CN111169621A - Multifunctional wing capable of being rotated to be in vertical state for safe separation - Google Patents
Multifunctional wing capable of being rotated to be in vertical state for safe separation Download PDFInfo
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- CN111169621A CN111169621A CN201911308849.4A CN201911308849A CN111169621A CN 111169621 A CN111169621 A CN 111169621A CN 201911308849 A CN201911308849 A CN 201911308849A CN 111169621 A CN111169621 A CN 111169621A
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- wing
- vertical state
- rotatable
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention belongs to the technical field of aircrafts, and particularly relates to a multifunctional wing capable of being rotated to a vertical state for safe separation. The technical scheme is as follows: the whole wing consists of an inner wing, a middle wing and an outer wing, wherein a tip chord of the inner wing is connected with a root chord of the middle wing, a rotating shaft is arranged at the joint, the middle wing and the outer wing can integrally rotate around the rotating shaft, the maximum rotating angle can be rotated to be vertical to the inner wing, the tip chord of the middle wing is connected with the root chord of the outer wing, a connection and separation mechanism is arranged at the joint, and the outer wing can be separated from the middle wing; the inner wing is an aircraft fixing structure, and airborne equipment and fuel oil can be additionally arranged in an inner cavity; the middle wing is a connecting structure of the inner wing and the outer wing, and adopts a wing shape with smaller relative thickness, and the internal cavity can be additionally provided with onboard equipment and can be used as a vertical tail after rotating; the outer wing is separable structure, can separate with the middle wing after rotatory to the position, adopts the great symmetrical wing section of relative thickness, and inside cavity can install the fuel additional.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a multifunctional wing capable of being rotated to a vertical state for safe separation.
Background
With the development of scientific technology, the application mode of the future aircraft will be changed, the change of the application mode of the aircraft needs a flexible flight mode as a support, and the flight mode of the future aircraft will have two newly-added important features: the first is wide speed range flight, and the second is cross-range flight. The wide-speed-range flight breaks through subsonic and supersonic flight speed ranges, and is expanded to a hypersonic flight speed range, namely the flight speed is expanded to more than mach number 5; the cross-domain flight means breaking through the traditional flight airspace of low altitude and medium altitude and extending to the near space and aerospace domain, namely extending to more than 100 kilometers from the flight altitude.
The flexible flying mode of the aircraft is realized by means of a powerful power system and a high-efficiency aerodynamic layout, particularly wing parts for generating aerodynamic benefits. For the wide-speed-range flying aircraft, the requirements of low-speed flying and hypersonic flying on the shape, reference area, aspect ratio, relative thickness and the like of wings are greatly different, and even conflict exists. Low-speed flight requires a large reference area and a large aspect ratio to pursue a high lift-drag ratio, and in order to meet the requirement of a flight path, the internal space of the wing is often required to be utilized, and the wing with a certain relative thickness is also necessary; the hypersonic flight pursues low resistance, and a thin wing with a small aspect ratio is an ideal choice. The conventional hypersonic aircraft is limited by the positioning and technical degree of task requirements, generally takes the maximum Mach number or cruise Mach number as a single design point, can keep a narrow flight speed range of high aerodynamic performance, and cannot well give consideration to the aerodynamic performance of a non-design point in a wide speed range. In order to solve the aerodynamic contradiction of wide-speed-range flight, the variable-configuration wing is an important solution.
With the development of future industrial manufacturing technologies, such as 3D printing technology, etc., the manufacturing and application of the modified wing becomes easy and cheaper, and the partial components can be designed to be used once or for a limited number of times, i.e. can be separated from the body during use, in order to realize specific functions.
Disclosure of Invention
The purpose of the invention is: the aircraft wing solution is applicable to the flight in a large airspace with the speed Mach number of 0-5 + and the wide speed range and the height of 0-100 kilometers, and has good aerodynamic performance in different flight states.
The technical scheme of the invention is as follows: a multifunctional wing capable of being rotated to a vertical state for safe separation comprises an inner wing 1, a middle wing 3 and an outer wing 5, wherein a sharp chord of the inner wing 1 is connected with a root chord of the middle wing 3, a rotating shaft 2 is arranged at the joint, the middle wing 3 and the outer wing 5 can integrally rotate around the rotating shaft 2, the sharp chord of the middle wing 3 is connected with the root chord of the outer wing 5, a connecting and separating structure 4 is arranged at the joint, and the outer wing 5 can be separated from the middle wing 3.
The maximum rotation angle of the middle wing 3 and the outer wing 5 integrally rotating around the rotation axis 2 may be perpendicular to the inner wing 1.
The inner wing 1 is an aircraft fixing structure, and a cavity for additionally installing airborne equipment or fuel oil is arranged inside the inner wing.
The middle wing 3 is internally provided with a cavity for additionally installing airborne equipment, and can be used as a vertical fin after being rotated.
And a cavity for adding fuel oil is arranged in the outer wing 5.
The middle wing 3 is 5-8% of the relative thickness of the wing profile.
The relative thickness of the outer wing 5 airfoil is 10-15%.
The connecting and separating structure 4 adopts a slide rail free separation mode.
The invention has the advantages that: according to the aircraft wing solution, in the subsonic flight stage, the inner wing, the middle wing and the outer wing are arranged on the same plane to form a wing with a large reference area and a large aspect ratio, so that a large lift-drag ratio is provided for an aircraft; the wings formed by the inner wings, the middle wings and the outer wings are not arranged in a vertical tail manner, so that the good stealth characteristic of the aircraft can be kept; the inner wing is an aircraft fixing structure, airborne equipment and fuel oil can be additionally arranged in the inner cavity, and the utilization rate of the inner space is improved; the middle wing adopts a wing shape with relatively small thickness, the characteristics of high strength rigidity and low resistance are considered, and the internal cavity can be provided with a sliding rail mechanism and a separating mechanism; the outer wing adopts the symmetrical wing section that relative thickness is great, and inside cavity can install the fuel additional, and low-speed stage is preferred to be used, can improve aircraft range. In transonic, supersonic and hypersonic flight stages, the middle wing and the outer wing integrally rotate to be perpendicular to the inner wing, the outer wing can be separated from the middle wing for reducing aircraft resistance, and in a flat flight state of the aircraft, due to the adoption of symmetrical wing sections, the generated lateral force and moment are small, free separation can be realized only by aerodynamic force, no additional separating force mechanism is needed, the middle wing can be used as an aircraft vertical tail, and the yaw aerodynamic characteristics of the high-speed aircraft are improved.
Drawings
Fig. 1 is a schematic view of a conventional airfoil.
FIG. 2 is a schematic view of a wing with the middle wing and the outer wing rotated to a vertical position as a whole.
FIG. 3 is a schematic view of a wing with the outer wing separated from the middle wing.
Wherein, 1 is an inner wing, 2 is a rotating shaft, 3 is a middle wing, 4 is a connecting and separating mechanism, and 5 is a rotary outer wing.
Detailed Description
The invention is described in detail below with reference to the figures and the use steps.
The wing of the invention in a conventional state is shown in figure 1, and the inner wing, the middle wing and the outer wing are in the same plane.
The wing of the invention, in which the wing and the outer wing integrally rotate to a vertical state, is shown in figure 2, the middle wing and the outer wing are integrally vertical to the inner wing, and the outer wing and the middle wing are not separated. The wing-shaped aircraft is composed of an inner wing 1, a middle wing 3 and an outer wing 5, wherein the sharp chord of the inner wing 1 is connected with the root chord of the middle wing 3, a rotating shaft 2 is arranged at the joint, the middle wing 3 and the outer wing 5 can integrally rotate around the rotating shaft 2, the sharp chord of the middle wing 3 is connected with the root chord of the outer wing 5, a connecting and separating structure 4 is arranged at the joint, and the outer wing 5 can be separated from the middle wing 3.
The maximum rotation angle of the middle wing 3 and the outer wing 5 integrally rotating around the rotation axis 2 may be perpendicular to the inner wing 1.
The inner wing 1 is an aircraft fixing structure, and a cavity for additionally installing airborne equipment or fuel oil is arranged inside the inner wing.
The middle wing 3 is internally provided with a cavity for additionally installing airborne equipment, and can be used as a vertical fin after being rotated.
And a cavity for adding fuel oil is arranged in the outer wing 5.
The middle wing 3 is 5-8% of the relative thickness of the wing profile.
The relative thickness of the outer wing 5 airfoil is 10-15%.
The connecting and separating structure 4 adopts a slide rail free separation mode.
The wing with the separated outer wing and the middle wing is shown in figure 3, the outer wing and the middle wing are not separated, and the middle wing is vertical to the inner wing.
A multi-function wing capable of being rotated to a vertical position for safe separation, comprising the steps of:
the method comprises the following steps: in an initial state, the inner wing (1), the middle wing (3) and the outer wing (5) are located on the same plane, airborne equipment and fuel oil are additionally arranged in a cavity inside the inner wing (1), a sliding rail mechanism and a separating mechanism are arranged in the cavity inside the middle wing (3), and the fuel oil is additionally arranged in the cavity inside the outer wing (5).
Step two: according to flight performance requirements, the middle wing (3) and the outer wing (5) integrally rotate around the rotating shaft (2) and can be perpendicular to the inner wing (1) at most.
Step three: according to the requirement of flight performance, under the condition that the whole of the middle wing (3) and the outer wing (5) is vertical to the inner wing (1), the outer wing (5) and the middle wing (5) are freely separated from the connecting and separating mechanism (4) by virtue of aerodynamic force, and the middle wing (3) is used as a vertical tail.
Step four: according to flight performance requirements, the middle wing (3) can rotate around the rotating shaft (2) in the opposite direction to be in the same plane with the inner face (1).
The skins and the framework structures of the inner wing (1) and the middle wing (3) are made of titanium alloy materials.
The outer wing (5) covering machine skeleton structure is made of aluminum alloy materials.
The connecting and separating mechanism (4) is mainly provided with a slide rail, an explosion wire and the like.
Claims (8)
1. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the wing-shaped aircraft is composed of an inner wing (1), a middle wing (3) and an outer wing (5), wherein a sharp chord of the inner wing (1) is connected with a root chord of the middle wing (3), a rotating shaft (2) is arranged at the joint, the middle wing (3) and the outer wing (5) can integrally rotate around the rotating shaft (2), the sharp chord of the middle wing (3) is connected with the root chord of the outer wing (5), a connecting and separating structure (4) is arranged at the joint, and the outer wing (5) can be separated from the middle wing (3).
2. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the maximum rotation angle of the middle wing (3) and the outer wing (5) which rotate integrally around the rotating shaft (2) can be vertical to the inner wing (1).
3. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the inner wing (1) is of an aircraft fixing structure, and a cavity for additionally installing airborne equipment or fuel oil is arranged inside the inner wing.
4. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the middle wing (3) is internally provided with a cavity for additionally installing airborne equipment, and can be used as a vertical tail after being rotated.
5. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: and a cavity for additionally installing fuel oil is arranged in the outer wing (5).
6. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the middle wing (3) is 5-8% in wing section relative thickness.
7. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the outer wing (5) is 10-15% in wing section relative thickness.
8. The utility model provides a rotatable to multi-functional wing of vertical state safety separation which characterized in that: the connecting and separating structure (4) adopts a slide rail free separation mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911308849.4A CN111169621A (en) | 2019-12-18 | 2019-12-18 | Multifunctional wing capable of being rotated to be in vertical state for safe separation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911308849.4A CN111169621A (en) | 2019-12-18 | 2019-12-18 | Multifunctional wing capable of being rotated to be in vertical state for safe separation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111169621A true CN111169621A (en) | 2020-05-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911308849.4A Pending CN111169621A (en) | 2019-12-18 | 2019-12-18 | Multifunctional wing capable of being rotated to be in vertical state for safe separation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111169621A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN103538718A (en) * | 2013-10-23 | 2014-01-29 | 上海大学 | Detaching mechanism for detaching wings of unmanned aerial vehicle |
| CN105438443A (en) * | 2015-12-08 | 2016-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Shape-preserving foldable wing |
| WO2017050333A1 (en) * | 2015-09-25 | 2017-03-30 | Airbus Ds Gmbh | Separable wing for an aircraft, aircraft having a separable wing, and method for landing an aircraft of this type |
| US20170113778A1 (en) * | 2015-10-01 | 2017-04-27 | Evolving Resources, Inc. | Detachable wing system for aircrafts |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN107792359A (en) * | 2017-10-19 | 2018-03-13 | 西北工业大学 | A kind of empty dual-purpose unmanned plane of water |
| CN108177760A (en) * | 2016-12-08 | 2018-06-19 | 上海交通大学 | VTOL personal aircraft |
| CN109703741A (en) * | 2019-01-28 | 2019-05-03 | 中国人民解放军国防科技大学 | Folding morphing wing and aircraft based on Sarrus structure drive |
-
2019
- 2019-12-18 CN CN201911308849.4A patent/CN111169621A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN103538718A (en) * | 2013-10-23 | 2014-01-29 | 上海大学 | Detaching mechanism for detaching wings of unmanned aerial vehicle |
| WO2017050333A1 (en) * | 2015-09-25 | 2017-03-30 | Airbus Ds Gmbh | Separable wing for an aircraft, aircraft having a separable wing, and method for landing an aircraft of this type |
| US20170113778A1 (en) * | 2015-10-01 | 2017-04-27 | Evolving Resources, Inc. | Detachable wing system for aircrafts |
| CN105438443A (en) * | 2015-12-08 | 2016-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Shape-preserving foldable wing |
| CN108177760A (en) * | 2016-12-08 | 2018-06-19 | 上海交通大学 | VTOL personal aircraft |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN107792359A (en) * | 2017-10-19 | 2018-03-13 | 西北工业大学 | A kind of empty dual-purpose unmanned plane of water |
| CN109703741A (en) * | 2019-01-28 | 2019-05-03 | 中国人民解放军国防科技大学 | Folding morphing wing and aircraft based on Sarrus structure drive |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200519 |