CN211252988U - Wing assembly of aircraft and aircraft - Google Patents
Wing assembly of aircraft and aircraft Download PDFInfo
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- CN211252988U CN211252988U CN201921178106.5U CN201921178106U CN211252988U CN 211252988 U CN211252988 U CN 211252988U CN 201921178106 U CN201921178106 U CN 201921178106U CN 211252988 U CN211252988 U CN 211252988U
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- aileron
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Abstract
The utility model discloses a wing subassembly and aircraft of aircraft. The wing assembly comprises a wing main body, ailerons and a steering engine. The aileron can overturn for the wing main part, and the wing main part is located to the steering wheel, and the power output shaft of steering wheel wears to locate the wing main part and power output shaft is connected with the aileron and overturns in order to drive the aileron, and power output shaft's extending direction is the same with the length direction of aileron. According to the utility model discloses a wing subassembly of aircraft can arrange the wire of being connected with the steering wheel in the wing main part, when dismantling the aileron, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong the life of aircraft. In addition, the extending direction of the power output shaft is the same as the length direction of the ailerons, so that the positions of the steering gears are convenient to arrange, the ailerons are driven by the steering gears to turn over, and the flexibility of the aileron movement can be improved.
Description
Technical Field
The utility model belongs to the technical field of the aircraft technique and specifically relates to a wing subassembly and aircraft of aircraft are related to.
Background
The fuselage of the composite fixed-wing aircraft contains various devices and wiring for realizing various functions of the aircraft, so that the composite fixed-wing aircraft is generally delivered from a factory and assembled well without being assembled by a user. However, the combined fixed-wing aircraft has a large volume, which brings great trouble to users to carry, and cannot meet various use requirements. For the reasons mentioned above, rapidly assemblable composite fixed wing aircraft have been rapidly developed.
However, the existing fast-assembling composite fixed-wing aircraft not only needs to change the mechanical structure, but also needs to design the strong electric wires and the signal wires of the motor as disconnectable electrical interfaces, and has complex disassembly and assembly processes and low reliability.
SUMMERY OF THE UTILITY MODEL
The application provides a wing subassembly of aircraft, the wing subassembly has simple structure, long service life's advantage.
The present application further provides a flying device having a wing assembly as described above.
According to the utility model discloses wing subassembly of aircraft, include: a wing body; an aileron that is invertible relative to the wing body; the steering engine is arranged on the wing main body, a power output shaft of the steering engine penetrates through the wing main body and is connected with the ailerons to drive the ailerons to turn over, and the extension direction of the power output shaft is the same as the length direction of the ailerons.
According to the utility model discloses wing assembly of aircraft through setting up the steering wheel in the wing main part, and the power output shaft of steering wheel passes the wing main part and is connected with the aileron, can arrange the wire of being connected with the steering wheel in the wing main part from this, when dismantling the aileron, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong the life of aircraft. In addition, the extending direction of the power output shaft is the same as the length direction of the ailerons, so that the positions of the steering gears are convenient to arrange, the ailerons are driven by the steering gears to turn over, and the flexibility of the aileron movement can be improved.
In some embodiments, the wing body is adapted to be disposed in a midsection of a fuselage of the aircraft and comprises: one end of the first wing section is suitable for being connected with a fuselage, and the steering engine is arranged on the first wing section; the second wing section is connected with the other end of the first wing section, the aileron is arranged on the second wing section, and the aileron can turn over relative to the second wing section.
In some embodiments, the first wing section comprises: a wing section body adapted for connection to a fuselage; the fixing piece, the fixing piece with the pterygoid lamina main part is connected, the periphery of pterygoid lamina arm is suitable for the cover to locate to the fixing piece, the fixing piece with second pterygoid lamina is connected, the fixing piece with at least one in the pterygoid lamina main part is equipped with the steering wheel.
In some embodiments, the flap comprises: a first body portion connected with the second wing section; the first connecting assembly comprises a first connecting piece and a second connecting piece, the first connecting piece is connected with the fixing piece through the first connecting assembly, the first connecting piece is connected with the fixing piece, the first connecting piece is connected with the power output shaft, the second connecting piece is connected with the first connecting piece, and the first main body portion is connected with the first connecting piece through the second connecting piece.
In some embodiments, one of the first connecting piece and the second connecting piece is provided with a matching protrusion, and the other one is provided with a matching groove, and the matching protrusion is suitable for being arranged in the matching groove in a penetrating mode.
In some embodiments, the mating groove is elongated and the mating protrusion is cylindrical.
In some embodiments, the second connector is in the form of a hood, the second connector hood being provided at one end of the flap.
In some embodiments, the second wing section is removably connected to the first wing section.
In some embodiments, the wing body is adapted to be disposed aft of a fuselage of an aircraft, the aileron comprising: a second body portion connected to the wing body; the second coupling assembling, the second main part passes through the second coupling assembling with the tail boom seat of aircraft is connected, the second coupling assembling includes third connecting piece and fourth connecting piece, the third connecting piece with power take off shaft connects, the fourth connecting piece with the third connecting piece is connected, the second main part passes through the fourth connecting piece with the third connecting piece is connected.
In some embodiments, one of the third connecting piece and the fourth connecting piece is provided with a matching protrusion, and the other one is provided with a matching groove, and the matching protrusion is suitable for being arranged in the matching groove in a penetrating mode.
In some embodiments, the mating groove is elongated and the mating protrusion is cylindrical.
In some embodiments, the fourth connector is in the form of a hood, the fourth connector hood being provided at one end of the flap.
According to the utility model discloses aircraft, including the fuselage and as above the wing subassembly, the wing subassembly with the fuselage is connected.
According to the utility model discloses aircraft through setting up the steering wheel in the wing main part, and the power output shaft of steering wheel passes the wing main part and is connected with the aileron, can arrange the wire of being connected with the steering wheel in the wing main part from this, when dismantling the aileron, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong the life of aircraft. In addition, the extending direction of the power output shaft is the same as the length direction of the ailerons, so that the positions of the steering gears are convenient to arrange, the ailerons are driven by the steering gears to turn over, and the flexibility of the aileron movement can be improved.
The aircraft according to the embodiment of the utility model comprises a fuselage; the first wing assembly is the wing assembly, the first wing assembly is connected with the fuselage, and the first wing assembly is positioned in the middle of the fuselage; a wing arm disposed through the first wing assembly; the second wing component is connected with the rear end of the wing arm, and the second wing component is the wing component; the first power part is arranged at the front end of the wing arm; and the second power part is arranged on the machine body.
According to the utility model discloses aircraft through setting up the steering wheel in the wing main part, and the power output shaft of steering wheel passes the wing main part and is connected with the aileron, can arrange the wire of being connected with the steering wheel in the wing main part from this, when dismantling the aileron, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong the life of aircraft. In addition, the extending direction of the power output shaft is the same as the length direction of the ailerons, so that the positions of the steering gears are convenient to arrange, the ailerons are driven by the steering gears to turn over, and the flexibility of the aileron movement can be improved.
In some embodiments, the wing body of the second wing assembly is provided with a tail support seat, and the steering engine is arranged in the tail support seat.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural view of an aircraft according to an embodiment of the invention;
FIG. 2 is an enlarged partial schematic view at A of FIG. 1;
figure 3 is a schematic structural view of an aircraft according to an embodiment of the invention;
FIG. 4 is an enlarged partial schematic view at B of FIG. 3;
FIG. 5 is an enlarged partial schematic view at C of FIG. 3;
fig. 6 is a schematic partial structural view of an aircraft according to an embodiment of the invention;
fig. 7 is a schematic partial structural view of an aircraft according to an embodiment of the invention;
figure 8 is a schematic view of a mounting structure for an aircraft according to an embodiment of the invention;
figure 9 is a schematic view of a second and fourth connection for an aircraft according to an embodiment of the invention;
fig. 10 is a schematic view of a first and third connector of an aircraft according to an embodiment of the invention.
Reference numerals:
the aircraft (1000) is provided with a vehicle,
the body 100 is provided with a plurality of air holes,
the length of the wing arm 200, the tail boom seat 210,
the wing assembly 300 is shown in a schematic view,
a wing main body 320, a first wing section 321, a wing section main body 322, a fixing member 323, a plug hole 3231, a through hole 3232, a second wing section 324, a plug column 3241,
the first wing assembly 300a, the flap 310, the mating groove 313, the mating protrusion 315,
a first body portion 311a, a first connecting member 312a, a second connecting member 314a,
a second wing assembly 300b, a second body portion 311b, a third connection 312b, a fourth connection 314b,
a power take-off shaft 331 that is,
a first power member 400 and a second power member 500.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present invention, and should not be construed as limiting the present invention.
A wing assembly 300 of an aircraft 1000 and the aircraft 1000 according to embodiments of the invention are described below with reference to fig. 1-10.
As shown in fig. 1 and 3, a wing assembly 300 of an aircraft 1000 according to an embodiment of the present invention includes a wing main body 320, an aileron 310, and a steering engine. It should be noted that the wing assembly 300 may be disposed on the fuselage 100 of the aircraft 1000.
Specifically, the aileron 310 can be turned over relative to the wing body 320, the steering engine is disposed on the wing body 320, the power output shaft 331 of the steering engine is disposed through the wing body 320, the power output shaft 331 is connected to the aileron 310 to drive the aileron 310 to turn over, and the extending direction of the power output shaft 331 is the same as the length direction (the left and right direction shown in fig. 1 and 3) of the aileron 310.
According to the utility model discloses wing subassembly 300 of aircraft 1000, through setting up the steering wheel in wing main part 320, and the power output shaft 331 of steering wheel passes wing main part 320 and is connected with aileron 310, can arrange the wire of being connected with the steering wheel on wing main part 320 from this, when dismantling aileron 310, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong aircraft 1000's life. In addition, the extending direction of the power output shaft 331 is the same as the length direction of the aileron 310, so that the position of the steering engine can be conveniently distributed, the aileron 310 can be conveniently driven to turn by the steering engine, and the flexibility of the movement of the aileron 310 can be improved.
As shown in fig. 1-3, a wing body 320 may be located in the middle of the fuselage 100 of an aircraft 1000, according to some embodiments of the invention. And the wing body 320 may include a first wing section 321 and a second wing section 324. Wherein, the one end of first wing section 321 is suitable for being connected with fuselage 100, and the steering wheel is located first wing section 321, and second wing section 324 is connected with the other end detachably of first wing section 321, and the aileron 310 is located second wing section 324, and the aileron 310 can overturn for second wing section 324. It will be appreciated that by segmenting the wing body 320, the first and second wing segments 321, 324 can be separately stowed when it is desired to stow the wing assembly 300, thereby reducing the volume of space occupied by the wing assembly 300.
In addition, it should be noted that the wing assembly is one of the important components of the aircraft, and the main function of the wing assembly is to generate lift force, and a steering engine for adjusting the flight state of the aircraft is usually arranged on the wing assembly. When the aircraft is maintained and parts are replaced, the wing assembly is usually required to be detached, and when the wing assembly is detached, the steering engine and a wire connected with the steering engine are usually touched, so that the steering engine and the wire connected with the steering engine are easily damaged due to fatigue.
Through setting up the steering wheel in the first wing section 321 of being connected with fuselage 100, set up aileron 310 at second wing section 324, can arrange the wire of being connected with the steering wheel at first wing section 321 from this, when dismantling second wing section 324 from first wing section 321, then need not to dismantle the steering wheel and the wire of being connected with the steering wheel, thereby not only conveniently dismantle second wing section 324, can also reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong wing assembly 300's life.
In some embodiments, the second wing section 324 is provided with a plug-in post 3241, the fixing member 323 is provided with a plug-in hole 3231, and the plug-in member 3241 can be plugged into the plug-in hole 3231, thereby improving the connection stability between the first wing section 321 and the second wing section 324.
As shown in fig. 2, 4, and 8, in some embodiments, the first panel 321 may include a panel body 322 and a fastener 323. Wherein, the wing section main part 322 is suitable for being connected with the fuselage 100, and the mounting 323 is connected with wing section main part 322, and the mounting 323 is suitable for the periphery of the cover locating wing arm 200, and the mounting 323 is connected with second wing section 324, and at least one in mounting 323 and wing section main part 322 is equipped with the steering wheel. It should be noted that in some models, the wing arm 200 needs to be arranged on the aircraft 1000, and the wing arm 200 is convenient to assemble by arranging the fixing member 323; in addition, at least one of the fixing part 323 and the wing panel main body 322 is internally provided with a steering engine, so that the wires on the steering engine can be conveniently distributed.
In some embodiments, as shown in fig. 2, 4, the flap 310 may include a first body portion 311a and a first connection assembly. The first body portion 311a is connected to the fixing member 323 by a first connection assembly, which includes a first connection member 312a and a second connection member 314 a. The first body 311a may be connected to the second wing 324, the first connecting member 312a is connected to the fixing member 323, the first connecting member 312a is connected to the power output shaft 331, the second connecting member 314a is connected to the first connecting member 312a, and the first body 311a is connected to the first connecting member 312a through the second connecting member 314 a.
It is understood that the second wing section 324 can be used for supporting and connecting the first body portion 311a, and the fixing member 323 can be used for supporting and connecting the first connecting member 312 a. Through setting up first connecting piece 312a and second connecting piece 314a, can utilize first connecting piece 312a to transmit the power of power output shaft 331 to second connecting piece 314a on, second connecting piece 314a can transmit power to first main part 311a again, can utilize the steering wheel drive aileron 310 to overturn from this. When power is transmitted between the steering engine and the aileron 310, the first connecting piece 312a can rotate relative to the fixing piece 323, and the first main body part 311a can rotate relative to the wing segment.
In order to improve the stability of the engagement between the first connection member 312a and the second connection member 314a, in some embodiments, as shown in fig. 4, 9 and 10, one of the first connection member 312a and the second connection member 314a is provided with an engagement protrusion 315, and the other is provided with an engagement groove 313, and the engagement protrusion 315 is adapted to be inserted into the engagement groove 313. In order to improve the convenience of assembly between the first connection member 312a and the second connection member 314a, in some embodiments, as shown in fig. 10, the engagement groove 313 may have an elongated shape, and as shown in fig. 9, the engagement protrusion 315 may have a cylindrical shape. Therefore, when the fitting protrusion 315 is fitted into the fitting groove 313, the fitting groove 313 can provide a large fitting space for the fitting protrusion 315, and an operator can insert the fitting protrusion 315 into the fitting groove 313 conveniently.
According to some embodiments of the present invention, as shown in fig. 9, the second connecting element 314a may be in a cover shape, and the cover-shaped second connecting element 314a may cover the end of the flap 310, so as to facilitate the connection between the power output shaft 331 and the flap 310, and further improve the structural strength of the end of the flap 310 by using the second connecting element 314a, so as to protect the end of the flap 310, thereby reducing the fatigue damage of the flap 310 and prolonging the service life of the flap 310.
As shown in fig. 3 and 5, according to some embodiments of the present invention, the wing body 320 may be located at the tail of the fuselage 100 (i.e., the rear of the fuselage 100) of the aircraft 1000, and the aileron 310 may include a second body portion 311b and a second connection assembly. Wherein the second main body part 311b is connected with the tail boom seat 210 of the aircraft 1000 through the second connection assembly. The second connection assembly may include a third connection 312b and a fourth connection 314 b. The second main body 311b is connected to the wing main body 320, the third connection member 312b is connected to the power output shaft 331, the fourth connection member 314b is connected to the third connection member 312b, and the second main body 311b is connected to the third connection member 312b through the fourth connection member 314 b. It should be noted that the wing main body 320 may be used to support and connect the second main body portion 311b, and the third connecting member 312b is used to transmit the power of the power output shaft 331 to the fourth connecting member 314b, and the fourth connecting member 314b may transmit the power to the second main body portion 311b, so that the aileron 310 may be driven to turn over by the steering engine.
In order to improve the stability of the engagement between the third connection member 312b and the fourth connection member 314b, in some embodiments, as shown in fig. 9 and 10, one of the third connection member 312b and the fourth connection member 314b is provided with an engagement protrusion 315, and the other is provided with an engagement groove 313, and the engagement protrusion 315 is adapted to be inserted into the engagement groove 313. In order to improve the convenience of assembly between the third connector 312b and the fourth connector 314b, in some embodiments, as shown in fig. 10, the engagement groove 313 may have a long bar shape, and the engagement protrusion 315 may have a cylindrical shape. Therefore, when the fitting protrusion 315 is fitted into the fitting groove 313, the fitting groove 313 can provide a large fitting space for the fitting protrusion 315, and an operator can insert the fitting protrusion 315 into the fitting groove 313 conveniently.
In some embodiments, as shown in FIG. 5, the fourth connector 314b may be in the shape of a cap, the fourth connector 314b being disposed over an end of the flap 310. On one hand, the connection between the power output shaft 331 and the aileron 310 is facilitated, and on the other hand, the structural strength of the end part of the aileron 310 can be improved by using the fourth connecting piece 314b, so that the end part of the aileron 310 is protected, the fatigue damage of the aileron 310 can be reduced, and the service life of the aileron 310 can be prolonged.
As shown in fig. 1-10, an aircraft 1000 according to an embodiment of the present invention includes a fuselage 100 and a wing assembly 300 as described above, wherein the wing assembly 300 is connected to the fuselage 100.
According to the utility model discloses aircraft 1000 through setting up the steering wheel in wing main part 320, and the power output shaft 331 of steering wheel passes wing main part 320 and is connected with aileron 310, can arrange the wire of being connected with the steering wheel on wing main part 320 from this, when dismantling aileron 310, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong aircraft 1000's life. In addition, the extending direction of the power output shaft 331 is the same as the length direction of the aileron 310, so that the position of the steering engine can be conveniently distributed, the aileron 310 can be conveniently driven to turn by the steering engine, and the flexibility of the movement of the aileron 310 can be improved.
It should be noted that the wing assembly 300 may be disposed forward, in the middle, or aft of the fuselage 100. In addition, the wing assemblies 300 may be provided in multiple groups, and the multiple groups of wing assemblies 300 may be symmetrically disposed about the fuselage 100. For example, as shown in FIG. 1, the wing assemblies 300 may be provided in four groups, two of which are located in the middle of the fuselage 100 and two of which are located aft of the fuselage 100. It should be noted that the wing assembly 300 located at the rear of the fuselage 100 may be referred to as an empennage.
As shown in fig. 1 to 10, an aircraft 1000 according to an embodiment of the present invention includes a fuselage 100, a first wing assembly 300a, a wing arm 200, a second wing assembly 300b, a first power member 400 disposed at a front end of the wing arm 200, and a second power member 500 disposed at the fuselage 100.
The first wing assembly 300a may be disposed in the middle of the fuselage 100, and the wing body 320 of the first wing assembly 300a may include a first wing section 321 and a second wing section 324. As shown in fig. 3, one end of the first wing segment 321 is adapted to be connected to the fuselage 100, the steering engine is disposed on the first wing segment 321, the second wing segment 324 is detachably connected to the other end of the first wing segment 321, the aileron 310 is disposed on the second wing segment 324, and the aileron 310 is rotatable relative to the second wing segment 324. It will be appreciated that by segmenting the wing body 320, when it is desired to stow the first wing assembly 300a, the first wing segment 321 and the second wing segment 324 can be stowed separately, thereby reducing the volume of space occupied by the wing assembly 300.
Through setting up the steering wheel in the first wing section 321 of being connected with fuselage 100, set up aileron 310 on second wing section 324, can arrange the wire of being connected with the steering wheel at first wing section 321 from this, when dismantling second wing section 324 from first wing section 321, then need not to dismantle the steering wheel and the wire of being connected with the steering wheel, thereby not only conveniently dismantle second wing section 324, can also reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong wing assembly 300's life.
As shown in fig. 2, 4 and 8, the first panel 321 may include a panel body 322 and a fixing member 323. Wherein, the wing section main part 322 is suitable for being connected with the fuselage 100, and the mounting 323 is connected with wing section main part 322, and the mounting 323 is suitable for the periphery of the cover locating wing arm 200, and the mounting 323 is connected with second wing section 324, and at least one in mounting 323 and wing section main part 322 is equipped with the steering wheel. As shown in fig. 1 and 8, the fixing member 323 has a through hole 3232, and the wing arm 200 is inserted into the through hole 3232.
As shown in fig. 2 and 4, the flap 310 may include a first body portion 311a, a first connector 312a, and a second connector 314 a. The first body 311a can be connected to the second wing 324, the first connecting member 312a is disposed on the fixing member 323, the first connecting member 312a is connected to the power output shaft 331, the second connecting member 314a is connected to the first connecting member 312a, and the first body 311a is connected to the first connecting member 312a through the second connecting member 314 a.
It is understood that the second wing section 324 can be used for supporting and connecting the first body portion 311a, and the fixing member 323 can be used for supporting and connecting the first connecting member 312 a. Through setting up first connecting piece 312a and second connecting piece 314a, can utilize first connecting piece 312a to transmit the power of power output shaft 331 to second connecting piece 314a on, second connecting piece 314a can transmit power to first main part 311a again, can utilize the steering wheel drive aileron 310 to overturn from this. When power is transmitted between the steering engine and the aileron 310, the first connecting piece 312a can rotate relative to the fixing piece 323, and the first main body part 311a can rotate relative to the wing segment.
As shown in fig. 5, the second wing assembly 300b may be an empennage of the aircraft 1000. The second wing assembly 300b is connected to the rear end of the wing arm 200, the wing body 320 of the second wing assembly 300b may be located at the tail of the fuselage 100 (i.e., the rear side portion of the fuselage 100), and the aileron 310 may include a second body portion 311b, a third connection member 312b, and a fourth connection member 314 b. The second main body 311b is connected to the wing main body 320, the third connection member 312b is connected to the power output shaft 331, the fourth connection member 314b is connected to the third connection member 312b, and the second main body 311b is connected to the third connection member 312b through the fourth connection member 314 b. It should be noted that the wing main body 320 may be used to support and connect the second main body portion 311b, and the third connecting member 312b is used to transmit the power of the power output shaft 331 to the fourth connecting member 314b, and the fourth connecting member 314b may transmit the power to the second main body portion 311b, so that the aileron 310 may be driven to turn over by the steering engine.
In some embodiments, as shown in fig. 3 and 5, the wing body 320 of the second wing assembly 300 is provided with a tail support seat 210, and the steering engine is disposed in the tail support seat 210. Through setting up the steering wheel in tail stay seat 210, can arrange the wire of being connected with the steering wheel in tail stay seat 210 from this, when dismantling aileron 310, need not to dismantle the steering wheel to can reduce the probability of the fatigue damage of steering wheel and the wire of being connected with the steering wheel, and then can prolong aircraft 1000's life.
In the description of the present invention, it should be understood that the terms "front", "back", "left", "right", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. In the description of the present invention, "a plurality" means two or more.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (15)
1. A wing assembly for an aircraft, comprising:
a wing body;
an aileron that is invertible relative to the wing body;
the steering engine is arranged on the wing main body, a power output shaft of the steering engine penetrates through the wing main body and is connected with the ailerons to drive the ailerons to turn over, and the extension direction of the power output shaft is the same as the length direction of the ailerons.
2. The wing assembly of an aircraft of claim 1, wherein the wing body is adapted to be disposed in a midsection of a fuselage of the aircraft and comprises:
one end of the first wing section is suitable for being connected with a fuselage, and the steering engine is arranged on the first wing section;
the second wing section is connected with the other end of the first wing section, the aileron is arranged on the second wing section, and the aileron can turn over relative to the second wing section.
3. The wing assembly of an aircraft of claim 2, wherein the first wing section comprises:
a wing panel body adapted for connection with the fuselage;
the fixing piece, the fixing piece with the pterygoid lamina main part is connected, the periphery of pterygoid lamina arm is suitable for the cover to locate to the fixing piece, the fixing piece with second pterygoid lamina is connected, the fixing piece with at least one in the pterygoid lamina main part is equipped with the steering wheel.
4. The wing assembly of an aircraft of claim 3, wherein the aileron comprises:
a first body portion connected with the second wing section;
the first connecting assembly comprises a first connecting piece and a second connecting piece, the first connecting piece is connected with the fixing piece through the first connecting assembly, the first connecting piece is connected with the fixing piece, the first connecting piece is connected with the power output shaft, the second connecting piece is connected with the first connecting piece, and the first main body portion is connected with the first connecting piece through the second connecting piece.
5. The wing assembly of an aircraft of claim 4, wherein one of the first and second connectors is provided with a mating projection and the other is provided with a mating slot, the mating projection being adapted to be received in the mating slot.
6. The wing assembly of an aircraft of claim 5, wherein the mating slot is elongated and the mating projection is cylindrical.
7. The wing assembly of an aircraft of claim 4, wherein the second connector is in the form of a shroud, the second connector shroud being provided at one end of the aileron.
8. The wing assembly of the aircraft of claim 2, wherein the second wing section is removably coupled to the first wing section.
9. The wing assembly of an aircraft of claim 1, wherein the wing body is adapted to be disposed aft of a fuselage of the aircraft, the aileron comprising:
a second body portion connected to the wing body;
the second coupling assembling, the second main part passes through the second coupling assembling with the tail boom seat of aircraft is connected, the second coupling assembling includes third connecting piece and fourth connecting piece, the third connecting piece with power take off shaft connects, the fourth connecting piece with the third connecting piece is connected, the second main part passes through the fourth connecting piece with the third connecting piece is connected.
10. The wing assembly of an aircraft of claim 9, wherein one of the third and fourth connectors is provided with a mating projection and the other is provided with a mating slot, the mating projection being adapted to be received in the mating slot.
11. The wing assembly of an aircraft of claim 10, wherein the mating slot is elongated and the mating projection is cylindrical.
12. The wing assembly of an aircraft of claim 9, wherein the fourth connector is in the form of a shroud, the fourth connector shroud being provided at one end of the aileron.
13. An aircraft, characterized in that it comprises:
a body;
a wing assembly connected to the fuselage, the wing assembly being in accordance with any one of claims 1 to 12.
14. An aircraft, characterized in that it comprises:
a body;
a first wing assembly according to any of claims 1-8, the first wing assembly being connected to the fuselage and being located in a middle portion of the fuselage;
a wing arm disposed through the first wing assembly;
a second wing component connected to the aft end of the wing arm, the second wing component being a wing component according to any one of claims 1 and 9-12;
the first power part is arranged at the front end of the wing arm;
and the second power part is arranged on the machine body.
15. The aircraft of claim 14, wherein the wing body of the second wing assembly is provided with a tail support seat, and the steering engine is arranged in the tail support seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921178106.5U CN211252988U (en) | 2019-07-24 | 2019-07-24 | Wing assembly of aircraft and aircraft |
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| CN114104263A (en) * | 2021-12-09 | 2022-03-01 | 中航金城无人系统有限公司 | Wing folding mechanism and unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114104263A (en) * | 2021-12-09 | 2022-03-01 | 中航金城无人系统有限公司 | Wing folding mechanism and unmanned aerial vehicle |
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