CN111903209B - Missile head fairing separator - Google Patents
Missile head fairing separator Download PDFInfo
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- CN111903209B CN111903209B CN200910125379.8A CN200910125379A CN111903209B CN 111903209 B CN111903209 B CN 111903209B CN 200910125379 A CN200910125379 A CN 200910125379A CN 111903209 B CN111903209 B CN 111903209B
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- fairing
- actuating cylinder
- gunpowder
- missile
- separation
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Abstract
The invention relates to a missile head fairing separation device.A gunpowder actuating cylinder is arranged on a missile body through a gunpowder actuating cylinder mounting seat and passes through a conical section of a fairing head to be separated from the fairingThe metal bush that the combined material covering is connected compresses tightly on the preceding terminal surface of powder pressurized strut, its characterized in that: the gunpowder actuating cylinder mounting seat is connected with the bottom thread L of the gunpowder actuating cylinder through a steel threaded bushing2And a stop pin for controlling the stroke of the piston is arranged on the inner wall of the gunpowder actuating cylinder, and the control stroke L of the stop pin is 60 mm. The technical scheme of the invention has the advantages that: the structure is simple, the disassembly and the assembly are convenient, the weight is light, the counter impact acting force on the missile body during the separation is small, the reliable separation of the fairing can be ensured under the subsonic speed condition, and the fairing can be applied to the separation of fairings in various subsonic speed states of missiles or in supersonic speed states of small missiles through modification.
Description
Technical Field
The invention relates to a missile head fairing separation device, and belongs to the technical field of product structures.
Background
At present, a plurality of types of missiles at home and abroad adopt a television imaging guidance technology, the guidance technology requires that the missiles have optical glass windows, and the existence of the optical glass windows reduces the stealth performance of the missiles, so that the longer the flight time of the guidance type missiles, the higher the discovered probability and the lower the survival capability of the guided missiles; in the supersonic flight state, the missile may cause ablation of the optical window due to high-speed friction with air, so that the television imaging guidance fails.
The problem can be well solved by additionally arranging the head fairing for the missile. The missile head fairing made of the same material as the missile body can improve the stealth capability of the missile in the flying process and protect an optical window. However, the fairing prevents the missile from searching and finding the target during missile launching attack, so that the missile needs to be separated from the missile body at the flight end.
The separation technology of the head cover is applied to a few missiles (such as a British storm precursor series) abroad, but the specific content of the separation technology is not disclosed, and through the knowledge of the relevant data of the separation technology of the head fairing of the limited British storm precursor series missile, the head fairing adopts a slicing separation mode, and the fairing separation mode needs to arrange a plurality of cutting ropes, so that the inner structure of the fairing is complex and the connection and installation are troublesome. In China, the technology is mainly applied to satellite launch vehicles, and missiles are not applied yet. The fairing of the carrier rocket is huge in size, the separation structure is convenient to arrange, the satellite fairings are separated outside the atmosphere, the separation resistance is extremely small, and the implementation is easy, so that the satellite fairing separation technology is difficult to transplant to the missile.
Disclosure of Invention
The invention provides a missile head fairing separation device designed and provided aiming at the prior art, and aims to realize separation of a missile fairing, move towards the oblique front of a missile body during separation, avoid a missile flight safety region and realize reliable separation.
The fairing is additionally arranged at the head of the missile, so that the overall aerodynamic shape of the missile after the fairing is installed meets the requirements, the aerodynamic resistance is small when the fairing is separated, and finally, the missile body is kept in a better aerodynamic shape after the fairing is separated.
On the premise that the total impact provided by the power source is unchanged, the lighter the hood is, the greater the initial separation speed is, and the farther the distance of the relative projectile motion is.
The technical problem to be solved by the technical scheme of the invention is as follows: the fairing device is applied to the missile, meets the requirements on the pneumatic appearance before and after separation, generates smaller impact force on the missile body as far as possible during separation, and can realize safe and reliable separation in the atmosphere.
The missile fairing is designed to firstly carry out missile body appearance trimming, a hood appearance which meets the pneumatic requirement and is smoothly connected with a missile is established on the basis of meeting the minimum space required by a separation mechanism, then a primary separation mechanism is designed, the pneumatic separation process is simulated by adopting modern engineering numerical analysis software CFD-FASTRAN, basic factors such as safety distance, separation initial impulse, hood separation rear track and the like required by hood separation under different attack angles are calculated, parameter optimization design is carried out by combining the specific conditions of the missile body, the parameters of a power source are determined, detailed hood parts are designed, and finally the hood separation condition is verified by means of ground tests, wind tunnel tests and the like.
Through design and a large number of experiments, the technical scheme of the invention comprises the following specific contents:
the missile head fairing separating device takes a gunpowder actuating cylinder as a power source, the gunpowder actuating cylinder is installed on a missile body through a gunpowder actuating cylinder installation seat, a metal bushing connected with a composite material skin is tightly pressed on the front end face of the gunpowder actuating cylinder through a fairing head conical section, and the missile head fairing separating device is characterized in that: the gunpowder actuating cylinder mounting seat is connected with the bottom thread L of the gunpowder actuating cylinder through a steel threaded bushing2And a stop pin for controlling the stroke of the piston is arranged on the inner wall of the gunpowder actuating cylinder, and the control stroke L of the stop pin is 60 mm.
Description of the drawings:
FIG. 1 is a schematic view of the overall structure of the separation apparatus of the present invention
FIG. 2 is a schematic view of the powder actuator of the release mechanism of the present invention
Detailed Description
The technical scheme of the invention is further detailed in the following by combining the drawings and the embodiment:
referring to attached drawings 1-2, the missile head fairing separating device is composed of a fairing head conical section, a fairing modification section, an actuating cylinder mounting seat and a gunpowder actuating cylinder. Wherein, the gunpowder actuating cylinder 6 is arranged on the bullet body 8 through the gunpowder actuating cylinder mounting seat 5, a threaded hole is processed at the rear end of the fairing head conical section 1, and the threaded hole passes through the fairing head conical section 1 and the head thread L of the gunpowder actuating cylinder 61Connecting, pressing a metal bushing 2 connected with a composite material skin 3 on the front end inclined plane of a gunpowder actuating cylinder 6, and connecting a gunpowder actuating cylinder mounting seat 5 with the bottom thread L of the gunpowder actuating cylinder 6 through a steel threaded bushing 42And a stop pin 13 for controlling the stroke of the piston 9 is arranged on the inner wall of the gunpowder actuating cylinder 6, and the control stroke L of the stop pin is 60 mm.
After the metal bushing 2 is machined, the composite material skin 3 is laid on the outer surface, the outer surface of the metal bushing 2 is provided with a step 12 to increase the connection strength with the composite material skin 3, the front section of the inner surface of the metal bushing 2 is conical, the rear section of the inner surface of the metal bushing 2 is cylindrical, and the conical surface presses the front end face of the gunpowder actuating cylinder 6. The front end of the composite material skin 3 is conical in shape and gradually transits to the rear end to be smoothly tangent to the shape of the projectile body.
The middle of the outer surface of the powder actuating cylinder 6 is provided with a circular boss 11 which is tightly pressed on the front end surface of the powder actuating cylinder mounting seat 5.
The actuator cylinder mounting base 5 is used for transmitting a reaction force generated when the gunpowder actuator cylinder 6 does work to the projectile body 8 so as to protect the optical window 7 from being impacted. The front section of the actuating cylinder mounting seat 5 is cylindrical, and a step is processed in the hollow part for embedding the steel threaded bushing 4; the rear section of the mounting seat 5 is spherical for protecting the optical window 7. The inner surface of the steel threaded bushing 4 is provided with threads for fixing the gunpowder actuating cylinder 6.
The powder actuator 6 is a core component of the fairing separation device, and the design parameters of the powder actuator can be determined only after the design of all other fairing parts is finished. And integrating the mass, the mass center, the rotational inertia, the fairing appearance and other factors of the fairing part and the simulation actuating cylinder, performing detailed calculation, separation simulation analysis and other steps, and determining the parameters of the gunpowder actuating cylinder such as total impact, installation angle, mass center and the like.
When the fairing is installed, firstly, the steel threaded bush 4 is pressed into the step surface of the actuating cylinder installation seat 5 from the rear; then the bottom thread L of the gunpowder actuating cylinder 6 is arranged2Screwing the powder actuating cylinder 6 into the steel threaded bush 4 from the front until the rear end face of the middle annular boss 11 of the powder actuating cylinder 6 tightly presses the front end face of the actuating cylinder mounting seat 5; then the combined material skin and the fairing trimming section are arranged on the elastomer 8 together, and the composite material skin 3 is fixed by screws; finally, the conical section 1 of the fairing head is screwed into the head thread L on the piston 9 of the exposed powder actuating cylinder 61And (4) until the conical surface at the front end of the gunpowder actuating cylinder 6 tightly presses the inclined surface at the inner front section of the metal bushing 2, the installation of the fairing is finished.
The separation of the integral impulse forward-moving type fairing device can be roughly divided into two stages:
hood separation stage 1: after receiving a cover throwing instruction, the gunpowder actuating cylinder 6 is ignited, the threaded piston 9 starts to move under the driving of gunpowder 10, and the conical surface of the metal bushing 2 is extruded to drive the conical section 1 of the fairing head and the composite material skin 3 to move forwards, so that the composite material skin 3 and the fixing screw of the projectile body 8 are sheared. The recoil force is transmitted to the body 8 through the actuator cylinder mounting base 5.
Hood separation stage 2: after the powder actuating cylinder 6 works for a certain distance, the stop pin 13 arranged in the powder actuating cylinder stops the piston 9 to move, and at the moment, the conical section 1 of the fairing head and the fairing modification section reach the preset speed, so that the powder actuating cylinder 6 and the actuating cylinder mounting seat 5 are dragged to move together, and the aim that the fairing separating device is completely separated from the projectile body is achieved.
Aiming at specific parameters of a certain type of missile, the missile integral impulse type forward separation device produced according to the technical scheme of the invention is successful.
The technical scheme of the invention has the advantages that: the structure is simple, the disassembly and the assembly are convenient, the weight is light, the counter impact acting force on the missile body during the separation is small, the reliable separation of the fairing can be ensured under the subsonic speed condition, and the fairing can be applied to the separation of fairings in various subsonic speed states of missiles or in supersonic speed states of small missiles through modification.
Claims (3)
1. A missile head fairing separation device is composed of a fairing head conical section (1), a fairing modification section, a gunpowder actuator cylinder mounting seat (5) and a gunpowder actuator cylinder (6), wherein the gunpowder actuator cylinder (6) is mounted on a missile body (8) through the gunpowder actuator cylinder mounting seat (5), a threaded hole is machined in the rear end of the fairing head conical section (1), and head threads L passing through the fairing head conical section (1) and the gunpowder actuator cylinder (6)1The connection, the fairing head conical section (1) compresses a metal bushing (2) connected with a composite material skin (3) on the front end face of the gunpowder actuating cylinder (6), and the connection is characterized in that: the gunpowder actuating cylinder mounting seat (5) is connected with the bottom thread L of the gunpowder actuating cylinder (6) through a steel threaded bushing (4)2And a stop pin (13) for controlling the stroke of the piston (9) is arranged on the inner wall of the gunpowder actuating cylinder (6), and the control stroke L of the stop pin is 60 mm.
2. The missile nose fairing separation unit of claim 1, wherein: the outer surface of the metal bushing (2) is provided with a step (12) to increase the connection strength with the composite material skin (3), the front section of the inner surface of the metal bushing (2) is conical, the rear section of the inner surface of the metal bushing is cylindrical, and the conical surface is pressed on the front end face of the powder actuating cylinder (6).
3. The missile nose fairing separation unit of claim 1, wherein: the middle of the outer surface of the powder actuating cylinder (6) is provided with a circular boss (11) which is tightly pressed on the front end surface of the powder actuating cylinder mounting seat (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910125379.8A CN111903209B (en) | 2009-12-30 | 2009-12-30 | Missile head fairing separator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910125379.8A CN111903209B (en) | 2009-12-30 | 2009-12-30 | Missile head fairing separator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111903209B true CN111903209B (en) | 2013-10-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910125379.8A Active CN111903209B (en) | 2009-12-30 | 2009-12-30 | Missile head fairing separator |
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| CN (1) | CN111903209B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625338A (en) * | 2018-12-12 | 2019-04-16 | 湖北航天飞行器研究所 | The radome fairing and rocket that can be cast aside certainly |
| CN110631433A (en) * | 2019-08-20 | 2019-12-31 | 西安航天动力技术研究所 | Shear screw type hood separating mechanism |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN112504031A (en) * | 2020-11-27 | 2021-03-16 | 北京宇航系统工程研究所 | Variable-force-line long-stroke actuating device suitable for rotary throwing of fairing |
-
2009
- 2009-12-30 CN CN200910125379.8A patent/CN111903209B/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625338A (en) * | 2018-12-12 | 2019-04-16 | 湖北航天飞行器研究所 | The radome fairing and rocket that can be cast aside certainly |
| CN109625338B (en) * | 2018-12-12 | 2022-07-15 | 湖北航天飞行器研究所 | Self-throwing-away fairing and rocket |
| CN110631433A (en) * | 2019-08-20 | 2019-12-31 | 西安航天动力技术研究所 | Shear screw type hood separating mechanism |
| CN110631433B (en) * | 2019-08-20 | 2021-08-17 | 西安航天动力技术研究所 | Shear screw type hood separating mechanism |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN111006837B (en) * | 2019-11-22 | 2021-10-01 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN112504031A (en) * | 2020-11-27 | 2021-03-16 | 北京宇航系统工程研究所 | Variable-force-line long-stroke actuating device suitable for rotary throwing of fairing |
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