CN100557374C - Separable structure material - Google Patents
Separable structure material Download PDFInfo
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- CN100557374C CN100557374C CNB2006800102051A CN200680010205A CN100557374C CN 100557374 C CN100557374 C CN 100557374C CN B2006800102051 A CNB2006800102051 A CN B2006800102051A CN 200680010205 A CN200680010205 A CN 200680010205A CN 100557374 C CN100557374 C CN 100557374C
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- composite
- overlay region
- pyrotechnic material
- layer
- composite layer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
- F42B15/38—Ring-shaped explosive elements for the separation of rocket parts
Abstract
A kind of separable structure (10) comprises the composite that is separated or disconnected by active pyrotechnic material.According to an embodiment, described structure comprises a pair of composite lamainated structure part (12,14), and each composite lamainated structure partly includes a plurality of composite layers (16,18).Described part all extends into overlay region (20), and the composite bed of described two structure divisions can be arranged alternately in described overlay region, and is overlapped.Active material (24) also is arranged in the described overlay region, for example in the layer (29) between paired composite layer.Described active material be can light, the described pyrotechnic material of described overlay region and the matrix or the resin material of described composite layer are positioned at destruction.This makes described structure separate along the defiber that is positioned at described overlay region.Described separation just can take place in the fiber that need not to disconnect described composite.
Description
The application requires to enjoy the priority of the U.S. Provisional Patent Application of submitting on April 8th, 2,005 60/669695, and the full content of above-mentioned application is attached to herein for your guidance.
Technical field
The present invention relates to separable, can disconnect or the general field of destructible structural material.
Background technology
The inter-stage body that is used for multiple-stage missile is to be made by the light metal of for example aluminium always.The aluminum body is for example to utilize that the pyrotechnical of Linear Shaped Charge disconnects always.Such aluminum inter-stage body has brought significant weight unfavorable, thus with lighter material for example composite to substitute will be favourable.Yet composite has the fiber that is difficult to disconnect, so that needs to use bigger Linear Shaped Charge.This has reduced to change into the weight advantage of composite, and has increased the detonate value of the shock and vibration that cause of Linear Shaped Charge.Other alternative plans of having attempted are for example used to disconnect material in bigger composite construction among a small circle, and this causes more needing to rely on securing member described structure is kept together.Securing member uses increase can the increase system complexity, reduce the globality of described structure simultaneously.
In sum, be appreciated that and make improvement to this technical field.
Summary of the invention
According to an aspect of the present invention, using active pyrotechnic material to make to the resin evaporation of small part composite or with other form destroys, thereby even under the situation that is not having substantive disconnection or destruction composite fiber, also can realize separation, disconnection or the decomposition basically of described material.
According to a further aspect in the invention, a kind of separable structure comprises a pair of part with a plurality of composite layers.Composite layer is overlapping and can interlock in the overlay region.Active pyrotechnic material is set in place in the overlay region between at least some layers.Pyrotechnic material is connected with igniter.The resin that makes in the composite layer of lighting of pyrotechnic material evaporates, destroys or damage its integrality, thereby composite layer is separated from each other in the overlay region, so that separate the described part of described structure.
According to another aspect of the invention, a kind of method that is used to separate separable structure comprises and lights the active pyrotechnic material that is arranged in described structure, so that the composite layer of described structure is separated from each other.
In accordance with a further aspect of the present invention, composite has bearing fiber and activated pyrotechnic fiber.The activated pyrotechnic fiber can be lighted, so that the resin material to the described composite of small part evaporates, perhaps destroys its integrality with other form.
According to a further aspect in the invention, a kind of separable laminated construction comprises: the composite that is made of a plurality of composite layers; Be arranged on the active pyrotechnic material between the composite layer; And be used to light active laminated material so that the igniter that the part of described laminated construction is separated along defiber.
In accordance with a further aspect of the present invention, a kind of separable laminated construction comprises: the composite that is made of a plurality of composite layers; Be arranged on the active pyrotechnic material between a pair of composite layer; Thereby and be used to light the igniter that part that active pyrotechnic material makes described laminated construction is separated along defiber.Described defiber is positioned at the overlapping therein overlay region of composite layer.Active pyrotechnic material is arranged to the fiber that integrality by the matrix material that reduces composite need not to disconnect composite layer separates the composite in the overlay region.
According to a further aspect in the invention, a kind of method that is used to make the structure separation comprises: dispose described structure, so that a plurality of composite layers of described structure are overlapping in the overlay region of described structure; So that beyond each composite layer extends described overlay region in the both sides of first side of described overlay region or second side rather than described overlay region; And the active pyrotechnic material that makes described structure is positioned at described overlay region; And light described active material, separate with the composite layer that extends into described overlay region second side so that extend into the composite layer of described overlay region first side.
In accordance with a further aspect of the present invention, a kind of sandwich comprises: matrix material; Be positioned at the active pyrotechnic material of described matrix material; And the bearing fiber that is positioned at described matrix material.Described bearing fiber is bigger than described active pyrotechnic material fibre strength.
In order to realize above-mentioned and relevant purpose, the present invention includes detailed description after this and claim in the feature that particularly points out.The following description and accompanying drawing have at length been set forth exemplary embodiments more of the present invention.Yet these embodiment only represent several in the variety of way that can adopt the principle of the invention.By below in conjunction with the accompanying drawing detailed description of the invention, other purposes of the present invention, advantage and new feature are apparent.
Description of drawings
The following drawings, not necessarily pro rata:
Fig. 1 is the cross-sectional view according to a separable structure part of the present invention;
Fig. 2 shows detonating of separable structure shown in Figure 1 and separates;
Fig. 3 is the cross-sectional view of structure shown in Figure 1, wherein shows being connected of described structure and other inseparable structures;
Fig. 4 shows at a place or the guided missile of structure is as depicted in figs. 1 and 2 used in many places;
Figure 5 shows that cross-sectional view according to the first optional embodiment of separable structure of the present invention;
Fig. 6 shows the possible application of another one of separable structure illustrated in figures 1 and 2, is used to disconnect the jet vane of guided missile or rocket engine;
Fig. 7 be schematically illustrated according to separable composite of the present invention the layer plane;
Fig. 8 is to use the oblique view of an embodiment of the structure that material layer shown in Figure 7 makes; And
Figure 9 shows that another embodiment of the present invention can decompose the plane of composite.
The specific embodiment
A kind of separable structure that maybe can disconnect comprises the composite that is separated or disconnected by active pyrotechnic material.According to an embodiment, described structure comprises a pair of composite lamainated structure part, and each composite lamainated structure partly comprises a plurality of composite layers.Each composite lamainated structure partly extends in the overlay region, and the composite bed of described two structure divisions can be crisscross arranged in described overlay region, and is overlapped.Active material also is arranged in this overlay region, for example described structure division each between the composite layer the layer in.Described active material can be lighted, and is positioned at the described pyrotechnic material of overlay region and the matrix or the resin material of composite layer with destruction.This makes described structure disconnect or separation along the defiber in the overlay region.Need not to disconnect any fiber of composite layer, described disconnection or separation just can take place.Therefore, can adopt the explosive material of relatively small amount to separate high-intensity composite construction.The explosive force required with disconnecting composite fiber is compared, and this a spot of explosive has reduced the shock and vibration load that described structure is caused.Described disconnect or separable structure needing in the various application of isolating construction part can be used for.Example comprises the separation of guided missile level and the separation of guided missile nose-cone.
With reference to Fig. 1, separable structure 10 comprises the first composite structure part 12 and the second composite structure part 14.Composite structure part 12 and 14 constitutes by a plurality of composite layers, and the first composite structure part 12 comprises that first composite layer, 16, the second composite structure parts 14 comprise second composite layer 18. Composite layer 16 and 18 includes the fiber that combines by matrix or resin.Each first composite layer 16 and second composite layer 18 have overlapped ends 26 and 28 separately respectively, and overlapped ends 26 and 28 is overlapping and staggered in overlay region 20.
The active pyrotechnic material 24 that is positioned at overlay region 20 combines the composite layer 16 and 18 of overlay region 20.Active pyrotechnic material 24 can comprise and is arranged on a plurality of discrete active pyrotechnic material layer between adjacent composite layer 16 and 18 or fills up 29.Active pyrotechnic material layer 29 is connected with electric igniter 30 by ignition signal line 34.Ignition signal line 34 be arranged in one or more active pyrotechnic material layers 29 igniter 36 for example the line bridging connect.In case send appropriate signals from electric igniter 30, pyrotechnic reaction just is activated in active pyrotechnic material 24.
When the signal of telecommunication, electric current or pulse by ignition signal line 34 from electric igniter 30 when igniter 36 sends, in the active pyrotechnic material 24 of active pyrotechnic material layer 29, will light a fire.This pyrotechnic reaction is the blast that produces heat.The heat that blast produced of active pyrotechnic material 24 makes for example resin evaporation of matrix material in composite layer 16 and 18.This has just destroyed the mechanical connection between the lap (end) 26 and 28 of in overlay region 20 conductive composites layer 16 and 18.The result is that conductive composites structure division 12 separates along the defiber 40 that is positioned at overlay region 20 with 14.This separation is presented among Fig. 2.It is emphasized that taking place between composite structure part 12 and 14 to separate is because the resin of staggered composite layer 16 and 18 mechanical connections is damaged.Separation is not to be that disconnection owing to the fiber of conductive composites layer 16 and 18 takes place, and follows disconnection although be appreciated that some of fiber that the reaction of active pyrotechnic material 24 can relate to composite layer 16 and 18.
Because separable structure 10 is that by removing to composite layer 16 and 18 overlapping 26 and 28 provides the resin of integrality to realize along the separation of defiber 40, rather than realize by the fiber that disconnects composite layer, therefore disconnect composite fiber so that structure disconnects or the system that separates compares with relying on, can use more a spot of pyrotechnic material.The 10 necessary explosive force minimizings of separation separable structure mean can use more a spot of active material.And, still compare with realize the situation of separating by the fiber that disconnects composite, less by impulsive force and vibration force that active pyrotechnic material 24 blasts cause.Be appreciated that for prevent to can with the precise part of separable structure 10 mechanical connections, for example can be arranged on the optical device in the guided missile that comprises described separable structure 10, cause possible infringement, need reduce shock and vibration load.
In addition, be appreciated that, in described separable structure 10, the power of active pyrotechnic material layer 29 is advantageously not only towards the direction of the described structural outer external diameter direction of cylindrical-shaped structure (for example towards) effect, and inwardly towards the direction of the described inside configuration internal diameter direction of cylindrical-shaped structure (for example towards) effect.This can effectively utilize the energy that is produced in the reaction of active pyrotechnic material 24, simultaneously no longer need be in order to the internal structure of explosive force protection, for example steel blast ring to be provided.
The favourable part of another of described separable structure 10 is, compares with the fragment that is produced that separates of metal structure or continuous composite construction, and the quantity of the fragment that described separation forms or infringement potentiality are littler.The destruction of matrix or resin can cause the evaporation and/or the pulverizing of material, and in contrast, the blast of other types structure divides defection to cause producing heavier metal or complex fiber material bulk.
Fig. 2 and Fig. 3 show the separable structure 10 in conjunction with the part of conduct level seperator structure 41, and this grade seperator structure 41 is used for a pair of level 42 and 44 of break up missile 50.The first composite structure part 12 is connected with the first order 42 by the sunk screw 52 that is positioned at first hole 53.Similarly, the second composite structure part 14 is connected with the second level 44 by a series of sunk screws 54 that are positioned at second hole 55.Separable structure 10 advantageously need not to be connected to level 42 and 44 by any extra part that is used for the bigger structure of intensity (for example total length composite log or aluminum inter-stage section).With comprise the inter-stage section that is used for segregative weakened part or comprise that for example being used to install the inter-stage section of the supernumerary structure of the explosive of gentle explosive charge compares that the part that is used to install that separable structure 10 uses still less.Separable structure 10 provides intensity big, the in light weight separated structures that but is easy to, and the explosive that it can enough relatively small amounts also separates with relatively little shock and vibration.Advantageously, the active pyrotechnic material 24 of separable structure 10 is combined in the structure in the overlay region 20 integratedly.The energy that this helps effectively utilizing explosive and is discharged advantageously need not to re-use extra member simultaneously and comes confining blast power.
Owing in described separable structure, except the hole 53 and 55 that is used for screw 52 and 54, do not need extra hole, therefore kept the integrality of the composite of separable structure 10 to greatest extent.Other form that separable structure is assembled in the extra hole that is used to install or be used to will further weaken composite or the other materials of making this structure.Utilize separable structure shown in Figure 1 to avoid this further weakening.More hole also can reduce the integral rigidity of body, thereby guidance control is had a negative impact.
Be appreciated that the screw that passes the hole for use is connected separable structure 10 with other structure members, also have many alternative modes.Other alternative examples comprise V-belt anchor clamps, suitable screw thread, belt plug-in unit and open flume type interface.
By making composite layer 16 and 18 only overlapping in overlay region 20, realized the easily separated property of separable structure 10.Be appreciated that for fear of using extra active pyrotechnic material 24 weight of avoiding using extra composite to bring is unfavorable, and/or make between composite structure part 12 and 14 and separate, advantageously limit the lap between composite layer 16 and 18.Yet more broadly, be appreciated that separable structure 10 materials can be configured to admit of overlapping on a large scale between composite structure part 12 and 14.Advantageously, the first composite structure part 12 does not have substantive part to extend to second bonding pad 58 basically, adopts second screw 54 that separable structure 10 is connected with the second level 44 in second bonding pad 58.Similarly, advantageously, the second composite structure part 14 does not have substantive part to extend to first bonding pad 56 basically, adopts sunk screw 52 that separable structure 10 is connected with the first order 42 in first bonding pad 56.In other words, advantageously, separable structure 10 is configured to not have basically composite fiber to extend to the bottom (being connected with the first order 42 at this separable structure 10) of separable structure 10 from the top (being connected with the second level 44 at this separable structure 10) of separable structure 10.By making arbitrary specific composite fiber only partly pass separable structure 10, along defiber 40 separation or disconnection separable structure 10 time, need not to disconnect a large amount of composite fibers.Again in other words, the second composite structure part 14 does not extend into first lateral areas 62, this first lateral areas 62 be positioned at overlay region 20 outer and along first direction 64 away from defiber 40.The first composite structure part 12 does not extend into second lateral areas 68, this second lateral areas 68 be positioned at overlay region 20 outer and along second direction 66 away from defiber 40.Direction 64 and 66 is opposite each other basically.
Composite can be to use any one of various materials of the successive substrates of being strengthened by the fiber that is fit to.Matrix material can be any one of various suitable materials, for example thermosetting or thermal soften plastic or resin.The example of the resin that is fit to comprises epoxy resin, cyanate ester resin (CE), polyimide resin (PI) and bimaleimide resin (BMI)." resin " speech repeatedly uses at this paper, basically in order to represent this matrix material.Strengthening material can be a carbon fibre material.Alternatively, also can use other material that is fit to, for example suitable polymer fiber or glass fibre.
Active material can be any one of various materials that produces suitable pyrotechnic reaction when lighting.For example, active material can be the gel castings, Bi
2O
3/ Mg.
Fig. 4 shows each position that separable structure 10 (or embodiment of other separable structure disclosed herein) can adopt on guided missile 50.Separable structure 10 can be used to make the first order 42 of guided missile to separate with the second level 44 along defiber 80.Alternatively or extraly, separable structure 10 can be used for separating and throwing the part of putting nose-cone 84.For example, separable structure 10 can use along the defiber between nose- cone lobe 88 and 90 86.Separable structure also can use along the line between nose-cone 84 and body 96 94.
Fig. 5 shows the optional embodiment of separable structure 10, and the layout in overlay region 20 is slightly different.The Fig. 1 of being different from part embodiment illustrated in fig. 5 is that Fig. 5 embodiment is arranged on each overlapping ends 26 of composite layer 16 or 18 and 28 both sides (first type surface) with active pyrotechnic material layer 29.(side (first type surface) that active material layer 29 only is arranged on each composite overlapping ends 26 and 28 embodiment illustrated in fig. 1.Therefore, in the embodiment shown in fig. 1, per 3 one deck only to be arranged in layer by layer be one of active pyrotechnic material layer 29.)
In layout shown in Figure 5, active pyrotechnic material layer 29 is arranged on the both sides of each composite end 26 or 28, like this, is separating composite structure part 12 and better performance can arranged at 14 o'clock.On the other hand, layout shown in Figure 1 can increase the intensity of separable structure 10 materials.
Fig. 6 shows another possible application of the above separable structure, is used to separate and/or destroys jet vane in order to the control guided missile.Separable structure 10, or other structure embodiment as herein described can be used as all or part of of one group of jet vane 100.Active structure can be used for disconnecting simultaneously all jet vanes 100.This is not the problem that can produce when side by side separating with guided missile basically with regard to having eliminated in jet vane.Some but not all the existence of jet vanes can cause the unstable flight of guided missile.Can disconnect or separable structure 10 can be arranged in the jet vane 100 or spreads all over the optional position of the various appropriate locations of jet vane 100.Can utilize electric igniter to ignite active material in all jet vanes 100 simultaneously.
Fig. 7 shows also to can be used as and can destroy or the composite of lighting 200 of detachable material.Composite 200 comprises bearing fiber 202 and active material fiber 204.At least some bearing fibers 202 are along main loading direction 206 orientations.Active material fiber 204 (and some bearing fibers 202 of possibility) is along inferior loading direction 208 orientations that are basically perpendicular to main loading direction 206. Fiber 202 and 204 is surrounded by resin or matrix material 210.Active material fiber 204 can collect bunch together, thereby forms the Disengagement zone 214 in the composite 200.With with the above similar mode, active material fiber 204 can be connected with electric igniter, and can utilize suitable current detonation.Therefore, the active pyrotechnic material fiber part that can be used as composite is arranged in the composite layer.Active material fiber 204 preferably with bear less load towards setting.Composite construction can be made of multilayer materials 200, described layer towards being such, so that active material preferably is provided with away from the position of bearing the load on main loading direction 206, and the active material fiber 204 that makes each layer is overlapping substantially or be positioned at such zone, in this zone, the active material fiber can be used to disconnect, separate, destroy or weaken the part of structure synergistically.
Bearing fiber can be a carbon fiber, and resin 210 can be the above fiber that is fit to any one.Active material fiber 204 can be the fiber of being made by for example above-described those active materials of material that are fit to.
Fig. 8 shows the separable structure 220 that is made of multilayer materials 200.Separable structure 220 is cylindric, has to be orientated the active material fiber 204 that bears the circumferential stress that is applied on the separable structure 220.Usually, to the requirement of the material that bears circumferential stress not as requirement harshness to the material that bears axial stress, tensile stress or compression stress.Therefore, although active material fiber 204 intensity can be weaker than bearing fiber 202, active material fiber 204 still can satisfy and is used to bear the requirement that is applied to the circumferential stress on the separable structure 220.
Fig. 9 shows the modification of the composite 200 that can light, and wherein all fibres along time loading direction 208 all is an active material fiber 204.Bearing fiber 202 all is provided with along main loading direction 206.In case be appreciated that 204 burnings of active material fiber, described material 200 can decompose fully.
The composite 200 that can light has useful characteristic, and promptly active material and resin 210 are provided with in intimate contact, and in fact spreads all over composite 200 ground and scatter.This helps the more efficiently in whole or in part disconnection or the destruction of composite 200.The actual disconnection of composite 200 or destroy can relate to and utilize active material so that weaken or disconnect at least some bearing fibers 202.Alternatively or extraly, be appreciated that, the evaporation or the destruction of the resin material of the encirclement active material 204 of lighting and therefore taking place of active material fiber 204, can weaken the integrality of composite 200 fully, make it decompose, destroy, disconnect, separate or the structural failures of other form thereby be applied to load on the material.
Be configured with a lot of possible modification shown in Fig. 7-9.Can be with active material fiber and bearing fiber along main loading direction and time two-way setting of loading direction, thus the separability or the destructibility of bearer properties of realizing ideal and final material.
The above be separable, can disconnect some examples that maybe can decompose composite.Be appreciated that this composite can be various structures for various uses.Other possible application comprise, as self-propelled weapon or the guided missile part of cruise missile for example, are used for separating or destroying parts, for example are used for access doors, wing door or cover cap that multiple weapon will be dished out awing.
Although the invention has been described and description at specific preferred embodiment, those skilled in the art are reading and are understanding on the basis of specification and accompanying drawing, and it is conspicuous making the substitutions and modifications that are equal to.Especially, about the various functions that realize by the above member (parts, assembly, equipment, form etc.), unless otherwise noted, the term (comprising " device " mentioned) that is used to describe these members is intended to corresponding to any member of realizing described member specific function (that is to say functional equivalent), even structurally be not equal to disclosed structure in order to the function that realizes exemplary embodiment of the present described herein.In addition, although above special characteristic of the present invention is to describe the only one or more of embodiment and describe at some, but this feature can combine with one or more other features of other embodiment, and this is that need and useful for any that provide or specific application.
Claims (12)
1, a kind of separable structure of lamination comprises:
Composite by a plurality of composite layers (16,18) formation;
Be arranged on the active pyrotechnic material (24) between the described composite layer; And
Igniter is used to light described active pyrotechnic material, thereby the part of described separable structure is separated along defiber (40);
Wherein said composite comprises first and second composite structures parts (12,14);
Described first and second composite structures part comprises a plurality of continuous first and second composite layers (16,18) respectively;
The end of described first and second composite layers (26,28) is only overlapping in overlay region (20); And
Wherein said active pyrotechnic material is attached in the described separable structure in described overlay region.
2, separable structure as claimed in claim 1 is characterized in that, described first composite layer extends away from described overlay region along first direction (64);
Described second composite layer extends away from described overlay region along the second direction (66) that is different from described first direction.
3, separable structure as claimed in claim 1 or 2 is characterized in that, described defiber is positioned at described overlay region.
4, separable structure as claimed in claim 2 is characterized in that, described first direction and described second direction are opposite each other basically.
5, separable structure as claimed in claim 2, it is characterized in that, described active pyrotechnic material comprises active pyrotechnic material layer (29), and it is positioned at described overlay region, and between one of them first composite layer and one of them second composite layer of being adjacent.
6, separable structure as claimed in claim 5 is characterized in that, described active pyrotechnic material comprises other active pyrotechnic material layer, and each other active pyrotechnic material layer is between corresponding first composite layer and second composite layer.
7, separable structure as claimed in claim 2 is characterized in that, has the hole (53,55) of group separately respectively in the described composite structure part, and described hole is positioned at outside the described overlay region, is used for being connected with each structural elements.
8, separable structure as claimed in claim 1 is characterized in that, described separable structure is that the level of guided missile (50) is separated the part of structure (41).
9, separable structure as claimed in claim 1 is characterized in that, described separable structure is the part of guided missile nose-cone (84).
10, a kind of method that structure is separated, described method comprises:
Described structure is configured to,
Make that a plurality of composite layers (16,18) of described structure are overlapping in the overlay region (20) of described structure;
Make each composite layer extend beyond outside the described overlay region in the both sides of first side of described overlay region or second side rather than described overlay region; And
Make the active pyrotechnic material (24) of described structure in described overlay region is attached to described structure; And
Light described active pyrotechnic material, separate with the composite layer that extends beyond described overlay region second side so that extend beyond the composite layer of described overlay region first side.
11, method as claimed in claim 10, it is characterized in that, described active pyrotechnic material comprises active pyrotechnic material layer (29), and it is positioned at described overlay region, and between one of them first composite layer and one of them second composite layer of being adjacent.
As claim 10 or 11 described methods, it is characterized in that 12, the matrix material that makes in the composite layer of lighting of described active pyrotechnic material evaporates.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US66969505P | 2005-04-08 | 2005-04-08 | |
| US60/669,695 | 2005-04-08 | ||
| US11/190,297 | 2005-07-27 |
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| CN101151503A CN101151503A (en) | 2008-03-26 |
| CN100557374C true CN100557374C (en) | 2009-11-04 |
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| CNB2006800102051A Expired - Fee Related CN100557374C (en) | 2005-04-08 | 2006-03-22 | Separable structure material |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101995192B (en) * | 2010-08-24 | 2013-07-17 | 湖北航天技术研究院总体设计所 | Head-body separation device with guide function |
| CN102700715A (en) * | 2012-06-12 | 2012-10-03 | 河南师范大学 | Quick disconnection device for escape |
| CN114184097A (en) * | 2021-12-01 | 2022-03-15 | 上海航天设备制造总厂有限公司 | Protective clothing and protective method for large-diameter rocket body railway transportation |
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| US5170004A (en) * | 1991-08-05 | 1992-12-08 | Teledyne Industries, Inc. | Hydraulic severance shaped explosive |
| CN1089225A (en) * | 1992-11-02 | 1994-07-13 | 奥比托科学公司 | Frangible joint separation system |
| US5372071A (en) * | 1993-07-13 | 1994-12-13 | Tracor, Inc. | Thrusting separation system |
| US5567535A (en) * | 1992-11-18 | 1996-10-22 | Mcdonnell Douglas Corporation | Fiber/metal laminate splice |
| US5993929A (en) * | 1996-07-04 | 1999-11-30 | Dornier Gmbh | Carbon fiber reinforced separating laminate |
| US6148729A (en) * | 1998-04-27 | 2000-11-21 | Alliant Techsystems Inc. | Missile severance device |
| CN1314842A (en) * | 1998-10-12 | 2001-09-26 | 日东纺绩株式会社 | Reinforcing fiber base for composite material |
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2006
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5170004A (en) * | 1991-08-05 | 1992-12-08 | Teledyne Industries, Inc. | Hydraulic severance shaped explosive |
| CN1089225A (en) * | 1992-11-02 | 1994-07-13 | 奥比托科学公司 | Frangible joint separation system |
| US5567535A (en) * | 1992-11-18 | 1996-10-22 | Mcdonnell Douglas Corporation | Fiber/metal laminate splice |
| US5372071A (en) * | 1993-07-13 | 1994-12-13 | Tracor, Inc. | Thrusting separation system |
| US5993929A (en) * | 1996-07-04 | 1999-11-30 | Dornier Gmbh | Carbon fiber reinforced separating laminate |
| US6148729A (en) * | 1998-04-27 | 2000-11-21 | Alliant Techsystems Inc. | Missile severance device |
| CN1314842A (en) * | 1998-10-12 | 2001-09-26 | 日东纺绩株式会社 | Reinforcing fiber base for composite material |
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| CN101151503A (en) | 2008-03-26 |
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