CN113772087A - Variant aircraft with variable sweepback wings and head deflection - Google Patents
Variant aircraft with variable sweepback wings and head deflection Download PDFInfo
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- CN113772087A CN113772087A CN202111203177.8A CN202111203177A CN113772087A CN 113772087 A CN113772087 A CN 113772087A CN 202111203177 A CN202111203177 A CN 202111203177A CN 113772087 A CN113772087 A CN 113772087A
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- 238000000034 method Methods 0.000 claims description 11
- 230000008859 change Effects 0.000 abstract description 5
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
- B64C39/005—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a horizontal transversal axis
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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Abstract
The application provides a variant aircraft of sweepback wing and head deflection, variant aircraft includes: the aircraft comprises an aircraft head, an aircraft fuselage, a left swept wing, a right swept wing, a head deflection device and a swept wing deflection device; wherein the head deflection device is arranged between the aircraft head and the aircraft fuselage; the left swept wing deflection device is arranged between the left swept wing and the right swept wing; the head deflection device is used for controlling the head of the aircraft to deflect; and the swept wing deflection device is used for controlling the left swept wing and the right swept wing to sweep. The fuselage streamline of the variant aircraft provided by the application is gentle, the principle of the deformation mechanism is simple and easy to realize, and the aerodynamic performance of the aircraft flying at subsonic speed and low supersonic speed is improved by means of the change of the aerodynamic appearance of the aircraft head and the sweepback wings.
Description
Technical Field
The application relates to the technical field of design of variant flight chess, in particular to a variant aircraft with variable sweepback wings and head deflection.
Background
The aircraft is complex in required task, only the aircraft with the fixed shape is designed, the design result is necessarily chosen under various working conditions, and the resistance of low supersonic speed is sacrificed for meeting the lift force of subsonic speed flight. That is, the aerodynamic characteristics of a fixed-wing aircraft with a multi-mode flight mission in each speed range are not optimal.
In order to solve the problems, researchers provide a variant aircraft which can change the aerodynamic layout of the aircraft according to the change of the flight environment and the flight mission and maintain the optimal flight performance, so that the requirement that the aircraft carries out various missions at different heights and different flight speeds is met. The morphing aircraft can improve the aerodynamic performance of the aircraft and increase the flight endurance. In the prior art, there are also related studies, such as: patent CN110979682A discloses a variable-area duck-type forward swept wing variant aircraft, which adopts a duck-type layout, has quadrangular wings, and can be combined with an aircraft body to form triangular wings when the duck wings are retracted. The duck wing at the head part is arranged at the head part of the aircraft, and the empennage of the aircraft body can be attached to the aircraft body or unfolded towards the rear side around the connecting rotating shaft. The wing can increase aircraft span when the wing expandes completely, but among the prior art, the configuration of variant aircraft is comparatively complicated, and the fuselage streamline is not gentle, can obviously increase the resistance when supersonic speed flies, and the practicality is not strong.
Disclosure of Invention
The application provides a variant aircraft with variable sweepback wings and head deflection, which can be used for solving the technical problems that the configuration of the variant aircraft is complex and the streamline of a fuselage is not smooth.
The application provides a variant aircraft with variable sweepback wings and head deflection, which comprises:
the aircraft comprises an aircraft head, an aircraft fuselage, a left swept wing, a right swept wing, a head deflection device and a swept wing deflection device;
wherein the head deflector is disposed between the aircraft head and the aircraft fuselage; the swept wing deflection device is arranged between the left swept wing and the right swept wing;
the head deflection device is used for controlling the aircraft head to deflect;
the swept wing deflection device is used for controlling the left swept wing and the right swept wing to sweep.
Optionally, the head deflecting device includes an upper piston cylinder, an upper telescopic mechanism, a lower piston cylinder, a lower telescopic mechanism, and a support seat;
wherein the upper piston cylinder and the upper telescopic mechanism form a first head deflection device; the lower piston cylinder and the lower telescopic mechanism form a second head deflection device;
the first head deflection device and the second head deflection device have the same structure and are vertically symmetrical relative to the supporting seat;
wherein one end of the upper piston cylinder is hinged with the aircraft head; the other end is movably connected with the upper telescopic mechanism;
one end of the lower piston cylinder is hinged with the aircraft head; the other end is movably connected with the lower telescopic mechanism.
Optionally, when the aircraft head requires an upward deflection; the upper telescopic mechanism and the upper piston cylinder slide closely; the lower telescopic mechanism and the lower piston cylinder slide away from each other to drive the aircraft head to deflect upwards.
Optionally, when the aircraft head requires downward deflection; the upper telescopic mechanism slides away from the upper piston cylinder; the lower telescopic mechanism and the lower piston cylinder slide closely to drive the aircraft head to deflect downwards.
Optionally, the swept wing deflector comprises: the nut seat, the upper connecting rod, the lower connecting rod and the ball screw;
the nut seat is hinged with the upper connecting rod and the lower connecting rod respectively;
the ball screw is arranged at the position of the central shaft of the morphing aircraft and is connected with the nut seat;
the upper connecting rod is hinged with the left swept wing, and the lower connecting rod is hinged with the right swept wing.
Optionally, when the left swept wing and the right swept wing need to be retracted, the nut seat moves along the central axis direction of the ball screw in a direction close to the machine body, and the nut seat drives the upper connecting rod and the lower connecting rod to retract;
the upper connecting rod drives the left swept wing to rotate towards the interior of the aircraft body around a hinge point of the morphing aircraft;
the lower connecting rod drives the right swept wing to rotate towards the interior of the aircraft body around a hinge point of the morphing aircraft.
Optionally, when the left swept wing and the right swept wing need to be unfolded, the nut seat moves along the central axis direction of the ball screw in a direction away from the machine body, and the nut seat drives the upper connecting rod and the lower connecting rod to be unfolded;
the upper connecting rod drives the left swept wing to rotate in the direction far away from the aircraft body around the hinge point of the morphing aircraft;
the lower connecting rod drives the right swept wing to rotate in the direction far away from the aircraft body around the hinge point of the morphing aircraft.
Optionally, the morphing aircraft further comprises a skin wrapped around the exterior of the head deflector.
The fuselage streamline of the variant aircraft provided by the application is gentle, the principle of the deformation mechanism is simple and easy to realize, and the aerodynamic performance of the aircraft flying at subsonic speed and low supersonic speed is improved by means of the change of the aerodynamic appearance of the aircraft head and the sweepback wings. The flying attitude is adjusted by deflecting the angle of the warhead, and the rapid response control in the process of the high-speed flying of the missile is realized. In the subsonic speed stage, the swept wings are completely unfolded, so that the stress area and the lift force of the aircraft are increased. And in the low supersonic speed stage of the aircraft, the swept wings are contracted into the missile body, so that the flying resistance borne by the aircraft is reduced.
Drawings
FIG. 1 is a schematic view of a low supersonic velocity time axis structure of a variant aircraft with variable swept wings and head deflection, which is applicable to an embodiment of the present application;
FIG. 2 is a schematic structural view of a variant aircraft with variable swept-back wings and head deflection provided by the embodiment of the application at a low supersonic speed;
FIG. 3 is a schematic view of a head deflector according to an embodiment of the present application;
FIG. 4 is a schematic structural diagram of an aircraft head deflected downward according to an embodiment of the present disclosure;
fig. 5 is a schematic structural diagram of a swept wing deflector according to an embodiment of the present application.
Detailed Description
To make the objects, technical solutions and advantages of the present application more clear, embodiments of the present application will be described in further detail below with reference to the accompanying drawings.
A possible system architecture to which the embodiments of the present application are applicable will be first described with reference to fig. 1.
Refer to fig. 1, which schematically illustrates a low supersonic velocity time axis structural diagram of a variant aircraft with variable sweepback wings and head deflection, to which an embodiment of the present application is applicable.
Fig. 2 is a schematic view of a low supersonic speed front view structure of a variant aircraft with variable swept-back wings and head deflection provided for the embodiment of the present application.
The application provides a variant aircraft with variable sweepback wings and head deflection, which comprises: the aircraft comprises an aircraft head 1, an aircraft fuselage 3, a left swept wing 4, a right swept wing 5, a head deflector and a swept wing deflector.
Wherein the head deflection device is arranged between the aircraft head 1 and the aircraft fuselage 3. The swept wing deflector is arranged between the left swept wing 4 and the right swept wing 5.
The head deflection device is used for controlling the deflection of the aircraft head 1.
The swept wing deflection device is used for controlling the left swept wing 4 and the right swept wing 5 to carry out sweepback.
Fig. 3 is a schematic structural diagram of a head deflector according to an embodiment of the present invention. In the embodiment of the application, the rotation interval of the head deflector is [ -8 degrees, 8 degrees ].
During low supersonic speed flight, partial lift force is provided by deflecting the windward angle of the aircraft head, and the higher the Mach number of the aircraft is, the more obvious the lift force of the missile is raised.
In the embodiment of the present application, the head deflecting device includes an upper piston cylinder 6, an upper telescopic mechanism 9, a lower piston cylinder 7, a lower telescopic mechanism 10, and a support seat 8.
Wherein the upper piston cylinder 6 and the upper telescopic mechanism 9 constitute a first head deflection device. The lower piston cylinder 7 and the lower telescopic mechanism 10 constitute a second head deflecting means.
The first head deflector is of the same construction as the second head deflector and is vertically symmetrical about the support base 8.
Wherein, one end of the upper piston cylinder 6 is hinged with the aircraft head 1. The other end is movably connected with an upper telescopic mechanism 9.
One end of the lower piston cylinder 7 is hinged with the aircraft head 1. The other end is movably connected with the lower telescopic mechanism 10.
The supporting seat 8 is fixedly installed on the aircraft body 3, and the function of keeping the distance between the aircraft head 1 and the aircraft body 3 unchanged is achieved.
When the aircraft head 1 needs to be deflected upwards. The upper telescopic mechanism 9 and the upper piston cylinder 6 slide close to each other. The lower telescopic mechanism 10 and the lower piston cylinder 7 slide away from each other to drive the aircraft head 1 to deflect upwards.
Specifically, when aircraft head 1 need upwards deflect, its head declination scope is 0 ~ 8, goes up telescopic machanism 9 and upwards rotates around 3 pin joints of aircraft fuselage, goes up telescopic machanism 9 and the distance of last piston cylinder 6 and begins to reduce, goes up the piston cylinder and slides to aircraft fuselage 3 along pin joint line direction, and lower telescopic machanism 10 is upwards rotatory around 3 pin joints of aircraft fuselage, and the distance of lower telescopic machanism 10 and lower piston cylinder 7 begins to increase, and lower piston cylinder slides to the direction of keeping away from aircraft fuselage 3 along pin joint line direction.
Fig. 4 is a schematic structural diagram of an aircraft head deflected downward according to an embodiment of the present application.
When the aircraft head 1 needs to be deflected downwards. The upper telescoping mechanism 9 slides away from the upper piston cylinder 6. The lower telescopic mechanism 10 and the lower piston cylinder 7 slide closely to drive the aircraft head 1 to deflect downwards.
Specifically, when the aircraft head needs to deflect downwards, the head deflection angle range is-8 degrees to 0 degrees, the lower telescopic mechanism 10 rotates upwards around a hinge point of the aircraft body 3, the distance between the lower telescopic mechanism 10 and the lower piston cylinder 7 begins to decrease, the lower piston cylinder 7 slides towards the aircraft body 3 along the hinge point connecting line direction, the upper telescopic mechanism 9 rotates upwards around the hinge point of the aircraft body 3, the distance between the upper telescopic mechanism 9 and the upper piston cylinder 6 begins to increase, and the upper piston cylinder slides towards the direction far away from the aircraft body 3 along the hinge point connecting line direction.
Fig. 5 is a schematic structural diagram of a swept wing deflector according to an embodiment of the present application.
In an embodiment of the present application, a swept wing deflector includes: a nut seat 11, an upper connecting rod 12, a lower connecting rod 13 and a ball screw 14.
The nut seat 11 is hinged to the upper link 12 and the lower link 13.
The ball screw 14 is disposed at a position of a central axis of the morphing aircraft, and is connected with the nut socket 11.
The upper connecting rod 12 is hinged with the left swept wing 4, and the lower connecting rod 13 is hinged with the right swept wing 5.
In the embodiment of the application, the sweep angle is changed within the range of 0-40 degrees, and the resistance of the variant aircraft is reduced.
When the left swept wing 4 and the right swept wing 5 need to be contracted, the nut seat 11 moves towards the direction close to the machine body along the central axis direction of the ball screw 14, and the nut seat 11 drives the upper connecting rod 12 and the lower connecting rod 13 to be contracted.
The upper connecting rod 12 drives the left swept wing 4 to rotate towards the interior of the aircraft body 3 around the hinge point of the morphing aircraft.
The lower connecting rod 13 drives the right swept wing 5 to rotate towards the interior of the aircraft body 3 around the hinge point of the morphing aircraft.
When the variant aircraft flies at subsonic speed, the sweep angle is reduced and is restored to 0 degrees again. Specifically, when the left swept wing 4 and the right swept wing 5 need to be unfolded, the nut seat 11 moves in a direction away from the machine body along the central axis direction of the ball screw 14, and the nut seat 11 drives the upper connecting rod 12 and the lower connecting rod 13 to be unfolded.
The upper connecting rod 12 drives the left swept wing 4 to rotate around the hinge point of the morphing aircraft in the direction away from the aircraft body 3.
The lower connecting rod 13 drives the right swept wing 5 to rotate around the hinge point of the morphing aircraft in the direction away from the aircraft body 3.
The morphing aircraft further comprises a skin 2, and the skin 2 is wrapped on the outer part of the head deflection device, so that the aircraft head 1 is kept smooth with the outer surface of the aircraft fuselage 3 and bears the aerodynamic load of the aircraft during low supersonic speed flight.
The fuselage streamline of the variant aircraft provided by the application is gentle, the principle of the deformation mechanism is simple and easy to realize, and the aerodynamic performance of the aircraft flying at subsonic speed and low supersonic speed is improved by means of the change of the aerodynamic appearance of the aircraft head and the sweepback wings. The flying attitude is adjusted by deflecting the angle of the warhead, and the rapid response control in the process of the high-speed flying of the missile is realized. In the subsonic speed stage, the swept wings are completely unfolded, so that the stress area and the lift force of the aircraft are increased. And in the low supersonic speed stage of the aircraft, the swept wings are contracted into the missile body, so that the flying resistance borne by the aircraft is reduced.
The same and similar parts in the various embodiments in this specification may be referred to each other. Since it is substantially similar to the method embodiment, the description is simple, and the relevant points can be referred to the description in the method embodiment.
The above-described embodiments of the present application do not limit the scope of the present application.
Claims (8)
1. A morphing aircraft with variable swept wings and head deflection, the morphing aircraft comprising:
the aircraft comprises an aircraft head (1), an aircraft fuselage (3), a left swept wing (4), a right swept wing (5), a head deflection device and a swept wing deflection device;
wherein the head deflection device is arranged between the aircraft head (1) and the aircraft fuselage (3); the swept wing deflection device is arranged between the left swept wing (4) and the right swept wing (5);
the head deflection device is used for controlling the aircraft head (1) to deflect;
the swept wing deflection device is used for controlling the left swept wing (4) and the right swept wing (5) to sweep.
2. The method according to claim 1, wherein the head deflection device comprises an upper piston cylinder (6), an upper telescopic mechanism (9), a lower piston cylinder (7), a lower telescopic mechanism (10) and a support seat (8);
wherein the upper piston cylinder (6) and the upper telescopic mechanism (9) form a first head deflection device; the lower piston cylinder (7) and the lower telescopic mechanism (10) form a second head deflection device;
the first head deflection device and the second head deflection device are identical in structure and are vertically symmetrical relative to the supporting seat (8);
wherein one end of the upper piston cylinder (6) is hinged with the aircraft head (1); the other end is movably connected with the upper telescopic mechanism (9);
one end of the lower piston cylinder (7) is hinged with the aircraft head (1); the other end is movably connected with the lower telescopic mechanism (10).
3. Method according to claim 2, characterized in that when the aircraft head (1) needs to be deflected upwards; the upper telescopic mechanism (9) and the upper piston cylinder (6) slide close to each other; the lower telescopic mechanism (10) and the lower piston cylinder (7) slide away from each other to drive the aircraft head (1) to deflect upwards.
4. Method according to claim 2, characterized in that when the aircraft head (1) needs to be deflected downwards; the upper telescopic mechanism (9) slides away from the upper piston cylinder (6); the lower telescopic mechanism (10) and the lower piston cylinder (7) slide closely to drive the aircraft head (1) to deflect downwards.
5. The method of claim 1, wherein the swept wing deflector comprises: the nut seat (11), the upper connecting rod (12), the lower connecting rod (13) and the ball screw (14);
the nut seat (11) is hinged with the upper connecting rod (12) and the lower connecting rod (13) respectively;
the ball screw (14) is arranged at the position of the central shaft of the morphing aircraft and is connected with the nut seat (11);
the upper connecting rod (12) is hinged with the left swept wing (4), and the lower connecting rod (13) is hinged with the right swept wing (5).
6. The method according to claim 5, characterized in that when the left swept wing (4) and the right swept wing (5) need to be contracted, the nut seat (11) moves along the central axis direction of the ball screw (14) to approach the fuselage direction, and the nut seat (11) brings the upper connecting rod (12) and the lower connecting rod (13) to be contracted;
the upper connecting rod (12) drives the left swept wing (4) to rotate towards the interior of the aircraft body (3) around a hinge point of the morphing aircraft;
the lower connecting rod (13) drives the right swept wing (5) to rotate towards the interior of the aircraft body (3) around a hinge point of the morphing aircraft.
7. The method according to claim 5, characterized in that when the left swept wing (4) and the right swept wing (5) need to be unfolded, the nut seat (11) moves away from the fuselage along the central axis direction of the ball screw (14), and the nut seat (11) brings the upper link (12) and the lower link (13) to be unfolded;
the upper connecting rod (12) drives the left swept wing (4) to rotate around a hinge point of the morphing aircraft in a direction away from the aircraft body (3);
the lower connecting rod (13) drives the right swept wing (5) to rotate around a hinge point of the morphing aircraft in the direction away from the aircraft body (3).
8. The method according to claim, characterized in that the morphing aircraft further comprises a skin (2), the skin (2) being wrapped outside the head deflector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111203177.8A CN113772087A (en) | 2021-10-15 | 2021-10-15 | Variant aircraft with variable sweepback wings and head deflection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111203177.8A CN113772087A (en) | 2021-10-15 | 2021-10-15 | Variant aircraft with variable sweepback wings and head deflection |
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| Publication Number | Publication Date |
|---|---|
| CN113772087A true CN113772087A (en) | 2021-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111203177.8A Pending CN113772087A (en) | 2021-10-15 | 2021-10-15 | Variant aircraft with variable sweepback wings and head deflection |
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| CN (1) | CN113772087A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2594766A (en) * | 1946-11-30 | 1952-04-29 | Esther C Goddard | Apparatus for steering aircraft |
| US3069112A (en) * | 1956-08-20 | 1962-12-18 | Raymond T Patterson | Radome |
| US4579298A (en) * | 1981-04-08 | 1986-04-01 | The Commonwealth Of Australia | Directional control device for airborne or seaborne missiles |
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| CN103523223A (en) * | 2013-10-28 | 2014-01-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse course control system and transverse course control method for flying wing configuration |
| CN105318794A (en) * | 2014-07-31 | 2016-02-10 | 南京理工大学 | Deflection warhead |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
| CN211711070U (en) * | 2019-12-12 | 2020-10-20 | 中国民用航空飞行学院 | Variable sweepback wing driving device of unmanned aerial vehicle and variable sweepback wing unmanned aerial vehicle |
| CN113232828A (en) * | 2021-05-31 | 2021-08-10 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
-
2021
- 2021-10-15 CN CN202111203177.8A patent/CN113772087A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2594766A (en) * | 1946-11-30 | 1952-04-29 | Esther C Goddard | Apparatus for steering aircraft |
| US3069112A (en) * | 1956-08-20 | 1962-12-18 | Raymond T Patterson | Radome |
| US4579298A (en) * | 1981-04-08 | 1986-04-01 | The Commonwealth Of Australia | Directional control device for airborne or seaborne missiles |
| US5538202A (en) * | 1993-11-02 | 1996-07-23 | Northrop Grumman Corporation | Hydraulic actuation system for aircraft control surfaces |
| CN103523223A (en) * | 2013-10-28 | 2014-01-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse course control system and transverse course control method for flying wing configuration |
| CN105318794A (en) * | 2014-07-31 | 2016-02-10 | 南京理工大学 | Deflection warhead |
| CN211711070U (en) * | 2019-12-12 | 2020-10-20 | 中国民用航空飞行学院 | Variable sweepback wing driving device of unmanned aerial vehicle and variable sweepback wing unmanned aerial vehicle |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | Variable-area duck-type forward-swept wing variant aircraft |
| CN113232828A (en) * | 2021-05-31 | 2021-08-10 | 南京航空航天大学 | Deflection control mechanism of deformable structure of supersonic aircraft head |
Non-Patent Citations (1)
| Title |
|---|
| 张志勇等: "偏转头弹箭飞行特性", 《空气动力学学报》 * |
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