CN116395126A - Chord-wise four-stage series driving camber-changing wing design - Google Patents

Abstract

The invention discloses a steering engine driving-based chord direction four-stage serial driving camber-changing wing structure, and belongs to the technical field of aviation equipment. The wing comprises a wing spar, a skin, a polyhedral truss supporting structure, a limiting connecting rod, an actuator, a rotating shaft, a skin limiting head, a skin limiting groove and the like. Structure 1 is a front edge rigid section skin, and structures 2-7 are front edge rigid section structural members; structures 8 through 41 are trailing edge camber actuator segments. When the trailing edge actuating section of the chord direction four-stage serial driving camber-changing wing receives the instruction, the four steering engines are driven according to the respective instruction, and the synthesized motion of the steering engines changes the camber of the wing. The limiting sliding groove on the skin can limit deformation, warping and the like of the skin, and has the function of keeping the appearance of the wing. When the wing does not receive an actuating instruction, the steering engine is positioned at a neutral position, so that the original aerodynamic shape of the wing is maintained; upon receipt of an actuation command, the wing may deflect upward or downward to achieve corresponding aerodynamic performance in flight. The wing bending driving device is simple, has the characteristic of large bending change, can actively or passively change the wing shape, and can obtain different aerodynamic characteristics. The torsion wing can be combined by adopting a modularized assembly design.

Description

Chord-wise four-stage series driving camber-changing wing design

Technical Field

The invention relates to a chord direction four-stage series driving camber-changing wing which can be used for a fixed-wing aircraft.

Background

The camber-changing wing is a short name of four-stage serial driving camber-changing wing in chord direction, is a wing which changes the camber of the wing by the action of a chord direction driving piece, is suitable for different pneumatic working conditions, and can be widely applied to military machines and civil machines. The camber-changing wing can increase the lift-drag ratio, improve the buffeting characteristic of the wing, and improve the lift coefficient during cruising. The skin is smooth and seamless all the time in the deformation process, and is coherent and free of abrupt change. The seamless variant is beneficial to maintaining the air laminar flow state of the airfoil and the airframe, improving the lift-drag ratio, deferring the separation of the boundary layer, reducing noise, relieving flutter, wing tip vortex adverse phenomena and the like, thereby improving maneuverability, stealth, riding comfort, fuel economy and the like.

Disclosure of Invention

The invention provides a chord direction four-stage series driving camber-changing wing scheme using a polyhedral truss structure as an internal support, which aims to solve the problems that the current fixed wing aircraft wing can only obtain high lift-drag ratio under a single working condition, has earlier separation of an auxiliary surface layer, larger noise, poor maneuverability, low stealth, riding comfort and poor fuel economy, and the force transmission load of a wing rib by a plate rib is concentrated.

The invention adopts the following technical scheme for solving the technical problems:

the invention provides a chord-wise four-stage series driving camber-changing mode, which utilizes four steering engines to be assembled in series to realize camber-changing control of the rear edge, and simultaneously uses a connecting rod to connect a polyhedral truss structure to drive the skins of all wing segments to form a camber-changing wing.

The wing section 2 is provided with a specific first polyhedral truss structure supporting skin;

the wing segments 3 are provided with a specific second polyhedral truss structure 2 supporting skin;

the wing segments 4 are provided with a special third polyhedral truss structure 3 supporting skin;

the trailing edge section is provided with a special polyhedral truss structure 4 supporting skin;

the front edge section and the wing section 2 are connected through a first limiting sliding groove assembly in a covering limiting manner, and a limiting head moves in a sliding groove track;

the skin limit between the wing segment 2 and the wing segment 3 is connected by a second limit sliding groove component, and a limit head runs in a sliding groove track;

the wing panel 3 and the wing panel 4 are connected through a third limiting sliding groove assembly in a covering limiting manner, and a limiting head moves in a sliding groove track;

the wing section 4 is connected with the skin limit between the rear edge section through a fourth limit sliding groove assembly, and a limit head runs in a sliding groove track;

the wing section 2 and the wing section 3 are connected through a first limiting connecting rod 11 in a structure limiting manner;

the structural limit between the wing segments 3 and 4 is connected by a second limit connecting rod 14;

the structural limit between the wing segment 4 and the rear edge segment is connected by a third limit connecting rod 17;

drawings

Fig. 1 is a schematic view of the appearance of the present invention.

FIG. 2 is a schematic view of the trailing edge deflected upward 57 degrees.

FIG. 3 is a schematic view of the trailing edge deflected 40 degrees downward.

Fig. 4 is a schematic view in partial cross-section.

Fig. 5 is a schematic view of the internal structure.

Fig. 6 is a schematic diagram of an internal drive arrangement.

Fig. 7 is a schematic view of a polyhedral truss structure of panel 2.

Fig. 8 is a schematic view of a polyhedral truss structure of a wing segment 3.

Fig. 9 is a schematic view of a polyhedral truss structure of a wing segment 4.

FIG. 10 is a schematic view of a trailing edge section polyhedral truss structure.

Fig. 11 is a schematic view of a polyhedral truss structured spacing link.

Fig. 12 is a schematic view of a limiting chute structure. Wherein (a) is a limit slide block and (b) is a slide groove.

In the figure: 1 is a front edge skin, 2 is a front edge stringer, 3 is a front edge wing rib, 4 is a front edge tubular beam 1, 5 is a front edge tubular beam 2, 6 is a front edge strip, and 7 is a front edge wing beam.

Detailed Description

The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:

the invention relates to a chord-wise four-stage serial driving camber wing, wherein the appearance of a middle state is shown in a figure 1, the rear edge is deflected upwards and camber is shown in a figure 2, the rear edge is deflected downwards and camber is shown in a figure 3, a concrete structure is shown in a figure 4, and the wing comprises a front edge skin 1, a front edge stringer 2, N front edge ribs 3, a front edge first tubular beam 4, a front edge second tubular beam 5, N front edge strips 6, a front edge spar 7, N front edge polyhedral truss supports 8, N first polyhedral trusses 9, N first pin shafts 10, N first limit connecting rods 11, N second polyhedral trusses 12, N second pin shafts 13, N second limit connecting rods 14, N third polyhedral trusses 15, N third pin shafts 16, N third limit connecting rods 17, N fourth polyhedral trusses 18, N fourth pin shafts 19, a rear edge polyhedral truss support 20, a rear edge skin 21, N rear edge rib 22, a rear edge transmission block 23, a rear edge transmission block 24, a fourth pin shafts 25, a fourth rocker arm support frame 26, a third rocker arm support frame 33, a third rocker arm support frame 34, a fourth rocker arm support frame 33, a third rocker arm support frame 34, a fourth rocker arm support frame 33, a third rocker arm support frame 30, a fourth rocker arm support frame 33, a fourth rocker arm support frame 30, a third rocker arm support frame 30. The value of N may be selected according to actual requirements, for example, 2, 3, 4, 5, and 6, and n=2 is selected in the embodiment of the present invention. The steering engine with the number two, three and four is used as a general component, and a proper model in the market can be selected to replace according to actual requirements.

The working principle of the invention is as follows:

according to the invention, the steering engine drives the rocker arm to transfer rotary motion to form the camber-changing wing, the front edge part formed by the structures 1 to 8 is used as a fixed part, the front edge part is connected with the machine body in actual use, the first bracket 41 is rigidly connected with the front edge part through a screw, meanwhile, the first bracket 41 is used for fixing the first steering engine 40, and the first steering engine 40 rotates after receiving a signal to drive the first rocker arm 37 to rotate.

The first rocker arm 37 is rigidly connected with the second bracket 35, the second bracket 35 is used for fixing the second steering engine 34, the second steering engine 34 and the first steering engine 40 can simultaneously receive the same or different signals, the second steering engine 34 generates rotation after receiving the signals, and the second rocker arm 33 is driven to generate rotation.

The second rocker arm 33 is rigidly connected with the third support 32, the third support 32 is used for fixing the third steering engine 30, the first steering engine 40 and the second steering engine 34 can simultaneously receive the same or different signals, the third steering engine 30 rotates after receiving the signals, and the third rocker arm 29 is driven to rotate.

The third rocker arm 29 is rigidly connected with the fourth support 27, the fourth support 27 is fixedly provided with the fourth steering engine 26, the first steering engine 40, the second steering engine 34 and the third steering engine 30 can simultaneously receive the same or different signals, and the fourth steering engine 26 generates rotation after receiving the signals and drives the fourth rocker arm 25 to generate rotation.

The fourth rocker arm 25 is connected with the transmission fixing 24 to clamp the rear edge spar 21, and the rear edge spar 21, the fourth polyhedral truss 18, the fourth pin shaft 19, the rear edge polyhedral truss support 20 and the rear edge rib 22 form a rear edge, and the rear edge is driven by the fourth rocker arm 25.

The rear edge polyhedral truss support 20 is connected with the fourth polyhedral truss 19 through a fourth pin shaft 18, and the third limit connecting rod 17 rotates around the fourth pin shaft 18 between the third limit connecting rod and the structures 18-25, and is provided with an upper limit of 14.25 degrees and a lower limit of 10 degrees. The third polyhedral truss 15 is used for supporting the skin 28 of the wing segment 4, is connected with the third limit connecting rod 17 through the third pin shaft 16, and transmits rotation from the polyhedral truss 19. The second polyhedral truss 12 is used for supporting the skin 31 of the wing segment 3, is connected with the second limit connecting rod through a second pin shaft 13, and transmits rotation from the polyhedral truss 15. The first polyhedral truss 9 is used for supporting the skin 36 of the wing segment 2, is connected with the first limit connecting rod 11 through the first pin shaft 10, and transmits rotation from the polyhedral truss 12.

The wing after the camber change has different pneumatic characteristics, and can deflect corresponding angles according to actual needs in flight, for example, the wing can deflect at a small angle to increase lift and reduce drag, the wing can deflect at a large angle to increase lift and increase drag, and the wing can deflect at a large angle to discharge lift and increase drag.

Claims (3)

1. The chord four-stage series driving camber wing device is characterized by comprising front edge rigid wing segments (1, 2, 3, 4, 5, 6, 7), control surface truss structure installation frames (8, 20), polyhedral truss structures (9, 12, 15, 18), limit connecting rods (11, 14, 17), trailing edge structures (21, 22), movable wing segment skins (23, 28, 31, 36), driving components (25, 26, 27, 29, 30, 32, 33, 34, 35, 37, 40, 41) and limit sliding grooves (38, 39); wherein:

each polyhedral truss structure (9, 12, 15, 18) is designed according to the size of the wing section where the polyhedral truss structure is positioned;

the transmission elements (27, 32, 35) are specifically designed according to the airfoil center line.

2. Chordwise four-stage tandem drive assembly (25, 26, 27, 29, 30, 32, 33, 34, 35, 37, 40, 41) as claimed in claim 1, connected with a transmission fixture (24) to drive the trailing edge wing sections (18, 19, 20, 21, 22, 23) to act, wherein the wing section 2 polyhedral truss structure (9) is fixedly connected with the wing section 2 skin (36) during movement, the wing section 3 polyhedral truss structure (12) is fixedly connected with the wing section 3 skin (31), and the wing section 4 polyhedral truss structure (15) is fixedly connected with the wing section 4 skin (28).

3. A limit runner assembly (38, 39) is installed between the leading edge section skin (1) and the panel 2 skin (36), the panel 2 skin (36) and the panel 3 skin (31), the panel 3 skin (31) panel 4 skin (28), the panel 4 skin (28) and the trailing edge section skin (23) according to claim 1 for limiting buckling of the respective skins. Wherein the number of the limit chute assemblies (38, 39) can be uniformly arranged in a plurality according to the span length.

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