CN106370056A - Device capable of realizing launch of leaving guide rails simultaneously by combined supporting of adaptor and projectile belt - Google Patents
Device capable of realizing launch of leaving guide rails simultaneously by combined supporting of adaptor and projectile belt Download PDFInfo
- Publication number
- CN106370056A CN106370056A CN201610779855.8A CN201610779855A CN106370056A CN 106370056 A CN106370056 A CN 106370056A CN 201610779855 A CN201610779855 A CN 201610779855A CN 106370056 A CN106370056 A CN 106370056A
- Authority
- CN
- China
- Prior art keywords
- guide rail
- adapter
- bearing band
- supporting
- projectile
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Support Of The Bearing (AREA)
Abstract
The invention discloses a device capable of realizing launch of leaving guide rails simultaneously by combined supporting of an adaptor and a projectile belt. The device comprises an upper restricting guide rail, a high lower guide rail, a low lower guide rail and the adapter, wherein the lateral motion of the rear half, behind the mass center of a projectile body, of the projectile body is restricted by the upper restricting guide rail and the high lower guide rail through the projectile belt; an orienting knob on the projectile belt and the high lower guide rail cooperate with each other to restrict the circumferential rotation of the projectile body; the front half, before the mass center of the projectile body, of the projectile body is supported by the adapter which is in clearance fit with the low lower guide rail; the adapter and the projectile body move together in the axial direction of the projectile body during a launching restriction period; and the adapter is divorced from the projectile body while being separated from the low lower guide rail, and meanwhile the projectile belt breaks away from the restrictions of the upper restricting guide rail and the high lower guide rail simultaneously. The device provided by the invention ensures the advantages of realizing launch of leaving guide rails simultaneously, meanwhile has the characteristics of simple structure, reliable movement, no influence on aerodynamic characteristics of the projectile body and the like, and can provide a guarantee for safe and reliable launch of leaving guide rails simultaneously.
Description
Technical field
The present invention relates to the discharger that leaves the right or normal track while a kind of rocket projectile, guided missile, this discharger be used for realizing rocket projectile,
Leave the right or normal track while guided missile directional transmissions.
Background technology
When rocket projectile, guided missile tilt transmitting, orientation support pattern is impact initial disturbance, and then affects emission security trajectory
Distribution and the key factor of control efficiency.In current rocket projectile, guided missile launcher, mainly have non-concurrent leave the right or normal track and
Leave the right or normal track two class modes simultaneously.Non-concurrent leaves the right or normal track mode when body barycenter leaves orientation supporting structure, and the gravity of body is at rear portion
The moment that orientation bearing position produces can lead to rocket projectile, guided missile to produce angle of significantly bowing, and increases initial disturbance during transmitting.
The mode that simultaneously leaves the right or normal track, in emission process, discharges to the supporting of the orientation of body simultaneously, can effectively reduce body and bows and bring
Initial disturbance, is at home and abroad applied in many types of device, the such as beagle of the U.S., Nai Ji, patriot i, ii, Muscovite
The rocket projectiles such as sa-2, sa-6 and Fu Laoke or guided missile all employ the directional transmissions mode that simultaneously leaves the right or normal track.
Leave the right or normal track at the same time in radiation pattern, dry for avoiding body integral sinking under gravity and discharger to produce
Relate to, constraint or the supporting of body can be realized using various ways.Typical mode have under body mode of hanging, guide rail convert into mode with
And ladder support pattern.Wherein under body, the hanging cooperation by the leg on body and guide rail hangs over body under orientation guide rail
, there is the interference being enough prevented effectively between body integral sinking and guide rail side, but firing box (cylinder) entirety stiffness is required higher；Lead
Body is bearing in above guide rail by rail convertible, and body leaves the right or normal track moment, and guide rail quickly converts under particular organization effect drops to the ground, with
Avoid the interference between body integral sinking and guide rail, structure is complex, and reliability is relatively low；Ladder support pattern adopt front low after
High guide rail form is matched with body leg, with the collision sunk with fromer rail after avoiding body to leave the right or normal track, due on body
Leg need match with ladder guide rail, it usually needs using the stand bar structure of large-size, in projectile flight to rocket projectile,
The aerodynamic characteristic of guided missile has appreciable impact.
Content of the invention
In view of this, the invention provides the discharger that leaves the right or normal track while the supporting of a kind of adapter and bearing band combines,
Ensure to leave the right or normal track simultaneously transmitting advantage while, have that structure is simple, reliable in action, the features such as do not affect body aerodynamic characteristic, energy
The transmitting that leaves the right or normal track while being enough safe and reliable provides safeguard.
The supporting of adapter and bearing band leaves the right or normal track while combining discharger, and this device includes practical upper bound guide rail, bottom
High guide rail, the low guide rail in bottom and adapter, ancillary equipment is bearing band and orientation button on body and body；
The latter half of the barycenter of body passes through bearing band and constrains the lateral of body by the high guide rail of practical upper bound guide rail and bottom
Motion, the orientation button on bearing band is circumferentially rotated with bottom high guide rail fiting constraint body, and the first half of the barycenter of body leads to
Cross the adapter that low guide clearance coordinates with bottom to realize supporting, adapter and body are within the transmitting constraint phase jointly along body axle
To motion, while adapter guide rail low with bottom separates also with body depart from, bearing band lose simultaneously practical upper bound guide rail and under
The constraint to it for portion's upper rail.
Further, when conjunction thorax puts in place, adapter and bottom low guide rail contacting surface tailing edge are to bottom low guide rail front end face
Distance is equal with the distance of bearing band and bottom high guide rail contacting surface tailing edge to bottom high guide rail front end face.
Further, pass through the gap fiting constraint of boss and groove between the low guide rail of described adapter lower surface and bottom
Adapter lateral movement and deflection.
Further, the bearing band on described body and the high guide rail contact of practical upper bound guide rail and bottom coordinate, and by upper
Portion constrains the v shape contact surface constraints body lateral movement of the high guide rail of v shape contact surface and bottom of guide rail.
Further, described adapter includes body, cut spring, seat pin and guide ring, and the bottom of seat pin is fixed on this
In seat pin mounting groove on body, cut spring is sleeved on seat pin, and guide ring is assemblied in the stepped hole of the upper end of seat pin mounting groove
Interior, coordinate for gap between guide ring and stepped hole, two ends ring flange and the guide ring with seat pin bottom respectively of cut spring
Contact；The head of seat pin is coordinated with the cooperation interporal lacuna on body, and body is contacted with guide ring and separated by guide ring compression
Spring.
Further, described body is machined with pneumatic parting surface, the aerodynamic force that pneumatic parting surface produces can promote
Adapter is separated with body.
Further, described body adopts expanded material.
Beneficial effect: the present invention achieves rocket using adapter with the bearing band supporting mode of combining or guided missile leaves the right or normal track simultaneously
Tilt transmitting, be conducive to reducing the angle disturbance of bowing of body launching phase；The using cooperatively, of adapter and bearing band on body not
Need to increase the structure of the impact aerodynamic force such as leg, reduce the impact to body aerodynamic configuration；The making of v shape contact surface guide rail
With constraining vertical, lateral motion and rotational freedom, reducing the complexity of discharger structure simultaneously.
Brief description
Fig. 1 is the overall structure diagram of the present invention.
Fig. 2 is the left view of Fig. 1；
Fig. 3 is the right view of Fig. 1；
Fig. 4 is the structural representation of adapter；
Fig. 5 is that during transmitting, adapter leaves the right or normal track view.
Wherein, 1- body, 2- bearing band, 3- orientation button, 4- practical upper bound guide rail, the high guide rail in 5- bottom, the low guide rail in 6- bottom,
7- adapter, 8- body, 9- cut spring, 10- seat pin, 11- guide ring, 12- barycenter, the pneumatic parting surface of 13-.
Specific embodiment
Develop simultaneously embodiment below in conjunction with the accompanying drawings, describes the present invention.
As shown in Figure 1, the invention provides the discharger that leaves the right or normal track while the supporting of a kind of adapter and bearing band combines,
This device includes practical upper bound guide rail 4, the high guide rail in bottom 5, the low guide rail in bottom 6 and adapter 7, ancillary equipment be body 1 and
Bearing band 2 on body and orientation button 3；
The difference in height of the high guide rail of the low guide rail in bottom 6 and bottom 5 crosses the low guide rail in bottom 6 front end by body breech face when launching
Deflection during face determines, the low guide rail in bottom 6 upper surface has boss or groove for being coordinated with adapter 7；Bottom is high
Guide rail 5 upper surface adopts v shape structure, and milling in the middle part of it is put down and had gathering sill.Practical upper bound guide rail is v shape structure, such as accompanying drawing 2 He
Shown in 3.
Adapter 7 is arranged in barycenter 12 front lower place of body 1, adapter 7 and the cooperation of the low guide rail contact in bottom；Bearing band 2 He
Orientation button 3 is arranged in body barycenter rear, and high guide rail 5 is engaged with bottom.
The latter half of the barycenter 12 of body 1 constrains body 1 by bearing band 2 by the high guide rail of practical upper bound guide rail 4 and bottom 5
Lateral movement, orientation the circumferentially rotating of button 3 high guide rail 5 fiting constraint body 1 with bottom on bearing band 2, the barycenter 12 of body 1
First half realize supporting by the adapter 7 of the cooperation of low guide rail 6 gap with bottom, adapter 7 and body 1 are in transmitting constraint
Jointly along body axially-movable in phase, also depart from body while adapter 7 guide rail 6 low with bottom separates, bearing band 2 loses simultaneously
Go the constraint to it of practical upper bound guide rail 4 and bottom upper rail 5.
Adapter 7 upper surface is engaged with body 1 surface, adapter lower surface and low guide rail contact, and passes through boss
Gap fiting constraint adapter lateral movement with groove and deflection；Bearing band on body and high guide rail contact cooperation, and pass through
The v shape contact surface constraints body lateral movement of the v shape contact surface of the high guide rail in bottom 5 and practical upper bound guide rail 4.Orientation on body
Button is coordinated with the gathering sill gap on high guide rail, and constraint body circumferentially rotates.
As shown in Figure 3, adapter 7 includes body 8, cut spring 9, seat pin 10 and guide ring 11, and body 8 front end face is opened
As pneumatic parting surface, body 8 adopts expanded material on 45 degree of inclined-planes；The bottom of seat pin 10 is fixed on the seat pin mounting groove on body
Interior, cut spring 9 is sleeved on seat pin, and guide ring 11 is assemblied in the step in the hole of the upper end of seat pin mounting groove, guide ring 11 with
Coordinate for gap between stepped hole, the two ends of cut spring 9 are contacted with the ring flange of seat pin 10 bottom and guide ring 11 respectively；Seat
The head of pin 10 is coordinated with the cooperation interporal lacuna on body 1, and body 1 is contacted with guide ring 11 and separates bullet by guide ring compression
Spring 9.
Rocket, guided missile are left the right or normal track while being combined with bearing band supporting using adapter when radiation pattern is implemented and launched and include closing
Lock, the motion of constraint phase, three states of unconfinement phase motion, its operation principle is:
1) blocking.In the lockout condition, body 1 is played blocking device using gear and is connected with the high guide rail in bottom 5, in transmitting
Before, blocking device discharges, and so that body 1 is moved axially forwards along guide rail.Gear plays blocking device and is not belonging to the concrete of the present invention
Content.
2) constraint phase motion.After the motion of constraint phase refers to rocket or guided missile igniting, componental movement degree of freedom is subject to discharger about
The kinestate of bundle.In constraint phase motion stage, body 1 acts on lower edge directive (body is axially) motion in motor power, its
Its freedom of motion enters row constraint by each structure in the present invention.Wherein body vertical sunken caves degree of freedom by adapter 7 with
Bearing band 2 supports common constraint, and the vertical upper jump motion of body 1 is constrained by practical upper bound guide rail 4, and body elevating movement is led by bottom height
Rail 5 and practical upper bound guide rail 4 constrain jointly, body 1 lateral movement and lateral deflection by the high guide rail in bottom 5 V-shaped contact surface and
The V-shaped contact surface of practical upper bound guide rail 4 constrains jointly, and body 1 circumferentially rotates by the gathering sill of orientation button 3 and the high guide rail in bottom 5
Coordinate into row constraint.In constraint phase motion stage, adapter 7 under with body 1 by the effect of the seat pin 10 of shaft hole matching with bullet
Body 1 moves along directive together.
3) unconfinement phase motion.Reach the low guide rail in bottom in the contact surface tailing edge of adapter 7 lower surface and the low guide rail in bottom 6
During 6 front end face, bearing band 2 reaches the high guide rail in bottom 5 front end face with the contact surface tailing edge of the high guide rail in bottom 5 simultaneously, now transmitting dress
Put the degree of freedom constraint release to body 1 motion, body 1 enters the motion of unconfinement phase.After adapter constraint release, adapter is subject to
The aerodynamic force producing on cut spring pretightning force, pneumatic parting surface and gravity collective effect, pass through axis hole gap with body 1
Cooperation in the hole abjection from body for the seat pin 10 of the adapter 7 of cooperation, adapter 7 is rapidly separated and comes off from body 1 surface,
Referring to accompanying drawing 5.Hereafter, body 1 is no longer influenced by the impact of discharger, continues fortune under motor power and Aerodynamic force action
Dynamic.
In sum, these are only presently preferred embodiments of the present invention, be not intended to limit protection scope of the present invention.
All any modification, equivalent substitution and improvement within the spirit and principles in the present invention, made etc., should be included in the present invention's
Within protection domain.
Claims (7)
1. adapter leaves the right or normal track discharger it is characterised in that this device includes practical upper bound while combining with bearing band supporting
Guide rail, the high guide rail in bottom, the low guide rail in bottom and adapter, ancillary equipment is bearing band and orientation button on body and body；
The latter half of the barycenter of body passes through the lateral movement that bearing band is constrained body by the high guide rail of practical upper bound guide rail and bottom,
The circumferentially rotating of orientation button and bottom high guide rail fiting constraint body on bearing band, the first half of the barycenter of body by with
The adapter of portion's low guide clearance cooperation is realized supporting, and adapter and body are common within the transmitting constraint phase axially to be transported along body
Dynamic, also depart from body while adapter guide rail low with bottom separates, bearing band loses on practical upper bound guide rail and bottom simultaneously
The constraint to it for the guide rail.
2. adapter as claimed in claim 1 leaves the right or normal track discharger with bearing band supporting it is characterised in that closing while combining
When thorax puts in place, the distance of adapter and bottom low guide rail contacting surface tailing edge to bottom low guide rail front end face is led with bottom height with bearing band
The distance of rail contact surface tailing edge to bottom high guide rail front end face is equal.
3. adapter as claimed in claim 1 or 2 and bearing band supporting leaves the right or normal track while combining discharger, and its feature exists
In by the gap fiting constraint adapter lateral movement of boss and groove between the low guide rail of described adapter lower surface and bottom
And deflection.
4. the supporting of adapter as claimed in claim 3 and bearing band leaves the right or normal track discharger it is characterised in that institute while combining
The bearing band stated on body is coordinated with the high guide rail contact of practical upper bound guide rail and bottom, and by the v shape contact of practical upper bound guide rail
The v shape contact surface constraints body lateral movement of the high guide rail in face and bottom.
5. the supporting of adapter as claimed in claim 3 and bearing band leaves the right or normal track discharger it is characterised in that institute while combining
State adapter and include body, cut spring, seat pin and guide ring, the bottom of seat pin is fixed in the seat pin mounting groove on body,
Cut spring is sleeved on seat pin, and guide ring is assemblied in the step in the hole of the upper end of seat pin mounting groove, guide ring and stepped hole it
Between for gap cooperation, the two ends of cut spring are contacted with the ring flange of seat pin bottom and guide ring respectively；The head of seat pin and bullet
Cooperation interporal lacuna cooperation on body, body is contacted with guide ring and compresses cut spring by guide ring.
6. the supporting of adapter as claimed in claim 5 and bearing band leaves the right or normal track discharger it is characterised in that institute while combining
State and pneumatic parting surface is machined with body, the aerodynamic force that pneumatic parting surface produces can promote adapter to separate with body.
7. the supporting of adapter as claimed in claim 6 and bearing band leaves the right or normal track discharger it is characterised in that institute while combining
State body and adopt expanded material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610779855.8A CN106370056B (en) | 2016-08-30 | 2016-08-30 | Adapter leaves the right or normal track emitter while bearing band bearing is combined |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610779855.8A CN106370056B (en) | 2016-08-30 | 2016-08-30 | Adapter leaves the right or normal track emitter while bearing band bearing is combined |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106370056A true CN106370056A (en) | 2017-02-01 |
| CN106370056B CN106370056B (en) | 2018-06-19 |
Family
ID=57898750
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610779855.8A Active CN106370056B (en) | 2016-08-30 | 2016-08-30 | Adapter leaves the right or normal track emitter while bearing band bearing is combined |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106370056B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144181A (en) * | 2017-06-28 | 2017-09-08 | 北京航天三发高科技有限公司 | One kind closes thorax machine and its application method |
| CN107643020A (en) * | 2017-10-13 | 2018-01-30 | 南京理工大学 | A kind of new adaptor for being applicable to special-shaped bullet |
| CN108534602A (en) * | 2018-05-29 | 2018-09-14 | 湖北三江航天万峰科技发展有限公司 | The adjustment method and its regulating mechanism of the small-bore double V-shaped guide rail of firing box |
| CN109895412A (en) * | 2019-02-26 | 2019-06-18 | 湖北三江航天万峰科技发展有限公司 | A kind of adapter moulding process |
| CN110193208A (en) * | 2019-05-23 | 2019-09-03 | 北京机电工程研究所 | Aircraft model transmitting tube adapter and model emission test system |
| CN112696978A (en) * | 2020-12-24 | 2021-04-23 | 彩虹无人机科技有限公司 | Small missile ground launching height falling prevention method |
| CN113772114A (en) * | 2021-10-18 | 2021-12-10 | 贵州航天天马机电科技有限公司 | Aircraft adapter and manufacturing method thereof |
| CN114414626A (en) * | 2022-01-21 | 2022-04-29 | 安徽理工大学 | Combustible gas detonation drive generator for high-speed loading |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1073399A (en) * | 1996-09-02 | 1998-03-17 | Mitsubishi Electric Corp | Launching cylinder for guided airframe |
| DE102011109839A1 (en) * | 2011-08-09 | 2013-02-28 | Diehl Bgt Defence Gmbh & Co. Kg | Method for attaching e.g. guided shooting missile to e.g. rocket launcher in airplane, involves removing protective cap from one interface such that another interface is connected with protective cap |
| CN203857870U (en) * | 2014-05-13 | 2014-10-01 | 北京理工大学 | Adapter guide rail combined box type launching device |
| CN104864774A (en) * | 2015-05-25 | 2015-08-26 | 北京理工大学 | Self-catapulting launching device for guided missile |
| CN105151350A (en) * | 2015-09-02 | 2015-12-16 | 北京航天发射技术研究所 | Boxing device for simultaneous de-orbit firing |
-
2016
- 2016-08-30 CN CN201610779855.8A patent/CN106370056B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1073399A (en) * | 1996-09-02 | 1998-03-17 | Mitsubishi Electric Corp | Launching cylinder for guided airframe |
| DE102011109839A1 (en) * | 2011-08-09 | 2013-02-28 | Diehl Bgt Defence Gmbh & Co. Kg | Method for attaching e.g. guided shooting missile to e.g. rocket launcher in airplane, involves removing protective cap from one interface such that another interface is connected with protective cap |
| CN203857870U (en) * | 2014-05-13 | 2014-10-01 | 北京理工大学 | Adapter guide rail combined box type launching device |
| CN104864774A (en) * | 2015-05-25 | 2015-08-26 | 北京理工大学 | Self-catapulting launching device for guided missile |
| CN105151350A (en) * | 2015-09-02 | 2015-12-16 | 北京航天发射技术研究所 | Boxing device for simultaneous de-orbit firing |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144181A (en) * | 2017-06-28 | 2017-09-08 | 北京航天三发高科技有限公司 | One kind closes thorax machine and its application method |
| CN107144181B (en) * | 2017-06-28 | 2023-05-23 | 北京航天三发高科技有限公司 | Bore closing machine and use method thereof |
| CN107643020A (en) * | 2017-10-13 | 2018-01-30 | 南京理工大学 | A kind of new adaptor for being applicable to special-shaped bullet |
| CN108534602A (en) * | 2018-05-29 | 2018-09-14 | 湖北三江航天万峰科技发展有限公司 | The adjustment method and its regulating mechanism of the small-bore double V-shaped guide rail of firing box |
| CN109895412A (en) * | 2019-02-26 | 2019-06-18 | 湖北三江航天万峰科技发展有限公司 | A kind of adapter moulding process |
| CN110193208A (en) * | 2019-05-23 | 2019-09-03 | 北京机电工程研究所 | Aircraft model transmitting tube adapter and model emission test system |
| CN112696978A (en) * | 2020-12-24 | 2021-04-23 | 彩虹无人机科技有限公司 | Small missile ground launching height falling prevention method |
| CN113772114A (en) * | 2021-10-18 | 2021-12-10 | 贵州航天天马机电科技有限公司 | Aircraft adapter and manufacturing method thereof |
| CN114414626A (en) * | 2022-01-21 | 2022-04-29 | 安徽理工大学 | Combustible gas detonation drive generator for high-speed loading |
| CN114414626B (en) * | 2022-01-21 | 2023-11-03 | 安徽理工大学 | Combustible gas detonation drive generator for high-speed loading |
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| Publication number | Publication date |
|---|---|
| CN106370056B (en) | 2018-06-19 |
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