CN112193404A - Z-shaped folding wing variable aircraft - Google Patents
Z-shaped folding wing variable aircraft Download PDFInfo
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- CN112193404A CN112193404A CN202011090635.7A CN202011090635A CN112193404A CN 112193404 A CN112193404 A CN 112193404A CN 202011090635 A CN202011090635 A CN 202011090635A CN 112193404 A CN112193404 A CN 112193404A
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- wing
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- planetary gear
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The invention discloses a Z-shaped folding wing variable aircraft, which comprises: the airplane body and the folding three-section wing; the folding three-section wing comprises: the inner wing, the middle wing, the outer wing, the inner rotating shaft mechanism and the outer rotating shaft mechanism; wherein the inner wing is fixed to the outside of the fuselage; interior pivot mechanism includes: the first cabin barrel is fixed with the inner wing, the first transmission shaft is arranged in the first cabin barrel, the first motor is used for driving the first transmission shaft to rotate, and the first planetary gear train structure is connected with the first transmission shaft; the first planetary gear train structure is used for driving the middle wing to rotate around the first transmission shaft at a constant speed; outer pivot mechanism includes: the second cabin barrel is fixed with the middle wing, the second force transmission shaft is arranged in the second cabin barrel, the second motor is used for driving the second force transmission shaft to rotate, and the second planetary gear train structure is connected with the second force transmission shaft; the second planetary gear train structure is used for driving the outer wing to rotate around the second force transmission shaft at a constant speed. The invention realizes the stable variant of the wing based on the planetary gear train structure.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to a Z-shaped folding wing variable aircraft.
Background
With the rapid development of the aviation industry, the civil and military fields have put higher demands on the aircraft: the aircraft can execute various flight tasks, and the whole flight range comprises various flight states such as cruising, attacking, intercepting and the like. Achieving these flight conditions requires an aircraft with the ability to efficiently compromise subsonic high lift-to-drag ratio cruise and supersonic penetration versus aerodynamic forces. However, for the conventional aerodynamic configuration aircraft, the aerodynamic requirements of subsonic flight and supersonic flight are difficult to satisfy simultaneously. At present, most of aircrafts are fixed-wing aircrafts, the aircrafts with large aspect ratio and large wing area are not suitable for supersonic flight generally, and the aircrafts with small aspect ratio and small wing area lose subsonic flight performance while meeting the requirement of supersonic flight.
The existing variant aircraft can change the self pneumatic appearance according to the task requirement or the requirement of the flight environment, so that the current appearance state is suitable for the flight condition, and the aircraft can achieve the best flight performance in various flight states. The wing of the morphing aircraft mainly comprises an inner rotating shaft mechanism, an inner wing, an outer rotating shaft mechanism and an outer wing. Wherein, the rotating shaft mechanism mainly comprises a power mechanism, an actuating cylinder and a crank rocker mechanism. The working principle is as follows: the power mechanism drives the action cylinder to drive the rocker of the crank-rocker mechanism to rotate, so that the wing is driven to rotate. However, the above-mentioned variant aircraft mainly has several problems:
(1) the crank rocker mechanism occupies large space and is easy to damage;
(2) the crank rotation of the crank rocker mechanism is variable-speed reciprocating motion, so that the crank rocker mechanism has quick return characteristic, the rotation speed is not uniform, and the stability of the action of the rotating shaft mechanism is easily influenced;
(3) the crank rocker mechanism takes a crank as a driving part and a rocker as a driven part, and dead points are generated in the action process of the mechanism.
Disclosure of Invention
The invention aims to improve the existing variant aircraft, and provides a variant folding wing aircraft which can execute flight mission requirements according to actual flight environment, change the structural appearance of the aircraft, and achieve the subsonic flight capability with high lift-drag ratio and higher supersonic flight performance.
In order to achieve the above object, the present invention provides a Z-shaped folding wing variable body aircraft, comprising: the folding three-section wing comprises a fuselage and a pair of folding three-section wings which are respectively arranged on two sides of the fuselage; the folded three-section wing comprises: the wing structure comprises an inner wing, a middle wing, an outer wing, an inner rotating shaft mechanism for connecting the inner wing and the middle wing, and an outer rotating shaft mechanism for connecting the middle wing and the outer wing; wherein the inner wing is fixed to an outer side of the fuselage; the inner rotary shaft mechanism includes: the first cabin barrel is fixed with the inner wing, the first transmission shaft is arranged in the first cabin barrel, the first motor is used for driving the first transmission shaft to rotate, and the first planetary gear train structure is connected with the first transmission shaft; the first planetary gear train structure is used for driving the middle wing to rotate around the first transmission shaft at a constant speed; the outer pivot mechanism includes: the second cabin barrel is fixed with the middle wing, the second force transmission shaft is arranged in the second cabin barrel, the second motor is used for driving the second force transmission shaft to rotate, and the second planetary gear train structure is connected with the second force transmission shaft; the second planetary gear train structure is used for driving the outer wing to rotate around the second force transmission shaft at a constant speed.
Optionally, the first planetary gear train structure is arranged at both ends of the first transmission shaft.
Optionally, the first planetary gear train structure includes: the planetary gear set comprises a first sun gear, four first planet gears which are equidistantly arranged on the periphery of the first sun gear, an inner gear ring which is concentric with the first sun gear, and a first planet carrier which is used for supporting the first planet gears; the first planet wheel is arranged between the first sun wheel and the inner gear ring and is in meshed connection with the first sun wheel and the inner gear ring; the inner gear ring is fixedly connected with the middle wing.
Optionally, the second planetary gear train structure is arranged at both ends of the second force transmission shaft.
Optionally, the second planetary gear train structure includes: the planetary gear set comprises a second sun gear, four second planetary gears which are equidistantly arranged on the periphery of the second sun gear, an outer gear ring which is concentric with the second sun gear, and a second planetary gear carrier which is used for supporting the second planetary gears; the second planet gear is arranged between the second sun gear and the outer gear ring and is in meshed connection with the second sun gear and the outer gear ring; the outer gear ring is fixedly connected with the outer wing.
Optionally, the first motor and the second motor are both stepping motors.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention realizes the stable and uniform rotation of the aircraft wing through the inner and outer sets of rotating shaft mechanisms.
(2) The wing folding angle control device can accurately control the folding angle of the wing, can simultaneously change the aspect ratio and the shape of the wing, has wider variation range, and can execute various flight tasks.
(3) The mechanism is simple, easy to realize and high in part universality.
Drawings
FIG. 1 is a schematic structural view of a folded state of a Z-folded wing convertible aircraft according to the present invention;
FIG. 2 is a schematic structural diagram of the Z-shaped folding wing variable body aircraft in an unfolded state;
FIG. 3 is a front view of the Z-folded wing morphing aircraft of the present invention in an unfolded state;
FIG. 4 is a schematic structural view of the folded three-piece wing of the present invention in an open position;
FIG. 5 is a schematic structural view of an inner rotating shaft mechanism according to the present invention;
FIG. 6 is a schematic structural view of an outer rotating shaft mechanism according to the present invention;
fig. 7 is a schematic flight flow diagram of the Z-shaped folding wing morphing aircraft.
In the figure: 1-a fuselage; 2-inner wing;
30-an inner rotating shaft mechanism, 31-a first cabin barrel, 32-a first transmission shaft, 33-a first sun gear, 34-a first planet gear, 35-an inner gear ring and 36-a first planet carrier;
4-middle wing; 50-an outer rotating shaft mechanism, 51-a second cabin barrel, 52-a second force transmission shaft, 53-a second sun gear, 54-a second planet gear, 55-an outer gear ring and 56-a second planet gear carrier;
6-outer wing, 7-air inlet, 8-cockpit, 9-horizontal tail, 10-engine and 11-vertical tail.
Detailed Description
The technical solution of the present invention is further described below with reference to the accompanying drawings and examples.
As shown in fig. 1 to 3, the Z-shaped folding wing variable body aircraft of the present invention includes: the wing-shaped airplane comprises a fuselage 1 and a pair of folding three-section wings which are respectively arranged on two sides of the fuselage 1; as shown in fig. 4, folding three wings comprises: the inner wing 2, the middle wing 4, the outer wing 6, the inner rotating shaft mechanism 30 and the outer rotating shaft mechanism 50; wherein the inner wing 2 is fixed to the outside of the fuselage 1; as shown in fig. 5, the inner spindle mechanism 30 includes: the first cabin barrel 31 is fixed with the inner wing 2, the first power transmission shaft 32 is arranged in the first cabin barrel 31, the first motor is used for driving the first power transmission shaft 32 to rotate, and the first planetary gear train structure is connected with the first power transmission shaft 32; under the driving of the first motor, the first planetary gear train structure drives the middle wing 4 to rotate around the first transmission shaft 32 at a constant speed; as shown in fig. 6, the outer spindle mechanism 50 includes: a second cabin tube 51 fixed with the middle wing 4, a second force transmission shaft 52 arranged in the second cabin tube 51, a second motor used for driving the second force transmission shaft 52 to rotate, and a second planetary gear train structure connected with the second force transmission shaft 52; under the drive of the second motor, the second planetary gear train structure drives the outer wing 6 to rotate around the second force transmission shaft 52 at a constant speed.
The fuselage 1 of the invention is used as an aircraft body, contains an equipment cabin and a storage cabin, and can be used for placing equipment such as reconnaissance, communication and the like. The cockpit 8 is positioned above the fuselage 1; an engine 10 is installed inside the fuselage 1, and an air inlet 7 of the engine 10 is positioned at the lateral rear end of the cockpit 8 and is distributed in an inverted V shape.
In some embodiments, a pair of horizontal tails 9 is symmetrically distributed on two sides of the tail of the fuselage 1 along the horizontal direction; a pair of vertical tails 11 are positioned above the aft portion of the fuselage 1 and are symmetrically distributed along the fuselage axis.
Referring to fig. 5, the first planetary gear train structure of the present invention is a pair, which is respectively disposed at two ends of the first transmission shaft 32. The first planetary gear train structure includes: a first sun gear 33, a first planet gear 34, a ring gear 35, and a first carrier 36. The first sun gear 33 and the first transmission shaft 32 rotate coaxially.
The first planet gears 34 are arranged between the first sun gear 33 and the ring gear 35 and are in meshing connection with the first sun gear 33 and the ring gear 35; in some embodiments, the number of the first planet gears 34 may be four, and the first planet gears are arranged at equal intervals on the circumference of the first sun gear 33 and are supported and connected by the first planet carrier 36. The first carrier 36 is mounted on the first barrel 31.
The first motor is a stepping motor, the stepping motor drives the first power transmission shaft 32 to rotate, the first sun gear 33 is driven to rotate, the first planet gear 34 rotates around the first sun gear 33 and simultaneously rotates around the gear axis of the first planet gear to transmit power, the inner gear ring 35 is driven to rotate, and the middle wing 4 connected with the inner gear ring 35 rotates around the first power transmission shaft 32.
The invention fully utilizes the precise control characteristic of the stepping motor to improve the precision of the rotation angle of the inner rotating shaft mechanism 30, and can ensure that the middle wing 4 rotates and folds clockwise and anticlockwise relative to the inner wing 2 around the first transmission shaft 32 at a constant speed until the limit angle is 105 degrees.
Referring to fig. 6, the second planetary gear set of the present invention is a pair of planetary gear sets, which are respectively disposed at two ends of the second transmission shaft 52. The second planetary gear train structure includes: a second sun gear 53, second planet gears 54, an outer ring gear 55, and a second planet carrier 56. The second sun gear 53 and the second force transmission shaft 52 rotate coaxially.
The second planet gears 54 are arranged between the second sun gear 53 and the outer ring gear 55 and are in meshed connection with the second sun gear 53 and the outer ring gear 55; in some embodiments, the number of the second planet gears 54 may be four, and the four second planet gears are arranged at equal intervals on the circumference of the second sun gear 53 and are supported and connected by the second planet gear carrier 56. A second planetary carrier 56 is mounted on the second pod 51.
The second motor is a stepping motor, and the stepping motor drives the second force transmission shaft 52 to rotate, so as to drive the second sun gear 53 to rotate, so that the second planet gear 54 rotates around the second sun gear 53 and simultaneously rotates around the gear axis of the second planet gear to transmit power, and further drives the outer gear ring 55 to rotate, so that the outer wing 6 connected with the outer gear ring 55 rotates around the second force transmission shaft 52.
The invention fully utilizes the precise control characteristic of the stepping motor to improve the precision of the rotation angle of the outer rotating shaft mechanism 50, and can ensure that the outer wing 6 rotates and folds clockwise and anticlockwise relative to the middle wing 4 around the second force transmission shaft 52 at a constant speed until the limit angle is 105 degrees.
In some embodiments, considering that the extreme positions of the forward and reverse rotation of the inner rotating shaft mechanism 30 and the outer rotating shaft mechanism 50 may cause malfunction, the present invention adds a forward rotation limit switch and a reverse rotation limit switch at the extreme positions.
As shown in fig. 7, the folded three-piece wings of the present invention are in a horizontal disposition when not folded. When the inner rotating shaft mechanism 30 is folded inwards and the outer rotating shaft mechanism 50 is folded outwards, the wings on the two sides of the aircraft are distributed in a Z-shaped state to form a symmetrical wing type. After the folding wing is folded, the wing span is reduced, the chord length is unchanged, so that the wing span area is reduced, and the aspect ratio is changed therewith, thereby changing the aerodynamic appearance of the aircraft and increasing the practicability of the aircraft.
Based on the above state, the wing change state of the Z-shaped folding wing variable body aircraft during the flight process is described as follows:
s1, when the aircraft takes off, the wings are completely unfolded, the wing area reaches the maximum, and the wind area is large;
s2, the aircraft carries out wing folding action in flight, changes the aerodynamic appearance of the aircraft, changes the aspect ratio and enhances the flight performance of the aircraft;
s3, folding wings of the aircraft are folded to a limit state and are in a Z shape;
s4, when the aircraft is in a cruising state, the wings are completely unfolded, the lift-drag ratio is increased, the demand on power is reduced, and the working time of the aircraft is prolonged;
s5, the aircraft can be subjected to wing folding change according to the flight environment, so that the performance of the aircraft is enhanced;
s6, when the aircraft finishes the flight task and is ready to land, the wings are in a fully unfolded state.
In conclusion, the Z-shaped folding wing transformable aircraft realizes stable transformation of wings based on a planetary gear train structure, can execute flight task requirements according to actual flight environment, changes the structural appearance of the aircraft, and achieves the effects of good supersonic flight performance and subsonic flight capability with high lift-drag ratio.
While the present invention has been described in detail with reference to the preferred embodiments, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.
Claims (6)
1. A Z-shaped folding wing variable body aircraft, which is characterized by comprising: the folding wing comprises a machine body (1) and a pair of folding three-section wings which are respectively arranged on two sides of the machine body (1); the folded three-section wing comprises: the wing-shaped aircraft comprises an inner wing (2), a middle wing (4), an outer wing (6), an inner rotating shaft mechanism (30) for connecting the inner wing (2) and the middle wing (4), and an outer rotating shaft mechanism (50) for connecting the middle wing (4) and the outer wing (6); wherein the inner wing (2) is fixed to the outside of the fuselage (1);
the inner spindle mechanism (30) includes: the wind power generation device comprises a first cabin barrel (31) fixed with the inner wing (2), a first transmission shaft (32) arranged in the first cabin barrel (31), a first motor used for driving the first transmission shaft (32) to rotate, and a first planetary gear train structure connected with the first transmission shaft (32); the first planetary gear train structure is used for driving the middle wing (4) to rotate around the first transmission shaft (32) at a constant speed;
the outer spindle mechanism (50) includes: the second cabin barrel (51) is fixed with the middle wing (4), the second force transmission shaft (52) is arranged in the second cabin barrel (51), the second motor is used for driving the second force transmission shaft (52) to rotate, and the second planetary gear train structure is connected with the second force transmission shaft (52); the second planetary gear train structure is used for driving the outer wing (6) to rotate around the second force transmission shaft (52) at a constant speed.
2. The Z-shaped folding wing variable body aircraft according to claim 1, characterized in that the first planetary gear train structure is arranged at both ends of the first transmission shaft (32).
3. The Z-fold wing variable body aircraft of claim 1, wherein the first planetary gear train structure comprises: the planetary gear set comprises a first sun gear (33), four first planet gears (34) which are equidistantly arranged on the periphery of the first sun gear (33), an inner gear ring (35) which is concentric with the first sun gear (33), and a first planet carrier (36) which is used for supporting the first planet gears (34); the first planet gears (34) are arranged between the first sun gear (33) and the inner gear ring (35) and are in meshing connection with the first sun gear (33) and the inner gear ring (35); the inner gear ring (35) is fixedly connected with the middle wing (4).
4. The Z-shaped folding wing variable aircraft according to claim 1, characterized in that the second planetary gear train structure is arranged at both ends of the second force transmission shaft (52).
5. The Z-shaped folding wing variable body aircraft according to claim 1, characterized in that the second planetary gear train structure comprises: a second sun gear (53), four second planet gears (54) which are equidistantly arranged on the periphery of the second sun gear (53), an outer gear ring (55) which is concentric with the second sun gear (53), and a second planet gear carrier (36) which is used for supporting the second planet gears (54); the second planet wheels (54) are arranged between the second sun wheel (53) and the outer ring gear (55) and are in meshing connection with the second sun wheel (53) and the outer ring gear (55); the outer gear ring (55) is fixedly connected with the outer wing (6).
6. The Z-shaped folding wing variable body aircraft of claim 1, wherein the first motor and the second motor are both stepper motors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011090635.7A CN112193404A (en) | 2020-10-13 | 2020-10-13 | Z-shaped folding wing variable aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011090635.7A CN112193404A (en) | 2020-10-13 | 2020-10-13 | Z-shaped folding wing variable aircraft |
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| Publication Number | Publication Date |
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| CN112193404A true CN112193404A (en) | 2021-01-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011090635.7A Pending CN112193404A (en) | 2020-10-13 | 2020-10-13 | Z-shaped folding wing variable aircraft |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20200140060A1 (en) * | 2018-11-01 | 2020-05-07 | Viettel Group | Wing Deployment Mechanism and Design Method using Pneumatic Technique |
| CN112849391A (en) * | 2021-03-31 | 2021-05-28 | 成都纵横大鹏无人机科技有限公司 | Unfolding-direction folding mechanism of variable wing of unmanned aerial vehicle and unmanned aerial vehicle |
| CN112960106A (en) * | 2021-04-06 | 2021-06-15 | 上海工程技术大学 | Deformable wing and deformation method |
| CN113669426A (en) * | 2021-07-19 | 2021-11-19 | 中国空间技术研究院 | Hinge device |
| CN114889804A (en) * | 2022-04-19 | 2022-08-12 | 清华大学 | Variant flying-wing aircraft |
| CN115009507A (en) * | 2022-04-19 | 2022-09-06 | 清华大学 | Multi-connecting-rod type single-wing double-wing variant aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20200140060A1 (en) * | 2018-11-01 | 2020-05-07 | Viettel Group | Wing Deployment Mechanism and Design Method using Pneumatic Technique |
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| CN112849391A (en) * | 2021-03-31 | 2021-05-28 | 成都纵横大鹏无人机科技有限公司 | Unfolding-direction folding mechanism of variable wing of unmanned aerial vehicle and unmanned aerial vehicle |
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| CN114889804A (en) * | 2022-04-19 | 2022-08-12 | 清华大学 | Variant flying-wing aircraft |
| CN115009507A (en) * | 2022-04-19 | 2022-09-06 | 清华大学 | Multi-connecting-rod type single-wing double-wing variant aircraft |
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Application publication date: 20210108 |
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