CN203461148U - Interstage separating device with detonating connector for aircraft - Google Patents
Interstage separating device with detonating connector for aircraft Download PDFInfo
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- CN203461148U CN203461148U CN201320504331.XU CN201320504331U CN203461148U CN 203461148 U CN203461148 U CN 203461148U CN 201320504331 U CN201320504331 U CN 201320504331U CN 203461148 U CN203461148 U CN 203461148U
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- priming adapter
- detonating
- shaft part
- external diameter
- connector
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Abstract
The utility model relates to an interstage separating device with a detonating connector for an aircraft. The interstage separating device comprises the detonating connector, an adapter and a detonating connector base, wherein the detonating connector base is fixed on an aircraft housing; internal threads are arranged in the detonating connector base; the inner part of the detonating connector adopts a hollow columnar structure; external threads are arranged at the upper end and the lower end of the detonating connector respectively; the inner part of the adapter adopts a hollow columnar structure; internal threads are arranged at the inner part of the lower end of the adapter; the external threads at the upper end of the detonating connector are matched and connected with the internal threads at the lower end of the adapter; the external threads at the lower end of the detonating connector are matched and connected with the internal threads of the detonating connector base; one end of a detonating fuse arranged in the aircraft housing penetrates into the detonating connector along a transition fillet, and is flush with the upper end surface of the detonating connector. The interstage separating device adopts split-type design, shortens the processing period greatly, and reduces the processing difficulty. The detonating fuse assembly is relatively controllable and reliable. The mounting times of a traditional detonating connector is changed from once to twice, so that the end of the detonating fuse is cut more easily, and the reliability of the separating device is improved.
Description
Technical field
The present invention relates to Flight Vehicle Stage Separation technical field, be specifically related to a kind of Flight Vehicle Stage Separation priming adapter device.
Background technology
Linear separation device is widely used in the isolating construction of spacecraft and guided missile, has that its coupling stiffness is good, synchronism and a high reliability.Exploding fuse disengagement gear is that aerospacecraft satisfactorily completes one of indispensable framing member of aerial mission, is widely used in the connection of multistage housing with separated.Priming adapter is the important component part of exploding fuse disengagement gear.Mild detonating fuze disengagement gear is a kind of as linear separation device, because it is simple in structure, the stage separation of advantage the is widely used in guided missile such as fitting operation is convenient, compatible with environment is high.
Mild detonating fuze disengagement gear is to using mild detonating fuze (MDF) as detachment dynamic source, completes the cutting of housing, realizes the separation of intended target.Because mild detonating fuze disengagement gear has the advantages such as reliability is high, synchronism good, safety is good, it is applied on guided missile and carrier rocket more and more widely.Mild detonating fuze disengagement gear is comprised of protective case, mild detonating fuze (MDF), separated housing, attaching parts, priming adapter etc.Wherein priming adapter has been mainly location, support exploding fuse end and the effect being connected with firing device with priming adapter seat.
But because exploding fuse is the weak link of linear separation device, its stretch-proof, anti-shearing, abrasion resistance is poor, this processes enough excessive fillets with regard to the priming adapter that requires to be in contact with it and is avoided scratching, is interrupted exploding fuse.Existing priming adapter complex structure, adds and need use the non-traditional machinings such as electro spark man-hour, and operation is complicated, and the production cycle is long.
Summary of the invention
The technical matters that will solve of the present invention is to provide a kind of processing of being convenient to, and enhances productivity, and exploding fuse assembling is more controlled, reliable, improves the split type Flight Vehicle Stage Separation priming adapter device of disengagement gear reliability.
In order to solve the problems of the technologies described above, technical scheme of the present invention is that a kind of Flight Vehicle Stage Separation priming adapter device, comprises priming adapter, transfer tube, priming adapter seat;
Described priming adapter seat is fixed on aircraft casing, and its inside is provided with negative thread; Described priming adapter is inner hollow column structure, and its upper and lower two ends are provided with outside thread; Described transfer tube is the column structure of inner hollow, and its inside, lower end is provided with negative thread; The upper external screw thread of described priming adapter is connected with the screw-internal thread fit of transfer tube lower end; The lower end outside thread of described priming adapter is connected with the screw-internal thread fit of priming adapter seat;
Be arranged on the termination of the exploding fuse in aircraft casing along penetrating described priming adapter, and the termination of this exploding fuse and the upper surface of described priming adapter flush.
Described priming adapter is inner hollow outer step axle shape structure, and it comprises large external diameter shaft part and little external diameter shaft part, and described large external diameter shaft part outside face is provided with outside thread.
Between described little external diameter shaft part and large external diameter shaft part, be provided with the one or six side, the one or six side is connected with large external diameter shaft part integral type with described little external diameter shaft part.
Between two adjacent external surfaces of described the one or six side, offer the first penetrating insurance hole.
Between described large external diameter shaft part outer face and the inner hollow structure of priming adapter, be provided with excessive fillet.
Described transfer tube is the column structure of inner hollow, and its inside, lower end is provided with negative thread, and the outside thread of the little external diameter shaft part of described priming adapter is connected with the screw-internal thread fit of transfer tube one end; The large external diameter shaft part of described priming adapter is connected with the screw-internal thread fit of priming adapter seat inside by outside thread.
Described transfer tube upper end outside face is provided with the two or six side.
Between two adjacent external surfaces of described the two or six side, offer the second penetrating insurance hole.
Beneficial effect of the present invention:
(1) the present invention adopts split design, to the processing of priming adapter knuckle, can avoid adopting electro spark non-traditional machining, adopts machined into, greatly shortens the process-cycle, has reduced difficulty of processing.
(2) exploding fuse assembling is more controlled, reliable.
(3) the present invention is improved to twice installation by traditional priming adapter once mounting, is more prone to cut exploding fuse termination, makes exploding fuse installing condition more controlled simultaneously, improves the reliability of disengagement gear.
Accompanying drawing explanation
Fig. 1 is a kind of Flight Vehicle Stage Separation priming adapter of the present invention device schematic diagram;
Fig. 2 is the lateral plan of the priming adapter of a kind of Flight Vehicle Stage Separation priming adapter of the present invention device;
Fig. 3 is the front elevation of the priming adapter of a kind of Flight Vehicle Stage Separation priming adapter of the present invention device;
Fig. 4 is the transfer tube lateral plan of a kind of Flight Vehicle Stage Separation priming adapter of the present invention device;
Fig. 5 is the transfer tube front elevation of a kind of Flight Vehicle Stage Separation priming adapter of the present invention device;
In figure: 1-knuckle, 2-the one or six side, 3-the first insurance hole, 4-outside thread, 5-negative thread, 6-the second insurance hole, 7-the two or six side, 8-the three or six side, 9-exploding fuse, 10-priming adapter seat, 11-priming adapter, 12-transfer tube.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is described further.
A kind of Flight Vehicle Stage Separation priming adapter of the present invention device, comprises priming adapter 11, transfer tube 12, priming adapter seat 10 as shown in Figure 1;
Described priming adapter seat 10 is fixed on aircraft casing, and its inside is provided with negative thread;
Described priming adapter 11 is inner hollow outer step axle shape structure, it comprises large external diameter shaft part and little external diameter shaft part, between described little external diameter shaft part and large external diameter shaft part, being provided with the one or six side 2, the one or six sides 2 and described little external diameter shaft part is connected with external diameter shaft part integral type greatly; Described large external diameter shaft part outside face is provided with outside thread; Between two adjacent external surfaces of described the one or six side 2, offer the first penetrating insurance hole 3; Between described large external diameter shaft part outer face and the inner hollow structure of priming adapter 11, be provided with excessive fillet 1;
The column structure that described transfer tube 12 is inner hollow, its inside, one end is provided with negative thread, and other end outside face is provided with the two or six side 8, offers the second penetrating insurance hole 6 between two adjacent external surfaces of described the two or six side 8;
The outside thread of the little external diameter shaft part of described priming adapter 11 is connected with the screw-internal thread fit of transfer tube 12 one end; The large external diameter shaft part of described priming adapter 11 is connected with the screw-internal thread fit of priming adapter seat 10 inside by outside thread;
Described the one or six side 2 is the operations of tightening and get loose of being convenient to described priming adapter 11 and priming adapter seat 10, and loosens by the first insurance hole 3; Described the two or six side 8 is the operations of tightening and get loose of being convenient to described priming adapter 11 and transfer tube 12, and loosens by the second insurance hole 6;
The termination that is arranged on the exploding fuse 9 in aircraft casing penetrates described priming adapter 11 along described excessive fillet 1, and the termination of this exploding fuse 9 flushes with the little external diameter shaft part upper surface of described priming adapter 11.
Concrete installation process is as follows:
First exploding fuse 9 fixing by aircraft casing and protective case after; its termination is passed by priming adapter seat 10, and exploding fuse 9 is passed to priming adapter 11, then priming adapter 11 is connected with priming adapter seat 10; utilize six sides 2 to tighten, and locking by insurance hole 3.Cut the unnecessary length of exploding fuse 9, make its termination concordant with priming adapter 11 terminations.Then, utilize six sides 8 that transfer tube 12 and priming adapter 11 are tightened, locking by insurance hole 6.
To priming adapter design of the present invention and processing mode, in the situation that not changing its function, the equivalent transformation carrying out or alternative, also falls into protection scope of the present invention.
Claims (8)
1. a Flight Vehicle Stage Separation priming adapter device, is characterized in that: comprise priming adapter, transfer tube, priming adapter seat;
Described priming adapter seat is fixed on aircraft casing, and its inside is provided with negative thread; Described priming adapter is inner hollow column structure, and its upper and lower two ends are provided with outside thread; Described transfer tube is the column structure of inner hollow, and its inside, lower end is provided with negative thread; The upper external screw thread of described priming adapter is connected with the screw-internal thread fit of transfer tube lower end; The lower end outside thread of described priming adapter is connected with the screw-internal thread fit of priming adapter seat;
Be arranged on the termination of the exploding fuse in aircraft casing along penetrating described priming adapter, and the termination of this exploding fuse and the upper surface of described priming adapter flush.
2. according to priming adapter device claimed in claim 1, it is characterized in that: described priming adapter is inner hollow outer step axle shape structure, and it comprises large external diameter shaft part and little external diameter shaft part, described large external diameter shaft part outside face is provided with outside thread.
3. according to priming adapter device claimed in claim 2, it is characterized in that: between described little external diameter shaft part and large external diameter shaft part, be provided with the one or six side, the one or six side is connected with large external diameter shaft part integral type with described little external diameter shaft part.
4. according to priming adapter device claimed in claim 3, it is characterized in that: between two adjacent external surfaces of described the one or six side, offer the first penetrating insurance hole.
5. according to priming adapter device claimed in claim 2, it is characterized in that: between described large external diameter shaft part outer face and the inner hollow structure of priming adapter, be provided with excessive fillet.
6. according to priming adapter device claimed in claim 2, it is characterized in that: the column structure that described transfer tube is inner hollow, its inside, lower end is provided with negative thread, and the outside thread of the little external diameter shaft part of described priming adapter is connected with the screw-internal thread fit of transfer tube one end; The large external diameter shaft part of described priming adapter is connected with the screw-internal thread fit of priming adapter seat inside by outside thread.
7. according to priming adapter device claimed in claim 2, it is characterized in that: described transfer tube upper end outside face is provided with the two or six side.
8. according to priming adapter device claimed in claim 7, it is characterized in that: between two adjacent external surfaces of described the two or six side, offer the second penetrating insurance hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320504331.XU CN203461148U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device with detonating connector for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320504331.XU CN203461148U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device with detonating connector for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203461148U true CN203461148U (en) | 2014-03-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320504331.XU Expired - Lifetime CN203461148U (en) | 2013-08-19 | 2013-08-19 | Interstage separating device with detonating connector for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203461148U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
-
2013
- 2013-08-19 CN CN201320504331.XU patent/CN203461148U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140305 |