CN107941100B - A kind of rectifier stack and guided missile suitable for multi-load guided missile - Google Patents
A kind of rectifier stack and guided missile suitable for multi-load guided missile Download PDFInfo
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- CN107941100B CN107941100B CN201711116301.0A CN201711116301A CN107941100B CN 107941100 B CN107941100 B CN 107941100B CN 201711116301 A CN201711116301 A CN 201711116301A CN 107941100 B CN107941100 B CN 107941100B
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- load
- guided missile
- rectification
- support
- rectifier stack
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The present invention provides a kind of rectifier stack and guided missile suitable for multi-load guided missile, belongs to Integrated Missile Design field.The guided missile includes at least two load, the rectifier stack includes load support, rectify bar bracket and rectification bar, load support is variable cross-section hollow structure, the first end outer diameter of load support is consistent with missile cabin outer diameter, second end is closed end, second end is equipped with the mounting hole with load quantity Matching, load is symmetrically mounted on load support by mounting hole, the second end for rectifying bar bracket and load support connects, rectifying bar includes strut and disk, disk is connect by strut with rectification bar bracket, rectification bar is located at the symmetrical centre of at least two load, and in state of flight, disk is located in front of load.The purpose of rectification drag reduction is realized by the way that rectification bar is directly arranged, is avoided using radome fairing bring additional quality, is met the lightweight requirements of guided missile, improve the reliability of multi-load guided missile.
Description
Technical field
The present invention relates to a kind of Integrated Missile Design technical field, the guided missile of especially a kind of multitask load rectifies dress
It sets.
Background technique
Guided missile can encounter biggish resistance and harsh thermal environment in flight, lead to missile load failure, it is therefore desirable to
Rectifier stack is set in nose of missile, to guarantee guided missile normal flight.
Existing rectifier stack generally includes radome fairing and its separator.
With the promotion of guided missile carrying capacity, multi-load form has become the development trend of guided missile, with multi-load guided missile
Appearance, the presence of radome fairing is larger to the physical constraint of load shape envelope, be unable to satisfy the requirement of multi-load flexible configuration,
Simultaneously because the presence of radome fairing, limits guided missile lightweight and reliability.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of rectifier stack and guided missile suitable for multi-load guided missile,
The purpose of rectification drag reduction is realized by the way that rectification bar is directly arranged, avoids using radome fairing bring additional quality, disappears
In addition to radome fairing is to the physical constraint of load shape envelope, it can satisfy the flexible configuration of multi-load, meet the lightweight of guided missile
It is required that improving the reliability of multi-load guided missile.
For achieving the above object, the present invention includes following technical solution:
A kind of rectifier stack suitable for multi-load guided missile, the guided missile include at least two load, the rectifier stack
Including load support, rectification bar bracket and rectification bar, the load support is variable cross-section hollow structure, the of the load support
One end outer diameter is consistent with missile cabin outer diameter, and second end is closed end, and the second end is equipped with and the load quantity Matching
Mounting hole, the load are symmetrically mounted on the load support by the mounting hole, the rectification bar bracket and the load
The second end of lotus bracket connects, and the rectification bar includes strut and disk, and the disk passes through the strut and the rectification bar
Bracket connection, the rectification bar are located at the symmetrical centre of at least two load, and in state of flight, the disk is located at
In front of the load.
In an alternative embodiment, the rectifier stack suitable for multi-load guided missile, rectifying bar bracket further includes
Cushion block and support frame, the cushion block and the support frame correspond, and the cushion block passes through the support frame
It is arranged between two adjacent load.
In an alternative embodiment, the guided missile includes two load, and the rectification bar bracket includes two supporting legs, described
Two supporting leg one end are connect with the second end of the load support, and the other end crosses, and the rectification bar is located at described two supporting legs
The position that crosses.
In an alternative embodiment, the guided missile includes three load, and the rectification bar bracket includes three supporting legs, described
Three supporting leg one end are connect with the second end of the load support, and the other end crosses, and the rectification bar is located at three supporting legs
The position that crosses.
In an alternative embodiment, the rectification bar bracket is connected by the second end of the support frame and the load support
It connects.
In an alternative embodiment, the flatness of the installation mating surface of the load and the load support is not more than 0.1.
In an alternative embodiment, the strut is telescopic strut, and when guided missile is in non-state of flight, the strut is received
Contracting, when guided missile is in state of flight, the strut stretching, extension keeps the disk 400-500mm higher than the load.
In an alternative embodiment, the diameter of the disk is 150-250mm.
In an alternative embodiment, the combination of the profile of the second end and at least two load and the support frame
Envelope contour matching.
A kind of multi-load guided missile, including at least two load and bay section, further include rectifier stack, and the rectifier stack includes
Load support, rectification bar bracket and rectification bar, the load support are variable cross-section hollow structure, the first end of the load support
Outer diameter is consistent with the bay section outer diameter, connect with the bay section, and the second end of the load support is closed end, the second end
Equipped with the mounting hole with the load quantity Matching, the load is symmetrically mounted on the load support by the mounting hole
On, the rectification bar bracket is connect with the second end of the load support, and the rectification bar includes strut and disk, the disk
It being connect by the strut with the rectification bar bracket, the rectification bar is located at the symmetrical centre of at least two load, and
In state of flight, the disk is located in front of the load.
Compared with the prior art, the invention has the advantages that:
(1) rectifier stack provided in an embodiment of the present invention suitable for multi-load guided missile, by setting load support one end
It is set to enclosed construction, constantly acting load is installed by the mounting hole at the end, outer gas stream is to bay section internal unit when avoiding flight
Influence, bar will be rectified by setting rectification bar bracket the symmetrical centre of load is set and rectify the disk position of bar in flight
In front of load, the flow field structure of multi-load nose of missile is changed, the interference between multi-load is reduced, realizes rectification drag reduction
Purpose, avoid and eliminate radome fairing using radome fairing bring additional quality to the physics of load shape envelope about
Beam can satisfy the flexible configuration of multi-load, meet the lightweight requirements of guided missile, improve the reliability of multi-load guided missile；
(2) by setting cushion block, colliding with each other between each load is avoided.
Detailed description of the invention
Fig. 1 rectifier stack structural schematic diagram provided in an embodiment of the present invention suitable for multi-load guided missile；
Fig. 2 is rectifier stack provided in an embodiment of the present invention and load assembling structure schematic diagram；
Fig. 3 is another viewing angle constructions schematic diagram after rectifier stack provided in an embodiment of the present invention and load assembly；
Fig. 4 a is rectifier stack part provided in an embodiment of the present invention and three load assembling schematic diagrams；
Fig. 4 b is the rectifier stack partial structural diagram provided in an embodiment of the present invention for being suitable for three load guided missiles；
Fig. 5 a is rectifier stack part provided in an embodiment of the present invention and four load assembling schematic diagrams；
Fig. 5 b is the rectifier stack partial structural diagram provided in an embodiment of the present invention for being suitable for four load guided missiles；
Fig. 6 is the rectifier stack provided in an embodiment of the present invention for being suitable for four load guided missiles and four load assembling schematic diagrams；
Fig. 7 is the top view after the rectifier stack that embodiment 1 provides and the assembly of two load；
Fig. 8 a is the aerodynamic force analogous diagram after the rectifier stack assembly that embodiment 1 provides；
Fig. 8 b is the aerodynamics simu1ation figure after the rectifier stack assembly that comparative example 2 provides.
Specific embodiment
The working principle of the invention is further explained and is illustrated with reference to the accompanying drawing.
Referring to Fig. 1 and Fig. 2, the embodiment of the invention provides a kind of rectifier stacks suitable for multi-load guided missile, such as Fig. 2 institute
Showing, the guided missile includes at least two load 6, and the rectifier stack includes load support 1, rectifies bar bracket 4 and rectification bar 5,
As shown in Figure 1, load support 1 is variable cross-section hollow structure, the first end outer diameter of load support 1 is consistent with missile cabin outer diameter,
Second end is closed end, and the second end is equipped with the mounting hole 11 with 6 quantity Matching of load, and load 6 is symmetrical by mounting hole 11
It is mounted on load support 1, rectification bar bracket 4 is connect with the second end of load support 1, and rectification bar 5 includes strut 51 and disk
52, disk 52 is connect by strut 51 with rectification bar bracket 4, and rectification bar 5 is located at the symmetrical centre of at least two load, and
In state of flight, disk 52 is in the front of load 6.
Specifically, in the embodiment of the present invention, load 6 may include guided missile warhead, bait and penetration aids etc., and the present invention is not
It limits；Specifically, in the embodiment of the present invention, to be further reduced resistance, the profile A of 1 second end of load support is with Missile Body
Head Design of Aerodynamic Configuration, it is preferably consistent or almost the same with the envelope contour for all components being directly connected to therewith；The present invention is real
Example is applied using heading as positive direction, disk 52 is located at 6 front of load.
Rectifier stack provided in an embodiment of the present invention suitable for multi-load guided missile, by the way that load support one end to be arranged to
Enclosed construction installs constantly acting load, shadow of the outer gas stream to bay section internal unit when avoiding flight by the mounting hole at the end
It rings, rectification bar is arranged in the symmetrical centre of load by setting rectification bar bracket, in flight, the disk for rectifying bar, which is located at, to be carried
In front of lotus, the flow field structure of multi-load nose of missile is changed, the interference between multi-load is reduced, realizes the mesh of rectification drag reduction
, it avoids using radome fairing bring additional quality, eliminates radome fairing to the physical constraint of load shape envelope, it can
To meet the flexible configuration of multi-load, meet the lightweight requirements of guided missile, improves the reliability of multi-load guided missile.
Further, the rectifier stack suitable for multi-load guided missile further includes cushion block 3 and support frame 2, is delayed
It rushes cushion block 3 and support frame 2 corresponds, cushion block 3 is arranged between two adjacent load 6 by support frame 2.Cushion
The preferred natural rubber of block 3 or fluorubber.By the way that cushion block is arranged, colliding with each other between each load is avoided.
In in an optional implementation, cushion block 3 can be the cushion block formed by shedding airbag fold, shed air bag use
Multilayer flexible material is cladded with damping material, such as natural rubber or fluorubber；By the way that air bag will be shed as cushion block, throw
Spilling air bag can be with gas generator and piping connection inside guided missile, separation in bullet separation, between bullet and load support
Nut work releases connected between bullet and load support, the preset spring works being pressed below bullet, forward by bullet
A distance is pushed, guarantees that engine jet pipe is extracted from load support, then, air bag inflation is shed, pushes controllable bullet past
Left and right sides separation, the position and inflation rule for shedding air bag can be adjusted according to bullet centroid position, to ensure to separate appearance
State.
Referring to Fig. 1-3, in an alternative embodiment, the guided missile includes two load 6, and rectification bar bracket 4 includes two
Supporting leg, described two supporting leg one end are connect by support frame 2 with the second end of load support 1, and the other end crosses, and rectify 5, bar
In the position that crosses of described two supporting legs.
Referring to fig. 4, the guided missile includes three load 6, and rectification bar bracket 4 includes three supporting legs, three supporting legs one
End is connect by three support frames 2 with the second end of load support 1 respectively, and the other end crosses, and rectification bar 5 is located at three branch
The position that crosses of leg.As shown in figure 4, three support frames 2 are connected to form a whole back-to-back in the present embodiment, the structure branch
Support is firm, and is convenient for location and installation.
And so on, as shown in figure 5, the embodiment of the present invention can also include 4 load and 5 load etc..
For the airtightness for further increasing 1 second end of load support, load 6 and the installation mating surface of load support 1 (are carried
The outer surface of 1 installation position of lotus and the inner surface of mounting hole wall) flatness be not more than 0.1.
In an alternative embodiment, strut 51 is telescopic strut, and when guided missile is in non-state of flight, strut is shunk, when
When guided missile is in state of flight, strut stretching, extension makes the high 400-500mm of 52 weight/HP ratio of disk 6.When disk is excessively high, the rectification of formation
Flow field regions are too small, and rectification effect is poor, when too low, are easy to cause resistance excessive with load collective effect.
The diameter of the disk is 150-250mm, and the preferred 25-75mm of thickness can bring resistance when disk diameter is excessive
Increase, has served as hour, rectification effect cannot be reached.
The embodiment of the invention also provides a kind of multi-load guided missiles, including at least two load and bay section, further include rectification
Component, the rectifier stack include load support, rectification bar bracket and rectification bar, and the load support is the hollow knot of variable cross-section
Structure, the first end outer diameter of the load support is consistent with the bay section outer diameter, connect with the bay section, and the of the load support
Two ends are closed end, and the second end is equipped with the mounting hole with the load quantity Matching, and the load passes through the mounting hole
It is symmetrically mounted on the load support, the rectification bar bracket is connect with the second end of the load support, the rectification bar
Including strut and disk, the disk is connect by the strut with the rectification bar bracket, the rectification bar described in extremely
The symmetrical centre of few two load.
The preferably above-mentioned rectifier stack embodiment of the rectifier stack that the present embodiment uses provides, and specifically describes referring to above-mentioned implementation
Example, details are not described herein.
The following are a specific embodiments of the invention:
Embodiment 1
The rectifier stack for present embodiments providing a kind of double load guided missiles, as shown in Fig. 2, the rectifier stack includes load
Bracket 1, cushion block 3, support frame 2, rectification bar bracket 4 and rectification bar 5；As shown in Figure 1, load support 1 is that variable cross-section is hollow
Structure, the first end of load support 1 are circle, and outer diameter is consistent with missile cabin outer diameter, there are two 1 second end of load support is removed and set
Outside mounting hole 11, the closing of other positions；Two load 6 are symmetrically mounted on load support 1 by two mounting holes 11 respectively, and
The flatness of load 6 and the installation mating surface of load support 1 is 0.1；Cushion block 3 is arranged by support frame 2 in load support 1
The medium position of second end end face makes the discrete two sides of two load 6；It rectifies bar bracket 4 and passes through support frame 2 and load support 1
Second end connection, as shown in fig. 7, the envelope contour a of two load 6 and support frame 2 is similar to ellipse, load support 1 second
The profile A at end is ellipse；Rectifying bar 5 includes strut 51 and disk 52, and 52 diameter of disk is 200mm, with a thickness of 50mm, disk
52 are connect by strut 51 with rectification bar bracket 4, and rectification bar 5 is located at the symmetrical centre of at least two load, and strut 51
For telescopic support struts, in state of flight, strut stretching, extension makes disk 52 the front 500m of load 6 at, when non-state of flight, props up
Bar is shunk.
Comparative example 1
This comparative example provides a kind of rectifier stack of double load guided missiles, what the rectifier stack structure and embodiment 1 provided
Rectifier stack structure is identical, unique the difference is that being not provided with rectification bar bracket 4 and rectification bar 5.
Comparative example 2
This comparative example provides a kind of rectifier stack of double load guided missiles, which includes radome fairing and be arranged whole
The outer rectification bar connecting with radome fairing of stream cover, the load of application are same as Example 1.
Referring to Fig. 8, aerodynamic force simulation calculation is carried out to embodiment 1, comparative example 1 and comparative example 2, is found in Ma2 or less,
The rectifier stack aerodynamic drag reduction that embodiment 1 provides is unobvious, but significantly reduces pressure disturbances area between two bullets, reduces
Aerodynamic force and Aerodynamic Heating between bullet；The shock wave formed when Ma2 or more high speed effectively reduces aerodynamic drag；
The frictional-loss coefficient of comparative example 2 is 0.2846, and 1 frictional-loss coefficient of embodiment is 0.2669, it can be seen that, it is real
The rectifier stack for applying the offer of example 1 adds the rectification rectifier stack rectification effect of rod type suitable with radome fairing.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.The specific embodiment is only pair
Spirit of that invention gives an example.The personnel of the technical field of the invention can do different repair to the specific embodiment
Change or supplement or replace by a similar method, but without departing from spirit of the invention or surmounts the appended claims and defined
Range.
Claims (10)
1. a kind of rectifier stack suitable for multi-load guided missile, the guided missile includes at least two load, which is characterized in that described
Rectifier stack includes load support, rectification bar bracket and rectification bar, and the load support is variable cross-section hollow structure, the load
The first end outer diameter of bracket is consistent with missile cabin outer diameter, and second end is closed end, and the second end is equipped with and the charge number
Flux matched mounting hole, the load are symmetrically mounted on the load support by the mounting hole, the rectification bar bracket
It is connect with the second end of the load support, the rectification bar includes strut and disk, and the disk passes through the strut and institute
Rectification bar bracket connection is stated, the rectification bar is located at the symmetrical centre of at least two load, and in state of flight, described
Disk is located in front of the load.
2. the rectifier stack according to claim 1 suitable for multi-load guided missile, which is characterized in that further include cushion block
And support frame, the cushion block and the support frame correspond, the cushion block is arranged by the support frame in phase
Between two adjacent load.
3. the rectifier stack according to claim 1 suitable for multi-load guided missile, which is characterized in that the guided missile includes two
A load, the rectification bar bracket include two supporting legs, and described two supporting leg one end are connect with the second end of the load support,
The other end crosses, and the rectification bar is located at the position that crosses of described two supporting legs.
4. the rectifier stack according to claim 1 suitable for multi-load guided missile, which is characterized in that the guided missile includes three
A load, the rectification bar bracket include three supporting legs, and described three supporting leg one end are connect with the second end of the load support,
The other end crosses, and the rectification bar is located at the position that crosses of three supporting legs.
5. the rectifier stack according to claim 2 suitable for multi-load guided missile, which is characterized in that the rectification bar bracket
It is connect by the support frame with the second end of the load support.
6. the rectifier stack according to claim 1 suitable for multi-load guided missile, which is characterized in that the load with it is described
The flatness of the installation mating surface of load support is not more than 0.1.
7. the rectifier stack according to claim 1 suitable for multi-load guided missile, which is characterized in that the strut is flexible
Strut, when guided missile is in non-state of flight, the strut is shunk, and when guided missile is in state of flight, the strut stretching, extension makes
The disk is 400-500mm higher than the load.
8. the rectifier stack according to claim 1 or claim 7 suitable for multi-load guided missile, which is characterized in that the disk
Diameter is 150-250mm.
9. the rectifier stack according to claim 2 suitable for multi-load guided missile, which is characterized in that the wheel of the second end
The wide combination envelope contour at least two load and the support frame matches.
10. a kind of multi-load guided missile, including at least two load and bay section, which is characterized in that it further include rectifier stack, it is described whole
Stream component includes load support, rectification bar bracket and rectification bar, and the load support is variable cross-section hollow structure, the load branch
The first end outer diameter of frame is consistent with the bay section outer diameter, connect with the bay section, and the second end of the load support is closed end,
The second end is equipped with the mounting hole with the load quantity Matching, and the load is symmetrically mounted on described by the mounting hole
On load support, the rectification bar bracket is connect with the second end of the load support, and the rectification bar includes strut and disk,
The disk is connect by the strut with the rectification bar bracket, and the rectification bar is located at the symmetrical of at least two load
Center, and in state of flight, the disk is located in front of the load.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711116301.0A CN107941100B (en) | 2017-11-13 | 2017-11-13 | A kind of rectifier stack and guided missile suitable for multi-load guided missile |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711116301.0A CN107941100B (en) | 2017-11-13 | 2017-11-13 | A kind of rectifier stack and guided missile suitable for multi-load guided missile |
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| Publication Number | Publication Date |
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| CN107941100A CN107941100A (en) | 2018-04-20 |
| CN107941100B true CN107941100B (en) | 2019-08-09 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003016849A2 (en) * | 2001-08-13 | 2003-02-27 | Allied Aerospace Industries, Inc. | Method and apparatus for testing engines |
| CN102954740A (en) * | 2012-11-16 | 2013-03-06 | 上海宇航系统工程研究所 | Hood capturing device of reverse thrust rocket fairing and capturing method thereof |
| CN206269681U (en) * | 2016-12-15 | 2017-06-20 | 福州幻科机电科技有限公司 | Escape tower radome fairing booster rocket with the remote control hang gliding tail vane wing |
| CN107238331A (en) * | 2017-07-27 | 2017-10-10 | 董兰田 | Biphase rectification bullet shells |
-
2017
- 2017-11-13 CN CN201711116301.0A patent/CN107941100B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003016849A2 (en) * | 2001-08-13 | 2003-02-27 | Allied Aerospace Industries, Inc. | Method and apparatus for testing engines |
| CN102954740A (en) * | 2012-11-16 | 2013-03-06 | 上海宇航系统工程研究所 | Hood capturing device of reverse thrust rocket fairing and capturing method thereof |
| CN206269681U (en) * | 2016-12-15 | 2017-06-20 | 福州幻科机电科技有限公司 | Escape tower radome fairing booster rocket with the remote control hang gliding tail vane wing |
| CN107238331A (en) * | 2017-07-27 | 2017-10-10 | 董兰田 | Biphase rectification bullet shells |
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| Publication number | Publication date |
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| CN107941100A (en) | 2018-04-20 |
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