CN117645007B - Aircraft with combined folding wings - Google Patents
Aircraft with combined folding wings Download PDFInfo
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- CN117645007B CN117645007B CN202410116188.XA CN202410116188A CN117645007B CN 117645007 B CN117645007 B CN 117645007B CN 202410116188 A CN202410116188 A CN 202410116188A CN 117645007 B CN117645007 B CN 117645007B
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- 230000007246 mechanism Effects 0.000 claims abstract description 47
- 230000007704 transition Effects 0.000 claims description 25
- 239000002131 composite material Substances 0.000 claims description 6
- 230000001154 acute effect Effects 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 3
- 238000007665 sagging Methods 0.000 claims description 3
- 241001290198 Dicliptera Species 0.000 claims 2
- 238000010586 diagram Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
- B64U30/16—Variable or detachable wings, e.g. wings with adjustable sweep movable along the UAV body
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides an aircraft with combined folding wings, which relates to the technical field of aircrafts and comprises: the machine body is provided with a mounting part; the folding wing mechanism comprises a pair of front wings and a pair of rear wings, and one end, close to each other, of each front wing and each rear wing is rotatably connected with the mounting part; the folding wing mechanism comprises a first state and a second state, when the folding wing mechanism is in the first state, a pair of front wings are mutually stuck and arranged on one side of the mounting part, which is close to the front end of the machine body, and a pair of rear wings are mutually stuck and arranged on one side of the mounting part, which is close to the tail end of the machine body; when the wing is in the second state, a pair of front wings and a pair of rear wings are respectively unfolded towards two sides of the machine body, and the front wings and the rear wings which are positioned on the same side of the machine body are tightly attached; and the driving mechanism is used for simultaneously driving the front wing and the rear wing to rotate so as to enable the folding wing mechanism to switch between a first state and a second state. The aircraft with the combined folding wings has the advantage of being stable in the initial flight stage.
Description
Technical Field
The invention relates to the technical field of aircrafts in general, in particular to an aircraft with combined folding wings.
Background
The folding wing technology is mainly applied to the field of folding wing unmanned aerial vehicles and the field of missile medicine. The earliest folding wing aircraft LOCAAS was a concept proposed by american roman and developed successfully in 1994. In 2001, the company AeroVironment develops an SOAR shooting unmanned aerial vehicle, and then based on the model, a spring knife individual unmanned aerial vehicle combat system is further provided, and the system has the advantages of being strong in portability, high in hitting precision, multiple in application scene and the like.
The folding wing aircraft is launched by the launching tube. At present, the folded wing layout is formed by folding the wings of the aircraft backwards to be a main stream layout, the folded wings are often placed in a vertically stacked mode, and the left and right wings of the layout are asymmetric at the moment of opening the folded wing span, so that additional yaw and roll moments can be generated, and the stability of the aircraft in the initial flight stage is further affected.
Disclosure of Invention
In view of the above-described drawbacks or deficiencies of the prior art, it is desirable to provide an aircraft with a combination folding wing to address the above-described problems.
The invention provides an aircraft with combined folding wings, comprising:
the machine body is provided with an installation part;
The folding wing mechanism comprises a pair of front wings and a pair of rear wings, and one ends, close to each other, of the front wings and the rear wings are rotatably connected with the mounting part; the folding wing mechanism comprises a first state and a second state, when the folding wing mechanism is in the first state, a pair of front wings are mutually clung to each other and are arranged on one side of the mounting part, which is close to the front end of the machine body, and a pair of rear wings are mutually clung to each other and are arranged on one side of the mounting part, which is close to the tail end of the machine body; when the front wing and the rear wing are in the second state, the pair of front wings and the pair of rear wings are respectively unfolded towards the two sides of the machine body, and the front wings and the rear wings which are positioned on the same side of the machine body are tightly attached;
The driving mechanism is respectively in transmission connection with the front wing and the rear wing and is used for driving the front wing and the rear wing to rotate simultaneously so as to enable the folding wing mechanism to be switched between the first state and the second state.
According to the technical scheme provided by the invention, the rear wing comprises a first wing part, a second wing part and a transition part, wherein the second wing part is positioned at one end of the first wing part far away from the installation part, and the transition part is positioned between the first wing part and the second wing part; the first chord length is smaller than the second chord length, the first chord length is the chord length of the first wing part, and the second chord length is the chord length of the second wing part; the trailing edge of the first wing part, the trailing edge of the second wing part and the trailing edge of the transition part are flush, and the leading edge of the transition part, the leading edge of the first wing part and the leading edge of the second wing part form a step shape.
According to the technical scheme provided by the invention, the third chord length is equal to the difference between the second chord length and the first chord length, and is less than or equal to half of the second chord length, and the third chord length is the chord length of the front wing.
According to the technical scheme provided by the invention, the wing tip of the front wing forms an acute angle with the front edge of the front wing, and the wing tip of the front wing is matched with the front edge shape of the transition part.
According to the technical scheme provided by the invention, the shape of the wing tip of the front wing is a straight line or a monotonic curve.
According to the technical scheme provided by the embodiment of the invention, the first chord length is smaller than or equal to half of the width of the machine body, and the second chord length is larger than half of the width of the machine body.
According to the technical scheme provided by the invention, the intersection point of the front edge of the transition part and the front edge of the first wing part and the axial position of the first centroid in the axial direction of the fuselage are the same, and the first centroid is the centroid of the aircraft when the folding wing mechanism is in the first state.
According to the technical scheme provided by the invention, the driving mechanism comprises:
The driving assembly comprises a driving part and a driving part, and the driving part is used for driving the driving part to rotate around the axis of the driving part;
The driven assembly comprises a first-stage driven part and a plurality of second-stage driven parts, the second-stage driven parts are respectively arranged on the rotating shafts of the front wing and the rear wing, and the second-stage driven parts are meshed with each other; the primary driven part is arranged on the rotating shaft of one of the front wings or the rotating shaft of one of the rear wings, and is meshed with the driving part.
According to the technical scheme provided by the invention, a sinking structure is arranged on one side of the machine body, which is used for installing the folding wing mechanism, and the folding wing mechanism is arranged at the sinking structure so as to reduce the height of the folding wing mechanism on the surface of the machine body.
According to the technical scheme provided by the invention, the sections of the ends, close to each other, of the front wing and the rear wing are in the same semicircle.
Compared with the prior art, the invention has the beneficial effects that: when the folding wing mechanism is in the first state, the aircraft is conveniently placed in the launching tube, the launching tube is convenient for launching the aircraft, and in the initial flight stage when the aircraft leaves the launching tube, the folding wing mechanism in the first state provides stable flight support for the aircraft; after the aircraft leaves the launching tube, the driving mechanism synchronously drives the front wings and the rear wings to rotate, so that a pair of front wings and a pair of rear wings are respectively unfolded towards two sides of the aircraft body, and then complete wings are formed on the two sides of the aircraft body, so that the wings are ensured to be always left-right symmetrical in the unfolding process, and the stability of the aircraft in an initial flight stage is ensured.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of an aircraft with composite folding wings according to the present invention in a first state;
FIG. 2 is a schematic view of an aircraft with composite folding wings according to the present invention in a second state;
FIG. 3 is an enlarged schematic view of FIG. 2A;
FIG. 4 is a schematic diagram of a driving mechanism;
FIG. 5 is a schematic diagram of the drive and driven gears in driving relationship;
FIG. 6 is a schematic diagram of the drive relationship between synchronizing gears;
FIG. 7 is a plan view showing the positional relationship of the front and rear wings in a first state;
fig. 8 is a plan view showing the positional relationship between the front wing and the rear wing in the second state.
Reference numerals: 100. a body; 110. a mounting part; 200. a front wing; 210. a first leading edge; 220. a first trailing edge; 230. a first wing tip; 300. a rear wing; 310. a first wing section; 311. a second leading edge; 312. a second trailing edge; 320. a second wing section; 321. a third leading edge; 322. a third trailing edge; 330. a transition section; 331. a fourth leading edge; 332. a fourth trailing edge; 400. a driving mechanism; 410. an active component; 411. a driving device; 412. a drive gear; 420. a driven assembly; 421. a driven gear; 422. a synchronizing gear; 430. a fairing; 440. a rotation shaft; 500. a sagging structure.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the invention are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Referring to fig. 1-8, the present invention provides an aircraft with a composite folding wing, comprising:
A body 100, wherein a mounting part 110 is arranged on the body 100;
A folding wing mechanism including a pair of front wings 200 and a pair of rear wings 300, wherein one ends of the front wings 200 and the rear wings 300, which are close to each other, are rotatably connected with the mounting portion 110; the folding wing mechanism comprises a first state and a second state, when in the first state, a pair of front wings 200 are mutually abutted and arranged on one side of the mounting part 110 near the front end of the machine body 100, and a pair of rear wings 300 are mutually abutted and arranged on one side of the mounting part 110 near the tail end of the machine body 100; when in the second state, the pair of front wings 200 and the pair of rear wings 300 are respectively unfolded towards two sides of the fuselage 100, and the front wings 200 and the rear wings 300 positioned on the same side of the fuselage 100 are tightly attached;
the driving mechanism 400 is in transmission connection with the front wing 200 and the rear wing 300 respectively, and is used for driving the front wing 200 and the rear wing 300 to rotate simultaneously so as to enable the folding wing mechanism to switch between the first state and the second state.
Specifically, in fig. 1, the left side is the front end of the fuselage 100, and the right side is the tail end of the fuselage 100; the fuselage 100 is used for installing one side of folding wing mechanism is concave to form the subsidence structure 500, the height of subsidence structure 500 is less than the height of fuselage 100 front end, makes when folding wing mechanism is arranged in subsidence structure 500 department, in order to reduce folding wing mechanism is in the height of fuselage 100 surface lets folding wing structure's upper surface is more close fuselage 100, accessible fuselage 100 front end keeps off folding wing mechanism when the aircraft flies, and then reduces the aircraft when folding wing mechanism is in the windage when the first state flies. The driving mechanism 400 is disposed inside the body 100 and corresponding to the mounting portion 110. The end of the front wing 200 and the end of the rear wing 300 are respectively provided with a rotating shaft 440, and the rotating shafts 440 of the front wing 200 and the rotating shafts 440 of the rear wing 300 extend into the fuselage 100 and are in transmission connection with the driving mechanism 400.
Specifically, referring to fig. 1,2 and 7, a distance between the mounting portion 110 and an end of the sinking structure 500 near the front end of the fuselage 100 is a first set distance, a distance between the mounting portion 110 and an end of the sinking structure 500 far from the front end of the fuselage 100 is a second set distance, a length of the front wing 200 is C1, a length of the rear wing 300 is C2, a length C1 of the front wing 200 is less than the first set distance, and a length C2 of the rear wing 300 is not limited by the length.
Further, the rear wing 300 includes a first wing part 310, a second wing part 320, and a transition part 330, the second wing part 320 being located at an end of the first wing part 310 remote from the mounting part 110, the transition part 330 being located between the first wing part 310 and the second wing part 320; the first chord length is less than the second chord length, the first chord length is the chord length of the first wing portion 310, and the second chord length is the chord length of the second wing portion 320; the trailing edge of the first wing part 310, the trailing edge of the second wing part 320 and the trailing edge of the transition part 330 are flush, and the leading edge of the transition part 330, the leading edge of the first wing part 310 and the leading edge of the second wing part 320 are stepped.
Specifically, referring to fig. 1 and 2, for convenience of explanation, the leading edge of the front wing 200 is referred to herein as a first leading edge 210, the trailing edge of the front wing 200 is referred to as a first trailing edge 220, the leading edge of the first wing portion 310 is referred to as a second leading edge 311, the trailing edge of the first wing portion 310 is referred to as a second trailing edge 312, the leading edge of the second wing portion 320 is referred to as a third leading edge 321, the trailing edge of the second wing portion 320 is referred to as a third trailing edge 322, the leading edge of the transition portion 330 is referred to as a fourth leading edge 331, and the trailing edge of the transition portion 330 is referred to as a fourth trailing edge 332. The second trailing edge 312, the third trailing edge 322 and the fourth trailing edge 332 are connected in a straight line, the second leading edge 311, the third leading edge 321 and the fourth leading edge 331 form a stepped structure, when in the first state, the first trailing edge 220 is in a same straight line with the second leading edge 311, when switching from the first state to the second state, the pair of front wings 200 are opened and respectively rotate toward the rear wings 300 on the corresponding sides, and simultaneously, the pair of rear wings 300 are opened and respectively rotate toward the front wings 200 on the corresponding sides, when in the second state, the first trailing edge 220 is tightly attached to the second leading edge 311, and when in the second state, the first leading edge 210 is connected in a straight line with the third leading edge 321.
Because the second trailing edge 312, the third trailing edge 322, and the fourth trailing edge 332 are on the same straight line, and the chord length of the first wing portion 310 is smaller than the chord length of the second wing portion 320, a gap space is formed on the rear wing 300, and when in the second state, the front wing 200 is embedded into the gap and forms a complete wing in cooperation with the rear wing 300.
Further, a third chord length is equal to a difference between the second chord length and the first chord length, and the third chord length is less than or equal to half of the second chord length, and the third chord length is the chord length of the front wing 200.
Specifically, the chord length of the front wing 200 is H3, the chord length of the second wing portion 320 is H2, and the chord length of the first wing portion 310 is H1, where h3=h2-H1, so that when the front wing 200 is attached to the rear wing 300, the front wing 200 can be completely placed in the gap space, and the whole wing is in a regular shape, so that the stability of the flying system in the subsequent flying stage is improved.
If the chord length of the front wing 200 is too large, in the first state, the first trailing edge 220 is located outside the second leading edge 311, so that additional resistance is added to the initial flight phase of the aircraft, so that H3 and H2 are required to satisfy H3 and H2/2, so that in the first state, the extension of the first trailing edge 220 relative to the second leading edge 311 is avoided, and the flight resistance of the front wing 200 in the initial flight phase of the aircraft is reduced.
Further, the wing tip of the front wing 200 is at an acute angle to the front edge of the front wing 200, and the wing tip of the front wing 200 matches the front edge shape of the transition 330.
In particular, referring to fig. 2, for ease of illustration, the wing tip of the front wing 200 is referred to herein as a first wing tip 230. The included angle between the first wing tip 230 and the first front edge 210 is an acute angle, the included angle between the first wing tip 230 and the first rear edge 220 is an obtuse angle, when in the first state, the pair of front wings 200 are tightly attached to each other, and then the pair of first wing tips 230 of the front wings 200 form a pointed structure for reducing wind resistance when the aircraft flies in the first state when the folding wing mechanism is in the first state. By shaping the first wing tip 230 to match the shape of the fourth leading edge 331, the front wing 200 can closely conform to the rear wing 300 into an integral wing when in the second state.
Further, the shape of the wing tip of the front wing 200 is a straight line or a monotonic curve.
In particular, the first wing tip 230 may be configured to be linear or monotonically curved, and when the first wing tip 230 is configured to be monotonically curved, the monotonic curve may be a convex curve or a concave curve.
Further, the first chord length is less than or equal to half the width of the fuselage 100 and the second chord length is greater than half the width of the fuselage 100.
Further, the intersection of the leading edge of the transition portion 330 and the leading edge of the first wing portion 310 is the same as the first centroid in the axial direction of the fuselage 100, the first centroid being the centroid of the aircraft when the folding wing mechanism is in the first state.
Specifically, by setting the chord length of the first wing portion 310 to be less than or equal to half the width of the fuselage 100, the first wing portion 310 does not add additional drag during the initial flight phase of the aircraft when in the first state. In this embodiment, the chord length of the first wing portion 310 is equal to half the width of the fuselage 100.
Since the chord length of the second wing 320 is set to be greater than half the width of the fuselage 100, the second wing 320 can provide a low head pitch moment when the aircraft is flying at a positive angle of attack when in the first state, and since the chord length of the first wing 310 is equal to half the width of the fuselage 100 in this embodiment, the transition 330 can also provide a low head pitch moment when the aircraft is flying at a positive angle of attack, thereby enhancing the longitudinal static stability of the aircraft. For ease of illustration, the intersection of the second leading edge 311 and the fourth leading edge 331 is referred to herein as a first intersection, and when the first intersection is located on a side of the first centroid near the front end of the aircraft, the transition portion 330 and the second wing portion 320 located on a side of the first centroid near the front end of the aircraft counteract a portion of the low head pitch moment, thereby resulting in reduced longitudinal stability of the aircraft; when the first intersection point is located on the side of the first centroid away from the front end of the aircraft, the position of the first centroid away from the front end of the aircraft, where the transition portion 330 and the second wing portion 320 are placed, is wasted, and it is also impossible to ensure that the pitching moment of the nose of the aircraft is maximum when the aircraft flies at a positive angle of attack, that is, the static stability in the longitudinal direction cannot be maximized; by setting the axial positions of the first intersection point and the first centroid to be the same, the transition portion 330 and the second wing portion 320 are just placed at the position of the side of the first centroid away from the front end of the aircraft, so that the longitudinal static stability of the aircraft is ensured to be the maximum.
Further, the driving mechanism 400 includes:
the driving component 410, wherein the driving component 410 comprises a driving part and a driving part, and the driving part is used for driving the driving part to rotate around the axis of the driving part;
A driven assembly 420, wherein the driven assembly 420 comprises a primary driven part and a plurality of secondary driven parts, the secondary driven parts are respectively arranged on the rotating shafts 440 of the front wing 200 and the rear wing 300, and the secondary driven parts are meshed with each other; the primary driven portion is mounted on the rotation shaft 440 of one of the front wings 200 or on the rotation shaft 440 of one of the rear wings 300, and is engaged with the driving portion.
Specifically, the driving mechanism 400 is mounted on the mounting portion 110, and the driving assembly 410 includes: a driving device 411 and a driving gear 412; the driving device 411 serves as the driving part, and the driving gear 412 serves as the driving part. The driven assembly 420 includes: a driven gear 421 and four synchronizing gears 422, the driven gear 421 serving as the primary driven portion, and the synchronizing gears 422 serving as the secondary driven portion.
The driving shaft of the driving device 411 is fixedly connected with the driving gear 412, four synchronizing gears 422 are fixedly connected with four rotating shafts 440, four synchronizing gears 422 are circumferentially arranged and adjacent synchronizing gears 422 are meshed with each other, the driven gear 421 is fixedly connected with one of the rotating shafts 440, and the driving device 411 is disposed in a gap between the four synchronizing gears 422. The working principle of the driving mechanism 400 is referring to fig. 5 and 6, in which the arrow direction is the rotation direction, the driving device 411 rotates to drive the driving gear 412 to rotate, the driving gear 412 drives the driven gear 421 to rotate, and further drives the rotation shaft 440 provided with the driven gear 421 and the synchronizing gear 422 on the rotation shaft 440 to rotate, and one synchronizing gear 422 rotates to drive other synchronizing gears 422 to rotate, so that synchronous rotation of the front wing 200 and the rear wing 300 is achieved, and synchronicity and stability of the front wing 200 and the rear wing 300 in switching between the first state and the second state are ensured.
The driving mechanism 400 further comprises a fairing 430, wherein the fairing 430 is arranged at one side of the front wing 200 and the rear wing 300 away from the driving component 410, and the front end and the rear end of the fairing 430 are respectively arranged in a pointed structure, so that wind resistance is reduced; the top surface of the fairing 430 is configured to be curved and curved downward at the front and rear ends. By providing the fairing 430, the stability of the aircraft during flight is further improved.
Further, the cross section of the end of the front wing 200 and the rear wing 300, which are close to each other, is the same semicircle.
Specifically, the cross sections of the ends of the front wing 200 and the first wing 310, which are close to each other, are arranged in the same semicircle shape, so that the front wing 200 and the rear wing 300 are prevented from interfering with each other when switching between the first state and the second state.
The above description is only illustrative of the preferred embodiments of the present invention and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the invention referred to in the present invention is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present invention (but not limited to) having similar functions are replaced with each other.
Claims (7)
1. An aircraft with composite fold wings, comprising:
A body (100), wherein an installation part (110) is arranged on the body (100);
The folding wing mechanism comprises a pair of front wings (200) and a pair of rear wings (300), and one end, close to each other, of the front wings (200) and the rear wings (300) is rotatably connected with the mounting part (110); the folding wing mechanism comprises a first state and a second state, when the folding wing mechanism is in the first state, a pair of front wings (200) are mutually clung to each other and are arranged on one side of the mounting part (110) close to the front end of the machine body (100), and a pair of rear wings (300) are mutually clung to each other and are arranged on one side of the mounting part (110) close to the tail end of the machine body (100); when in the second state, a pair of front wings (200) and a pair of rear wings (300) are respectively unfolded towards two sides of the machine body (100), and the front wings (200) and the rear wings (300) which are positioned on the same side of the machine body (100) are tightly attached;
The driving mechanism (400) is respectively connected with the front wing (200) and the rear wing (300) in a transmission way and is used for driving the front wing (200) and the rear wing (300) to rotate at the same time so as to enable the folding wing mechanism to be switched between the first state and the second state;
the rear wing (300) comprises a first wing part (310), a second wing part (320) and a transition part (330), wherein the second wing part (320) is positioned at one end of the first wing part (310) away from the mounting part (110), and the transition part (330) is positioned between the first wing part (310) and the second wing part (320); the first chord length is less than a second chord length, the first chord length being the chord length of the first wing portion (310), the second chord length being the chord length of the second wing portion (320); the trailing edge of the first wing part (310), the trailing edge of the second wing part (320) and the trailing edge of the transition part (330) are flush, and the leading edge of the transition part (330), the leading edge of the first wing part (310) and the leading edge of the second wing part (320) form a step shape;
-the wing tip of the front wing (200) is at an acute angle to the front edge of the front wing (200), and-the wing tip of the front wing (200) matches the shape of the front edge of the transition (330);
the intersection of the leading edge of the transition portion (330) and the leading edge of the first wing portion (310) is the same as a first centroid of the aircraft in the first state when the folding wing mechanism is in the axial position of the fuselage (100).
2. The aircraft with combined folded wings according to claim 1, characterized in that a third chord length is equal to the difference between the second chord length and the first chord length, and that the third chord length is less than or equal to half the second chord length, the third chord length being the chord length of the front wing (200).
3. The aircraft with combined folding wing according to claim 2, characterized in that the shape of the wing tip of the front wing (200) is a straight line or a monotonic curve.
4. An aircraft with composite fold wings according to claim 3, wherein the first chord length is less than or equal to half the width of the fuselage (100) and the second chord length is greater than half the width of the fuselage (100).
5. The aircraft with composite folding wing according to any one of claims 1 to 4, characterized in that the drive mechanism (400) comprises:
a driving component (410), wherein the driving component (410) comprises a driving part and a driving part, and the driving part is used for driving the driving part to rotate around the axis of the driving part;
the driven assembly (420) comprises a first-stage driven part and a plurality of second-stage driven parts, the plurality of second-stage driven parts are respectively arranged on rotating shafts (440) of the front wing (200) and the rear wing (300), and the plurality of second-stage driven parts are meshed with each other; the primary driven portion is mounted on a rotation shaft (440) of one of the front wings (200) or on a rotation shaft (440) of one of the rear wings (300), and is engaged with the driving portion.
6. An aircraft with combined folding wing according to any of claims 1-4, characterized in that the side of the fuselage (100) on which the folding wing mechanism is mounted is provided with a sagging structure (500), the folding wing mechanism being placed at the sagging structure (500) to reduce the height of the folding wing mechanism at the surface of the fuselage (100).
7. The aircraft with combined folding wing according to any one of claims 1 to 4, characterized in that the front wing (200) and the rear wing (300) have the same semicircular cross section at the ends that are close to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410116188.XA CN117645007B (en) | 2024-01-29 | 2024-01-29 | Aircraft with combined folding wings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410116188.XA CN117645007B (en) | 2024-01-29 | 2024-01-29 | Aircraft with combined folding wings |
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| Publication Number | Publication Date |
|---|---|
| CN117645007A CN117645007A (en) | 2024-03-05 |
| CN117645007B true CN117645007B (en) | 2024-08-20 |
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| CN202410116188.XA Active CN117645007B (en) | 2024-01-29 | 2024-01-29 | Aircraft with combined folding wings |
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9108713B2 (en) * | 2009-09-09 | 2015-08-18 | Aerovironment, Inc. | Elevon control system |
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