CN104833277A - Cutting device for missile stage separation - Google Patents
Cutting device for missile stage separation Download PDFInfo
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- CN104833277A CN104833277A CN201510209869.1A CN201510209869A CN104833277A CN 104833277 A CN104833277 A CN 104833277A CN 201510209869 A CN201510209869 A CN 201510209869A CN 104833277 A CN104833277 A CN 104833277A
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- initiator
- flexible linear
- shaped charge
- protective cover
- missile
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a cutting device for missile stage separation. The cutting device comprises a shield (1), a rubber shield (2), a cutting rope (3) and exploders (4); the inner edge, which is in contact with the rubber shield (2), of the cutting rope (3) is of a U-shaped structure, the outer edge of the cutting rope (3) is of a V-shaped structure, the opening of which is outward, the two structures are closed to form an annular closed cavity, and explosive is loaded in the cavity; the shield (1) is in contact with the rubber shield (2) to wrap the rubber shield (2) and the cutting rope (3); the inner edge of the shield (1) is provided with four grooves (11), which are evenly distributed at the interval of 90 degrees, and a mounting hole (12) which is connected with the cavity is formed in each groove (11) in order to mount and fix one of the exploders (4); detonating cables (5) are connected with detonation signal cables (8) through steering engine plug connectors, so that a signal can be transmitted to detonate the cables. The cutting device has the advantages of stable connection, high detonation synchronism, low destructiveness and full cutting when being used for missile stage separation.
Description
Technical field
The invention discloses a kind of Stage Separation of Missile cutter sweep, belong to aviation machine technical field.
Background technology
For guided missile system, in order to effective carrier is transmitted into predetermined target, need the level completing predetermined work to carry out unlocking and being separated with cabin section, it is separated releasing process and is directly connected to the success or failure that guided missile completes aerial mission.Therefore, the stage separation device of guided missile is the critical component of guided missile.The stage separation device of guided missile will complete two kinds of different functions when real work.To guarantee that two separating components connect reliably before separation; When being separated, ensure that two separating components are separated reliably, and will guarantee in separation process or after being separated, the harm of the continuation of the journey level normal flight that do not have an impact.Thus, for Stage Separation of Missile, select a kind of suitable separator to be vital, following requirement must be reached to the design of guided missile inter-stage firer separator:
(1) connect before load bearing requirements is separated and ensure that guided missile body is connected reliably with separated parts, accurate positioning.
(2) reliable separation claimed apparatus should make separated part and guided missile body rapidly, accurately and reliably unlock and be separated, and must ensure to unlock and the reliability be separated.
(3) be separated impact require to require in separation process to impact guided missile body, disturbance is little, do not damage guided missile body.
(4) seal request device will ensure after being separated that its body contains the not contaminated impact guidance of infrared guidance window.
(5) maintainability claimed apparatus should simply, motion flexibly, be easy to adjustment, working service is convenient.
Current Stage Separation of Missile cutting mode mainly divides two kinds, i.e. point type separator and linear separation device.Point type separator includes the assemblies such as blasting bolt, release screw bolt, separation nut, is characterized in that separated body was exactly two-part structure originally, connects together by pieces resolution element, and when detachment is desired, resolution element unlocks, thus removes connection.Point type separator is mainly updated with perfect on the basis of blasting bolt, early stage blasting bolt, structure is simple, connect reliable, but separation is impacted comparatively large, often has fragment and pollutes generation, along with the appearance of release screw bolt, separation nut and bandage type separator, taken on a new look further to its attachment force and pollution plot aspect, but its structure is complicated further, assembly difficulty strengthens.Linear separation device comprises flexible linear-shaped charge rope, gasbag-type linear-shaped charge, expansion tube etc.The feature of line formula separator is separated body was continuous and complete cabin body originally, was cut to two parts with the line formula separator be arranged on parting surface.This kind of separator has flexible linear-shaped charge rope, gasbag-type linear-shaped charge, expansion tube etc.The advantages such as line formula separator typical flexible linear-shaped charge rigging has that structure is simple, good reliability, separation are rapid, but also there is obvious shortcoming:
(1) instant of detonation damage ratio is more serious.
(2), during cutting assembly work, requirement effectively can make organizational separation, and bomb fragments can not be made to enter cabin body affect other components and parts, and therefore general cutting assembly is made up of protective cover, flexible linear shaped charge.Although protective cover plays fixing flexible linear shaped charge and prevent fragment from entering in bullet; but cutting different-thickness is different with the explosive forces that the structure of material needs; when impulsive force is very large, be difficult to ensure that protective cover is not destroyed, obviously simple protective cover can not ensure these requirements.
(3) at the selection of material, what extensively adopt is lead pipe, and its shortcoming is that fusing point is low, easily gasifies in Jet Formation.
(4) in detonation way, for ring device, many employings two insensitiveness initiators, the shortcoming of such design is, insensitiveness initiator Main Function point is more concentrated, and becomes 180 ° of distributions, in the timeliness of igniting, be difficult to ensure flexible linear shaped charge 360 ° can detonate simultaneously, and the power energy relative equilibrium of ignition charge.
Summary of the invention
For the technical problem that prior art exists, this invention is intended to provide a kind of stable connection, synchronism of detonating is high, destructiveness is little, cut Stage Separation of Missile cutter sweep completely.
Based on above-mentioned purpose, the present invention provide firstly a kind of Stage Separation of Missile cutter sweep, described device is made up of protective cover 1, rubber boot 2, flexible linear shaped charge 3 and initiator 4, the inner edge that described flexible linear shaped charge 3 and rubber boot 2 are fitted is that U-shaped constructs, outer rim is the V-shaped configuration of outward opening, described U-shaped structure to the enclosed cavity being combined into annular, is filled with explosive with V-shaped configuration in described cavity; Protective cover 1 and rubber boot 2 are fitted, by coated to rubber boot 2 and flexible linear shaped charge 3; Flexible linear shaped charge 3 is ignited by four insensitiveness initiators, described protective cover 1 inner edge is provided with 4 grooves 11, is uniformly distributed in 90 ° of spacing, arranges the installing hole 12 be connected with described cavity in groove 11, is used for installing and fixing initiator 4; Described initiator 4 is connected with firing cable 5, and described firing cable 5 is connected with the time break cable 8 transmitting time break.
In a preferred technical scheme, described firing cable 5 is that steering wheel plug-in unit connects with the connection of time break cable 8, and its series sequence is time break cable 8, steering wheel card socket 7, steering wheel plug-in unit plug 6 and firing cable 5.
Preferably, described flexible linear shaped charge 3 is made up of red copper material.For the shortcoming that lead flexible linear shaped charge exists, the present invention selects that density is high, plasticity good, fusing point is high, the better red copper of cutting effect is as flexible linear shaped charge material.
Preferably, described rubber boot 2 is made up of natural rubber.
Material for protective cover 1 requires that it has higher intensity, and such as high-strength alloy Steel material is made.
Preferably, described initiator 4 is insensitiveness initiator.
Preferably, described steering wheel plug-in unit sheet metal exposed part heat-shrink tube wraps up.
Preferably, described installing hole 12, in 90 ° of distributions, installs initiator 4 in installing hole 12.The installation of initiator 4 and should be able to play the effect of fixing initiator with the connection of installing hole 12, such as, can adopt and be threaded.
Preferably, described initiator 4 is because the Thickness Ratio of protective cover is thicker with the connection of installing hole 12, and initiator is boss structure and length is not long, therefore groove is set on protective cover, object is that initiator can better be contacted with flexible linear shaped charge, reduces initiator emergence part simultaneously, saves inner space.
On the other hand, present invention also offers a kind of guided missile being assembled with above-mentioned cutter sweep.
In a preferred technical scheme, at the ribs 10 for cut missile airframe 9 being arranged annular spread, described protective cover 1 fits tightly arrangement with ribs 10 ringwise along cut body 9, lock cutter sweep with fixation clamp 13 and to be fixed on cut body 9, stress groove 14 is set at the sticking part of cut body 9 and cutter sweep and flexible linear shaped charge 3 correspondence position.
Preferably, fixation clamp 13 is uniformly distributed along protective cover 1 with 90 ° of spacing, cut body 9 and fixation clamp 13 arranges corresponding screw hole 15a and screw hole 15b respectively and fixes for screw.
In the present invention, rubber boot is between protective cover and flexible linear shaped charge, and its Main Function is the explosive forces in the non-directional direction produced after slackening flexible linear shaped charge work, stops bomb fragments simultaneously, and the impulsive force arriving protective cover like this will weaken greatly.Compare other technologies, this technology overcomes the destroyed risk of protective cover, and structure is more reliable.
Adopt protective cover and rubber boot two bed device parcel flexible linear shaped charge, play effect that is fixing, that protect and add strong impact force directional cutting.
In the present invention, flexible linear shaped charge adopts red copper material, and density is high, and plasticity is good, and not easily gasifies in Jet Formation, good cutting effect.
For linear-shaped charge device, the present invention designs 4 initiators, and distribution in 90 °, and axially symmetrical, such initiator has four centrostigmas on 360 ° of hoops, with powder charge cavity 360 ° for datum level, centered by four centrostigmas, can expand to both sides after initiator work, more can shorten the explosive initiation time in flexible linear shaped charge 360 °, make it closer to synchronous ignition, thus produce synchronous explosive force, cut part circumference is disconnected simultaneously.
For the guided missile that two-stage is separated, after the work of cutting assembly device, cutter sweep needs to abandon together with separated part, because detonator detonates signal is that the time break line of drawing by being positioned at front end provides, when requiring to be separated, time break line will separate with initiator simultaneously, can not catch hold of initiator.So be separated time time break cable and initiator can reliable separation extremely important.
In the present invention, time break line is not directly connected with initiator, but draws one section of firing cable on initiator, is connected between initiator cable with time break cable with pluggable steering wheel plug-in unit.Steering wheel plug-in unit is that plug and socket are pluggable, and the plug of steering wheel plug-in unit is connected with firing cable, and steering wheel card socket is connected with time break line, plug insertion socket and clamping.The advantage of steering wheel plug-in unit is, not easily disconnects, can bear vibration larger in flight course after plug and socket clamp.Need the axial load unpluged not to be high especially, ensure that initiator and time break cable can reliably disconnect, and be separated rapidly, by initiator jettisoning simultaneously.
Accompanying drawing explanation
Fig. 1. Stage Separation of Missile cutter sweep schematic perspective view;
Fig. 2. Stage Separation of Missile cutter sweep medial surface schematic diagram;
Fig. 3. Stage Separation of Missile cutter sweep medial surface initiator installation site detail view;
Fig. 4. Stage Separation of Missile cutter sweep flexible linear shaped charge and fixture detail view;
Fig. 5. Stage Separation of Missile cutter sweep initiator and flexible linear shaped charge detail view;
Fig. 6. Stage Separation of Missile cutter sweep steering wheel plug-in unit detail view.
Description of reference numerals:
1 protective cover
2 rubber boot
3 flexible linear shaped charges
4 initiators
5 firing cable
6 steering wheel plug-in unit plugs
7 steering wheel card socket
8 time break cables
9 missile airframes
10 ribs
11 grooves
12 installing holes
13 fixation clamps
14 stress grooves
15 screw holes (a, b)
Detailed description of the invention
Further describe the present invention below in conjunction with specific embodiment, advantage and disadvantage of the present invention will be more clear along with description.But these embodiments are only exemplary, do not form any restriction to protection scope of the present invention.
The technology of the present invention is as Stage Separation of Missile device, and range of application is the structure that guided missile, target missile etc. need two-stage or multi-stage separation.The purposes of this product is: from receiving control system time break, cutting assembly is started working, and cuts body, body two-stage is reliably separated along bullet circumference, requires to ensure other components and parts safety in bullet in separation process
Embodiment
Present embodiment describes the application of specific product in a kind of target missile of the present invention.Product is made up of protective cover, initiator, flexible linear shaped charge, rubber boot etc.
Show the stereogram of the present invention's specific product as shown in Figure 1, the main body of described device is the cutting assembly device adapted with missile airframe, and cutting assembly device ecto-entad is followed successively by protective cover 1, rubber boot 2, flexible linear shaped charge 3.Cut body wants cutting part to arrange stress groove, and cutting assembly is aimed at stress groove and installed.Protective cover and rubber boot being installed 4 along 360 ° of circumference is 90 ° of equally distributed initiators 4 of spacing, and initiator 4 is connected with firing cable 5.
Show the inner side diagram of the present invention's specific product as shown in Figure 2, in fig. 2, what be set up in parallel with ring protection cover 1 is a ribs 10, and the figure illustrates 4 along 360 ° of circumference is in 90 ° of equally distributed initiators 4 of spacing 3.On the cross section of ring protection cover 1, show the flexible linear shaped charge 3 that the present invention is arranged, and the rubber boot 2 between flexible linear shaped charge 3 and protective cover 1.Firing cable 5 is connected with in addition on initiator 4.
Show the present invention's specific product medial surface initiator installation site detail view as shown in Figure 3.The local that Fig. 3 shows a protective cover medial surface is formed; there is at protective cover medial surface the groove 11 of a rectangular configuration; circular installing hole 12 is provided with in groove 11; to install and fixing initiator 4; the connection of initiator 4 and installing hole 12, for being threaded, connects the cavity in flexible linear shaped charge in installing hole.
Show the present invention's specific product medial surface flexible linear shaped charge and fixture detail view as shown in Figure 4.At the ribs 10 for cut missile airframe 9 being arranged annular spread, described protective cover 1 fits tightly arrangement with ribs 10 ringwise along cut body 9, lock cutter sweep with fixation clamp 13 and be fixed on cut body 9, stress groove 14 is set at the sticking part of cut body 9 and cutter sweep and flexible linear shaped charge 3 correspondence position.Fixation clamp 13 is uniformly distributed along protective cover 1 with 90 ° of spacing, cut body 9 and fixation clamp 13 arranges corresponding screw hole 15a (Fig. 2 display) and screw hole 15b respectively and fixes for screw.
Show the detailed distribution of initiator and flexible linear shaped charge in the present invention's specific product as shown in Figure 5.In Figure 5; the rubber-coated protective cover 2 in protective cover 1 inner edge; laminating flexible linear shaped charge 3 in rubber boot 2; the inner edge that flexible linear shaped charge 3 and rubber boot 2 are fitted is that U-shaped constructs; outer rim is the V-shaped configuration of outward opening; described U-shaped structure to the enclosed cavity being combined into annular, is filled with explosive with V-shaped configuration in described cavity.Described protective cover 1 inner edge is provided with groove 11, this groove has 4, in as shown in Figure 1 be that 90 ° of spacing are uniformly distributed in protective cover 1 inner edge, the initiator installing hole 12 be connected with described cavity is set in groove 11, in installing hole 12, be provided with initiator 4, initiator 4 is connected with firing cable 5.
Show the schematic diagram that the present invention's specific product centered rudder machine transplanting of rice part connects as shown in Figure 6.In figure 6, initiator 4 is installed in groove 11, and initiator 4 is connected with firing cable 5, and firing cable 5 is that steering wheel plug-in unit connects with the connection of time break cable 8, and the connection of steering wheel plug-in unit is connected to form by steering wheel card socket 7 and steering wheel plug-in unit plug 6.Its series sequence is time break cable 8, steering wheel card socket 7, steering wheel plug-in unit plug 6 and firing cable 5.
Cutter sweep structure provided by the invention processing is simple, easy for installation, takes up room less, can not affect other components and parts and install and work in installation process, and reserves more spaces and be supplied to the equipment such as cable, and can not disturb the adjacent components and parts of cabin, front and back section.
In specific product of the present invention, rubber boot becomes U-shaped with protective cover registration interface designs, reduces difficulty of processing like this, plays the effect of parcel simultaneously and is convenient to fix.Flexible linear shaped charge material is red copper, interior filling explosive.The coated flexible linear shaped charge of rubber boot, material is natural rubber, relies on the elasticity of natural rubber itself, and after flexible linear shaped charge is ignited, outside orientation, the impulsive force in other directions can be slackened by rubber boot, and flexible linear shaped charge bomb fragments is also blocked simultaneously.Be protective cover outside rubber boot, protective cover adopts the material that strength ratio is higher, acts on except fixing flexible linear shaped charge; also can stop the shock wave after blast and bomb fragments, because strength ratio is higher, self can not easily destroy; can not make like this to produce bomb fragments in bullet, thus protect other components and parts.In addition protective cover and rubber boot double shielding, prevents explosion time construction debris to enter injury to other components and parts in cabin.
Flexible linear shaped charge is ignited by four insensitiveness initiators, and be connected with steering wheel plug-in unit between firing cable with time break cable, steering wheel plug-in unit sheet metal exposed part heat-shrink tube wraps up, and can prevent sheet metal from exposing oxidized in atmosphere.Initiation current is passed to initiator by steering wheel plug-in unit and is ignited explosive in flexible linear shaped charge by time break.Flight test result shows, and after cutter sweep work, because four initiators are being uniformly distributed circumferentially, the impulsive force of generation is more symmetrical, and the power be subject to when the firing cable connected in bullet is disconnected evenly, can not the static stability of jamming bomb flight.By impulsive force and the gravity abandoning part below, firing cable and time break cable disconnect at steering wheel plug-in unit place, and initiator is abandoned simultaneously, and two-stage is reliably separated, and cutting assembly with abandoning partial exfoliation, can not affect body above and working on.
Cutting assembly is with fixing card and need cutting structure to fix; after cutter sweep cutting provided by the invention; cutting assembly is abandoned part together with separation and is separated completely with reserve part; cut surface is more regular; cutting fragment is less; after detonating, protective cover is not destroyed, and bomb fragments does not enter internal structure.
Claims (10)
1. a Stage Separation of Missile cutter sweep, described device is made up of protective cover (1), rubber boot (2), flexible linear shaped charge (3) and initiator (4), the inner edge that described flexible linear shaped charge (3) and rubber boot (2) are fitted is that U-shaped constructs, outer rim is the V-shaped configuration of outward opening, described U-shaped structure to the enclosed cavity being combined into annular, is filled with explosive with V-shaped configuration in described cavity; Protective cover (1) and rubber boot (2) are fitted, by coated to rubber boot (2) and flexible linear shaped charge (3); Flexible linear shaped charge (3) is ignited by four insensitiveness initiators, 4 grooves (11) are provided with in described protective cover (1) inner edge, be uniformly distributed in 90 ° of spacing, the installing hole (12) be connected with described cavity is set in groove (11), is used for installing and fixing initiator (4); Described initiator (4) is connected with firing cable (5), and described firing cable (5) is connected with the time break cable (8) transmitting time break.
2. device according to claim 1, it is characterized in that, described firing cable (5) is that steering wheel plug-in unit connects with the connection of time break cable (8), and its series sequence is time break cable (8), steering wheel card socket (7), steering wheel plug-in unit plug (6) and firing cable (5).
3. device according to claim 2, is characterized in that, described flexible linear shaped charge (3) is made up of red copper material.
4. device according to claim 2, is characterized in that, described rubber boot (2) is made up of natural rubber.
5. device according to claim 2, is characterized in that, described initiator (4) is insensitiveness initiator.
6. device according to claim 2, is characterized in that, described steering wheel plug-in unit sheet metal exposed part heat-shrink tube wraps up.
7. device according to claim 2, is characterized in that, described installing hole (12), in 90 ° of distributions, installs initiator (4) in installing hole (12).
8. one kind is assembled with the guided missile of the arbitrary described cutter sweep of claim 1-7.
9. guided missile according to claim 8, it is characterized in that, at the ribs (10) for cut missile airframe (9) being arranged annular spread, described protective cover (1) fits tightly arrangement with ribs (10) ringwise along cut body (9), with fixation clamp (13) locking cutter sweep be fixed in (9) on cut body, stress groove (14) is set at the sticking part of cut body (9) and cutter sweep and flexible linear shaped charge (3) correspondence position.
10. guided missile according to claim 9, it is characterized in that, fixation clamp (13) is uniformly distributed along protective cover (1) with 90 ° of spacing, cut body (9) and fixation clamp (13) arranges corresponding screw hole (15a) and screw hole (15b) respectively and fixes for screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510209869.1A CN104833277A (en) | 2015-04-29 | 2015-04-29 | Cutting device for missile stage separation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510209869.1A CN104833277A (en) | 2015-04-29 | 2015-04-29 | Cutting device for missile stage separation |
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| Publication Number | Publication Date |
|---|---|
| CN104833277A true CN104833277A (en) | 2015-08-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510209869.1A Pending CN104833277A (en) | 2015-04-29 | 2015-04-29 | Cutting device for missile stage separation |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547055A (en) * | 2016-01-28 | 2016-05-04 | 晋西工业集团有限责任公司 | Two-stage separating mechanism for civil rocket |
| CN109596012A (en) * | 2018-11-28 | 2019-04-09 | 中国空空导弹研究院 | A kind of cable-styled active Safety system of missile-borne aircraft cutting |
| CN110779400A (en) * | 2019-10-31 | 2020-02-11 | 上海机电工程研究所 | Aircraft interstage separation structure and method |
| CN111453002A (en) * | 2020-04-13 | 2020-07-28 | 北京中科宇航技术有限公司 | Carrier rocket, fire cutting cable protection cover and assembly thereof |
| CN112504032A (en) * | 2021-02-02 | 2021-03-16 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
| CN113124716A (en) * | 2021-04-20 | 2021-07-16 | 上海机电工程研究所 | Protection device for guided missile interstage cutting separation |
| CN113295058A (en) * | 2021-04-28 | 2021-08-24 | 北京星途探索科技有限公司 | Novel interstage electric signal separation mechanism |
| CN113581498A (en) * | 2021-06-23 | 2021-11-02 | 北京宇航系统工程研究所 | Explosion impact resistant and inward cutting separating device |
| CN115839287A (en) * | 2023-01-03 | 2023-03-24 | 东方空间(西安)宇航技术有限公司 | Rocket engine self-destruction device, rocket engine and rocket assembly method |
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| CN111453002A (en) * | 2020-04-13 | 2020-07-28 | 北京中科宇航技术有限公司 | Carrier rocket, fire cutting cable protection cover and assembly thereof |
| CN112504032B (en) * | 2021-02-02 | 2021-04-13 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
| CN112504032A (en) * | 2021-02-02 | 2021-03-16 | 星河动力(北京)空间科技有限公司 | Carrier rocket and cutting assembly for interstage separation of carrier rocket |
| CN113124716A (en) * | 2021-04-20 | 2021-07-16 | 上海机电工程研究所 | Protection device for guided missile interstage cutting separation |
| CN113295058A (en) * | 2021-04-28 | 2021-08-24 | 北京星途探索科技有限公司 | Novel interstage electric signal separation mechanism |
| CN113581498A (en) * | 2021-06-23 | 2021-11-02 | 北京宇航系统工程研究所 | Explosion impact resistant and inward cutting separating device |
| CN113581498B (en) * | 2021-06-23 | 2023-04-14 | 北京宇航系统工程研究所 | Explosion impact resistant and inward cutting separating device |
| CN115839287A (en) * | 2023-01-03 | 2023-03-24 | 东方空间(西安)宇航技术有限公司 | Rocket engine self-destruction device, rocket engine and rocket assembly method |
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Application publication date: 20150812 |