CN110282161A - Radome fairing separator and its separation method - Google Patents
Radome fairing separator and its separation method Download PDFInfo
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- CN110282161A CN110282161A CN201910446678.5A CN201910446678A CN110282161A CN 110282161 A CN110282161 A CN 110282161A CN 201910446678 A CN201910446678 A CN 201910446678A CN 110282161 A CN110282161 A CN 110282161A
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- Prior art keywords
- radome fairing
- engine
- cover
- pushes away
- separation
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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 present invention relates to a kind of radome fairing separators of military machine technical field, including radome fairing cover, before pull out engine, side pushes away engine, apparatus to cause bursting and connection tripper, before pull out engine, side pushes away engine and apparatus to cause bursting is arranged inside radome fairing cover, before pull out engine and be located at radome fairing cover inner tip, side pushes away the rear portion that engine is pulled out before engine is located at, apparatus to cause bursting pulls out engine before being located at and side pushes away between engine, the tail portion of radome fairing cover is arranged in connection tripper, connect tripper connection radome fairing cover and main, before pull out engine, side pushes away engine, apparatus to cause bursting and connection tripper cooperate with each other, separate radome fairing cover securely and reliably with main.The present invention can in high speed, two-stage separation is being fast implemented under dense atmosphere environment, separation process structure is not interfered, and the disturbance such as oscillation, impact, pneumatic is small when separation, and separation process synchronism is good, stability is high, and separation method realizability is strong.
Description
Technical field
The present invention relates to military equipment technology fields, and in particular, to a kind of radome fairing separator and its separation method.
Background technique
Separation transmitting problem is the important mechanics problem of one kind for needing to solve in Aeronautics and Astronautics and weapon system, such as empty
Middle transmitting, the projectile of endoatmosphere aircraft, the throwing cover of aircraft, vehicle, store Combinations are launched, separation and air-breathing between rocket stage
Formula aircraft throws cover etc..With the development of military technology, vehicle rocket satellite fairing isolation technics and it is hypersonic fly
Row device isolation technics has become research emphasis in recent years.
The major function of carrier rocket satellite fairing is that rocket provides well when flight to payload in atmosphere
Environment, avoid the influence by the various disturbing factors of atmosphere；After rocket flies out atmosphere, by radome fairing jettisoning (or
Make radome fairing separation), the design of radome fairing separation system must make the top speed of crossing of radome fairing as required completely disengage rocket body, and
And any collision does not occur with payload in radome fairing or rocket body.Hypersonic aircraft separation system is to fly aircraft
Predetermined work is had been completed during row, and afterwards in-flight useless is partially separated jettisoning, so as to improve aircraft
Mass property, improve its performance.
The basic demand of separation system are as follows: to ensure that two choristas reliably connect before separation；In separation, again
Ensure that two choristas are reliably separated, and to guarantee in separation process and after separation, does not constitute and be enough to influence to continue aircraft
Crisis of normal flight, such as excessive vibration, impact, collision and environmental pollution etc..
Application No. is the Chinese invention patents of CN201410229227.3 to disclose a kind of rocket projectile connection separation mechanism, packet
Include preceding connector, rear connector, screw, key；It is connected with rear connector by the connection structure of " screw thread plus key " in preceding connector,
During the duties such as transport, carrying usually, axial attachment force is undertaken by the thread segment between preceding connector and rear connector；
The circumferential shearing force that body high speed rotation generates in transmit state is undertaken by bond structure；When carrying out lock out operation, separation
Medicine need to only destroy the fastening glue between the connection screw thread between preceding connector and rear connector and screw and full circle threaded hole, realize
It opens the cabin.But the structure design portion is reasonable, inferior separating effect.
In the separated structure of existing rocket, point type connection, the separation of radome fairing vertical structure are realized using blasting bolt,
This separated structure haves the shortcomings that as follows: being distributed in the face of being longitudinally separated, spacing about 1.5 using multiple blasting bolts in separation
Rice, the loaded rigidity of parting surface is discontinuous, and concentration of local load is excessive；Each blasting bolt separation series connection, single bolt do not separate
It will lead to separation failure；The blasting bolt separation energy is only a, not redundancy, and medicament failure will lead to blasting bolt separation failure；
The mounting base size for installing blasting bolt is big, is located at outside cowling shell, influences flight aerodynamic configuration；It flies out at a high speed after separation
Bolt head mainly by the way of partial occlusion, avoid hitting the satellite and equipment in radome fairing, barrier structure installation is complicated,
The poor reliability of arresting structure is unable to satisfy separating property requirement, meanwhile, the bolt head to fly out at a high speed hits barrier structure and generates
The shock wave of high frequency influences around to design normal work.
Therefore, it is necessary to which two-stage separation, separation process can be fast implemented under high speed, dense atmosphere environment by designing one kind
Structure is not interfered, and the disturbance such as oscillation, impact, pneumatic is small when separation, and separation process synchronism is good, stability is high, and separation method can
Realisation strong radome fairing separator and its separation method.
Summary of the invention
In view of the drawbacks of the prior art, the object of the present invention is to provide a kind of radome fairing separator and its separation method,
The present invention can in high speed, two-stage separation is being fast implemented under dense atmosphere environment, separation process structure is not interfered, and when separation shakes
It is small the disturbance such as to swing, impact, is pneumatic, separation process synchronism is good, stability is high, and separation method realizability is strong.
The present invention relates to a kind of radome fairing separator, including radome fairing cover, it is preceding pull out engine, side pushes away engine, draws
Quick-fried device and connection tripper,
Engine is pulled out before described, the side pushes away engine and the apparatus to cause bursting is arranged in the radome fairing cover
Portion,
Pull out engine before described and be located at the radome fairing cover inner tip, the side push away engine be located at it is described before pull out hair
The rear portion of motivation and mass center close to the radome fairing cover, the apparatus to cause bursting be located at it is described before pull out engine and side pushes away and starts
Between machine, the tail portion of the radome fairing cover is arranged in the connection tripper, and the connection tripper connection is described whole
Cover cover and main are flowed,
Engine is pulled out before described, side pushes away engine, apparatus to cause bursting and connection tripper match work so that described whole
Stream cover cover can mutually be separated with main.
Further, the radome fairing cover and main nested lengths account for the radome fairing cover total length ratio and are
76.49%.
Further, it is three jet pipe solid engines that engine is pulled out before described.
Further, it is jet pipe solid engines that the side, which pushes away engine,.
Further, the apparatus to cause bursting includes igniter, primacord and initiator, the igniter, the primacord
The intracorporal top of radome fairing cover, the igniter, the primacord and the initiator are arranged at the initiator
It is successively ignited according to ignition sequence.
Further, ignition sequence is first to ignite the connection tripper, then ignite it is described before pull out engine,
It finally ignites the side and pushes away engine.
Further, the connection tripper is multiple, and multiple connection trippers are evenly distributed on described whole
The periphery of cover cover is flowed, the radome fairing cover is connected as one by multiple connection trippers with main.
Further, the connection tripper is separation bolt.
Correspondingly, the invention also discloses a kind of separation method of radome fairing separator, include the following steps:
Step 1: after receiving separation firing command, apparatus to cause bursting work, connection tripper explosion unlock；
Step 2: pulling out engine before the primacord activation of apparatus to cause bursting, radome fairing cover is extracted forward；
Step 3: after radome fairing cover and main reach safe distance, fuzing system, armament primacord active side pushes away engine,
Radome fairing cover is laterally pushed open, guarantees that radome fairing cover is separated with main to safe range.
Further, the safe range is that safe distance is not less than 3m in radome fairing separation 0.5s.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, radome fairing separator of the invention can fast implement two-stage separation under high speed, dense atmosphere environment, point
Do not interfere from procedure structure, the disturbance such as oscillation, impact, pneumatic is small when separation, and separation process synchronism is good, stability is high, separation
Method realizability is strong；
2, radome fairing separator of the invention, structure is simple, compact, compact, good operating stability, reliability
By force, it applies on radome fairing, is structure as a whole before separation with radome fairing, design is rationally, practical；
3, radome fairing fast separating process of the invention, the separation method is simple, easy to operate, convenient for staff to whole
Stream cover carries out quick separating.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon.
Fig. 1 is the long nested structural schematic diagram of radome fairing of the invention；
Fig. 2 is long nested diagrammatic cross-section of the invention；
Fig. 3 is long nested diagrammatic cross-section of the invention；
Fig. 4 be it is of the invention before pull out the schematic perspective view of engine；
Fig. 5 is the schematic perspective view that side of the invention pushes away engine；
Fig. 6 is the structural schematic diagram of separation firer's subsystem of the invention；
Fig. 7 be it is of the invention before pull out two for body relative position relation figures after engine operation；
Fig. 8 is that side of the invention pushes away two body relative position relation figures after engine operation.
Wherein, corresponding appended drawing reference in figure are as follows: 1- radome fairing cover pulls out engine before 2-, and the side 3- pushes away engine, and 4- draws
Quick-fried device, 5- connection tripper.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
Embodiment
Please refer to Fig. 1-8.As shown in figures 1-8, the embodiment of the invention provides a kind of radome fairing separators, including rectification
Cover cover 1, it is preceding pull out engine 2, side pushes away engine 3, apparatus to cause bursting 4 and connection tripper 5,
Engine 2 is pulled out before described, the side pushes away engine 3 and the apparatus to cause bursting 4 is arranged at the radome fairing cover 1
Inside,
Pull out engine 2 before described and be located at 1 inner tip of radome fairing cover, the side push away engine 3 be located at it is described before
Pull out engine 2 rear portion and close to the radome fairing cover 1 mass center, the apparatus to cause bursting 4 be located at it is described before pull out 2 for He of engine
Side pushes away between engine 3, and the tail portion of the radome fairing cover 1, the connection tripper is arranged in the connection tripper 5
The 5 connections radome fairing cover 1 and main pull out engine 2 before described, side pushes away engine 3, apparatus to cause bursting 4 and connection unlock fill
It sets 5 and matches work, the radome fairing cover 1 is mutually separated with main.
It is 76.49% that the radome fairing cover 1, which accounts for the 1 total length ratio of radome fairing cover with main nested lengths,.
It is three jet pipe solid engines that engine 2 is pulled out before described.It is jet pipe solid engines that the side, which pushes away engine 3,.
The apparatus to cause bursting 4 includes igniter, primacord and initiator, the igniter, the primacord and described
Quick-fried device is arranged at the top in the radome fairing cover 1, and the igniter, the primacord and the initiator are according to ignition
Sequence is successively ignited.
Ignition sequence is first to ignite the connection tripper 5, then ignite it is described before pull out engine 2, finally draw
The quick-fried side pushes away engine 3.
The connection tripper 5 be it is multiple, multiple connection trippers 5 are evenly distributed on the radome fairing cover
The radome fairing cover 1 is connected as one by 1 periphery, multiple connection trippers 5 with main.
The connection tripper 5 is separation bolt.
Correspondingly, the invention also discloses a kind of separation method of radome fairing separator, include the following steps:
Step 1: after receiving separation firing command, apparatus to cause bursting work, connection tripper explosion unlock；
Step 2: pulling out engine before the primacord activation of apparatus to cause bursting, radome fairing cover is extracted forward；
Step 3: after radome fairing cover and main reach safe distance, fuzing system, armament primacord active side pushes away engine,
Radome fairing cover is laterally pushed open, guarantees that radome fairing cover is separated with main to safe range.
The safe range is that safe distance outer contour minimum range is not less than 3m in radome fairing separation 0.5s.
As shown in fig. 6, detonation is transferred to separation bolt 5, separation by propagation of explosion component after initiator receives separation command
After the detonation separation of bolt 5, propagation of explosion component works on, and engine ignition is pulled out before lighting in succession and side pushes away engine ignition,
Before pull out engine operation, by radome fairing, fast and stable extracts (as shown in Figure 7) forward, and after delay scheduled time, side pushes away engine
Work, radome fairing cover is laterally pushed open (as shown in Figure 8), realizes the fast and stable of radome fairing cover and the long nested structure of main
Separation.
To sum up, the separation method for the radome fairing that the present invention uses, separation disturbance is small under high speed, dense atmosphere environment, point
Simple from apparatus structure, separation process synchronism is good, stability is high, and separation method realizability is strong；Radome fairing in separation process
It is integral, good rigidity, separation disturbance is small under high speed, dense atmosphere environment, and separation process synchronism is good, stability is high；?
Solid mouse is installed in radome fairing, separating force is provided, it is ensured that will not occurred with main in long nested structure separation process dry
It relates to, stability is good, high reliablity；It fully considers under high speed, dense atmosphere environment, aerodynamic drag and perturbed force are larger, before design
Pull out engine, side pushes away engine operation timing, it is ensured that meet the safe distance requirement during high-speed separation.
Although the invention has been described by way of example and in terms of the preferred embodiments, but it is not for limiting the present invention, any this field
Technical staff without departing from the spirit and scope of the present invention, may be by the methods and technical content of the disclosure above to this hair
Bright technical solution makes possible variation and modification, therefore, anything that does not depart from the technical scheme of the invention, and according to the present invention
Technical spirit any simple modifications, equivalents, and modifications to the above embodiments, belong to technical solution of the present invention
Protection scope.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of radome fairing separator, which is characterized in that including radome fairing cover (1), it is preceding pull out engine (2), side pushes away and starts
Machine (3), apparatus to cause bursting (4) and connection tripper (5),
Engine (2) is pulled out before described, the side pushes away engine (3) and the apparatus to cause bursting (4) is arranged at the radome fairing cover
Body (1) is internal,
Engine (2) are pulled out before described and are located at radome fairing cover (1) inner tip, and the side pushes away engine (3) positioned at described
Before pull out engine (2) rear portion and close to the radome fairing cover (1) mass center, the apparatus to cause bursting (4) be located at it is described before pull out
Engine (2) and side push away between engine (3), tail of connection tripper (5) setting in the radome fairing cover (1)
Portion, the connection tripper (5) connect the radome fairing cover (1) and main,
Engine (2) is pulled out before described, side pushes away engine (3), apparatus to cause bursting (4) and connection tripper (5) match work, make
Obtaining the radome fairing cover (1) can mutually separate with main.
2. radome fairing separator according to claim 1, which is characterized in that the radome fairing cover (1) and main are embedding
It is 76.49% that set length, which accounts for radome fairing cover (1) the total length ratio,.
3. radome fairing separator according to claim 2, which is characterized in that pulling out engine (2) before described is three jet pipes
Solid engines.
4. radome fairing separator according to claim 3, which is characterized in that it is solid for jet pipe that the side pushes away engine (3)
Body engine.
5. radome fairing separator according to claim 1, which is characterized in that the apparatus to cause bursting (4) include igniter,
Primacord and initiator, the igniter, the primacord and the initiator are arranged in the radome fairing cover (1)
Top, the igniter, the primacord and the initiator are successively ignited according to ignition sequence.
6. radome fairing separator according to claim 5, which is characterized in that the ignition sequence is first to ignite the company
Connect tripper (5), then ignite it is described before pull out engine (2), finally ignite the side and push away engine (3).
7. radome fairing separator according to claim 1, which is characterized in that the connection tripper (5) be it is multiple,
Multiple connections tripper (5) are evenly distributed on the periphery of the radome fairing cover (1), multiple connection trippers
(5) the radome fairing cover (1) is connected as one with main.
8. radome fairing separator according to claim 7, which is characterized in that the connection tripper (5) is separation
Bolt.
9. a kind of separation method of radome fairing separator, which comprises the steps of:
Step 1: after receiving separation firing command, apparatus to cause bursting work, connection tripper explosion unlock；
Step 2: pulling out engine before the primacord activation of apparatus to cause bursting, radome fairing cover is extracted forward；
Step 3: after radome fairing cover and main reach safe distance, fuzing system, armament primacord active side pushes away engine, will be whole
Stream cover cover is laterally pushed open, guarantees that radome fairing cover is separated with main to safe range.
10. the separation method of radome fairing separator according to claim 9, which is characterized in that the safe range is
Radome fairing separates safe distance in 0.5s and is not less than 3m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910446678.5A CN110282161A (en) | 2019-05-27 | 2019-05-27 | Radome fairing separator and its separation method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910446678.5A CN110282161A (en) | 2019-05-27 | 2019-05-27 | Radome fairing separator and its separation method |
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| CN110282161A true CN110282161A (en) | 2019-09-27 |
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ID=68002714
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| CN201910446678.5A Pending CN110282161A (en) | 2019-05-27 | 2019-05-27 | Radome fairing separator and its separation method |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110749250A (en) * | 2019-10-30 | 2020-02-04 | 中国科学院力学研究所 | Novel hypersonic aircraft safety cover |
| CN111174647A (en) * | 2020-03-13 | 2020-05-19 | 北京星际荣耀空间科技有限公司 | Split type rotary throwing separation method of rocket fairing |
| CN112459921A (en) * | 2020-11-13 | 2021-03-09 | 上海新力动力设备研究所 | Integral air injection device with multiple obliquely-cut spray pipes and air injection method |
| CN112815789A (en) * | 2021-01-21 | 2021-05-18 | 山东宇航技术有限公司 | Fairing horizontal throwing separation device with spring pushing and punching functions |
| 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 |
| CN113173270A (en) * | 2021-04-13 | 2021-07-27 | 西安航天动力技术研究所 | Sectional type piston separating mechanism |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2076058C1 (en) * | 1993-05-13 | 1997-03-27 | Юрий Семенович Соломонов | Multi-stage missile |
| CN1685194A (en) * | 2002-09-23 | 2005-10-19 | 波音公司 | Apparatus and method for releaseably joining elements |
| CN105597334A (en) * | 2015-09-22 | 2016-05-25 | 中国航天科技集团公司第四研究院第四十一研究所 | Solid rocket carrying device loaded with telecontrolled aircraft |
| JP2017121859A (en) * | 2016-01-07 | 2017-07-13 | 川崎重工業株式会社 | Fairing, rocket provided with the same, and separation method of fairing |
| CN109573115A (en) * | 2018-12-29 | 2019-04-05 | 湖北航天技术研究院总体设计所 | Radome fairing opening device |
-
2019
- 2019-05-27 CN CN201910446678.5A patent/CN110282161A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2076058C1 (en) * | 1993-05-13 | 1997-03-27 | Юрий Семенович Соломонов | Multi-stage missile |
| CN1685194A (en) * | 2002-09-23 | 2005-10-19 | 波音公司 | Apparatus and method for releaseably joining elements |
| CN105597334A (en) * | 2015-09-22 | 2016-05-25 | 中国航天科技集团公司第四研究院第四十一研究所 | Solid rocket carrying device loaded with telecontrolled aircraft |
| JP2017121859A (en) * | 2016-01-07 | 2017-07-13 | 川崎重工業株式会社 | Fairing, rocket provided with the same, and separation method of fairing |
| CN109573115A (en) * | 2018-12-29 | 2019-04-05 | 湖北航天技术研究院总体设计所 | Radome fairing opening device |
Non-Patent Citations (1)
| Title |
|---|
| 闫杰: "高动压下的整流罩分离控制", 《吸气式高超声速飞行器控制技术》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110749250A (en) * | 2019-10-30 | 2020-02-04 | 中国科学院力学研究所 | Novel hypersonic aircraft safety cover |
| CN111174647A (en) * | 2020-03-13 | 2020-05-19 | 北京星际荣耀空间科技有限公司 | Split type rotary throwing separation method of rocket fairing |
| CN111174647B (en) * | 2020-03-13 | 2021-04-27 | 北京星际荣耀空间科技股份有限公司 | Split type rotary throwing separation method of rocket fairing |
| CN112459921A (en) * | 2020-11-13 | 2021-03-09 | 上海新力动力设备研究所 | Integral air injection device with multiple obliquely-cut spray pipes and air injection method |
| CN112815789A (en) * | 2021-01-21 | 2021-05-18 | 山东宇航技术有限公司 | Fairing horizontal throwing separation device with spring pushing and punching functions |
| CN113173270A (en) * | 2021-04-13 | 2021-07-27 | 西安航天动力技术研究所 | Sectional type piston separating mechanism |
| CN113173270B (en) * | 2021-04-13 | 2023-04-07 | 西安航天动力技术研究所 | Sectional type piston separating mechanism |
| 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 |
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Application publication date: 20190927 |