CN108153997A - A kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method - Google Patents
A kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method Download PDFInfo
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- CN108153997A CN108153997A CN201810065015.4A CN201810065015A CN108153997A CN 108153997 A CN108153997 A CN 108153997A CN 201810065015 A CN201810065015 A CN 201810065015A CN 108153997 A CN108153997 A CN 108153997A
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- air intake
- intake ducts
- flexible covering
- flexible
- spring
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The present invention, which discloses a kind of flexible covering of deformable Bump air intake ducts and embeds matrix parameter, determines method, and step is as follows：Two kinds of forward and backward shapes are deformed according to deformable Bump air intake ducts, the corresponding two kinds of shapes provided in its flexible covering deformation range determine the corresponding elongation Δ of every spring in embedded flexible back bone using flexible covering deformation knots modificationi；Air bag inside and outside differential pressure Δ P is inhaled according to deformable Bump air intake ducts, calculates the load that flexible back bone undertakes, then calculate the load p that any spring is born in flexible back bonei；The every spring elongation Δ obtained according to step 1iAnd the load p that every spring of step 2 acquisition is borni, the structure type of skeleton and its corresponding calculation formula are embedded with reference to flexible covering, determines the relevant parameter of every spring in flexible back boneThe present processes while deformable Bump air intake ducts function is realized, can eliminate the limitation of the inlet engine compatibility of existing rigidity DSI air intake ducts, expand inlet engine compatibility Asia hypervelocity domain range.
Description
Technical field
The present invention relates to variant aircraft technology fields, more particularly to inhale, the deformable Bump air intake ducts field of inflatable, specifically
It relates to a kind of flexible covering of deformable Bump air intake ducts and embeds matrix parameter and determine method.
Background technology
The mankind take a hint from nature：Since the wing of birds can complete adaptive strain according to the change of flight environment of vehicle
Shape, the surface of wing torsion is seamless smooth and light weight, so can complete to spiral with high efficiency, glide, attack
Deng action.The trend of the enlightenment of the Nature and airplane design development has been directed toward the change with high efficiency and multi-mission adaptability jointly
Body aircraft, the technologies such as bionical deformation scheme and intellectual material and flexible structure are blended, have gradually formed and strained with Adaptation of structure
Variant technical research system based on shape and control.
Variant aircraft should be owned by good aerodynamic characteristic and high-performance, therefore, structure under different flight state
Need that there is good adaptivity, so needing to explore novel flexible structure, to meet the characteristic requirements of adaptive structure, most
It is applicable to eventually on variant aircraft.
In order to enable existing supersonic speed without boundary layer diverter air intake duct realize the high speed of Modern high-speed aircraft with it is low
The air-flow matching in speed each stage, improves mobility and improves cruising characteristics, the air intake duct of self-adapting changeable bulge shape can expire
Sufficient requirements above.
Invention content
The purpose of the present invention is to provide a kind of flexible coverings of deformable Bump air intake ducts to embed the matrix parameter side of determining
Method while deformable Bump air intake ducts function is realized, eliminates the limitation of the inlet engine compatibility of existing rigidity DSI air intake ducts
Property, expand inlet engine compatibility speed domain range.
To achieve the above object, it is true to embed matrix parameter for a kind of flexible covering of deformable Bump air intake ducts of present invention offer
Determine method, include the following steps：
A kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method, which is characterized in that including such as
Lower step：
Step 1：Two kinds of forward and backward shapes are deformed according to deformable Bump air intake ducts, it is corresponding to provide the deformation of its flexible covering
Two kinds of shapes in range determine the corresponding elongation of every spring in embedded flexible back bone using flexible covering deformation knots modification
Δi；
Step 2：Air bag inside and outside differential pressure Δ P is inhaled according to deformable Bump air intake ducts, calculates what flexible back bone undertook
Load, then calculate the load p that any spring is born in flexible back bonei；
Step 3：The every spring elongation Δ obtained according to step 1iAnd the load that every spring of step 2 acquisition is born
Lotus Pi, the structure type and its calculation formula of skeleton are embedded with reference to flexible covering, determines the phase of every spring in flexible back bone
Related parameter
Preferably, the air pressure of the flexible covering deformation range of the deformable Bump air intake ducts is 0.5~1.5 times of locality
Atmospheric pressure between.
Preferably, the shape before the flexible covering deformation is linear for fairing closing evagination, and deformed shape is
Fairing convex surface is crown.
Preferably, it is connected between the deformable Bump air intake ducts cavity and flexible covering using following steps：
The first cyclic annular bar-shaped trough is made on air intake duct cavity peripheric surface plate, for installing the connecting pin with fixed cylinder shape
Nail；
The corresponding with cavity slot first cyclic annular bar-shaped trough is made in air intake duct gland edge, it is columned for compressing
Connecting pin；
Columned connecting pin is passed through into corresponding circular hole in flexible back bone, to complete to install.
Preferably, it is sealed between the deformable Bump air intake ducts cavity and flexible covering using following steps：
The second cyclic annular bar-shaped trough is made on air intake duct cavity peripheric surface plate, and make in air intake duct gland edge with
The corresponding second cyclic annular bar-shaped trough of cavity slot, the second cyclic annular bar-shaped trough for installing and fixing seal band, wherein this second
Cyclic annular bar-shaped trough is located at the first cyclic annular bar-shaped trough inner ring side；
Sealed strip and flexible covering are compressed, to complete seal operation.
Matrix parameter is embedded by the flexible covering of the deformable Bump air intake ducts of the application and determines that method realization is deformable
While Bump air intake duct functions, the difficult point of the deformable Bump air intake ducts of lightweight is efficiently solved, and is applied in variant aircraft
Aspect makes it possible that variant aircraft has the flight space of bigger and more good flying quality, can also extend tradition and fly
The task and general operation effectiveness of row device.
Description of the drawings
Fig. 1 is the schematic diagram before the flexible air intake duct principle prototype denaturation of air pressure driving of one embodiment of the invention；Fig. 2 is this
Invent the flexible back bone schematic diagram of an embodiment；
Fig. 3 is the schematic diagram after the flexible air intake duct principle prototype denaturation of air pressure driving of one embodiment of the invention；Fig. 4 is this
It invents covering in an embodiment and samples schematic diagram；
Fig. 5 is one embodiment of the invention covering bulge schematic cross-section.
Specific embodiment
Matrix parameter is embedded to the flexible covering of the deformable Bump air intake ducts of the present invention below in conjunction with the accompanying drawings and determines method
It is described in further details.
It inhales, the concept of the deformable Bump air intake ducts of inflatable refers to that on the basis of traditional Bump air intake ducts application is soft
Property covering and by inhale, inflate type of drive realize the shape of Bump air intake ducts change, i.e.,：Bump air intake ducts have deformable
Ability, so as to formed a new generation Bump air intake ducts, refer to Fig. 1.
The suction of the present invention, the flexible covering of the deformable Bump air intake ducts of inflatable embed matrix parameter and determine method, including
Following steps (with reference to shown in Fig. 2).
Step 1：Two kinds of forward and backward shapes are deformed according to deformable Bump air intake ducts, referring specifically to Fig. 1 and Fig. 3, correspondence is given
Go out two kinds of shapes in its flexible covering deformation range, every is determined in embedded flexible back bone using flexible covering deformation knots modification
The corresponding elongation Δ of springi, here (i=1 ..., M+N), M and N represent the number of springs in direction in length and breadth respectively.
Step 2：Air bag inside and outside differential pressure Δ P is inhaled according to deformable Bump air intake ducts, calculates what flexible back bone undertook
Thus load calculates the load p that any spring is born in flexible back bonei(i=1 ..., M+N), M and N are represented respectively
The number of springs in direction in length and breadth.
Step 3：The every spring elongation Δ obtained according to step 1i(i=1 ..., M+N) and step 2 obtain every
The load p that root spring is borni(i=1 ..., M+N), M and N represents the number of springs in direction in length and breadth respectively here, with reference to flexibility
Covering embeds the structure type and its calculation formula of skeleton, so as to determine one group of every spring in flexible back bone correlation
Parameter
Step 4：According to what is obtained Required designing scheme can be provided.
It should be noted that it is connected between this kind of deformable Bump air intake ducts cavity and flexible covering using following steps：
1) the first cyclic annular bar-shaped trough is made on air intake duct cavity peripheric surface plate, for installing the connecting pin with fixed cylinder shape；2)
The corresponding with cavity slot first cyclic annular bar-shaped trough is made in air intake duct gland edge, for compressing columned connecting pin
Nail；3) columned connecting pin is passed through into corresponding circular hole in flexible back bone, to complete to install.This kind of deformable Bump simultaneously
It is sealed between air intake duct cavity and flexible covering using following steps：1) it is cyclic annular that second is made on air intake duct cavity peripheric surface plate
Bar-shaped trough, and the corresponding with cavity slot second cyclic annular bar-shaped trough is made in air intake duct gland edge, the second cyclic annular bar shaped
Slot is located at the first cyclic annular bar-shaped trough inner ring side for installing with fixing seal band, the wherein second cyclic annular bar-shaped trough；2) will
Sealed strip is compressed with flexible covering, to complete seal operation.
It should be noted that following supersonic aircraft is in entire flight envelope, the flexibility of deformable Bump air intake ducts
The air pressure of skin morph bulge range is selected between 0.5~1.5 times of local atmospheric pressure, wherein, numerical value is less than 1 and represents to inhale
Power, numerical value are more than 1 and represent pressure.
It should be noted that in the option screening stage, the difference of type and air intake duct geometric dimension for aircraft, inhale,
Inflated airbag inside and outside differential pressure Δ P can be in a certain range value.Such as：Between 0.1~0.5 times of local atmospheric pressure.
It is further illustrated below with specific numerical example.
Flexible covering model (as shown in Figure 4 and Figure 5) is established, bulge surface constraint circular diameter 900mm, in bulge curved surface
On in length and breadth direction it is each uniformly take 20 bands (width 45mm) carry out analysis calculating (note：Band on direction in length and breadth in Fig. 4 and Fig. 5
Simply it is depicted as 5).According to structural symmetry, one of direction section such as Fig. 5 in length and breadth is taken.Shape is heaved in circular flexible covering bulge
It is crown for fairing convex surface, because before deformation flexible covering deformable part be divided into fairing closing evagination it is linear, surrounding can be reduced to
Hinged constraint, so after inflating pressure, restrained circle passes through bulge spherical surface, and diameter becomes chord length.It is walked according to the calculating of aforementioned offer
Suddenly obtain it is related the results are shown in Table 1, using circumscribed base unit pattern formed flexible back bone and calculation formula：
Wherein, Uhv(N) deflection in the direction in length and breadth of entire flexible structure is represented；N represents the flexible structure of square
There is the number of outer cut unit per one side；N represents the number of turns of torsional spring in outer cut unit；F is represented in the face that flexible structure is born
The full payload in direction in length and breadth, and have F=N*P；P represents the external applied load that outer cut unit is born；Torsional spring is straight in the outer cut unit of D expressions
Diameter；D represents the diameter of torsional spring silk in outer cut unit；E represents the Young's modulus of flexible structure material.
The result corresponding with 0.1 atmospheric pressure of internal pressure of 1 element number of table 20
The degree of heaving of the covering after sealing inflation depends primarily on air pressure inside value, covering in-plane stiffness as shown in Table 1
With covering original shape size.Thus table can also obtain given covering and embed matrix parameter, and bulge covering heaves displacement and inside
The relationship of stress and external constraint power inside the correspondence and covering of inner gas pressure.For the mechanical characteristic of flexible covering
It is required that in addition on the basis of the band of cut unit composition, steel wire diameter, circle diameter and the corresponding number of turns of outer cut unit are adjusted,
It is allowed to obtain required deflection, it will be able to the relationship of the desired load of flexible back bone and deformation rate is obtained, so as to meet certainly
The demand of flexible covering in commensurate structure.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution recorded in foregoing embodiments or which part technical characteristic is equally replaced
It changes；And these modifications or replacement, the essence for various embodiments of the present invention technical solution that it does not separate the essence of the corresponding technical solution
God and range.
Claims (5)
1. a kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method, which is characterized in that including as follows
Step：
Step 1：Two kinds of forward and backward shapes are deformed according to deformable Bump air intake ducts, correspondence provides its flexible covering deformation range
In two kinds of shapes, determine the corresponding elongation Δ of every spring in embedded flexible back bone using flexible covering deformation knots modificationi；
Step 2：Air bag inside and outside differential pressure Δ P is inhaled according to deformable Bump air intake ducts, calculates the load that flexible back bone undertakes,
The load p that any spring is born in flexible back bone is calculated againi；
Step 3：The every spring elongation Δ obtained according to step 1iAnd the load p that every spring of step 2 acquisition is borni,
The structure type and its calculation formula of skeleton are embedded with reference to flexible covering, determines the relevant parameter of every spring in flexible back bone
2. the flexible covering of deformable Bump air intake ducts as described in claim 1 embeds matrix parameter and determines method, feature
Be, the air pressure of the flexible covering deformation range of the deformable Bump air intake ducts 0.5~1.5 times of local atmospheric pressure it
Between.
3. the flexible covering of deformable Bump air intake ducts as claimed in claim 2 embeds matrix parameter and determines method, feature
It is, the shape before the flexible covering deformation is linear for fairing closing evagination, and deformed shape is that fairing convex surface is preced with
Shape.
4. the flexible covering of deformable Bump air intake ducts as claimed in claim 3 embeds matrix parameter and determines method, feature
It is, is connected between the deformable Bump air intake ducts cavity and flexible covering using following steps：
The first cyclic annular bar-shaped trough is made on air intake duct cavity peripheric surface plate, for installing the connecting pin with fixed cylinder shape；
The corresponding with cavity slot first cyclic annular bar-shaped trough is made in air intake duct gland edge, for compressing columned connection
Pin；
Columned connecting pin is passed through into corresponding circular hole in flexible back bone, to complete to install.
5. the flexible covering of deformable Bump air intake ducts as claimed in claim 4 embeds matrix parameter and determines method, feature
It is, is sealed between the deformable Bump air intake ducts cavity and flexible covering using following steps：
The second cyclic annular bar-shaped trough is made on air intake duct cavity peripheric surface plate, and in the making of air intake duct gland edge and cavity
The corresponding second ring-type bar-shaped trough of slot, the second cyclic annular bar-shaped trough is for installation and fixing seal band, wherein second ring-type
Bar-shaped trough is located at the first cyclic annular bar-shaped trough inner ring side；
Sealed strip and flexible covering are compressed, to complete seal operation.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810065015.4A CN108153997B (en) | 2018-01-23 | 2018-01-23 | Method for determining parameters of flexible skin embedded skeleton of deformable Bump air inlet |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810065015.4A CN108153997B (en) | 2018-01-23 | 2018-01-23 | Method for determining parameters of flexible skin embedded skeleton of deformable Bump air inlet |
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| CN108153997A true CN108153997A (en) | 2018-06-12 |
| CN108153997B CN108153997B (en) | 2021-03-26 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109436293A (en) * | 2018-11-21 | 2019-03-08 | 南京航空航天大学 | A kind of shock wave control device |
| CN112052515A (en) * | 2020-08-04 | 2020-12-08 | 大连理工大学 | Flexible skin wrinkle suppression method for deformable wing |
| CN116750214A (en) * | 2023-08-18 | 2023-09-15 | 北京临近空间飞行器系统工程研究所 | Flexible heat-proof skin for ultra-high temperature environment |
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| CN101367434A (en) * | 2008-09-28 | 2009-02-18 | 哈尔滨工业大学 | Stressed-skin construction capable of implementing large area deformation |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109436293A (en) * | 2018-11-21 | 2019-03-08 | 南京航空航天大学 | A kind of shock wave control device |
| CN112052515A (en) * | 2020-08-04 | 2020-12-08 | 大连理工大学 | Flexible skin wrinkle suppression method for deformable wing |
| CN116750214A (en) * | 2023-08-18 | 2023-09-15 | 北京临近空间飞行器系统工程研究所 | Flexible heat-proof skin for ultra-high temperature environment |
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| CN108153997B (en) | 2021-03-26 |
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