CN106428512B - High-speed deformation aircraft - Google Patents
High-speed deformation aircraft Download PDFInfo
- Publication number
- CN106428512B CN106428512B CN201610997796.1A CN201610997796A CN106428512B CN 106428512 B CN106428512 B CN 106428512B CN 201610997796 A CN201610997796 A CN 201610997796A CN 106428512 B CN106428512 B CN 106428512B
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- shell
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- aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention relates to a kind of high-speed deformation aircraft, this high-speed deformation aircraft includes head, fuselage and power plant；The power plant is mounted on the tail portion of fuselage；The fuselage includes shell, and the shell is by memory metal sheet coiling and molding；Along the fuselage end on observation, the shell is oval in the spiral of coiling；The spiral ellipse has high-temperature-phase shape and low-temperature phase shape, under the condition of high temperature, the ratio of spiral oval outermost major radius and short radius, and the ratio being more than under low-temperature condition；Filled with buffering heat-conducting layer between adjacent memory metal sheet；It is disposed with work chamber, control cabinet and supply cabin determining shell interior；The control cabinet is electrically connected with power plant；The Flight Vehicle Structure is novel, unique, can be according to the difference of flying speed, and intelligence adjusts the outer shape of body, and to reduce the resistance of aircraft, reduce temperature arrising caused by friction, advantage is provided for the speed-raising of aircraft.
Description
Technical field
The present invention relates to a kind of aircraft, are a kind of deformable aircraft particularly.
Background technology
With the development of science and technology, aircraft one is can to carry out high-speed flight and hypervelocity flight；Aircraft was flying
Cheng Zhonghui is generated high temperature by air drag, and therefore, the shell of aircraft need to have preferable high temperature resistance；Meanwhile
With hydromechanical progress, scientists are found, fairshaped shell can provide larger lift for aircraft, while
Suffered resistance is smaller in fluid, is capable of the flight of high speed；But in the flight environment of vehicle of higher speed, shuttle-type can be fitted preferably
It answers；Therefore, optimum shape when compared with low velocity flight may be no longer desirable for higher speed, can increase air resistance instead
Power brings a negative impact for the speed-raising of itself；
Memory metal is called marmem, has recovery characters, wherein the memory with double-pass memory effect
Alloy, in low temperature, it has low-temperature phase shape, and when the temperature increases, its shape changes into high-temperature-phase shape.
Invention content
In view of the above-mentioned problems, the present invention provides a kind of high-speed deformation aircraft, the Flight Vehicle Structure is novel, unique, can
According to the difference of flying speed, intelligence adjusts the outer shape of body, to reduce the resistance of aircraft, reduce temperature arrising caused by friction,
Advantage is provided for the speed-raising of aircraft.
To solve the above problems, the technical solution adopted in the present invention is：This high-speed deformation aircraft includes head, machine
Body and power plant；The power plant is mounted on the tail portion of fuselage；
The fuselage includes shell, and the shell is by memory metal sheet coiling and molding；Along the fuselage end on observation, institute
It is oval in the spiral of coiling to state shell；The spiral ellipse has high-temperature-phase shape and low-temperature phase shape, under the condition of high temperature, spiral
The ratio of oval outermost major radius and short radius, the ratio being more than under low-temperature condition；
Filled with buffering heat-conducting layer between adjacent memory metal sheet；
In the sizing shell for being internally provided with hard of the shell；It is described determine shell interior be disposed with work chamber, control
Cabin and supply cabin；The control cabinet is electrically connected with power plant.
The beneficial effects of the invention are as follows：This high-speed deformation aircraft takes off under the drive of power plant, in flight course
In, the shell of aircraft and windage, shell gradually heat up；When aircraft is run at a low speed, casing surface temperature is relatively low, shell
Body is in low-temperature phase shape, and the outer surface of shell is in fuller ellipse at this time；It is promoted with the speed of aircraft, case temperature
It increases, buffering heat-conducting layer can will be in the outermost temperature conduction to internal layer of shell；When aircraft raises speed to a certain degree, shell
Temperature is more than critical value, and the shell deforms upon, and shell becomes platypelloid type, effectively reduces the resistance between aircraft and air
Power is more suitable for high-speed flight.
In deformation process, buffering heat-conducting layer can auxiliary shell smoothly deform, while temperature timely being transmitted, from
And promote the deformation of internal layer memory metal sheet.
The mentality of designing of the present invention can be additionally used in guided missile, shell etc., and the air drag after deformation effectively reduces, can
Speed promotion is effectively facilitated, to improve the range of shell.
Preferably, the buffering heat-conducting layer includes the sponge that heat-conducting metal silk is made；The structure can preferably be led
Heat promotes the deformation of shell；Buffering effect can be played in housing distortion simultaneously, ensures the stable deformation of shell, reduces and flies
Row device jolts.
Preferably, the buffering heat-conducting layer includes the stereoscopic grid made by high temperature resistant elastic material, described vertical
Doped with heat conductive filament in volume mesh；The structure being capable of the steady deformation of auxiliary shell；Simultaneously so that shell thermally equivalent.
Description of the drawings
Fig. 1 is vertical section structural schematic diagram of this high-speed deformation aircraft in low speed.
Fig. 2 is end section structural schematic diagram of the embodiment illustrated in fig. 1 in low speed.
Fig. 3 is vertical section structural schematic diagram of the embodiment illustrated in fig. 1 in high speed.
Fig. 4 is end section structural schematic diagram of the embodiment illustrated in fig. 1 in high speed.
Specific implementation mode
Embodiment
In the embodiment shown in Fig. 1 to Fig. 4, this high-speed deformation aircraft includes head 1, fuselage 2 and power plant
3；The power plant 3 is mounted on the tail portion of fuselage 2；
The fuselage 2 includes shell 21, and the shell 21 is by memory metal sheet coiling and molding；It is axial along the fuselage 2
Observation, the shell 21 are oval in the spiral of coiling；The spiral ellipse has high-temperature-phase shape and low-temperature phase shape, high temperature shape
Under state, the ratio of spiral oval outermost major radius and short radius, the ratio being more than under low-temperature condition；
Filled with buffering heat-conducting layer 22 between adjacent memory metal sheet；The buffering heat-conducting layer 22 includes heat conduction gold
Belong to the sponge that silk is made；Buffering heat-conducting layer 22 can also have other structures, and such as buffering heat-conducting layer 22 includes by high temperature resistant bullet
The stereoscopic grid that property material is made, doped with heat conductive filament in the stereoscopic grid；
In the sizing shell 23 for being internally provided with hard of the shell 21；It is disposed with work chamber inside the sizing shell 23
4, control cabinet 5 and supply cabin 6；The control cabinet 5 is electrically connected with power plant 3.
The beneficial effects of the invention are as follows：This high-speed deformation aircraft takes off under the drive of power plant 3, in flight course
In, the shell 21 of aircraft and windage, shell 21 gradually heat up；When aircraft is run at a low speed, 21 surface temperature of shell
Relatively low, shell 21 is in low-temperature phase shape, and the outer surface of shell 21 is in fuller ellipse at this time；It is carried with the speed of aircraft
It rises, 21 temperature of shell increases, and buffering heat-conducting layer 22 can will be in 21 outermost temperature conduction to internal layer of shell；When aircraft carries
Speed to a certain degree when, 21 temperature of shell is more than critical value, and the shell 21 deforms upon, and shell 21 becomes platypelloid type, is effectively dropped
Low resistance between aircraft and air, is more suitable for high-speed flight.
In the present embodiment, when 21 deformation of shell, buffering heat-conducting layer 22 being capable of the smoothly deformation of auxiliary shell 21, effectively drop
Low aircraft jolts；Temperature is timely transmitted simultaneously, to promote the deformation of internal layer memory metal sheet.
The mentality of designing of the present invention can be additionally used in guided missile, shell etc., and the air drag after deformation effectively reduces, can
Speed promotion is effectively facilitated, to improve the range of shell.
The foregoing is merely presently preferred embodiments of the present invention, is not intended to limit the invention, it is all the present invention spirit and
Within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention.
Claims (3)
1. a kind of high-speed deformation aircraft, this high-speed deformation aircraft include head（1）, fuselage（2）And power plant（3）；
The power plant（3）Mounted on fuselage（2）Tail portion；It is characterized in that：The fuselage（2）It include shell（21）, described
Shell（21）By memory metal sheet coiling and molding；Along the fuselage（2）End on observation, the shell（21）It is ellipse in the spiral of coiling
Circle；The spiral ellipse has high-temperature-phase shape and low-temperature phase shape, the oval outermost major radius of spiral of high-temperature-phase shape
With the ratio of short radius, it is more than the ratio of low-temperature phase shape；Filled with buffering heat-conducting layer between adjacent memory metal sheet
（22）；In the shell（21）The sizing shell for being internally provided with hard（23）；In the sizing shell（23）Inside is disposed with work
Make cabin（4）, control cabinet（5）With supply cabin（6）；The control cabinet（5）With power plant（3）Electrical connection.
2. high-speed deformation aircraft according to claim 1, it is characterised in that：The buffering heat-conducting layer（22）Include to lead
The sponge that hot wire is made.
3. high-speed deformation aircraft according to claim 1 or 2, it is characterised in that：The buffering heat-conducting layer（22）Including
There is the stereoscopic grid made by high temperature resistant elastic material, doped with heat conductive filament in the stereoscopic grid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610997796.1A CN106428512B (en) | 2016-11-14 | 2016-11-14 | High-speed deformation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610997796.1A CN106428512B (en) | 2016-11-14 | 2016-11-14 | High-speed deformation aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106428512A CN106428512A (en) | 2017-02-22 |
| CN106428512B true CN106428512B (en) | 2018-11-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610997796.1A Active CN106428512B (en) | 2016-11-14 | 2016-11-14 | High-speed deformation aircraft |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110471477A (en) * | 2019-08-24 | 2019-11-19 | 昆明研顶技术开发有限公司 | A kind of automatic changeable device of spacecraft superficial form |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5700337A (en) * | 1996-03-01 | 1997-12-23 | Mcdonnell Douglas Corporation | Fabrication method for composite structure adapted for controlled structural deformation |
| CN102510828A (en) * | 2009-09-25 | 2012-06-20 | 波音公司 | Structurally designed aerodynamic riblets |
| CN102933387A (en) * | 2010-06-04 | 2013-02-13 | 波音公司 | Shape memory alloy/fiber reinforced polymeric composite structures and method for forming |
| CN104816815A (en) * | 2015-05-08 | 2015-08-05 | 哈尔滨工业大学 | Shape memory alloy fiber and super-elastic body compound deformation skin |
| CN105109667A (en) * | 2015-08-24 | 2015-12-02 | 清华大学 | Variable structure with deflection hinge locking and shape memory alloy driving |
| CN105314092A (en) * | 2014-07-16 | 2016-02-10 | 波音公司 | Adaptive composite structure using shape memory alloys |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04103497A (en) * | 1990-08-23 | 1992-04-06 | Mitsubishi Heavy Ind Ltd | De-icing device |
-
2016
- 2016-11-14 CN CN201610997796.1A patent/CN106428512B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5700337A (en) * | 1996-03-01 | 1997-12-23 | Mcdonnell Douglas Corporation | Fabrication method for composite structure adapted for controlled structural deformation |
| CN102510828A (en) * | 2009-09-25 | 2012-06-20 | 波音公司 | Structurally designed aerodynamic riblets |
| CN102933387A (en) * | 2010-06-04 | 2013-02-13 | 波音公司 | Shape memory alloy/fiber reinforced polymeric composite structures and method for forming |
| CN105314092A (en) * | 2014-07-16 | 2016-02-10 | 波音公司 | Adaptive composite structure using shape memory alloys |
| CN104816815A (en) * | 2015-05-08 | 2015-08-05 | 哈尔滨工业大学 | Shape memory alloy fiber and super-elastic body compound deformation skin |
| CN105109667A (en) * | 2015-08-24 | 2015-12-02 | 清华大学 | Variable structure with deflection hinge locking and shape memory alloy driving |
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| Publication number | Publication date |
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| CN106428512A (en) | 2017-02-22 |
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Effective date of registration: 20180920 Address after: 362000 Cheong Mao Street champagne hall 1303, Zhongxing Street, Quangang District, Quanzhou, Fujian, China No. 8 Applicant after: Quanzhou Quangang Xinyue Industrial Technology Co., Ltd. Address before: 215200 Nan Yang village residents' committee, Ping Wang Town, Wujiang District, Suzhou, Jiangsu Applicant before: Zhong Binghua |
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Effective date of registration: 20190920 Address after: 244151 Shenqiao Village, Shun'an Town, Yian District, Tongling City, Anhui Province Patentee after: Mdt InfoTech Ltd in Anhui Address before: 362000 Champagne Mansion No. 8 1303, Changmao, Zhongxing Street, Quanzhou Quangang District, Fujian Province Patentee before: Quanzhou Quangang Xinyue Industrial Technology Co., Ltd. |