CN110155375A - Space debris prevention structure - Google Patents
Space debris prevention structure Download PDFInfo
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- CN110155375A CN110155375A CN201811257133.1A CN201811257133A CN110155375A CN 110155375 A CN110155375 A CN 110155375A CN 201811257133 A CN201811257133 A CN 201811257133A CN 110155375 A CN110155375 A CN 110155375A
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- Prior art keywords
- inner support
- protection coating
- external protection
- support layer
- honeycomb
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
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- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
- Vibration Dampers (AREA)
Abstract
The embodiment of the present invention provides a kind of space debris prevention structure, which includes inner support layer, middle layer and external protection coating, wherein inner support layer has the cavity of both ends open for fixing the middle layer, inner support layer, for accommodating to protector；Middle layer is arranged between inner support layer and external protection coating, and middle layer is at least made of honeycomb, and honeycomb is circumferentially arranged in inner support layer outer surface, and middle layer at least is used to absorb the energy of space junk；The outer surface for stating middle layer is circumferentially arranged in external protection coating, and the outer surface of external protection coating is also configured to the face of smoothly transitting, and external protection coating is for the space junk to be crushed.Safeguard structure provided in an embodiment of the present invention is able to solve big stress present in existing space fragment protective structure and concentrates, and can not carry out the technical issues of protecting and cannot reaching the requirement of shelter of the fragment bigger for diameter to space flight cabin comprehensively.
Description
Technical field
The present invention provides a kind of space debris prevention structure more particularly to a kind of Whipple formula hiperspace fragment is anti-
Protection structure belongs to protection of space debris technical field.
Background technique
The spacecraft of numerous earth orbital operations scientific research, location navigation, communication relaying, in terms of
Play extremely important effect.However, spacecraft is in the process of running, the aluminium oxide after the small burning to solid propellant rocket
Little particle seriously threatens greatly the safety of spacecraft to the space junk of carrier rocket final stage.The space junk of ultrahigh speed movement
When striking spacecraft, spacecraft can be made to occur into hole, perforation or even catastrophic destruction, and will lead to more space trashes
Generation.Currently, generally using the technology hand of active dodge in the world for diameter about in the large space fragment of 10cm or more
Section protects spacecraft, and monitoring and warning means are also increasingly advanced.And be more than for quantity 20,000,000,000 numerous Centimeter Levels
Space Debris, millimetre-sized small space junk, spacecraft can not be evaded to be collided with it, can only be by reinforcing spacecraft
Protective capacities carrys out passive protection.
The protective structure approach of spacecraft is roughly divided into whipple protection, filled type whipple is protected, netted double-deck anti-
Shield, multilayer surge guard etc..Existing safeguard structure mostly uses the protecting screen structure type of single-layer or multi-layer, such as patent application
Although CN105109709 and CN107140238, this kind of safeguard structure realize a degree of absorption dispersion space fragment, so
And on the one hand since four boundaries of this class formation are in free state, under space junk high speed impact, it will generate compared with
More stress, the scattering on boundary cause big stress to be concentrated, so that the structural strength of this class formation reduces, can not be used for a long time；Separately
On the one hand, it is confined to the structure type (plate) of this class formation, leads to that full protection can not be carried out to cabin；Furthermore these are anti-
The bullet cut off diameter that protection structure scheme measures rests on grade, and the protection that cannot reach the fragment bigger for diameter is wanted
It asks.
Summary of the invention
Brief summary of the present invention is given below, in order to provide the basic reason about certain aspects of the invention
Solution.It should be appreciated that this summary is not an exhaustive overview of the invention.It is not intended to determine key of the invention
Or pith, nor is it intended to limit the scope of the present invention.Its purpose only provides certain concepts in simplified form, with
This is as the preamble in greater detail discussed later.
The purpose of the present invention is to provide a kind of space debris prevention structure, safeguard structure provided by the invention is able to solve
Big stress present in existing space fragment protective structure is concentrated, and can not protect and cannot reach pair to space flight cabin comprehensively
In the requirement of shelter of the bigger fragment of diameter the technical issues of.
Technical solution of the invention:
A kind of space debris prevention structure is provided, which includes inner support layer, middle layer and external protection coating,
In, inner support layer has the cavity of both ends open for fixing the middle layer, inner support layer, for accommodating to protector；In
Interbed is arranged between inner support layer and external protection coating, and middle layer is at least made of honeycomb, and circumferentially setting exists honeycomb
Inner support layer outer surface, middle layer at least are used to absorb the energy of space junk；Circumferentially the outer of middle layer is stated in setting to external protection coating
Surface, the outer surface of external protection coating are also configured to the face of smoothly transitting, and external protection coating is for the space junk to be crushed.
Further, inner support layer is cylinder-like structure, and inner support layer is made of titanium alloy material.
Further, external protection coating is made of titanium alloy material or wave impedance gradient material is made.
Further, the outer surface of external protection coating is arc surface or continuous concave-convex transition shiny surface.
Further, middle layer further includes SiC fiber, is filled between the inner support layer and external protection coating except honeycomb
The region of structure.
Further, SiC fiber and inner support layer and external protection coating are mutually be bonded respectively；Honeycomb is with inner support layer and outside
Protective layer mutually welds respectively.
Further, honeycomb is negative stiffness honeycomb, with two groups of double coaxially arranged cellular units for one
Unit cell simultaneously carries out circumferential expand to form annular array structure along inner support layer outer surface.
Further, it for any one cellular unit, needs to meet between the apex height h and thickness t of cellular unit: 1.5
≤h/t≤6；The length l of cellular unit meets: 30mm≤l≤80mm.
Further, honeycomb is made of titanium alloy material.
Using above-mentioned technical proposal, have the cavity of both ends open to be used to accommodate wait protect by setting inner support layer
Part, middle layer honeycomb inner support layer outer surface is circumferentially set, the external protection coating for being crushed space junk is circumferentially set
It sets and states the outer surface of middle layer and the outer surface of external protection coating and be also configured to the face of smoothly transitting, one side above structure form can
To treat the protection that protector carries out enclosed, realize to the full protection of cabin, it is on the other hand above-mentioned to be successively circumferentially arranged
The big stress that each layer structure and the external protection coating with the face of smoothly transitting avoid safeguard structure is concentrated, and is realized and is eliminated boundary
Effect, keep structure stability and be able to bear the bigger shock loading of space junk, furthermore, in above-mentioned safeguard structure
On the basis of the excellent properties such as impact resistance load, additionally it is possible to realize the requirement of shelter for reaching the fragment bigger for diameter.The present invention
The hiperspace fragment protective structure that embodiment provides is Future Manned Space Flight, deep space exploration task and long-life satellite
Protection design provides a strong guarantee and technological reserve.
Detailed description of the invention
Included attached drawing is used to provide to be further understood from the embodiment of the present invention, and which constitute one of specification
Point, for illustrating the embodiment of the present invention, and come together to illustrate the principle of the present invention with verbal description.It should be evident that below
Attached drawing in description is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creation
Property labour under the premise of, be also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram according to space debris prevention structure provided in an embodiment of the present invention；
Fig. 2 is according to cellular unit structural schematic diagram provided in an embodiment of the present invention；
In above-mentioned attached drawing:
10, inner support layer；20, middle layer；21, honeycomb；22, SiC fiber；30, external protection coating.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Ground description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is right below
The description only actually of at least one exemplary embodiment be it is illustrative, never as to the present invention and its application or use
Any restrictions.Based on the embodiments of the present invention, those of ordinary skill in the art are without creative efforts
Every other embodiment obtained, shall fall within the protection scope of the present invention.
It should be noted that term used herein above is merely to describe specific embodiment, and be not intended to restricted root
According to the illustrative embodiments of the application.As used herein, unless the context clearly indicates otherwise, otherwise singular
Also it is intended to include plural form, additionally, it should be understood that, when in the present specification using term "comprising" and/or " packet
Include " when, indicate existing characteristics, step, operation, device, component and/or their combination.
Unless specifically stated otherwise, positioned opposite, the digital table of the component and step that otherwise illustrate in these embodiments
It is not limited the scope of the invention up to formula and numerical value.Simultaneously, it should be appreciated that for ease of description, each portion shown in attached drawing
The size divided not is to draw according to actual proportionate relationship.For technology, side known to person of ordinary skill in the relevant
Method and equipment may be not discussed in detail, but in the appropriate case, and technology, method and apparatus should be considered as authorizing specification
A part.In shown here and discussion all examples, any occurrence should be construed as merely illustratively, rather than
As limitation.Therefore, the other examples of exemplary embodiment can have different values.It should also be noted that similar label and word
Mother indicates similar terms in following attached drawing, therefore, once it is defined in a certain Xiang Yi attached drawing, then in subsequent attached drawing
It does not need that it is further discussed.
As background technique is previously mentioned, existing safeguard structure mostly uses the protecting screen structure type of single-layer or multi-layer,
Although this kind of safeguard structure realizes a degree of absorption dispersion space fragment, but there is also main problem below, a sides
Face is since four boundaries of this class formation are in free state, under space junk high speed impact, it will generate more answer
Power, the scattering on boundary cause big stress to be concentrated, so that the structural strength of this class formation reduces, can not maintain to stablize for a long time and make
With；On the other hand, it is confined to the structure type (plate) of this class formation, leads to that full protection can not be carried out to cabin；Furthermore this
The bullet cut off diameter that a little protective structure approach measure rests on grade, cannot reach the protection of the fragment bigger for diameter
It is required that.
The embodiment of the present invention is based on above-mentioned technical problem and provides a kind of space debris prevention structure, as shown in Figure 1, the protection
Structure includes inner support layer 10, middle layer 20 and external protection coating 30, wherein and inner support layer 10 is used to fix the middle layer 20,
It has the cavity for accommodating the both ends open to protector；The setting of middle layer 20 inner support layer 10 and external protection coating 30 it
Between, middle layer 20 is at least made of honeycomb 21, and the honeycomb 21 is circumferential to be arranged in 10 outer surface of inner support layer, middle layer
20 at least for absorbing the energy of space junk；The outer surface of middle layer 20, external protection coating 30 are stated in the circumferential setting of external protection coating 30
Outer surface be also configured to the face of smoothly transitting, external protection coating 30 is for the space junk to be crushed.
Using space debris prevention structure provided in an embodiment of the present invention, there is both ends open by setting inner support layer 10
Cavity with for accommodating, honeycomb 21 to protector such as cabin, middle layer 20 is circumferential to be arranged in 10 appearance of inner support layer
The outer surface of middle layer 20 and the appearance of external protection coating 30 are stated in face, the circumferential setting of the external protection coating 30 for being crushed space junk
Face is also configured to the face of smoothly transitting, and one side above structure form can carry out the protection of enclosed to cabin, realize to cabin
Full protection, on the other hand the above-mentioned each layer structure being successively circumferentially arranged and the external protection coating 30 with the face of smoothly transitting avoid
The big stress of safeguard structure is concentrated, and is realized and is eliminated boundary effect, keeps the stability of structure and be able to bear space
The bigger shock loading of fragment, furthermore, on the basis of the excellent properties such as the impact resistance load of above-mentioned safeguard structure, additionally it is possible to realize
Reach the requirement of shelter of the fragment bigger for diameter.
In the present embodiment, in order to which each layer structure of safeguard structure prevents cabin convenient for design and implementation and preferably
Shield, inner support layer 10 can configure interior cylindrical structure, and be made of titanium alloy material.It, will be interior using such configuration mode
Supporting layer 10 is configured to cylinder-like structure, it is seen that the inner support layer 10 is the hollow cylindrical structure of a both ends open, such
Structure is suitable for circumferential load impacting, and easy to form and be easy to implement the support to middle layer 20, in addition, selection inner support layer
10 be titanium alloy material, is on the one hand convenient for load transmission.On the other hand fragment kinetic energy can also be consumed again, realized more preferable to cabin
Ground protection.
In the present embodiment, the wall thickness of inner support layer 10 can be set to 2mm~3mm.
In the present embodiment, space junk is preferably crushed in order to realize, external protection coating 30 uses titanium alloy material
It is made or wave impedance gradient material is made, wherein the wave impedance gradient material is preferably wave impedance gradient Ti6Al4V polyamides
Amine fiber material, with abundant comminuting space fragment.
In the present embodiment, the outer surface of external protection coating 30 can be arc surface or continuous concave-convex transition shiny surface.Using
Such configuration mode configures arc surface or continuous concave-convex transition shiny surface for the outer surface of external protection coating 30, is different from existing
Plate structure (usually tool there are four side), which can eliminate boundary effect, and big stress is avoided to concentrate.
In above-described embodiment, in order to preferably be suitable for circumferential shock loading, external protection coating 30 is also configured as both ends open
Hollow cylinder structure, in the embodiment, as shown in Figure 1, the shape of typical safeguard structure is along the axial of safeguard structure
Section is an anchor ring.
As an embodiment of the present invention, in order to further ensure space junk is sufficiently crushed, configuration middle layer 20 is also
It may include SiC fiber 22, which is filled between the inner support layer 10 and external protection coating 30 except honeycomb 21
Region.Using such configuration mode, configuring middle layer 20 further includes SiC fiber 22, since 22 fiber of SiC fiber has very greatly
Intensity, can be further ensured that the space junk further progress not being crushed sufficiently is crushed, and by the honeycomb of same layer 21
Carry out energy absorption.
In the present embodiment, middle layer 20 is fixed between inner support layer 10 and external protection coating 30 in order to realize, wherein
SiC fiber 22 and inner support layer 10 and external protection coating 30 are mutually be bonded respectively；Honeycomb 21 and inner support layer 10 and external protection coating
30 mutually weld respectively, preferably progress spot welding connection.
As an embodiment of the present invention, above-mentioned honeycomb 21 is set as negative stiffness honeycomb, the negative stiffness bee
Nest structure with two groups of double coaxially arranged cellular units be a unit cell and along 10 outer surface of inner support layer carry out it is circumferential expand with
Form annular array structure.By such configuration mode, negative stiffness honeycomb, negative stiffness honeycomb are set by honeycomb 21
Structure not only has very strong energy-absorbing function, additionally it is possible to provide higher initial stiffness and compression strength, as shown in Figs. 1-2, bear
Rigidity honeycomb is existing a kind of honeycomb in the prior art, and in this not go into detail, and the embodiment of the present invention is double with two groups
Coaxially arranged cellular unit is a unit cell and carries out circumferential expand to form annular array knot along 10 outer surface of inner support layer
Structure, the negative stiffness honeycomb of the annular array structure, which can be realized, preferably absorbs the kinetic energy for absorbing space junk.
In the present embodiment, as shown in Fig. 2, in order to further realize preferably energy-absorbing effect, for any one cellular unit,
It needs to meet between the apex height h and thickness t of cellular unit: 1.5≤ht≤6；The length l of cellular unit meets: 30mm≤l≤
80mm。
In the present embodiment, above-mentioned honeycomb 21 is also made of titanium alloy material.In addition, the titanium alloy of above-mentioned meaning
Material is both preferably Titanium alloy TA15.
It is unidirectionally in the embodiment of the present invention, between each layer of safeguard structure, connects, progressive relationship, shock loading --
External protection coating 30-- negative stiffness honeycomb -- inner support layer 10-- waits for protector, is to depend on each other for existence between three, acts synergistically, and realizes
Utmostly to carry out broken and energy absorption to space junk, reach the requirement of shelter of the fragment bigger for diameter, and
It avoids big stress to concentrate, the stability of structure can be maintained for a long time, be Future Manned Space Flight, deep space exploration task and long-life
The protection design of satellite provides a strong guarantee and technological reserve.
For ease of description, spatially relative term can be used herein, as " ... on ", " ... top ",
" ... upper surface ", " above " etc., for describing such as a device shown in the figure or feature and other devices or spy
The spatial relation of sign.It should be understood that spatially relative term is intended to comprising the orientation in addition to device described in figure
Except different direction in use or operation.For example, being described as if the device in attached drawing is squeezed " in other devices
It will be positioned as " under other devices or construction after part or construction top " or the device of " on other devices or construction "
Side " or " under other devices or construction ".Thus, exemplary term " ... top " may include " ... top " and
" in ... lower section " two kinds of orientation.The device can also be positioned with other different modes and (is rotated by 90 ° or in other orientation), and
And respective explanations are made to the opposite description in space used herein above.
In addition, it should be noted that, limiting components using the words such as " first ", " second ", it is only for be convenient for
Corresponding components are distinguished, do not have Stated otherwise such as, there is no particular meanings for above-mentioned word, therefore should not be understood as to this
The limitation of invention protection scope.
These are only the preferred embodiment of the present invention, is not intended to restrict the invention, for those skilled in the art
For member, the invention may be variously modified and varied.All within the spirits and principles of the present invention, it is made it is any modification,
Equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Unspecified part of the present invention is known to the skilled person technology.
Claims (9)
1. a kind of space debris prevention structure, the safeguard structure includes inner support layer, middle layer and external protection coating, and feature exists
In the inner support layer has the cavity of both ends open for fixing the middle layer, the inner support layer, and the cavity is used for
It accommodates to protector；The middle layer is arranged between the inner support layer and external protection coating, and the middle layer is at least by honeycomb
Structure composition, the honeycomb are circumferentially arranged in the inner support layer outer surface, and the middle layer is at least used to absorb space
The energy of fragment；The outer surface of the middle layer is circumferentially arranged in the external protection coating, and the outer surface of the external protection coating is also set
It is set to the face of smoothly transitting, the external protection coating is for the space junk to be crushed.
2. a kind of space debris prevention structure according to claim 1, it is characterised in that: the inner support layer is cylindrical shape
Structure, the inner support layer are made of titanium alloy material.
3. a kind of space debris prevention structure according to claim 1, it is characterised in that: the external protection coating is closed using titanium
Golden material is made or wave impedance gradient material is made.
4. a kind of space debris prevention structure according to claim 1, it is characterised in that: the outer surface of the external protection coating
For arc surface or continuous concave-convex transition shiny surface.
5. a kind of space debris prevention structure according to claim 1, it is characterised in that: the middle layer further includes SiC
Fiber, the SiC fiber are filled in the region that the honeycomb is removed between the inner support layer and external protection coating.
6. a kind of space debris prevention structure according to claim 5, it is characterised in that: the SiC fiber with it is described interior
Supporting layer is mutually bonded respectively with the external protection coating；The honeycomb distinguishes phase with the inner support layer and the external protection coating
Welding.
7. a kind of space debris prevention structure described in -6 according to claim 1, it is characterised in that: the honeycomb is negative just
Honeycomb is spent, the negative stiffness honeycomb is with two groups of double coaxially arranged cellular units for a unit cell and along inner support layer
Outer surface carries out circumferential expand to form annular array structure.
8. a kind of space debris prevention structure according to claim 7, it is characterised in that: in the unit cell, for any
One cellular unit needs to meet: 1.5≤h/t≤6 between the apex height h and thickness t of the cellular unit；The cellular unit
Length l meet: 30mm≤l≤80mm.
9. a kind of space debris prevention structure according to claim 1, it is characterised in that: the honeycomb is closed using titanium
Golden material is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811257133.1A CN110155375B (en) | 2018-10-26 | 2018-10-26 | Space debris protective structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811257133.1A CN110155375B (en) | 2018-10-26 | 2018-10-26 | Space debris protective structure |
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| CN110155375A true CN110155375A (en) | 2019-08-23 |
| CN110155375B CN110155375B (en) | 2020-08-21 |
Family
ID=67645267
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811257133.1A Active CN110155375B (en) | 2018-10-26 | 2018-10-26 | Space debris protective structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110985581A (en) * | 2019-12-31 | 2020-04-10 | 北京机电工程研究所 | Repulsion type magnetic force negative stiffness honeycomb structure |
| CN111645884A (en) * | 2020-06-17 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
| CN111998028A (en) * | 2020-08-11 | 2020-11-27 | 北京机电工程研究所 | Damper for vibration suppression of spacecraft structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110985581A (en) * | 2019-12-31 | 2020-04-10 | 北京机电工程研究所 | Repulsion type magnetic force negative stiffness honeycomb structure |
| CN110985581B (en) * | 2019-12-31 | 2021-06-18 | 北京机电工程研究所 | Repulsion type magnetic force negative stiffness honeycomb structure |
| CN111645884A (en) * | 2020-06-17 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
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| CN111998028A (en) * | 2020-08-11 | 2020-11-27 | 北京机电工程研究所 | Damper for vibration suppression of spacecraft structure |
| CN111998028B (en) * | 2020-08-11 | 2022-04-12 | 北京机电工程研究所 | Damper for vibration suppression of spacecraft structure |
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| Publication number | Publication date |
|---|---|
| CN110155375B (en) | 2020-08-21 |
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