CN108995832B - Pneumatic booster-type interstage separation mechanism - Google Patents
Pneumatic booster-type interstage separation mechanism Download PDFInfo
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- CN108995832B CN108995832B CN201810834546.5A CN201810834546A CN108995832B CN 108995832 B CN108995832 B CN 108995832B CN 201810834546 A CN201810834546 A CN 201810834546A CN 108995832 B CN108995832 B CN 108995832B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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Abstract
The invention discloses a pneumatic booster-type interstage separation mechanism which comprises an interstage cabin shell, a connecting unlocking device and a booster cover, wherein the connecting unlocking device is arranged on the interstage cabin shell; the interstage cabin shell is fixed at the tail end of the upper stage through the connecting unlocking device, through holes are uniformly formed in the outer wall of the rear end of the interstage cabin shell in the circumferential direction, the pressurizing cover is fixed on the through holes, and the opening of the pressurizing cover faces the windward side and is used for guiding air into the interstage cabin to increase the resistance difference between the upper stage and the lower stage. The invention has simple structure, can increase the difference of two-stage pneumatic resistance and realizes reliable separation.
Description
Technical Field
The invention relates to the technical field of multi-stage missiles or rockets, in particular to a pneumatic booster-type interstage separation mechanism.
Background
For a small and medium-sized multi-stage missile or rocket with a tandem type layout, in order to reduce the speed loss of the missile or rocket and provide a channel for the work of an upper-stage engine, a lower-stage engine needs to be thrown away as soon as possible after the work of the lower-stage engine is finished, namely, interstage separation is realized. A typical tandem two-stage rocket layout is shown in figure 1.
According to published information, two interstage separation modes are commonly used at present, wherein one mode is a thermal separation mode, namely after the operation of a lower stage engine is finished, a mechanism connected with the upper stage is unlocked on the front end face of the interstage cabin, meanwhile, the upper stage engine or an auxiliary power device arranged in the interstage cabin is ignited to operate, and the lower stage is thrown away by means of the wake flow of the upper stage engine or the reverse thrust of the auxiliary power device; the other is a cold separation mode: after the lower stage engine finishes working, the mechanism connected with the front end face of the inter-stage cabin and the upper stage is unlocked, and then the two-stage safe separation is realized by means of the resistance difference between the lower stage and the upper stage.
Although the above method has certain feasibility, the following problems mainly exist:
(1) the thrust reversal auxiliary power device used in the stage separation of the multistage missile or rocket has a complex structure, increases one path of ignition time sequence, reduces the reliability, and inevitably leads to the increase of the product cost when the device is used for the stage separation.
(2) For the traditional cold separation mode, the separation rapidity mainly depends on the magnitude of the resistance difference of two stages, so that the missile or rocket with smaller diameter difference of two stages is difficult to adopt.
(3) The multi-stage missile or rocket usually adopts a thermal separation mode depending on the thrust of an engine at the upper stage, and has the defect that a connecting part between two stages is always in the wake flow of the engine at the upper stage in the separation process, and the rigidity, the strength, the ablation resistance and the reliability of the connecting part need to be considered.
Disclosure of Invention
In view of this, the invention provides a pneumatic supercharged interstage separation mechanism which is simple in structure, capable of increasing two-stage pneumatic resistance difference and capable of realizing reliable separation.
The specific embodiment of the invention is as follows:
a pneumatically pressurized interstage separation mechanism comprising an interstage compartment housing, a connection unlocking device, and a pressurized shroud;
the interstage cabin shell is fixed at the tail end of the upper stage through a connecting and unlocking device, through holes are uniformly formed in the outer wall of the rear end of the interstage cabin shell along the circumferential direction, the supercharging cover is fixed on the through holes, the opening of the supercharging cover faces the windward side, and the supercharging cover is used for guiding air into the interstage cabin to increase the resistance difference between the upper stage and the lower stage.
Further, the plenum cage profile is tapered in a drag direction, which is opposite to the flight direction.
Further, the pressurizing cover is a wedge-shaped shell structure consisting of two side surfaces and a top surface.
Further, the connecting and unlocking device adopts explosive bolts and is arranged on the butt joint end face of the inter-stage cabin shell and the upper stage.
Has the advantages that:
1. the pneumatic booster type interstage separation mechanism is formed by adding the interstage opening and the booster cover on the basis of a common interstage separation mechanism, two-stage separation is realized only by depending on the pneumatic resistance difference between the upper stage and the lower stage, and the pneumatic booster type interstage separation mechanism is simple in structure and flexible to use. And moreover, a cold separation mode is adopted, the design of preventing thermal ablation of the engine wake flow is not considered in the whole process of the interstage cabin, and the interstage cabin is simpler and more reliable.
2. The profile of the pressurizing cover is contracted along the resistance direction and is attached to the conical structure of the interstage cabin section, the radial length of the rocket is not increased, and the pneumatic profile is good.
3. The unlocking device adopts the explosive bolt, and the unlocking separation is simple and easy to realize.
Drawings
FIG. 1 is a schematic layout of a tandem two-stage rocket;
FIG. 2 is a schematic structural view of the present invention;
FIG. 3 is a schematic view of the structure of the interstage compartment;
FIG. 4 is a schematic structural view of a plenum cage;
FIG. 5 is a comparison of two-stage drag coefficient differences during rocket separation of a certain type;
fig. 6 shows the distance change between stages in a rocket separation process.
Wherein, 1-interstage cabin shell, 2-explosive bolt, 3-supercharging cover and 4-through hole.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a pneumatic supercharged interstage separation mechanism which comprises an interstage tank shell 1, an explosion bolt 2 and a supercharging cover 3, as shown in figure 2.
The interstage cabin shell 1 is positioned between the upper stage and the lower stage, and mainly has the functions of connecting the upper stage and the lower stage into a whole, maintaining the pneumatic appearance of a rocket or a missile in flight and meeting certain requirements on appearance, strength and rigidity. The connection surface of the interstage casing 1 and the tail end of the upper stage is an interstage separation surface. Through holes 4 are uniformly formed in the outer wall of the rear end of the interstage casing 1 along the circumferential direction.
The explosive bolts 2 are arranged on the butt joint end faces of the interstage tank shell 1 and the upper stage, so that the interstage tank and the upper stage can be reliably connected and disconnected.
The pressurizing cover 3 is a wedge-shaped shell structure consisting of two side surfaces and a top surface, the weight of the pressurizing cover 3 is reduced as much as possible under the condition of meeting the processing technology and the mechanical strength, the bottom plates extending out of the two side surfaces are fixedly connected with the interstage cabin shell 1 through screws, the pressurizing cover 3 covers the through hole 4, the opening faces the windward side, when the lower-stage resistance surface is increased, air is guided into the pressure inside the interstage cabin through the through hole 4 below the pressurizing cover 3, the resistance of the lower stage is improved, and the pneumatic resistance difference of the two stages is increased.
In the assembling process, the pressurizing cover 3 is fixed above the through hole 4 on the outer wall surface of the interstage casing 1 through a screw, the explosive bolt 2 is fixed with the mounting seat at the front end of the interstage casing, the rear end of the interstage casing is connected with the front end of the lower stage, and finally the whole of the interstage casing and the lower stage is connected with the rear end of the upper stage.
The interstage separation process is as follows: after the rocket is launched, the lower-stage engine is ignited to work firstly to realize the accelerated flight of the missile/rocket, after the lower-stage engine works, the missile/rocket upper control system sends a separation ignition instruction, the interstage explosion bolt 2 is ignited and disconnected, the upper stage and the lower stage are disconnected from the interstage separation surface, under the action of the pneumatic supercharging cover 3, the two stages are quickly separated under the action of the difference of resistance acceleration generated by large resistance difference, then the upper stage is ignited, and the missile/rocket continues to accelerate flight.
The pneumatic supercharged separation mechanism can realize two-stage safe and quick separation; in the separation process, the disturbance on the upper stage is small, the falling point of the debris on the lower stage can be predicted, and the success of the multi-flying test is verified.
The two curves in fig. 5 are the comparison of the two-stage drag coefficient differences for a certain type of rocket employing a common and a pressurized separation mechanism. Therefore, after the pneumatic supercharged interstage separation mechanism is used, the resistance coefficient difference between the upper stage and the lower stage is improved by more than one time.
The two-stage rocket provided with the pneumatic booster-type interstage separation mechanism and the common interstage separation mechanism is provided with a curve of the change of the separation distance along with time obtained by calculation, which is shown in figure 6. At a distance between the two stages greater than 1m, the separation process may be considered to be complete. Therefore, under the condition of adopting the pneumatic booster-type interstage separation mechanism, when the separation distance reaches 1m, the separation time only takes 0.16 s; under the condition of adopting a common interstage separation mechanism, when the separation distance reaches 1m, the separation time needs to be more than 0.23 s.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A pneumatic booster-type interstage separation mechanism is characterized by comprising an interstage tank shell, a connecting unlocking device and a booster cover;
the interstage cabin shell is fixed at the tail end of the upper stage through a connecting and unlocking device, through holes are uniformly formed in the outer wall of the rear end of the interstage cabin shell along the circumferential direction, the supercharging cover is fixed on the through holes, the opening of the supercharging cover faces the windward side, and the supercharging cover is used for guiding air into the interstage cabin to increase the resistance difference between the upper stage and the lower stage.
2. The pneumatically pressurized interstage separation mechanism of claim 1 wherein the plenum cage profile is tapered in a drag direction, the drag direction being opposite the direction of flight.
3. The pneumatically pressurized interstage separation mechanism of claim 2 wherein the plenum cage is a wedge shaped housing structure comprised of two side surfaces and a top surface.
4. The pneumatically pressurized interstage separation mechanism of claim 1 wherein said connection unlocking means is an explosive bolt disposed on the abutting end face of the interstage casing to the upper stage.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810834546.5A CN108995832B (en) | 2018-07-26 | 2018-07-26 | Pneumatic booster-type interstage separation mechanism |
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| CN201810834546.5A CN108995832B (en) | 2018-07-26 | 2018-07-26 | Pneumatic booster-type interstage separation mechanism |
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| CN108995832B true CN108995832B (en) | 2021-05-28 |
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| CN113405410B (en) * | 2021-08-20 | 2021-11-05 | 中国科学院力学研究所 | Interstage separation device suitable for rocket cold separation |
| CN113865444B (en) * | 2021-10-29 | 2023-07-28 | 重庆零壹空间科技集团有限公司 | Solid rocket cold separation device and use method thereof |
| CN115231005B (en) * | 2022-09-24 | 2022-12-20 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex wave effect |
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| FR2238144A1 (en) * | 1973-07-17 | 1975-02-14 | Dassault Electronique | Gas-energised free-running gyroscope - has its wheel and gas chamber separated by pressure tight partition |
| CN2524407Y (en) * | 2001-12-07 | 2002-12-04 | 中国航天科技集团公司第四研究院第四十一所 | Rocket erector |
| US6939319B1 (en) * | 2002-11-20 | 2005-09-06 | Conrad Anstead | Process and device for single use, needle-free intradermal, subcutaneous, or intramuscular injections |
| US8479654B2 (en) * | 2006-12-14 | 2013-07-09 | Metal Storm Limited | Stackable projectile |
| CN102494565B (en) * | 2011-11-11 | 2013-10-23 | 中国航天科技集团公司第四研究院第四十一研究所 | Separation mechanism of oriented rocket nose body |
| CN203811056U (en) * | 2014-05-06 | 2014-09-03 | 江西洪都航空工业集团有限责任公司 | Unlocking device for explosive bolt |
| CN203972842U (en) * | 2014-07-10 | 2014-12-03 | 边仁杰 | The two-way baking lid of a kind of ladle tank |
| CN104458201B (en) * | 2014-12-12 | 2017-05-03 | 中国航天空气动力技术研究院 | Stage separation wind tunnel free flight test device |
| CN205918517U (en) * | 2016-05-12 | 2017-02-01 | 西安航天动力技术研究所 | Big airborne solid rocket engine aircraft climb assisting unit |
| CN107238331B (en) * | 2017-07-27 | 2018-08-17 | 董兰田 | Biphase rectification bullet shells |
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