CN112124565A - Deformable high-speed helicopter short wing - Google Patents
Deformable high-speed helicopter short wing Download PDFInfo
- Publication number
- CN112124565A CN112124565A CN202011138386.4A CN202011138386A CN112124565A CN 112124565 A CN112124565 A CN 112124565A CN 202011138386 A CN202011138386 A CN 202011138386A CN 112124565 A CN112124565 A CN 112124565A
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- Prior art keywords
- helicopter
- frame assembly
- frame
- driving element
- speed
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- 239000000463 material Substances 0.000 claims description 30
- 239000011241 protective layer Substances 0.000 claims description 6
- 229910001018 Cast iron Inorganic materials 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 239000000741 silica gel Substances 0.000 claims description 3
- 229910002027 silica gel Inorganic materials 0.000 claims description 3
- 238000005253 cladding Methods 0.000 claims 1
- 239000002131 composite material Substances 0.000 description 3
- 230000008595 infiltration Effects 0.000 description 3
- 238000001764 infiltration Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a deformable high-speed helicopter short wing which comprises a driving element, a frame assembly and a skin, wherein the driving element and the frame assembly are rotatably connected with a helicopter body, the driving element is rotatably connected with the frame assembly, the driving element can drive the frame assembly to reciprocate, the frame assembly is of an unstable polygonal structure, one end of the frame assembly is rotatably connected with the helicopter body, and when the driving element drives the frame assembly to reciprocate, the frame assembly can deform, so that the maximum distance between the frame assembly and the helicopter body is changed. When the helicopter is suspended, the driving element drives the frame assembly to move, and the area of the frame assembly reaches the minimum. Along with the gradual increase of the front flying speed of the helicopter, the driving element drives the frame assembly to rotate reversely, so that the short wings of the helicopter are unfolded, and the short wings of the helicopter are completely unfolded after the wake flow of the main rotor wing of the helicopter deviates from the helicopter body, so as to provide larger lift force.
Description
Technical Field
The invention relates to the technical field of helicopters and peripheral supporting facilities thereof, in particular to a deformable short wing of a high-speed helicopter.
Background
Helicopters have their unique application value in many ways due to their high hovering efficiency, but their low flying speed is a short board compared to airplanes.
The composite helicopter is a method for solving the speed problem of the helicopter, and the fuselage of the composite helicopter is often provided with wings (hereinafter referred to as short wings) such as a composite helicopter X3 type high-speed helicopter which flies first in 2010, 9 and 6 days by european helicopter company. However, the wings installed on the helicopter are fixed wings, and the area of the wings cannot be changed.
The short wing of the helicopter body can provide a certain lift force for the helicopter to unload the rotor wing under the high-speed forward flight state so as to reduce the shock resistance and the counter flow area of the backward side blade in the forward flight process of the helicopter, and the maximum forward flight speed of the helicopter is improved.
When the combined helicopter flies vertically or flies at a low speed, the downward wash generated by the main rotor of the helicopter washes the fuselage and the short wing of the fuselage, and a considerable downward resistance is generated on the short wing of the fuselage, which adds a certain additional load to the helicopter and has certain influence on the hovering efficiency of the helicopter and the efficiency of the helicopter during vertical flight and low-speed forward flight.
The Chinese patent application with the publication number of CN111392030A discloses a retractable adjustable-angle helicopter stub, wherein a storage bin is arranged at the belly of a helicopter body, and the stub, a driving mechanism and a controller are all arranged in the storage bin. The short wing can be retracted when the helicopter is hovered or flies at low speed, and can be released when the helicopter flies at high speed. But this scheme need occupy the inside considerable space of helicopter, has caused the very big waste of helicopter inner space, and the practicality is relatively poor.
Therefore, how to change the current situation that the short wing of the combined helicopter body cannot simultaneously take into account various flight states of the helicopter in the prior art, and simultaneously avoid the phenomenon that the short wing of the body causes the internal space of the helicopter to be greatly occupied becomes a problem to be solved urgently by technical personnel in the field.
Disclosure of Invention
The invention aims to provide a deformable short wing of a high-speed helicopter, which solves the problems in the prior art, enables the short wing of the helicopter to adapt to various flight states of the helicopter and simultaneously reduces the influence of the short wing on the internal space of the helicopter.
In order to achieve the purpose, the invention provides the following scheme: the invention provides a helicopter frame assembly, which comprises a driving element, a frame assembly and a skin, wherein the driving element and the frame assembly are rotatably connected with a helicopter body, the driving element is rotatably connected with the frame assembly and can drive the frame assembly to reciprocate, the frame assembly is of a polygonal structure, the number of edges of the frame assembly is more than three, when the frame assembly and the helicopter body rotate relatively, the maximum distance between the frame assembly and the helicopter body is changed, the skin covers the frame assembly and is connected with the frame assembly, and the skin is made of a flexible material.
Preferably, the frame assembly comprises a connecting longitudinal beam and two parallel cross beams, one end of each cross beam is hinged with the helicopter body, two ends of each connecting longitudinal beam are connected with the two cross beams, the connecting longitudinal beam is hinged with the cross beams, and the connecting longitudinal beam is arranged at one end, far away from the helicopter body, of the cross beam; the driving element is hinged with the cross beam.
Preferably, the frame component is further provided with a middle longitudinal beam, the middle longitudinal beam is arranged between the connecting longitudinal beam and the helicopter body, the middle longitudinal beam and the connecting longitudinal beam are arranged in parallel, and the middle longitudinal beam is hinged and connected with the cross beam.
Preferably, the number of the middle longitudinal beams is multiple, and the multiple middle longitudinal beams are arranged at equal intervals.
Preferably, a filling material is arranged in a gap between the cross beam and the connecting longitudinal beam, the skin covers the filling material and is connected with the filling material, and the filling material can deform.
Preferably, the filling material is a paper honeycomb structure; the skin is made of silica gel cloth; the skin is riveted with the frame assembly through rivets, and the skin is bonded with the filling material.
Preferably, the deformable high-speed helicopter aileron further comprises a limiting block, the limiting block is connected with the helicopter body, the limiting block can be abutted against the frame assembly, and when the limiting block is abutted against the frame assembly, the distance between the frame assembly and the helicopter body is maximized.
Preferably, the limiting block is made of cast iron, a protective layer is arranged on the abutting surface of the limiting block and the frame assembly, and the protective layer is made of rubber.
Preferably, the driving element is a hydraulic rod, the driving element can drive the frame assembly to rotate around the helicopter body, and when the distance between the frame assembly and the helicopter body is minimum, one end, far away from the helicopter body, of the frame assembly inclines towards the tail direction of the helicopter.
Compared with the prior art, the invention has the following technical effects: the deformable high-speed helicopter short wing comprises a driving element, a frame assembly and a skin, wherein the driving element and the frame assembly are rotatably connected with a helicopter body, the driving element is rotatably connected with the frame assembly and can drive the frame assembly to reciprocate, the frame assembly is of a polygonal structure, the number of edges of the frame assembly is more than three, when the frame assembly and the helicopter body rotate relatively, the maximum distance between the frame assembly and the helicopter body changes, the skin covers the frame assembly and is connected with the frame assembly, and the skin is made of a flexible material. The deformable high-speed helicopter stub is provided with the frame assembly and the skin which jointly form the helicopter stub, the frame assembly is of an unstable polygonal structure, one end of the frame assembly is rotatably connected with a helicopter body, and the frame assembly can deform when the driving element drives the frame assembly to reciprocate, so that the maximum distance between the frame assembly and the helicopter body is changed. When the helicopter suspends, the driving element drives the frame assembly to move, the frame assembly deforms, so that the included angle between the frame assembly and the helicopter body is reduced, the maximum distance between the frame assembly and the helicopter body is reduced, the area of the frame assembly is minimized, namely the area of the short wing of the helicopter body is minimized, the included angle between the frame assembly and the helicopter body is also minimized, and the short wing of the helicopter is in a folding state when the helicopter suspends so as to reduce the infiltration area of the short wing of the helicopter and reduce the influence of the short wing of the helicopter body on the flight performance of the helicopter. Along with the gradual increase of the forward flying speed of the helicopter, the wake flow of the main rotor of the helicopter gradually deviates to the rear of the helicopter body, the additional load brought to the helicopter by the short wings of the helicopter body is gradually reduced, and the generated lift force is increased more and more. The driving element drives the frame assembly to rotate reversely until the maximum distance between the frame assembly and the helicopter body reaches the maximum, so that the unfolding of the short wings of the helicopter is realized, and the short wings of the helicopter are completely unfolded after the wake flow of the main rotor of the helicopter deviates from the helicopter body to provide larger lift force.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of the configuration of a transformable high-speed helicopter winglet according to the invention when folded;
FIG. 2 is a schematic view of the configuration of the transformable high-speed helicopter rotor of the present invention during deployment;
FIG. 3 is a schematic view of a transformable high speed helicopter winglet of the present invention in operation;
FIG. 4 is a schematic view of a transformable high speed helicopter rotor of the present invention in another operational state;
the helicopter comprises a helicopter body 1, a driving element 2, a limiting block 3, a cross beam 4, a filling material 5, a frame assembly 6, a connecting longitudinal beam 7 and a middle longitudinal beam 8.
It should be noted here that the skin is not shown in the above figures for the sake of clarity of the frame assembly and the filler material.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a deformable short wing of a high-speed helicopter, which solves the problems in the prior art, enables the short wing of the helicopter to adapt to various flight states of the helicopter and simultaneously reduces the influence of the short wing on the internal space of the helicopter.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Referring to fig. 1-4, fig. 1 is a schematic view showing a configuration of a deformable high-speed helicopter winglet of the present invention when folded, fig. 2 is a schematic view showing a configuration of a deformable high-speed helicopter winglet of the present invention when unfolded, fig. 3 is a schematic view showing a configuration of a deformable high-speed helicopter winglet of the present invention when operated, and fig. 4 is a schematic view showing a configuration of another configuration of a deformable high-speed helicopter winglet of the present invention when operated.
The invention provides a deformable high-speed helicopter short wing which comprises a driving element 2, a frame assembly 6 and a skin, wherein the driving element 2 and the frame assembly 6 are rotatably connected with a helicopter body 1, the driving element 2 is rotatably connected with the frame assembly 6, the driving element 2 can drive the frame assembly 6 to reciprocate, the frame assembly 6 is of a polygonal structure, the number of edges of the frame assembly 6 is more than three, when the frame assembly 6 and the helicopter body 1 rotate relatively, the maximum distance between the frame assembly 6 and the helicopter body 1 changes, the skin covers the frame assembly 6 and is connected with the frame assembly 6, and the skin is made of a flexible material.
The deformable high-speed helicopter stub is characterized in that a frame component 6 and a skin are arranged to jointly form the helicopter stub, the frame component 6 is of an unstable polygonal structure, one end of the frame component 6 is rotatably connected with a helicopter body 1, and when a driving element 2 drives the frame component 6 to reciprocate, the frame component 6 can deform, so that the maximum distance between the frame component 6 and the helicopter body 1 is changed, and meanwhile, the angle between the frame component 6 and the helicopter body 1 is changed, so that the folding and the unfolding of the helicopter stub are realized. When the helicopter suspends, the driving element 2 drives the frame assembly 6 to move, the frame assembly 6 deforms, so that the included angle between the frame assembly 6 and the helicopter body 1 is reduced, the maximum distance between the frame assembly 6 and the helicopter body 1 is reduced, the area of the frame assembly 6 is minimized, namely the area of the short wing of the helicopter body is minimized, the included angle between the frame assembly 6 and the helicopter body 1 is also minimized, the short wing of the helicopter is in a folding state when the helicopter suspends so as to reduce the infiltration area of the short wing of the helicopter, and the influence of the short wing of the helicopter body on the flight performance of the helicopter is reduced. Along with the gradual increase of the forward flying speed of the helicopter, the wake flow of the main rotor of the helicopter gradually deviates to the rear of the helicopter body, the additional load brought to the helicopter by the short wings of the helicopter body is gradually reduced, and the generated lift force is increased more and more. The driving element 2 drives the frame assembly 6 to rotate reversely until the maximum distance between the frame assembly 6 and the helicopter body 1 reaches the maximum, so that the short wings of the helicopter are unfolded, and the short wings of the helicopter are completely unfolded after the wake flow of the main rotor of the helicopter deviates from the helicopter body to provide larger lift force.
According to the deformable high-speed helicopter short wing, through the deformation of the helicopter short wing, the area of the short wing of the helicopter body during suspension can be reduced by at least 40% compared with the area of the short wing of the helicopter body during full unfolding during high-speed forward flight, the influence of the short wing of the helicopter body on the flight of the helicopter is reduced, meanwhile, the excessive occupation of the internal space of the helicopter by the short wing of the helicopter is avoided, the influence on the internal space of the helicopter is reduced, and the applicability of the helicopter is improved.
In the present embodiment, the frame assembly 6 includes a connecting longitudinal beam 7 and two parallel cross beams 4, one end of each cross beam 4 is hinged to the helicopter body 1, two ends of each connecting longitudinal beam 7 are connected to the two cross beams 4, each connecting longitudinal beam 7 is hinged to the cross beam 4, the connecting longitudinal beam 7 is disposed at one end of each cross beam 4 far away from the helicopter body 1, and the connecting longitudinal beam 7, the two cross beams 4 and the helicopter body 1 form a quadrilateral structure, so that the frame assembly 6 can deform; the driving element 2 is hinged with the cross beam 4, and the frame assembly 6 is driven to move by the cross beam 4. The frame component 6 can be adopted to construct the helicopter short wing, so that the deformation of the short wing is realized, the structure is simple, the operation is convenient, the frame structure is flexible and changeable, the frame structure can be determined according to actual conditions, and the applicability of the helicopter short wing is improved.
Wherein, frame subassembly 6 still sets up middle longeron 8, and middle longeron 8 sets up between connecting longeron 7 and helicopter fuselage 1, has improved frame subassembly 6's overall structure intensity, and middle longeron 8 sets up with connecting longeron 7 parallel, and middle longeron 8 links to each other with crossbeam 4 is articulated, and middle longeron 8 is parallel with connecting longeron 7, avoids it to influence frame subassembly 6 and warp.
Specifically, the number of the middle longitudinal beams 8 is multiple, the number of the middle longitudinal beams 8 can be specifically set according to actual needs, the multiple middle longitudinal beams 8 are arranged at equal intervals, the structural stability of the frame assembly 6 is improved, and in the specific embodiment, the number of the middle longitudinal beams 8 is three.
More specifically, filling materials 5 are arranged in gaps between the cross beams 4 and the connecting longitudinal beams 7, the filling materials 5 are covered by skins and connected with the filling materials 5, and the filling materials 5 are arranged, so that the structural integrity of the short wing of the helicopter is enhanced, the filling materials 5 can deform, and the filling materials 5 are prevented from influencing the deformation of the frame assembly 6.
Wherein, the filling material 5 is a paper honeycomb structure with a lower equivalent Poisson ratio in the surface, and meanwhile, the skin can be made of silica gel cloth; the skin is riveted with the frame assembly 6 by rivets and is bonded with the filling material 5, so that when the helicopter short wing is completely unfolded, the skin is in a completely tightened state, and the wind resistance is reduced.
In addition, still include stopper 3, stopper 3 links to each other with helicopter fuselage 1, and stopper 3 can be with 6 looks butt of frame subassembly, and when stopper 3 and 6 looks butts of frame subassembly, the distance between frame subassembly 6 and the helicopter fuselage 1 reaches the biggest, and the helicopter short wing expandes completely promptly. In the present embodiment, the limiting block 3 is disposed at an end of the cross beam 4 far from the driving element 2, and when the cross beam 4 rotates to abut against the limiting block 3, the cross beam 4 is perpendicular to the helicopter body 1, and the helicopter short wing is unfolded to the maximum area state. Set up stopper 3, guaranteed frame subassembly 6's limit deformation degree, improved operation work efficiency.
In order to improve the life of stopper 3, stopper 3 is made by the cast iron material of resistant striking, and stopper 3 sets up the protective layer with the butt face of frame subassembly 6, and the protective layer is made by the rubber material, effectively protects frame subassembly 6, covering and stopper 3, extension component life, stopper 3 can weld or utilize bolted connection with helicopter fuselage 1.
Further, the driving element 2 is a hydraulic rod, the hydraulic rod can stretch and retract to drive the frame assembly 6 to rotate around the helicopter body 1, and when the distance between the frame assembly 6 and the helicopter body 1 is minimum, one end, far away from the helicopter body 1, of the frame assembly 6 inclines towards the tail direction of the helicopter (the upper side in fig. 1 and 2). The driving element 2 is in a hydraulic rod form, the structure is simple, the control is convenient, and the occupation of the internal space of the helicopter is reduced to the maximum extent.
When the helicopter suspends, the driving element 2 drives the frame assembly 6 to move, the frame assembly 6 deforms, so that an included angle between the frame assembly 6 and the helicopter body 1 is reduced, the maximum distance between the frame assembly and the helicopter body 1 is reduced, the area of the frame assembly 6 is minimized, namely the area of the helicopter body short wing is minimized, the included angle between the frame assembly 6 and the helicopter body 1 is also minimized, the helicopter short wing is in a folding state when the helicopter suspends so as to reduce the infiltration area of the helicopter short wing, and the influence of the helicopter body short wing on the flight performance of the helicopter is reduced. Along with the gradual increase of the forward flying speed of the helicopter, the wake flow of the main rotor of the helicopter gradually deviates to the rear of the helicopter body, the additional load brought to the helicopter by the short wings of the helicopter body is gradually reduced, and the generated lift force is increased more and more. The driving element 2 drives the frame assembly 6 to rotate reversely until the frame assembly 6 is abutted to the limiting block 3, the short wing of the helicopter is completely unfolded, and the short wing of the helicopter is completely unfolded to provide larger lift force after the wake flow of the main rotor wing of the helicopter deviates from the fuselage.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. A deformable high-speed helicopter pony wing, characterized by: including drive element, frame subassembly and covering, drive element with frame subassembly all rotationally links to each other with the helicopter fuselage, drive element with frame subassembly rotates to be connected, drive element can drive frame subassembly reciprocating motion, frame subassembly is polygonized structure just the quantity on frame subassembly's limit is greater than three, when frame subassembly and helicopter fuselage take place the relative rotation, the maximum distance between frame subassembly and the helicopter fuselage changes, the covering cladding frame subassembly and the two link to each other, the covering is made by flexible material.
2. A transformable high-speed helicopter rotor as claimed in claim 1, wherein: the frame assembly comprises a connecting longitudinal beam and two cross beams arranged in parallel, one end of each cross beam is hinged with the helicopter body, two ends of each connecting longitudinal beam are connected with the two cross beams, the connecting longitudinal beams are hinged with the cross beams, and the connecting longitudinal beams are arranged at one ends, far away from the helicopter body, of the cross beams; the driving element is hinged with the cross beam.
3. A transformable high-speed helicopter rotor as claimed in claim 2, wherein: the frame component is further provided with a middle longitudinal beam, the middle longitudinal beam is arranged between the connecting longitudinal beam and the helicopter body, the middle longitudinal beam is parallel to the connecting longitudinal beam, and the middle longitudinal beam is hinged to the cross beam.
4. A transformable high speed helicopter winglet according to claim 3, wherein: the number of the middle longitudinal beams is multiple, and the middle longitudinal beams are arranged at equal intervals.
5. A transformable high-speed helicopter rotor as claimed in claim 2, wherein: and filling materials are arranged in gaps between the cross beams and the connecting longitudinal beams, the covering coats the filling materials and is connected with the filling materials, and the filling materials can deform.
6. A transformable high speed helicopter winglet according to claim 5, wherein: the filling material is of a paper honeycomb structure; the skin is made of silica gel cloth; the skin is riveted with the frame assembly through rivets, and the skin is bonded with the filling material.
7. A transformable high speed helicopter pony wing as claimed in any one of claims 1-6 wherein: the helicopter frame assembly is characterized by further comprising a limiting block, wherein the limiting block is connected with the helicopter body and can be abutted to the frame assembly, and when the limiting block is abutted to the frame assembly, the distance between the frame assembly and the helicopter body is maximized.
8. A transformable high-speed helicopter rotor as claimed in claim 7, wherein: the stopper is made by cast iron material, the stopper with the butt face of frame subassembly sets up the protective layer, the protective layer is made by rubber material.
9. A transformable high-speed helicopter rotor as claimed in claim 1, wherein: the driving element is a hydraulic rod and can drive the frame assembly to rotate around the helicopter body, and when the distance between the frame assembly and the helicopter body is minimum, one end, far away from the helicopter body, of the frame assembly inclines towards the tail direction of the helicopter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011138386.4A CN112124565A (en) | 2020-10-22 | 2020-10-22 | Deformable high-speed helicopter short wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011138386.4A CN112124565A (en) | 2020-10-22 | 2020-10-22 | Deformable high-speed helicopter short wing |
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| Publication Number | Publication Date |
|---|---|
| CN112124565A true CN112124565A (en) | 2020-12-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011138386.4A Pending CN112124565A (en) | 2020-10-22 | 2020-10-22 | Deformable high-speed helicopter short wing |
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| CN (1) | CN112124565A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753228A (en) * | 2021-09-16 | 2021-12-07 | 南京航空航天大学 | Helicopter with conventional layout and flight control method |
-
2020
- 2020-10-22 CN CN202011138386.4A patent/CN112124565A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753228A (en) * | 2021-09-16 | 2021-12-07 | 南京航空航天大学 | Helicopter with conventional layout and flight control method |
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