阅读说明：本技术 一种用于变体飞机的可收放式鸭翼装置及其使用方法 (Retractable duck wing device for morphing aircraft and using method thereof ) 是由 王宁 孙中超 赵姣 付颖斌 于 2019-11-12 设计创作，主要内容包括：本发明提出一种用于变体飞机的可收放式鸭翼装置及其使用方法,舱门在鸭翼展开时自动打开,鸭翼收回后自动封闭机身开口,并保持外表面的完整和光滑。本发明设计的可收放式鸭翼装置,在鸭翼驱动组件的驱动下,不需要时鸭翼能够收回机身内,需要时鸭翼能够展开,同时,鸭翼驱动组件与舱门驱动组件之间设计为联动,在鸭翼需要展开或收回时,舱门能自动打开和关闭,仅用一台电机即实现鸭翼的收放和舱门开闭的协同控制。另外,通过在舱门上设置柔性密封片,实现了鸭翼展开状态下的封严功能,保证机身外表面的完整和光滑,将鸭翼收放对飞机气动和隐身性能的不利影响降到最低。(The invention provides a retractable duck wing device for a morphing aircraft and a using method thereof. According to the retractable duck wing device, the duck wings can be retracted into the machine body when not needed under the driving of the duck wing driving assembly, the duck wings can be unfolded when needed, meanwhile, the duck wing driving assembly and the cabin door driving assembly are linked, the cabin door can be automatically opened and closed when the duck wings need to be unfolded or retracted, and the coordinated control of the folding and unfolding of the duck wings and the opening and closing of the cabin door can be realized only by one motor. In addition, the flexible sealing sheet is arranged on the cabin door, so that the sealing function of the duck wing in the unfolding state is realized, the completeness and smoothness of the outer surface of the airplane body are ensured, and the adverse effect of the duck wing folding and unfolding on the pneumatic and stealthy performances of the airplane is minimized.)

1. A retractable duck wing device for a morphing aircraft is characterized by comprising a cabin door assembly, a cabin door driving assembly, a duck wing assembly and a duck wing driving assembly;

the duck wing component comprises a duck wing (5) and a duck wing rotating shaft (7), and the duck wing (5) is fixedly connected to the duck wing rotating shaft (7);

the cabin door assembly comprises two cabin door supports (2), two cabin doors (3) and two flexible sealing pieces (4), the cabin doors (3) are hinged to the fuselage (1) through the cabin door supports (2), gaps matched with chordwise sections of the duck wings (5) are formed in the cabin doors (3), the flexible sealing pieces (4) are installed in the gaps, when the two cabin doors (3) are closed, openings in the fuselage (1) can be sealed, when the duck wings are in an unfolded state, the duck wings (5) are located at the gaps in the two cabin doors (3) after the two cabin doors (3) are closed, and the flexible sealing pieces (4) enable the gaps to be sealed;

the duck wing driving component drives the duck wing (5) to extend and retract from an opening on the fuselage (1) by driving the duck wing rotating shaft (7) to rotate;

the cabin door driving assembly is linked with the canard driving assembly and is used for driving the cabin door to open and close.

2. The retractable duck wing device for morphing aircraft according to claim 1, wherein the duck wing drive assembly comprises a sheave (8), a dial (9), a dial rotating shaft (10) and a motor (11), the sheave (8) and the dial (9) constitute a sheave mechanism; the grooved pulley (8) is fixedly connected to the duck wing rotating shaft (7), the output shaft of the motor (11) and the drive plate (9) are coaxially and fixedly connected to the drive plate rotating shaft (10), and the drive plate rotating shaft (10) is parallel to the duck wing rotating shaft (7).

3. The retractable duck wing device for morphing aircraft as claimed in claim 2, wherein the sheave (8) is provided with a radial groove (81), and two sides of the radial groove (81) are respectively provided with an arc-shaped groove (82); the dial plate (9) is provided with a roller (91), the diameter of the roller (91) is matched with the width of the radial groove (81), a circular boss (92) is arranged on the dial plate (9), the diameter of the boss (92) is matched with the arc-shaped groove (82), and one side, close to the roller (91), of the boss (92) is provided with an arc-shaped notch (93).

4. A retractable canard device for morphing aircraft according to claim 2, characterized in that the hatch drive assembly comprises a gear assembly, a reciprocating screw (17), a screw support (18), a slider (19) and two connecting rods (20); the reciprocating screw rod (17) is rotatably arranged on the screw rod support (18), the sliding block (19) is arranged on the reciprocating screw rod (17), two ends of one connecting rod (20) are respectively hinged with the sliding block (19) and one cabin door (3), and two ends of the other connecting rod (20) are respectively hinged with the sliding block (19) and the other cabin door (3); when the driving plate rotating shaft (10) rotates, the reciprocating screw rod (17) is driven to rotate through the gear component.

5. A retractable duck wing device for a morphing aircraft according to claim 4, wherein the gear assembly comprises a first gear (12), a second gear (13), a third gear (14), a fourth gear (15) and a fifth gear (16), the first gear (12) and the second gear (13) are conical gears, the first gear (12) is fixedly connected to the dial rotating shaft (10), the first gear (12) is meshed with the second gear (13), the second gear (13) is coaxially and fixedly connected with the third gear (14), the fifth gear (16) is fixedly connected to the reciprocating screw (17), and the third gear (14), the fourth gear (15) and the fifth gear (16) are meshed in sequence.

6. The retractable duck wing device for a morphing aircraft as claimed in claim 1, further comprising a central wing box (6), the duck wing shaft (7) being rotatably mounted on the central wing box (6), the duck wing drive assembly and the hatch drive assembly being mounted within the central wing box (6).

7. The method of using a retractable duck wing apparatus for a morphing aircraft as claimed in any one of claims 1 to 6, comprising:

1) the initial state is a duck wing retracting state, and the hatch door (3) is closed;

2) the cabin door driving component drives the cabin door (3) to move towards the opening direction;

3) after the opening width of the cabin door (3) is larger than the thickness of the duck wing (5), the duck wing driving assembly drives the duck wing (5) to move towards the unfolding direction, and the cabin door (3) continues to move towards the opening direction;

4) when the canard wing (5) is unfolded to a half position, the cabin door driving component drives the cabin door (3) to move towards the closing direction;

5) when the duck wing (5) is unfolded to the designed position, the duck wing driving assembly continues to drive the cabin door (3) to move towards the closing direction until the cabin door (3) moves to the closing position, and the flexible sealing sheet (4) is elastically deformed and clings to the outer surface of the duck wing (5) in the process;

6) the operation method of the duck wing (5) is opposite to the process.

Technical Field

The invention relates to the field of airplane structure design, in particular to a retractable duck wing device for a morphing airplane and a using method thereof.

Background

The retractable duck wing is an important means for changing the shape of the morphing aircraft and improving the performance of the morphing aircraft. Like the original Soviet Union-144 airplane which improves the characteristic of poor take-off and landing characteristics of the delta wing with small aspect ratio by a pair of retractable duck wings at the nose, the American F-14 airplane balances the phenomenon that the lift center moves backwards when the wing flies at supersonic speed and the main wing sweepes backwards by arranging a pair of retractable fan wings at the front side of the wing.

In recent years, stealth airplanes are increasingly researched in various countries, and higher requirements are put on the design of retractable duck wings. In view of eliminating the corner reflector effect and forming a lifting body with the wings, the fuselage of the modern stealth aircraft mostly adopts a wing body fusion structure consisting of concave-convex curves. The retractable duck wing and the sealing device thereof have the following requirements: the duck wing can be retracted and unfolded under the driving of the operating mechanism; the sealing device can be automatically opened when the duck wing is unfolded, and automatically closed when the duck wing is retracted, and the sealing effect is always kept in the flying process.

In an active airplane, the canard wing is mainly used for generating vortex, delaying stall, improving the performance of a large attack angle or solving the problem of stability dip in the transonic speed process, and simultaneously can reduce trimming resistance and enhance maneuverability. The duck wing has two main motion modes: (1) the leading edge is fixed and the trailing edge is provided with a flap-like mechanism, such as Sabo-37 in Sweden; (2) is mounted on the body through a rotating shaft in the Y direction and can rotate around the rotating shaft, such as 'gust', JAS-39 and the like. The research and the application of the existing canard wing mechanism in the airplane to be folded and unfolded backwards are less.

The original Soviet Union figure-144 passenger plane does not relate to the problem of stealth, and the retractable duck wing is directly arranged above the aircraft nose. The American F-14 fighter does not relate to the problem of stealth, and the retractable fan wing flat plate type structure is used as a fixed duck wing when being unfolded outwards and is used for improving the phenomenon that the lift force center moves backwards when the main wing sweepes backwards. After the fan wing is retracted inwards, the front edge of the fan wing is overlapped with the rectangular opening on the wing sleeve, and the rectangular opening is sealed. The wing is of a flat plate structure, is thin in thickness, has no shape modification at the front edge, is low in pneumatic efficiency, and cannot meet the requirements of modern high-performance stealth airplanes. In addition, the existing duck wing folding and unfolding mode based on an intelligent structure and materials is still in the conceptual research stage, and has a larger distance from the practical engineering. Therefore, based on traditional materials and structures, the retractable duck wing and the sealing device thereof which can meet the design requirements are designed for the morphing aircraft, and the practical significance is high.

Disclosure of Invention

Aiming at the problem that the aerodynamic shape of a future morphing aircraft is changed, a retractable duck wing device for the morphing aircraft and a using method thereof are provided, a cabin door is automatically opened when the duck wing is unfolded, the duck wing is automatically closed after being retracted, and the integrity and the smoothness of the outer surface are kept.

The invention is realized by the following technical scheme:

a retractable duck wing device for a morphing aircraft comprises a cabin door assembly, a cabin door driving assembly, a duck wing assembly and a duck wing driving assembly;

the duck wing component comprises a duck wing and a duck wing rotating shaft, and the duck wing is fixedly connected to the duck wing rotating shaft;

the cabin door assembly comprises two cabin door supports, two cabin doors and flexible sealing sheets, the two cabin doors are hinged and installed on the fuselage through the cabin door supports, gaps matched with chordwise sections of the duck wings are formed in the cabin doors, the flexible sealing sheets are installed in the gaps, when the two cabin doors are closed, the opening in the fuselage can be sealed, and when the two cabin doors are in an unfolded state, the duck wings are located at the gaps on the two cabin doors, and the flexible sealing sheets enable the gaps to be sealed;

the duck wing driving component drives the duck wing to extend and retract from the opening of the machine body by driving the duck wing rotating shaft to rotate;

the cabin door driving assembly is linked with the canard driving assembly and is used for driving the cabin door to open and close;

preferably, the duck wing driving component comprises a grooved wheel, a driving plate rotating shaft and a motor, wherein the grooved wheel and the driving plate form a grooved wheel mechanism; the grooved pulley is fixedly connected to the duck wing rotating shaft, the output shaft of the motor and the drive plate are coaxially and fixedly connected to the drive plate rotating shaft, and the drive plate rotating shaft is parallel to the duck wing rotating shaft.

Further, a radial groove is formed in the grooved wheel, and two arc-shaped grooves are formed in two sides of the radial groove respectively; the dial is provided with a roller, the diameter of the roller is matched with the width of the radial groove, a circular boss is arranged on the dial, the diameter of the boss is matched with the arc-shaped groove, and an arc-shaped notch is formed in one side, close to the roller, of the boss.

Further, the cabin door driving assembly comprises a gear assembly, a reciprocating screw rod, a screw rod support, a sliding block and two connecting rods; the reciprocating screw rod is rotatably arranged on the screw rod support, the sliding block is arranged on the reciprocating screw rod, two ends of one connecting rod are respectively hinged with the sliding block and one cabin door, and two ends of the other connecting rod are respectively hinged with the sliding block and the other cabin door; when the driving plate rotating shaft rotates, the reciprocating screw rod is driven to rotate through the gear assembly.

Further, the gear assembly includes first gear, second gear, third gear, fourth gear and fifth gear, and first gear and second gear are conical gear, and first gear fixed connection is in the driver plate pivot, and first gear and second gear meshing, the coaxial fixed connection of second gear and third gear is in the same place, and fifth gear fixed connection is on reciprocal lead screw, and third gear, fourth gear and fifth gear mesh in proper order.

Preferably, the aircraft further comprises a central wing box, the canard rotating shaft is rotatably arranged on the central wing box, and the canard driving assembly and the cabin door driving assembly are arranged in the central wing box.

The use method of the retractable duck wing device for the morphing aircraft comprises the following steps:

1) enabling the initial state to be a duck wing retracting state, and closing the cabin door;

2) the cabin door driving assembly drives the cabin door to move towards the opening direction;

3) after the opening width of the cabin door is larger than the thickness of the duck wing, the duck wing driving assembly drives the duck wing to move towards the unfolding direction, and the cabin door continues to move towards the opening direction;

4) when the duck wing is spread to a half position, the hatch door driving assembly drives the hatch door to move towards the closing direction;

5) when the duck wing is unfolded to the designed position, the duck wing driving assembly continues to drive the cabin door to move towards the closing direction until the cabin door moves to the closing position, and the flexible sealing sheet is elastically deformed and clings to the outer surface of the duck wing in the process;

6) the operation method of the duck wing withdrawing is opposite to the process.

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

according to the retractable duck wing device, the duck wings can be retracted into the machine body when not needed under the driving of the duck wing driving assembly, the duck wings can be unfolded when needed, meanwhile, the duck wing driving assembly and the cabin door driving assembly are linked, the cabin door can be automatically opened and closed when the duck wings need to be unfolded or retracted, and the coordinated control of the folding and unfolding of the duck wings and the opening and closing of the cabin door can be realized only by one motor. In addition, the flexible sealing sheet is arranged on the cabin door, so that the sealing function of the duck wing in the unfolding state is realized, the completeness and smoothness of the outer surface of the airplane body are ensured, and the adverse effect of the duck wing folding and unfolding on the pneumatic and stealthy performances of the airplane is minimized.

Furthermore, the separation of the movement of the cabin door and the duck wing is realized through a set of sheave mechanism, so that the two can not interfere in the movement process.

Furthermore, the automatic opening and closing of the cabin door are realized through a set of reciprocating screw rod mechanism, and the rotating direction of the motor is not required to be changed in the process; through the means, the duck wing can be unfolded (retracted) and the cabin door can be opened and closed only by controlling the motor to continuously rotate for a certain angle, and the structure and logic of a control system are simplified.

Drawings

FIG. 1 is a perspective view of the present invention with the wing of the duck retracted;

FIG. 2 is a perspective view of the present invention with the duck wings deployed (with the hatch door open);

FIG. 3 is a perspective view of the present invention with the duck wings deployed (with the hatch door closed);

FIG. 4 is a first perspective view of the internal structure of the duck wing in a retracted state;

FIG. 5 is a perspective view II of the internal structure of the duck wing in a retracted state;

FIG. 6 is a perspective view of the internal structure of the duck wing in the unfolded state;

FIG. 7 is an exploded view of the internal structure of the present invention;

FIG. 8 is a partial internal block diagram of the present invention;

FIGS. 9-12 are schematic views of the duck wing deployment process;

FIG. 13 is a perspective view of the hatch assembly in the closed state;

FIG. 14 is a perspective view of the hatch assembly in an open state;

FIG. 15 is a perspective view of the hatch door construction;

fig. 16 is a perspective view of the geneva gear;

figure 17 is a perspective view of a sheave arrangement;

fig. 18 is a perspective view of the dial structure;

fig. 19 is a perspective view of the dial and first gear structure.

In the figure, 1 is the fuselage; 2 is a cabin door support; 3 is a cabin door; 4 is a flexible sealing sheet; 5 is duck wing; 6 is the central wing box; 7 is a duck wing rotating shaft; 8 is a grooved wheel; 81 is a radial slot; 82 is an arc-shaped groove; 9 is a dial; 91 is a roller; 92 is a boss; 93 is an arc-shaped notch; 10 is a dial rotation shaft; 11 is a motor; 12 is a first gear; 13 is a second gear; 14 is a third gear; 15 is a fourth gear; 16 is a fifth gear; 17 is a reciprocating lead screw; 18 is a lead screw support; 19 is a slider; 20 is a connecting rod.

Detailed Description

The present invention will now be described in further detail with reference to specific examples, which are intended to be illustrative, but not limiting, of the invention.

The retractable duck wing device comprises two sets of cabin door components, a set of cabin door driving component, a set of duck wing driving component and a central wing box 6.

As shown in fig. 7 and 8, a set of duck wing assembly comprises a duck wing 5 and a duck wing rotating shaft 7, the duck wing 5 is fixedly connected to the duck wing rotating shaft 7, and the duck wing rotating shaft 7 is installed on the central wing box 6 through a vertical revolute pair.

As shown in fig. 16 to 19, a set of canard driving components includes a sheave 8, a dial 9, a dial rotating shaft 10 and a motor 11, the sheave 8 and the dial 9 constitute a sheave mechanism; a radial groove 81 is arranged on the grooved wheel 8, and two arc-shaped grooves 82 are respectively arranged on two sides of the radial groove 81; a roller 91 is arranged on the dial plate 9, the diameter of the roller 91 is matched with the width of the radial groove 81, a circular boss 92 is arranged on the upper side of the dial plate 9, the diameter of the circular boss is matched with the arc-shaped groove 82, and an arc-shaped notch 93 is arranged on one side, close to the roller 91, of the boss 92; the grooved wheel 8 is fixedly connected on the canard wing rotating shaft 7, the output shaft of the motor 11 and the drive plate 9 are coaxially and fixedly connected on a drive plate rotating shaft 10, and the drive plate rotating shaft 10 is arranged on the central wing box 6 through a vertical revolute pair. The dial rotation axis 10 is parallel to the canard rotation axis 7.

As shown in fig. 13, 14 and 15, the suite of door assemblies includes three door holders 2, a door 3 and a flexible sealing sheet 4, the door 3 is mounted on the three door holders 2 through joints thereof, and the door holders 2 are fixedly connected inside the fuselage 1; the hatch door 3 is provided with a gap matched with the chord-direction section of the duck wing 5, and a flexible sealing sheet 4 is arranged in the gap. The flexible sealing piece 4 conforms in shape and size to the indentation.

As shown in fig. 4 to 8, a set of hatch drive assemblies includes a first gear 12, a second gear 13, a third gear 14, a fourth gear 15, a fifth gear 16, a reciprocating screw 17, two screw supports 18, a slider 19 and two connecting rods 20; the first gear 12 and the second gear 13 are conical gears, and the other gears are straight cylindrical gears; the first gear 12 is fixedly connected on the dial rotating shaft 10, the first gear 12 is meshed with the second gear 13, the second gear 13 is coaxially fixedly connected with the third gear 14 to form a gear shaft, the gear shaft is arranged in the central wing box 6 through a rotating pair in the horizontal direction, the fourth gear 15 is arranged in the central wing box 6 through a rotating pair in the horizontal direction, the fifth gear 16 is fixedly connected on the reciprocating screw 17, and the third gear 14, the fourth gear 15 and the fifth gear 16 are sequentially meshed; the reciprocating screw 17 is arranged on two screw supports 18 through a revolute pair, the screw supports 18 are fixedly connected on the central wing box 6, the sliding block 19 is arranged on the reciprocating screw 17, two ends of one connecting rod 20 are respectively hinged with the sliding block 19 and one cabin door 3 through the revolute pair, and two ends of the other connecting rod 20 are respectively hinged with the sliding block 19 and the other cabin door 3 through the revolute pair.

As shown in fig. 1-3, the cross section of the fuselage 1 is spindle-shaped, the canard wing 5 is located in the middle of the fuselage 1, an opening for the canard wing 5 to extend out is arranged on the fuselage 1, the shape and size of the hatch door are consistent with those of the opening on the fuselage 1, and when the two hatch doors 3 are closed, the opening on the fuselage 1 can be sealed. Under the duck wing expansion state, two hatches 3 are closed the back, and duck wing 5 is located the breach department on two hatches 3, and flexible sealing strip 4 makes breach department seal.

The operation method and the process of the invention are as follows:

1. the initial state is a canard wing retracting state, the cabin door 3 is closed, the roller 91 is positioned outside the radial groove 81, and the canard wing 5 cannot rotate due to the limiting effect of the arc-shaped groove 82 and the boss 92;

2. the motor 11 is powered on to start rotating, the driving plate rotating shaft 10, the first gear 12 and the driving plate 9 are driven to rotate, the first gear 12 sequentially drives the second gear 13, the third gear 14, the fourth gear 15, the fifth gear 16 and the reciprocating lead screw 17 to rotate, the reciprocating lead screw 17 drives the sliding block 19 and the connecting rod 20 to move towards the outer side of the machine body 1, and simultaneously drives the cabin door 3 to be opened, in the process, the roller 91 is positioned outside the radial groove 81, and the canard wing rotating shaft 7 and the canard wing 5 cannot rotate, as shown in fig. 9;

3. after the opening width of the hatch door 3 is larger than the thickness of the duck wing 5, the roller 91 enters the radial groove 81, the sheave 8 and the duck wing rotating shaft 7 rotate under the driving of the motor 11, the duck wing 5 is unfolded, and the hatch door 3 is continuously opened, as shown in fig. 10;

4. when the canard 5 is unfolded to a half position, the sliding block 19 moves outwards to a limit position on the reciprocating screw 17, the grooved pulley 8 and the canard rotating shaft 7 continue to rotate under the driving of the motor 11, and the reciprocating screw 17 starts to drive the sliding block 19 to move inwards, as shown in fig. 11;

5. after the roller 91 is separated from the radial groove 81, the duck wing 5 is unfolded to the designed position, the motor 11 continues to rotate to drive the sliding block 19 to continue to move towards the inner side of the machine body 1 until the cabin door 3 moves to the closed position, as shown in fig. 12, in the process, the sealing sheet 4 is elastically deformed and is tightly attached to the outer surface of the duck wing 5, and the local sealing effect is realized;

6. the operation method of the duck wing 5 is reverse to the above process.