CN113320684B - Foldable wing surface for aircraft and folding and unfolding method thereof - Google Patents
Foldable wing surface for aircraft and folding and unfolding method thereof Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
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- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The invention discloses a foldable wing surface for an aircraft and a folding and unfolding method thereof. 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 wheel act on the extension plate together in the folding and unfolding process, 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, so that the matching 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 can be realized, and the movement speed change of the extension rod of the electric push rod can be controlled, so that the folding and unfolding angular speed of the wing tip can be uniform, the movement of the wing tip can be accurately controlled, and the movement of the wing tip is stable.
Description
Technical Field
The invention belongs to the field of aerospace, and particularly relates to a foldable wing surface for an aircraft and a folding and unfolding method thereof.
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 big wing can save more oil for the passenger plane in the flying process and reduce the flying cost of an 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 invention provides a foldable wing surface mechanism for an aircraft and a folding and unfolding method thereof, which aim at the development requirements of aerospace aircrafts and fill the blank of the wing folding and unfolding technology of domestic passenger planes.
The technical scheme adopted by the invention is as follows:
the invention relates to a foldable wing surface for an aircraft, which comprises a wing tip, a wing body, a first wing tip beam, a second wing tip beam, a first wing body beam, a second wing body beam, a wing tip ejector, rollers, a wing body baffle, a wing tip limiter, a wing tip ejector motor, an electric push rod motor, a wing body cross shaft, a wing tip hinge support and an extension plate. The first wingtip beam, the second wingtip beam and the extension plate are all fixed at the root of the wingtip of the wing, and the first wingtip beam and the second wingtip beam are positioned at two sides of the extension plate; the wing tip limiter and the wing tip hinge support are both fixed with the extension plate; an extension rod of the electric push rod is hinged on the wing tip hinge support; 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; the sleeve of the electric push rod is hinged with the wing body of the wing through a transverse shaft of the wing body; the electric push rod is powered by a driving motor; the first wing body beam and the second wing body beam are both fixed with 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; one end of the wingtip ejector is hinged with the other ends of the first wingbody beam and the second wingbody beam, and the other end of the wingtip ejector is hinged with the roller; the roller is embedded into a roller limiting groove formed in the wingtip limiter; 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 hinged end of the wing tip ejector and the first wing body beam are fixed; the wing body baffle is fixed with the wing body of the wing and is positioned above the middle position of the wingtip ejector.
Preferably, the roller is externally wrapped with a rubber sleeve.
Preferably, the included angle theta between the wing body of the wing and the extension plate2The calculation is as follows:
wherein L is1The distance L from the hinge center of the wing tip ejector and the first wing body beam to the hinge center of the first wing body beam and the first wing tip beam2The distance L from the hinge center of the wing tip ejector and the first wing body beam to the hinge center of the wing body and the electric push rod4The distance L from the hinge center of the first wing body beam and the first wing tip beam to the hinge center of the electric push rod and the wing tip hinge support0The length of the electric push rod is V when the extension rod of the electric push rod is in a complete retraction state1The motion speed of the extension bar of the electric push bar is t, and t is time.
Angular velocity omega of wing tip folding and unfolding2The calculation is as follows:
wherein,
angular velocity ω of wingtip ejector oscillation1The calculation is as follows:
wherein, theta1The included angle between the wing body of the wing and the wing tip push rod is formed; theta.theta.4The included angle between the wing tip ejector and the wing extension plate is set; l is3The distance from the hinge center of the wingtip ejector and the first wingbody beam to the center of a roller on the wingtip ejector.
Combining formula (2) and formula (5) to obtain:
angular velocity ω of wingtip folding and unfolding given by equation (2)2With the speed V of movement of the extension rod of the electric push rod1And the angular velocity ω of the wingtip ejector oscillation given by equation (6)1With the speed V of movement of the extension rod of the electric push rod1Relation, controlling the speed V of the extension rod of the electric push rod1Angular velocity omega associated with the tip ejector oscillation1The change of the extension bar of the electric push rod and the wing tip ejector realizes the matching motion when the electric push rod, the wing tip ejector and the roller act on the extension plate together in the folding and unfolding processes, and the motion speed V of the extension bar of the electric push rod is controlled1Angular velocity omega varying to fold and unfold the wingtips of wings2And (4) keeping the speed constant.
More preferably, the angular velocity ω of the swing of the extension bar of the electric putter3The calculation is as follows:
wherein, theta3Is the included angle between the wing body of the wing and the electric push rod.
The folding and unfolding method of the foldable wing surface for the aircraft comprises the following specific steps:
the folding process is as follows: the wing tip ejector motor, the wing tip ejector, the roller, the electric push rod and the electric push rod motor act together in the earlier stage of folding; the wing tip ejector motor drives the wing tip ejector to swing downwards, the wing tip ejector and the roller press the extension plate downwards and are separated from the roller limiting groove of the wing tip limiter, so that the extension plate swings downwards, the dead point position of the folded wing tip of the wing is broken, and the wing tip of the wing is driven to be lifted preliminarily; meanwhile, the electric push rod motor drives the extension rod of the electric push rod to push out, so that the extension plate swings downwards, and the extension rod of the electric push rod and the wing tip ejector motor move in a coordinated manner, so that wing tips of the wings are folded at a constant speed; and the wing tip ejector and the roller are separated from the extension plate at the later stage of folding, only the electric push rod motor drives the extension rod of the electric push rod to eject, so that the extension plate continues to swing downwards until the wing tip of the wing is vertical to the ground, and the wing tip ejector motor drives the wing tip ejector to swing upwards to reset.
The unfolding process is as follows: the electric push rod motor drives the extension rod of the electric push rod to retract in the early stage of unfolding, so that the wing tip of the wing swings downwards, and the wing tip ejector motor drives the wing tip ejector to swing downwards until the extension plate is contacted with the roller on the wing tip ejector; and in the later stage of unfolding, the wing tip ejector motor, the wing tip ejector, the roller, the electric push rod and the electric push rod motor act together, the electric push rod motor drives the extension rod of the electric push rod to continue retracting, the wing tip continues to swing downwards, meanwhile, the wing tip ejector motor drives the wing tip ejector to swing upwards and be embedded into the roller limiting groove of the wing tip limiter, the extension rod of the electric push rod and the wing tip ejector motor move in a coordinated manner, the wing tip is unfolded at a constant speed until the wing tip is completely unfolded and locked, and at the moment, the top surface of the wing tip ejector is limited by the wing body baffle.
Compared with the prior art, the invention 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 invention 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 type 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 a deployable airfoil for an aircraft according to the present invention;
FIG. 2 is a side view of a deployable airfoil for an aircraft in accordance with the present invention;
FIG. 3 is a schematic view of a tip structure of a foldable airfoil for an aircraft according to the present invention;
FIG. 4 is a schematic view of a wing body of a foldable airfoil for an aircraft according to the present invention;
FIG. 5 is a schematic diagram of the mechanism of a deployable airfoil for an aircraft according to the present invention;
FIG. 6 is a simplified dimension and motion diagram of a deployable airfoil for an aircraft in accordance with the present invention;
FIG. 7 is a schematic view of the assembly of the wingtip ejector and the wingtip retainer of the present invention;
FIG. 8 is a schematic view of the coordinated operation of the wingtip ejector and the electric push rod according to the present invention;
FIG. 9(a) is a schematic view of a foldable airfoil for an aircraft according to the present invention during a pre-deployment or post-deployment phase;
FIG. 9(b) is a schematic view of a tip ejector and roller disengaged from an extended plate during folding and unfolding of an extendable airfoil for an aircraft according to the present invention;
FIG. 9(c) is a schematic illustration of a fully deployed deployable airfoil for an aircraft according to the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, 2, 3, 4 and 7, a foldable wing surface for an aircraft comprises a wing tip 1, a wing body 12, a first wing tip beam 2, a second wing tip beam 3, a first wing body beam 4, a second wing body beam 5, a wing tip ejector 6, rollers 13, a wing body baffle 8, a wing tip stopper 9, a wing tip ejector motor 7, an electric push rod 10, an electric push rod motor 11, a wing body transverse shaft 14, a wing tip hinge support 15 and an extension plate 16. The wing tip 1 is the tip part of the airplane wing and is a part needing folding and unfolding; the first wingtip beam 2, the second wingtip beam 3 and the extension plate 16 are all fixed at the root of the wingtip 1 of the wing, and the first wingtip beam 2 and the second wingtip beam 3 are positioned at two sides of the extension plate 16; the wing tip limiter 9 and the wing tip hinge support 15 are both fixed with the extension plate 16; the extension rod of the electric push rod 10 is hinged on the wing tip hinge support 15;
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; 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; the electric push rod 10 is provided with a driving motor 11 for providing power for the electric push rod 10; the first wing body beam 4 and the second wing body beam 5 are both fixed with 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; one end of the wing tip ejector 6 is hinged with the other ends of the first wing body beam 4 and the second wing body beam 5, and the other end of the wing tip ejector is hinged with the roller 13; the roller 13 is embedded into a roller limiting groove formed in the wing tip limiter 9, and the roller limiting groove is used for limiting the roller 13 when the wing tip 1 is completely unfolded relative to the wing body 12; the base of the wing tip ejector motor 7 is fixed with the wing body 12, and the output shaft of the wing tip ejector motor 7 and the hinged end of the wing tip ejector 6 and the first wing body beam 4 are fixed; the wing body baffle 8 is fixed with the wing body 12 and used for limiting the wing tip ejector 6 when the wing tip 1 is completely unfolded relative to the wing body 12.
As a 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. 5 and 6, when the electric push rod 10, the wingtip ejector 6 and the roller 13 act on the extending plate 16 together during the folding and unfolding process (which occurs in the early stage and the late stage of the folding), in order to accurately control the movement of the wingtip 1 of the wing and stabilize the movement of the wingtip 1 of the wing, the angular velocity ω of the swinging of the wingtip ejector 6 is set below1And the extension bar movement speed V of the electric push bar 101The relationship is calculated as:
the angle theta between the wing body 12 and the extension plate 162The calculation is as follows:
wherein L is1The distance L from the center B of the articulation of the wingtip ejector 6 with the first wingbody beam 4 to the center A of the articulation of the first wingbody beam 4 with the first wingtip beam 22The distance L from the hinge center B of the wing tip ejector 6 and the first wing body beam 4 to the hinge center D of the wing body 12 and the electric push rod 104The distance L from the hinge center A of the first wing body beam 4 and the first wing tip beam 2 to the hinge center C of the electric push rod 10 and the wing tip hinge support 150The length of the electric putter 10 in the fully retracted state of the extension bar of the electric putter 10, t is the operation time.
Angular velocity omega of wing tip folding and unfolding2The calculation is as follows:
wherein,
angular velocity ω of the wingtip ejector 6 oscillation1The calculation is as follows:
wherein, theta1The included angle between the wing body 12 of the wing and the wing tip push rod 6 is shown; theta.theta.4The included angle between the wing tip ejector 6 and the wing extension plate 16; l is a radical of an alcohol3The distance from the centre B of articulation of the wing tip ejector 6 with the first wing body beam 4 to the centre of the roller 13 on the wing tip ejector 6.
Combining formula (2) and formula (5) to obtain:
angular velocity ω of wing tip 1 folding and unfolding given by formula (2)2With the speed V of movement of the extension rod of the power putter 101And the angular velocity ω of the swing of the wingtip ejector 6 given by the equation (6)1The speed V of the extension rod of the electric push rod 101Relation, control V1And omega1The change of the angle can realize the matching movement of the extension rod of the electric push rod 10 and the wing tip ejector 6 in the early folding stage and the later unfolding stage of the wing tip 1 of the wing, and control V1The angular velocity omega at which the wingtip 1 of the wing can be folded and unfolded can be obtained by the change of the velocity2And (4) keeping the speed constant.
As a more preferred embodiment, the angular velocity ω of the swing of the extension bar of the electric putter 103The calculation is as follows:
wherein, theta3The included angle between the wing body 12 and the electric push rod 10 is shown.
The two foldable wing surfaces for the aircraft are matched for use and symmetrically fixed on two sides of the aircraft body.
As shown in fig. 5, 6, 8, 9(a), 9(b) and 9(c), the folding and unfolding method of the foldable wing surface for the aircraft comprises the following steps:
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 wing tip ejector motor 7 drives the wing tip ejector 6 to swing downwards, the wing tip ejector 6 and the roller 13 press the extension plate 16 downwards and are separated from the roller limiting groove of the wing tip limiter 9, so that the extension plate 16 swings downwards, the dead point position of the folded state of the wing tip is broken, and the wing tip 1 of the wing is driven to lift preliminarily; 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 (5)
1. The utility model provides a can roll over exhibition airfoil for aircraft, includes wing wingtip, wing body, first wingtip roof beam, second wingtip roof beam, electric putter and electric putter motor, its characterized in that: the wing tip pushing device comprises a wing tip pushing device, a roller, a wing body baffle, a wing tip limiter, a wing tip pushing device motor, a wing body cross shaft, a wing tip hinge support and a stretching plate; the first wingtip beam, the second wingtip beam and the extending plate are all fixed at the root part of the wingtip of the wing, and the first wingtip beam and the second wingtip beam are positioned at two sides of the extending plate; the wing tip limiter and the wing tip hinge support are both fixed with the extension plate; an extension rod of the electric push rod is hinged on the wing tip hinge support; 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; the sleeve of the electric push rod is hinged with the wing body of the wing through a transverse shaft of the wing body; the electric push rod is powered by an electric push rod motor; the first wing body beam and the second wing body beam are both fixed with 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; one end of the wingtip ejector is hinged with the other ends of the first wingbody beam and the second wingbody beam, and the other end of the wingtip ejector is hinged with the roller; the roller is embedded into a roller limiting groove formed in the wingtip limiter; 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 first wing body beam are fixed; the wing body baffle is fixed with the wing body of the wing and is positioned above the middle position of the wing tip ejector.
2. The deployable airfoil for an aircraft according to claim 1, wherein: the roller is wrapped by a rubber sleeve.
3. The deployable airfoil for an aircraft according to claim 1, wherein: the included angle theta between the wing body of the wing and the extension plate2The calculation is as follows:
wherein L is1The distance L from the hinge center of the wing tip ejector and the first wing body beam to the hinge center of the first wing body beam and the first wing tip beam2The distance L from the hinge center of the wing tip ejector and the first wing body beam to the hinge center of the wing body and the electric push rod4The distance L from the hinge center of the first wing body beam and the first wing tip beam to the hinge center of the electric push rod and the wing tip hinge support0The length of the electric push rod is V when the extension rod of the electric push rod is in a complete retraction state1The motion speed of an extension rod of the electric push rod is shown, and t is time;
angular velocity omega of wing tip folding and unfolding2The calculation is as follows:
wherein,
angular velocity omega of wingtip ejector swing1The calculation is as follows:
wherein, theta1The included angle between the wing body of the wing and the wing tip push rod is formed; theta4The included angle between the wing tip ejector and the wing extension plate is set; l is3The distance from the hinge center of the wing tip ejector and the first wing body beam to the center of a roller on the wing tip ejector is obtained;
combining formula (2) and formula (5) to obtain:
angular velocity ω of wingtip folding and unfolding given by equation (2)2With the speed V of movement of the extension rod of the electric push rod1And the angular velocity ω of the wingtip ejector oscillation given by equation (6)1The movement speed V of the extension bar of the electric push rod1Relation, controlling the speed V of the extension rod of the electric push rod1Angular velocity omega associated with the tip ejector oscillation1The change realizes the matching motion of the extension bar of the electric push rod and the wing tip ejector when the electric push rod, the wing tip ejector and the roller act on the extension plate together in the folding and unfolding processes, and the motion speed V of the extension bar of the electric push rod is controlled1Angular velocity omega of wing tip to be folded and unfolded2And (4) keeping the speed constant.
4. A foldable airfoil for an aircraft according to claim 3, further comprising: angular velocity omega of swing of extension rod of electric push rod3The calculation is as follows:
wherein, theta3Is the included angle between the wing body of the wing and the electric push rod.
5. The method for folding and unfolding an unfoldable airfoil for an aircraft according to any of claims 1 to 4, wherein: the method comprises the following specific steps:
the folding process is as follows: the wing tip ejector motor, the wing tip ejector, the roller, the electric push rod and the electric push rod motor act together in the earlier stage of folding; the wing tip ejector motor drives the wing tip ejector to swing downwards, the wing tip ejector and the roller press the extension plate downwards and are separated from the roller limiting groove of the wing tip limiter, so that the extension plate swings downwards, the dead point position of the folded wing tip of the wing is broken, and the wing tip of the wing is driven to be lifted preliminarily; meanwhile, the electric push rod motor drives the extension rod of the electric push rod to push out, so that the extension plate swings downwards, and the extension rod of the electric push rod and the wing tip ejector motor move in a coordinated manner, so that wing tips of the wings are folded at a constant speed; the wing tip ejector and the roller are separated from the extension plate at the later stage of folding, only the electric push rod motor drives the extension rod of the electric push rod to eject, so that the extension plate continues to swing downwards until the wing tip of the wing is vertical to the ground, and the wing tip ejector motor drives the wing tip ejector to swing upwards to reset;
the unfolding process is as follows: the electric push rod motor drives the extension rod of the electric push rod to retract in the early stage of unfolding, so that the wing tip of the wing swings downwards, and the wing tip ejector motor drives the wing tip ejector to swing downwards until the extension plate is contacted with the roller on the wing tip ejector; and in the later stage of unfolding, the wing tip ejector motor, the wing tip ejector, the roller, the electric push rod and the electric push rod motor act together, the electric push rod motor drives the extension rod of the electric push rod to continue retracting, the wing tip continues to swing downwards, meanwhile, the wing tip ejector motor drives the wing tip ejector to swing upwards and be embedded into the roller limiting groove of the wing tip limiter, the extension rod of the electric push rod and the wing tip ejector motor move in a coordinated manner, the wing tip is unfolded at a constant speed until the wing tip is completely unfolded and locked, and at the moment, the top surface of the wing tip ejector is limited by the wing body baffle.
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| CN202110561634.4A CN113320684B (en) | 2021-05-23 | 2021-05-23 | Foldable wing surface for aircraft and folding and unfolding method thereof |
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| GB2528231A (en) * | 2014-04-24 | 2016-01-20 | Airbus Operations Ltd | An aircraft with a foldable wing tip device |
| EP3524514A1 (en) * | 2018-02-09 | 2019-08-14 | Airbus Operations GmbH | Actuation unit for actuating a foldable wing tip portion of a wing for an aircraft |
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