft, the axis of the movable shaft is parallel to the positioning axis, the limiting part is provided with a movable groove, the movable shaft is connected in the movable groove in a sliding mode, and the sliding direction is parallel to the positioning plane.

Preferably, the limiting piece is connected with the machine body through a fixing piece; the mounting with this body coupling of fuselage, be equipped with the slide bar on the locating part, be equipped with the slide bar hole on the mounting, slide bar sliding connection in the slide bar is downthehole, its slip direction with the length direction of fuselage body is the same.

Preferably, the driving piece is an electric control telescopic rod, the fixed end of the electric control telescopic rod is movably connected with the machine body, and the output end of the electric control telescopic rod is movably connected with the wings.

Preferably, the fixed end of the electric control telescopic rod is connected with the machine body through two serially connected revolute pairs, and the rotation axes of the two revolute pairs are perpendicular to each other;

the output end of the electric telescopic rod is rotatably connected with the wing, and the rotating axis of the electric telescopic rod is parallel to the rotating axis of the rotating pair which is close to the electric telescopic rod in the two rotating pairs.

Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:

according to the fuselage structure of the cross-medium aircraft, when the aircraft flies in the air, the driving piece drives the wings to unfold, and the wings and incoming flow air form a proper attack angle to provide lift force; when the underwater vehicle sails underwater, the driving piece drives the wings to be folded, the wings are contained in the wing containing grooves and matched with the vehicle body to form a rotating body shape, and water flow resistance is reduced.

Drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention.

Fig. 1 is a schematic structural view of a fuselage structure of a cross-medium aircraft according to the present invention in a collapsed state;

FIG. 2 is a schematic structural view of a fuselage structure of a cross-media aircraft of the present invention in a deployed state;

FIG. 3 is a partial structural schematic view of a fuselage structure of a cross-media aircraft of the present invention in a stowed configuration;

FIG. 4 is a schematic, fragmentary structural view of a fuselage structure of a cross-media aircraft of the present invention in a deployed state;

FIG. 5 is a schematic view of an airfoil according to the present invention;

FIG. 6 is a schematic view of a rotary member according to the present invention;

FIG. 7 is a schematic structural diagram of a position limiting element according to the present invention;

FIG. 8 is a schematic view of a rotary base according to the present invention;

FIG. 9 is a schematic view of a fastener of the present invention;

FIG. 10 is a schematic view of a mating connection of a wing and a rotating member of the present invention;

FIG. 11 is a schematic view of the cooperative engagement of a rotating member and a rotating base according to the present invention;

FIG. 12 is a schematic view of the connection between the rotating member and the limiting member according to the present invention;

FIG. 13 is a schematic view of the connection between the limiting element and the fixing element according to the present invention;

FIG. 14 is a schematic view of the connection between the rotating base and the limiting member according to the present invention;

FIG. 15 is a schematic view of the rotation of a coupling assembly of the present invention;

FIG. 16 is a schematic diagram of a bump structure according to the present invention;

FIG. 17 is a schematic view of a fastening plate of the present invention;

FIG. 18 is a schematic view of the mating connection of the wing and tab of the present invention;

FIG. 19 is a schematic structural view of an electrically controlled telescopic rod according to the present invention;

FIG. 20 is a schematic view of the electrical control telescopic rod and the main body of the electric control telescopic rod of the present invention;

FIG. 21 is a schematic view of the mating connection between the electrically controlled telescoping pole and the wing of the present invention;

FIG. 22 is a schematic view of the wing of the present invention just prior to deployment;

FIG. 23 is a schematic view of the present invention in a 30 wing deployment configuration;

FIG. 24 is a schematic view of the present invention in a 60 wing deployment configuration;

FIG. 25 is a schematic view of the present invention in a 90 wing deployment configuration;

FIG. 26 is a schematic view of the operation of the various structures of the present invention during wing deployment.

Description of the reference numerals:

1: a body of the machine body; 2: an airfoil; 21: a wing connecting groove; 22: a drive bit; 23: a groove; 3: a rotating member; 31: positioning the shaft; 32: a movable shaft; 33: a wing attachment hole; 4: rotating the base; 41: positioning the shaft hole; 42: a chute; 5: a limiting member; 51: a movable groove; 52: a slider; 53: a slide bar; 6: a fixing member; 61: a slide bar hole; 7: a bump; 71: a card slot; 8: a fixing plate; 9: an electric control telescopic rod.

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, without inventive effort, other drawings and embodiments can be derived from them.

For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. Moreover, in the interest of brevity and understanding, only one of the components having the same structure or function is illustrated schematically or designated in some of the drawings. In this document, "a" means not only "only one of this but also a case of" more than one ".

Referring to fig. 1 to 26, the present embodiment provides a fuselage structure of a cross-medium aircraft, which includes a fuselage body 1, two wings 2, a connecting assembly, and two driving members corresponding to the two wings 2. The fuselage body 1 is provided with two wing accommodating grooves along the length direction thereof, and the two wing accommodating grooves are respectively used for accommodating two wings 2. The aircraft body 1 is movably connected with the two wings 2 through the connecting components respectively, the driving parts are fixedly connected with the aircraft body 1, and the output ends of the driving parts are connected with the corresponding wings 2 and used for driving the wings 2 to fold or unfold.

In a furled state, the wings 2 are accommodated in the corresponding wing accommodating grooves and are used for underwater navigation, and the body 1 and the two wings 2 are mutually matched to form a rotator shape for reducing water flow resistance. In the unfolded state, the wings 2 are transversely unfolded relative to the fuselage body 1 for air flight, and the wings 2 form a proper attack angle with incoming air for providing lift force.

The structure of the present embodiment will now be explained.

In the fuselage structure of the cross-medium aircraft provided by the embodiment, in a furled state, the outer sides of the wings 2 and the fuselage body 1 are complementary to form a smooth, uniform and complete curved surface shape, as shown in fig. 1; in the unfolded state, the wing 2 has a wing-shaped structure, and can generate lift force through convection in the air to realize the flight of the aircraft, as shown in fig. 2.

In particular, the length of the wing 2 needs to be in a proper proportion to the fuselage body 1, and the wing 2 is provided with a corresponding wing profile, so that when the wing 2 is unfolded, the wing can provide enough lift for the aircraft. Through the mutual matching of the connecting component, the driving component and the like, the wing 2 can be fixed, rotated and moved on the corresponding degree of freedom, and finally the unfolding or folding state is achieved; and when the aircraft is in the unfolding state, the wings 2 are positioned at the upper part of the fuselage body 1 (relative to the aerial flight state), namely the aircraft is in an upper single-wing layout when the wings 2 are in the unfolding state, and the wing profiles of the wings 2 can form a proper attack angle with incoming air, so that the aircraft can generate enough lift force.

The connecting assembly comprises a rotating base 4, two rotating pieces 3 respectively corresponding to the two wings 2, a limiting piece 5 and a fixing piece 6. The rotating member 3 is provided with a positioning shaft 31, a movable shaft 32 and a wing connecting hole 33, the rotating base 4 is provided with two positioning shaft holes 41, and the positioning shaft 31 on the rotating member 3 is inserted into the corresponding positioning shaft hole 41 to realize the rotating connection between the rotating member 3 and the rotating base 4, as shown in fig. 11. The rotating axes of the rotating part 3 and the rotating base 4 are positioning axes which are parallel to each other, the plane where the two positioning axes are located is a positioning plane which is perpendicular to the length direction of the machine body 1.

The rotating base 4 is provided with a sliding groove 42, the limiting member 5 is provided with a sliding block 52, the sliding block 52 is slidably connected in the sliding groove 42, and the sliding direction is the same as the length direction of the machine body 1, as shown in fig. 14. The rotating member 3 is provided with a movable shaft 32, the axis of which is parallel to the positioning axis, the movable shaft 32 is slidably connected in the movable groove 51, and the sliding direction is parallel to the positioning plane, as shown in fig. 12. The fixing member 6 is connected to the main body 1, the limiting member 5 is provided with a sliding rod 53, the fixing member 6 is provided with a sliding rod hole 61, the sliding rod 53 is slidably connected to the inside of the sliding rod hole 61, and the sliding direction of the sliding rod 53 is the same as the length direction of the main body 1, as shown in fig. 13. The rotating member 3 is rotatably connected with the corresponding wing 2, specifically, a wing connecting groove 21 is arranged on the wing 2, a wing connecting hole 33 on the rotating member 3 is matched with the wing connecting groove 21, the rotating connection can be realized through structures such as a rotating shaft, and the rotating axis of the rotating member is parallel to the length direction of the wing 2, as shown in fig. 10. When the wing 2 drives the rotating member 3 to rotate, under the cooperation of the movable shaft 32 and the movable slot 51, the limiting member 5 is driven to move along the length direction of the fuselage body 1 under the limitation of the rotating base 4 and the fixing member 6.

A locking and unlocking mechanism is arranged between the fuselage body 1 and the wings 2 and used for locking the relative positions of the wings 2 and the fuselage body 1 in the unfolding state and simultaneously strengthening the structural strength of the fuselage body 1 and the wings 2 in the unfolding state. A specific locking and unlocking mechanism may include the groove 23 and the projection 7. The groove 23 is arranged on the wing 2, and a clamping groove 71 is arranged on the inner wall of the groove 23. The bump 7 is arranged on the machine body 1, and the bump 7 is connected with a clamping block in a sliding way. In a furled state, the protrusion 7 is accommodated in the groove 23 (the protrusion 7 and the groove 23 are not matched, and the volume of the groove 23 is larger than that of the protrusion 7, so that the groove 23 is conveniently buckled on the protrusion 7 in the movement process of the wing 2), and the clamping block is clamped and locked with the groove 23, as shown in fig. 18. An electric control part is arranged between the bump 7 and the fixture block and used for controlling the fixture block to slide relative to the bump 7, and when the wing 2 needs to be locked when being unfolded in place, the electric control part drives the fixture block to slide and stretch out to be clamped into the clamping groove 71 to realize clamping and locking; when the wing 2 needs to be folded, the electric control part drives the clamping block to slide and retract, and the clamping block is separated from the clamping groove 71 to be unlocked. Specifically, the electric control portion may be an electric telescopic rod or the like, as long as the fixture block can be extended and retracted relative to the projection 7 and can be fixed after being extended in place, which is not limited herein.

Because the structure of the convex block 7, the clamping block, the electric control part and the like needs to be arranged, the groove is formed in the machine body 1, and in order to enable the outer surface of the machine body 1 to be a complete curved surface as far as possible, the fixing plate 8 is arranged on the upper cover of the groove to seal the groove, and the through hole is formed in the fixing plate 8, so that the clamping block used for locking and part of the convex block 7 extend out. The outer curved surface of the fixing plate 8 is consistent with the shape curve of the machine body 1, and plays a role in maintaining the shape curve of the machine body 1 and the fixing lug 7.

Referring to fig. 19 to 21, the driving member may be an electrically controlled telescopic rod 9, a fixed end of the electrically controlled telescopic rod 9 is movably connected to the fuselage body 1, and an output end of the electrically controlled telescopic rod 9 is movably connected to the wing 2. In the present embodiment, the electric control telescopic rod 9 is driven by hydraulic pressure. The specific structure of the driving member or the specific driving manner of the electric control telescopic rod 9, etc., in other embodiments, other structures or driving manners may be adopted, which is not limited to this. The fixed end of the electric control telescopic rod 9 is connected with the machine body 1 through two serially connected revolute pairs, and the rotation axes of the two revolute pairs are mutually vertical. The wing 2 is provided with a driving position 22 which is used for being rotationally connected with the output end of the electric telescopic rod, and the rotation axis of the driving position is parallel to the rotation axis of the rotation pair which is close to the electric telescopic rod 9 in the two rotation pairs. Under the pushing action of the electric control telescopic rod 9, the wings 2 rotate to drive the rotating piece 3 to rotate.

Referring to fig. 22 to 26, taking the wing 2 as an example of unfolding, as shown in fig. 22, when the wing 2 is about to unfold, the electrically controlled telescopic rod 9 pushes up vertically, and at this time, the rotating member 3 does not rotate relative to the rotating base 4; as shown in fig. 23 and 24, the electric telescopic rod continues to extend out, and since the rotating member 3 and the wing 2 rotate in place and cannot rotate any more, the rotating member 3 starts to rotate relative to the rotating base 4 (simultaneously, the wing 2 is driven to rotate), the joint of the electric telescopic rod and the fuselage body 1 also starts to rotate, the electric telescopic rod starts to push obliquely, and simultaneously, the whole wing 2 is driven to move towards the tail of the fuselage body 1, and at this time, the rotating member 3 and the limiting member 5 are also driven to move towards the tail of the fuselage body 1; as shown in fig. 25, after the wing 2 is transversely unfolded in place, the electrically controlled telescopic rod 9 is driven to contract in a small range, the elevation angle of the wing 2 and the incoming air is adjusted, the groove 23 is covered on the projection 7 at the same time, the stretching of the electrically controlled telescopic rod 9 is stopped until the wing 2 is in place, and the fixture block on the driving projection 7 is clamped into the clamping groove 71 for locking.

The embodiments of the present invention have been described in detail with reference to the drawings, but the present invention is not limited to the embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.

Claims

1. The fuselage structure of the cross-medium aircraft is characterized by comprising a fuselage body, two wings, a connecting assembly and two driving pieces which respectively correspond to the two wings;

the fuselage body is provided with two wing accommodating grooves along the length direction of the fuselage body, and the two wing accommodating grooves are respectively used for accommodating two wings; the fuselage body is respectively movably connected with the two wings through the connecting component, the driving component is fixedly connected with the fuselage body, and the output end of the driving component is connected with the corresponding wings and used for driving the wings to fold or unfold;

2. The fuselage structure of the cross-media aircraft according to claim 1, wherein a locking and unlocking mechanism is provided between the fuselage body and the wing for locking the relative positions of the wing and the fuselage body in the deployed state.

3. The fuselage structure of the cross-media aircraft of claim 2, wherein the locking and unlocking mechanism comprises:

the groove is arranged on the wing, and a clamping groove is formed in the inner wall of the groove;

4. The fuselage structure of the cross-media aircraft of claim 1, wherein the connection assembly comprises:

the rotating base is connected with the machine body in a sliding mode, and the sliding direction is the length direction of the machine body;

5. The fuselage structure of the cross-media aircraft according to claim 4, wherein the rotating base is slidably connected to the fuselage body through a stopper, the stopper is slidably connected to the fuselage body, and a sliding direction of the stopper is the same as a length direction of the fuselage body;

6. The fuselage structure of the cross-media aircraft according to claim 5, characterized in that the axes of rotation of the swivel and the swivel base are positioning axes, and the plane of the two positioning axes is a positioning plane;

7. The fuselage structure of the cross-media aircraft according to claim 5, wherein the limiter and the fuselage body are connected by a fastener; the mounting with this body coupling of fuselage, be equipped with the slide bar on the locating part, be equipped with the slide bar hole on the mounting, slide bar sliding connection in the slide bar is downthehole, its slip direction with the length direction of fuselage body is the same.

8. The fuselage structure of the cross-media aircraft according to claim 1, wherein the driving member is an electrically controlled telescopic rod, a fixed end of the electrically controlled telescopic rod is movably connected with the fuselage body, and an output end of the electrically controlled telescopic rod is movably connected with the wings.

9. The fuselage structure of the cross-media aircraft according to claim 8, wherein the fixed end of the electrically-controlled telescopic rod is connected with the fuselage body through two serially-connected revolute pairs, and the rotation axes of the two revolute pairs are perpendicular to each other;