CN215399304U - Foldable wing surface for aircraft - Google Patents
Foldable wing surface for aircraft Download PDFInfo
- Publication number
- CN215399304U CN215399304U CN202121106851.6U CN202121106851U CN215399304U CN 215399304 U CN215399304 U CN 215399304U CN 202121106851 U CN202121106851 U CN 202121106851U CN 215399304 U CN215399304 U CN 215399304U
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- wing
- wingtip
- push rod
- hinged
- ejector
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Abstract
The utility model discloses a foldable wing surface for an aircraft, which comprises a wing tip, a wing body, a wing tip ejector motor, an electric push rod and an extension plate, wherein the wing tip ejector motor is connected with the wing tip ejector motor; the extension plate is fixed at the root of the wingtip of the wing; an extension rod of the electric push rod is hinged with one end of the extension plate, which is far away from the wingtips of the wings; a sleeve of the electric push rod is hinged with the wing body of the wing; one end of the wing body of the wing, which is close to the wing tip of the wing, is provided with a push rod placing groove, and the extension plate and the electric push rod are both arranged in the push rod placing groove; one end of the wingtip ejector is hinged with the root of the wingtip of the wing, and the other end of the wingtip ejector is abutted against the extending plate; the base of the wing tip ejector motor is fixed with the wing body of the wing, and the output shaft of the wing tip ejector motor and the end of the wing tip ejector hinged with the wing tip of the wing are fixed. The utility model can realize the matching motion of the extension rod of the electric push rod and the wing tip ejector in the early folding stage and the later unfolding stage of the wing tip, and the wing tip can be folded and unfolded at a constant speed and stably moves by controlling the movement of the extension rod of the electric push rod.
Description
Technical Field
The utility model belongs to the field of aerospace, and particularly relates to a foldable wing surface for an aircraft.
Background
China is the civil aviation market which is fastest in development and has the greatest potential in the world at present. With the establishment of the commercial airlines in China, a new journey of independently developing passenger planes in China is opened. Passenger aircraft often carry a larger amount of passenger, have a larger fuselage size than conventional passenger aircraft, and require larger wing span sizes and wing areas of passenger aircraft to provide the required lift. The large wing can save more oil for the passenger plane in the flying process and reduce the flying cost of the airline company. However, due to the limitations of airport field use codes, excessive wing size is not allowed, thereby resulting in folded and unfolded wing technology. When the wing span size of the designed wing is large, the wing tip end of the passenger plane is folded upwards when the passenger plane is parked on the ground through the wing folding and unfolding technology, the transverse size of the passenger plane is effectively reduced, the wing folding and unfolding technology also enables the airline company to park more passenger planes on the same place, the place expense of the airline company is reduced, the operation cost is effectively reduced, and the economic benefit is improved. In the aerospace craft, a great deal of demands are also placed on the foldable wings, and the foldable wings can change the wingspan of the aerospace craft and improve the performance of the aerospace craft according to different working environments and flight conditions. The wing surface folding and unfolding mechanism for the aircraft, which is simple and reliable in structure and stable in folding and unfolding, has important significance for the development of aviation airliners in China and the promotion of the development process of the aerospace field in China.
Disclosure of Invention
The utility model aims at the development requirements of aerospace aircrafts, fills the blank of the folding and unfolding technology of the wings of domestic passenger planes, and provides a foldable and unfoldable wing surface for an aircraft.
The technical scheme adopted by the utility model is as follows:
the utility model comprises a wing tip, a wing body, a wing tip ejector motor, an electric push rod and an extension plate; the extension plate is fixed at the root of the wingtip of the wing; an extension rod of the electric push rod is hinged with one end of the extension plate, which is far away from the wingtips of the wings; a sleeve of the electric push rod is hinged with the wing body of the wing; one end of the wing body of the wing, which is close to the wing tip of the wing, is provided with a push rod placing groove, and the extension plate and the electric push rod are both arranged in the push rod placing groove; one end of the wingtip ejector is hinged with the root of the wingtip of the wing, and the other end of the wingtip ejector is abutted against the extending plate; the base of the wing tip ejector motor is fixed with the wing body of the wing, and the output shaft of the wing tip ejector motor and the end of the wing tip ejector hinged with the wing tip of the wing are fixed.
Preferably, a first wingtip beam and a second wingtip beam are fixed at the root of the wingtip of the wing; the first wingtip beam and the second wingtip beam are positioned on two sides of the extending plate; a first wing body beam and a second wing body beam are fixed on the wing body of the wing; one end of the first wing body beam is hinged with the first wingtip beam, and one end of the second wing body beam is hinged with the second wingtip beam; the hinge joint of the wingtip ejector and the root of the wingtip of the wing is specifically as follows: the wingtip ejector is hinged to the other ends of the first wingbody beam and the second wingbody beam.
Preferably, the end of the wingtip ejector, which is not hinged with the root of the wingtip of the wing, is hinged with a roller.
More preferably, the roller is externally wrapped with a rubber sleeve.
Preferably, a wing tip limiter is fixed on the extension plate, and the end of the wing tip ejector, which is not hinged with the root of the wing tip of the wing, is embedded into a roller limiting groove formed in the wing tip limiter.
Preferably, a wing tip hinge support is fixed on the extension plate, the extension rod of the electric push rod is hinged to the extension plate specifically, and the sleeve of the electric push rod is hinged to the wing body of the wing through a wing body cross shaft.
Preferably, a wing body baffle is fixed on the wing body of the wing, and the wing body baffle is positioned above the middle position of the extension plate.
Preferably, the electric push rod is powered by a driving motor.
Compared with the prior art, the utility model has the following beneficial effects:
1. compared with the traditional multi-connecting-rod folding and unfolding wing or gear transmission folding and unfolding wing, the wing has the advantages of simple and clear configuration, high reliability, light weight and easiness in maintenance. The speed controllability of the electric push rod and the wing tip ejector is high, when the electric push rod, the wing tip ejector and the roller act on the extension plate together in the folding and unfolding processes (in the folding early stage and the unfolding later stage), the movement speed of the extension rod of the electric push rod and the change of the swinging angular speed of the wing tip ejector are controlled to realize the matched movement of the extension rod of the electric push rod and the wing tip ejector in the folding early stage and the unfolding later stage of the wing tip, and the variation of the movement speed of the extension rod of the electric push rod can make the folding and unfolding angular speed of the wing tip uniform, so that the movement of the wing tip is accurately controlled, and the movement of the wing tip is stable.
2. The wing pushing device is high in integration, and the wing flying state, namely the wing unfolding state, can be flatter due to the design of the wing tip pushing device and the horizontal arrangement of the electric push rod, so that the thickness and the structural design of the airplane wing are not influenced.
3. The utility model has stronger universality and no strict requirement on the size of the wing, and can adapt to the wings with different sizes by changing the selection of the push rod and the width of the wing tip ejector aiming at the airplanes with different sizes.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a side view of the present invention;
FIG. 3 is a schematic view of the wing tip of the present invention;
FIG. 4 is a schematic structural diagram of a wing body of the wing of the present invention;
FIG. 5 is a schematic diagram of the mechanism of the present invention;
FIG. 6 is a schematic view of the assembly of the wingtip ejector and the wingtip stop of the present invention;
FIG. 7 is a schematic view of the coordinated operation of the wingtip ejector and the electric push rod according to the present invention;
FIG. 8 is a schematic view of the present invention during the pre-fold or post-fold stage;
FIG. 9 is a schematic view of the wingtip ejector and roller disengaged from the extension plate during the collapsing process of the present invention;
fig. 10 is a schematic view of the present invention when fully deployed.
Detailed Description
The utility model is further described below with reference to the accompanying drawings.
As shown in fig. 1, 2, 3, 4, 5 and 7, the foldable wing surface for the aircraft comprises a wing tip 1, a wing body 12, a wing tip ejector 6, a wing tip ejector motor 7, an electric push rod 10 and a protruding plate 16; the wing tip 1 is the tip part of the airplane wing and is a part needing folding and unfolding; the extension plate 16 is fixed at the root of the wingtip 1 of the wing; an extension rod of the electric push rod 10 is hinged with one end of an extension plate 16 far away from the wingtip 1 of the wing; the sleeve of the electric push rod 10 is hinged with the wing body 12 of the wing; one end of the wing body 12 close to the wing tip 1 of the wing is provided with a push rod placing groove, and the extension plate 16 and the electric push rod 10 are both arranged in the push rod placing groove; one end of the wingtip ejector 6 is hinged with the root of the wingtip 1 of the wing, and the other end of the wingtip ejector abuts against the extension plate 16; the base of the wing tip ejector motor 7 is fixed with the wing body 12 of the wing, and the output shaft of the wing tip ejector motor 7 and the hinged end of the wing tip ejector 6 and the wing tip 1 of the wing are fixed.
As a preferred embodiment, as shown in fig. 1 and 3, a first wingtip beam 2 and a second wingtip beam 3 are fixed at the root of a wingtip 1 of a wing; the first wingtip beam 2 and the second wingtip beam 3 are positioned at two sides of the extension plate 16; a first wing body beam 4 and a second wing body beam 5 are fixed on the wing body 12 of the wing; one end of the first wing body beam 4 is hinged with the first wing tip beam 2, and one end of the second wing body beam 5 is hinged with the second wing tip beam 3; the hinging of the wingtip ejector 6 and the root of the wingtip 1 of the wing is as follows: the wingtip ejector 6 is hinged to the other end of the first wing-body beam 4 and the other end of the second wing-body beam 5.
As a preferred embodiment, as shown in fig. 6, the end of the wing tip ejector 6 not hinged to the root of the wing tip 1 is hinged to a roller 13.
As a more preferred embodiment, the rollers 13 are wrapped with a rubber sleeve to reduce wear on the extension plates 16.
As a preferred embodiment, as shown in fig. 6, a wing tip stopper 9 is fixed on the extension plate 16, and the end of the wing tip ejector 6 not hinged to the root of the wing tip 1 of the wing is embedded into a roller limiting groove formed in the wing tip stopper 9, and the roller limiting groove is used for limiting the wing tip ejector 6 when the wing tip 1 is completely unfolded relative to the wing body 12 of the wing.
As a preferred embodiment, as shown in fig. 1, 3, 4 and 6, a wing tip hinge support 15 is fixed on the extension plate 16, and the extension rod of the electric push rod 10 is hinged to the extension plate 16, specifically, hinged to the wing tip hinge support 15; the sleeve of the electric push rod 10 is hinged with a wing body 12 of the wing through a wing body transverse shaft 14.
As a preferred embodiment, as shown in fig. 1, a wing body baffle 8 is fixed on a wing body 12 of the wing and is used for limiting the wing tip ejector 6 when the wing tip 1 is completely unfolded relative to the wing body 12 of the wing.
As a preferred embodiment, as shown in fig. 1, the electric putter 10 is powered by a driving motor 11.
As shown in fig. 1, 5, 6, 8, 9 and 10, the foldable airfoil for the aircraft works according to the following principle:
the two foldable wing surfaces for the aircraft are matched for use and symmetrically fixed on two sides of the aircraft body.
The folding process is as follows: the wing tip ejector motor 7, the wing tip ejector 6, the roller 13, the electric push rod 10 and the electric push rod motor 11 act together in the earlier stage of folding; the wingtip ejector motor 7 drives the wingtip ejector 6 to swing downwards, the wingtip ejector 6 and the roller 13 press the extension plate 16 downwards and are separated from the roller limiting groove of the wingtip limiter 9, so that the extension plate 16 swings downwards, the dead point position of the folded wingtip of the wing is broken, and the wingtip 1 of the wing is driven to lift initially; meanwhile, the electric push rod motor 11 drives the extension rod of the electric push rod 10 to push out, so that the extension plate 16 swings downwards, and the extension rod of the electric push rod 10 and the wing tip ejector motor 7 move in a coordinated manner, so that the folding process is more stable; the wing tip ejector 6 and the roller 13 are separated from the extension plate 16 at the later stage of folding, only the electric push rod motor 11 drives the extension rod of the electric push rod 10 to eject, so that the extension plate 16 continues to swing downwards until the wing tip 1 of the wing is vertical to the ground, and the wing tip ejector motor 7 drives the wing tip ejector 6 to swing upwards to reset.
The unfolding process is as follows: the electric push rod motor 11 drives the extension rod of the electric push rod 10 to retract in the early stage of unfolding, so that the wing tip 1 of the wing swings downwards (the extension plate 16 swings upwards), and the wing tip ejector motor 7 drives the wing tip ejector 6 to swing downwards until the extension plate 16 is contacted with the roller 13 on the wing tip ejector 6; and in the later stage of unfolding, the wing tip ejector motor 7, the wing tip ejector 6, the roller 13, the electric push rod 10 and the electric push rod motor 11 act together, the electric push rod motor 11 drives the extension rod of the electric push rod 10 to continue retracting, the wing tip 1 of the wing continues swinging downwards, meanwhile, the wing tip ejector motor 7 drives the wing tip ejector 6 to swing upwards and be embedded into the roller limiting groove of the wing tip limiter 9, the extension rod of the electric push rod 10 and the wing tip ejector motor 7 move in a coordinated manner until the wing tip 1 of the wing is completely unfolded and locked, and at the moment, the top surface of the wing tip ejector 6 is limited by the wing body baffle 8.
Claims (8)
1. Foldable wing surface for aircraft, including wing wingtip, wing body and electric putter, its characterized in that: the wing tip pushing device comprises a wing tip pushing device motor and a protruding plate; the extension plate is fixed at the root of the wingtip of the wing; an extension rod of the electric push rod is hinged with one end of the extension plate, which is far away from the wingtips of the wings; a sleeve of the electric push rod is hinged with the wing body of the wing; one end of the wing body of the wing, which is close to the wing tip of the wing, is provided with a push rod placing groove, and the extension plate and the electric push rod are both arranged in the push rod placing groove; one end of the wingtip ejector is hinged with the root of the wingtip of the wing, and the other end of the wingtip ejector is abutted against the extending plate; the base of the wing tip ejector motor is fixed with the wing body of the wing, and the output shaft of the wing tip ejector motor and the end of the wing tip ejector hinged with the wing tip of the wing are fixed.
2. The deployable airfoil for an aircraft of claim 1, wherein: a first wingtip beam and a second wingtip beam are fixed at the root of the wingtip of the wing; the first wingtip beam and the second wingtip beam are positioned on two sides of the extending plate; a first wing body beam and a second wing body beam are fixed on the wing body of the wing; one end of the first wing body beam is hinged with the first wingtip beam, and one end of the second wing body beam is hinged with the second wingtip beam; the hinge joint of the wingtip ejector and the root of the wingtip of the wing is specifically as follows: the wingtip ejector is hinged to the other ends of the first wingbody beam and the second wingbody beam.
3. The deployable airfoil for an aircraft of claim 1, wherein: and the end of the wing tip ejector, which is not hinged with the root of the wing tip of the wing, is hinged with a roller.
4. The deployable airfoil for an aircraft of claim 3, wherein: the roller is wrapped by a rubber sleeve.
5. The deployable airfoil for an aircraft of claim 1, wherein: the extending plate is fixed with a wing tip limiter, and the end of the wing tip ejector, which is not hinged with the root of the wing tip of the wing, is embedded into a roller limiting groove formed in the wing tip limiter.
6. The deployable airfoil for an aircraft of claim 1, wherein: the extension plate is fixed with a wing tip hinge support, the extension rod of the electric push rod is hinged with the extension plate through a wing body cross shaft, and the sleeve of the electric push rod is hinged with the wing body of the wing through the wing body cross shaft.
7. The deployable airfoil for an aircraft of claim 1, wherein: the wing body of the wing is fixed with a wing body baffle which is positioned above the middle position of the extending plate.
8. The deployable airfoil for an aircraft of claim 1, wherein: the electric push rod is powered by a driving motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121106851.6U CN215399304U (en) | 2021-05-23 | 2021-05-23 | Foldable wing surface for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121106851.6U CN215399304U (en) | 2021-05-23 | 2021-05-23 | Foldable wing surface for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215399304U true CN215399304U (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121106851.6U Active CN215399304U (en) | 2021-05-23 | 2021-05-23 | Foldable wing surface for aircraft |
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| CN (1) | CN215399304U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115230946A (en) * | 2022-09-26 | 2022-10-25 | 成都市鸿侠科技有限责任公司 | Wing tip vortex flow control structure and control method |
-
2021
- 2021-05-23 CN CN202121106851.6U patent/CN215399304U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115230946A (en) * | 2022-09-26 | 2022-10-25 | 成都市鸿侠科技有限责任公司 | Wing tip vortex flow control structure and control method |
| CN115230946B (en) * | 2022-09-26 | 2022-12-02 | 成都市鸿侠科技有限责任公司 | Wing tip vortex flow control structure and control method |
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