CN201897433U - Launching beam for oblique launching - Google Patents
Launching beam for oblique launching Download PDFInfo
- Publication number
- CN201897433U CN201897433U CN2010206006314U CN201020600631U CN201897433U CN 201897433 U CN201897433 U CN 201897433U CN 2010206006314 U CN2010206006314 U CN 2010206006314U CN 201020600631 U CN201020600631 U CN 201020600631U CN 201897433 U CN201897433 U CN 201897433U
- Authority
- CN
- China
- Prior art keywords
- rail
- slide block
- sides
- guide track
- emission beam
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model provides a launching beam for oblique launching, which comprises a launching beam body, a front guide track, a rear guide track and a locking comb stopper. The front guide track and the rear guide track are in high-and-low track form, a guide for restraining a front supporting leg is arranged at the initial end of the front guide track of the low-track portion, the guide comprises a bracket slider, the lower portion of the bracket slider is embedded on the front guide track through outer turned edges which are arranged on two sides and matched with the front guide track, rotary shafts along the guide track direction are mounted in the middles of the outer turned edges on two sides of the bracket slider, lower ends of a pair of pinch plates are respectively hinged with the rotary shafts on two sides, torsional springs opposite in direction are mounted on the two rotary shafts, inwards cross hooks arranged at the upper ends of the pinch plates extend to a groove at the upper end of the bracket slider, the front supporting leg of a rocket bomb is embedded into the groove, a vertical hole with an upper opening is arranged in the bracket slider, a compression spring is disposed on the lower portion in the vertical hole, and a carrier rod is arranged on the compression spring. The vertical hole is a big-end-down stepped hole, and a limit boss on the middle lower portion of the carrier rod is arranged in the big lower portion of the vertical hole. Locking screws are arranged among two sides of the pinch plates and the bracket slider.
Description
Technical field
The utility model belongs to the missile-system ground equipment technical field, is specifically related to a kind of ramp-launched emission beam that is used for.
Background technology
At present in rocket projectile tilts emission; when employing leaves the right or normal track form simultaneously; owing to will above the emission beam, fly a period of time after rocket projectile leaves the right or normal track; and this moment is because the gravity effect; the rocket projectile segment distance that can drop, emission beam must have enough safe distances and guarantee that rocket projectile and emission beam do not bump.Generally be on the emission beam, to be provided with to allow opening mechanism; after rocket projectile leaves the right or normal track; allow opening mechanism make emission beam front end sink to getting out of the way rocket projectile; owing to be provided with movable device on the emission beam; the rigidity of emission beam is relatively poor during emission; little adapt to the system that rocket projectile is left the right or normal track and has relatively high expectations, and rocket projectile need be provided with long ridge protection, influence the aerodynamic configuration of rocket projectile.
Summary of the invention
The purpose of this utility model is to provide a kind of ramp-launched emission beam that is used for, design height rail and guider on this emission beam, preferably leave the right or normal track parameter and aerodynamic configuration preferably in the time of guaranteeing the rocket projectile emission, leave the right or normal track the back and not can with launch beam and bump.
The technical solution of the utility model: of the present utility modelly be used for ramp-launched emission beam and comprise emission beam body, fromer rail, rear rail, the locking bomb retaining device, its fromer rail and rear rail adopt height rail form, the guider of constraint front support leg is set at the top of low rail part fromer rail, guider comprises the bearing slide block, the bottom of bearing slide block is embedded on the fromer rail by the outer crimping with the fromer rail coupling of both sides, the gyroaxis along the guide rail direction is installed at the crimping middle part outside the both sides of bearing slide block, the lower end of a pair of buckle is hinged with the gyroaxis of both sides respectively, the opposite torsion spring of installation direction on two gyroaxises; The rocket projectile front support leg that the upper end of a pair of buckle has inside horizontal hook to extend the bearing upper end of slide block embeds with on the groove; The vertical hole that upper shed is arranged in the bearing slide block, vertically stage clip is placed in the bottom in the hole, is push rod above the stage clip.
Described vertical hole is a shoulder hole, and is up-small and down-big; The push rod middle and lower part has positive stop lug boss to be positioned at the following major part in vertical hole.
Establish lock-screw between the both sides of described a pair of buckle and the bearing slide block.
The difference in height of described fromer rail and rear rail is 200mm～240mm.
The gap of described bearing slide block and fromer rail is 1.2mm～2mm.
The novel inclination emission beam that provides comprises emission beam body, fromer rail, rear rail, locking bomb retaining device, guider.The front and back guide rail is screwed onto on the emission beam body; the locking bomb retaining device is arranged on the emission beam rear part; guider top is with after rocket projectile docks; utilize the constraint of fromer rail concave surface to make between the two reliably connection; after rocket projectile leaves the right or normal track; guider separates automatically with rocket projectile, guarantees rocket projectile good aerodynamic configuration of when flight.
Advantage of the present utility model: emission girder construction of the present utility model is simple, practical, safe and reliable, can provide the necessary parameter that leaves the right or normal track for rocket projectile.After rocket projectile left the right or normal track, the rocket projectile back guider that leaves the right or normal track separated automatically with rocket projectile, not can with the emission beam and on mechanism bump, and do not influence the aerodynamic configuration of rocket projectile.
Description of drawings
Fig. 1 is the general structure schematic diagram of the utility model emission beam.
Fig. 2 is the guide structure schematic diagram.
Fig. 3 is the A-A view of Fig. 2.
The specific embodiment
Below in conjunction with accompanying drawing and example the utility model is described in further detail.
As Fig. 1, Fig. 2, shown in Figure 3, the utility model emission beam comprises emission beam body 1, fromer rail 2, rear rail 3, locking bomb retaining device 4, its fromer rail 2 and rear rail 3 adopt height rail form, fromer rail 2 and rear rail 3 are screwed onto respectively on the low platform 1a and Gao Tai 1b of emission beam body 1, and locking bomb retaining device 4 is arranged on high platform 1b and rear rail 3 rear ends.
The guider 5 of constraint rocket projectile front support leg is set at the top of low rail part fromer rail 2, guider 5 comprises bearing slide block 5a, the bottom of bearing slide block 5a is embedded on the fromer rail 2 by the outer crimping 5a1 with fromer rail 2 couplings of both sides, the gyroaxis 5e along the guide rail direction is installed at the crimping middle part outside the both sides of bearing slide block 5a, the lower end of a pair of buckle 5g is hinged with the gyroaxis 5e of both sides respectively, and two gyroaxis 5e go up the opposite torsion spring 5f of installation direction; The rocket projectile front support leg that the upper end of a pair of buckle 5g has inside horizontal hook 5g1 to extend bearing slide block 5a upper end embeds with on the groove 5a2; The vertical hole 5b that upper shed is arranged in bearing slide block 5a, vertically stage clip 5d is placed in the bottom in the 5b of hole, is push rod 5c above the stage clip 5d.
Described vertical hole 5b is a shoulder hole, and is up-small and down-big; Push rod 5c middle and lower part has positive stop lug boss 5c1 to be positioned at the following major part of vertical hole 5b.
Establish lock-screw 5h between the both sides of described a pair of buckle 5g and the bearing slide block 5a.
Described fromer rail 2 is 200mm～240mm with the difference in height of rear rail 3.
The gap of described bearing slide block 5a and fromer rail 2 is 1.2mm～2mm.
When rocket projectile runs to assigned address on guide rail, regulate locking bomb retaining device 4, realize the axial restraint of rocket projectile.
When emission, unscrew lock-screw 5h, rely on this moment the constraint of fromer rail to make a pair of buckle 5g keep being pressed on the front support leg; After rocket projectile flies away from guide rail, fromer rail is to the constraint release of a pair of buckle 5g, under the effect of torsion spring 5f, a pair of buckle 5g wraparound rotating shaft gyroaxis 5e outwards rotates, releasing is to the constraint of front support leg 7, push rod 5c promotes front support leg 7 under the effect of stage clip 5d, guider is separated with rocket projectile front support leg 7.The open power of buckle after torsion spring 5f leaves the right or normal track as guider, after a pair of buckle 5g opened, stage clip promoted push rod and gives the relative rocket projectile of guider certain speed, guaranteed can not bump with rocket projectile after guider separates.
In the utility model, the difference in height of height rail is guaranteed can not bump with the emission beam after rocket projectile leaves the right or normal track, and the structure of guider is guaranteed the reliability and security that rocket projectile separates with the back that leaves the right or normal track in the reliability of rail emission.
Based on the said structure principle,, can adapt to the different rocket projectiles inclination emissions that require by changing gap and the guide structure between rail length, height rail difference in height, front and back guide rail and leg.
Claims (5)
1. one kind is used for ramp-launched emission beam, comprise emission beam body (1), fromer rail (2), rear rail (3), locking bomb retaining device (4), it is characterized in that: fromer rail (2) and rear rail (3) adopt height rail form, the guider (5) of constraint front support leg is set at the top of low rail part fromer rail (2), guider (5) comprises bearing slide block (5a), the bottom of bearing slide block (5a) is embedded on the fromer rail (2) by the outer crimping (5a1) with fromer rail (2) coupling of both sides, the gyroaxis (5e) along the guide rail direction is installed at the crimping middle part outside the both sides of bearing slide block (5a), the lower end of a pair of buckle (5g) is hinged with the gyroaxis (5e) of both sides respectively, and two gyroaxises (5e) are gone up the opposite torsion spring (5f) of installation direction; The rocket projectile front support leg that the upper end of a pair of buckle (5g) has inside horizontal hook (5g1) to extend bearing slide block (5a) upper end embeds with on the groove (5a2); The vertical hole (5b) that upper shed is arranged in bearing slide block (5a), vertically stage clip (5d) is placed in interior bottom, hole (5b), is push rod (5c) above the stage clip (5d).
2. according to claim 1ly be used for ramp-launched emission beam, it is characterized in that: vertically hole (5b) is a shoulder hole, and is up-small and down-big; Push rod (5c) middle and lower part has positive stop lug boss (5c1) to be positioned at the following major part in vertical hole (5b).
3. according to claim 1 and 2ly be used for ramp-launched emission beam, it is characterized in that: establish lock-screw (5h) between the both sides of a pair of buckle (5g) and the bearing slide block (5a).
4. according to claim 1 and 2ly be used for ramp-launched emission beam, it is characterized in that: fromer rail (2) is 200mm～240mm with the difference in height of rear rail (3).
5. according to claim 1 and 2ly be used for ramp-launched emission beam, it is characterized in that: bearing slide block (5a) is 1.2mm～2mm with the gap of fromer rail (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206006314U CN201897433U (en) | 2010-11-10 | 2010-11-10 | Launching beam for oblique launching |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206006314U CN201897433U (en) | 2010-11-10 | 2010-11-10 | Launching beam for oblique launching |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201897433U true CN201897433U (en) | 2011-07-13 |
Family
ID=44255339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206006314U Expired - Fee Related CN201897433U (en) | 2010-11-10 | 2010-11-10 | Launching beam for oblique launching |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201897433U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494642A (en) * | 2016-10-18 | 2017-03-15 | 湖北航天技术研究院总体设计所 | A kind of large-tonnage vehicle locking device |
| CN112432555A (en) * | 2020-11-11 | 2021-03-02 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| 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 |
-
2010
- 2010-11-10 CN CN2010206006314U patent/CN201897433U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494642A (en) * | 2016-10-18 | 2017-03-15 | 湖北航天技术研究院总体设计所 | A kind of large-tonnage vehicle locking device |
| CN106494642B (en) * | 2016-10-18 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of large-tonnage vehicle locking device |
| CN112432555A (en) * | 2020-11-11 | 2021-03-02 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| CN112432555B (en) * | 2020-11-11 | 2023-10-13 | 河南北方红阳机电有限公司 | Ground throwing device for simulating airborne projectile launching |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2658842C (en) | Method and apparatus for retrieving a hovering aircraft | |
| CN201897433U (en) | Launching beam for oblique launching | |
| CN110758762B (en) | Unmanned aerial vehicle ejection locking releasing device and method | |
| CN202848037U (en) | Recovery device of cable-hanging type unmanned aerial vehicle | |
| CN205707374U (en) | A kind of unmanned plane air crash protection device | |
| CN104590288B (en) | The control method of low speed magnetic suspension train suspension unstability in a kind of reply | |
| FR2936491B1 (en) | METHOD FOR LARGING AN EXTERNAL LOAD CARRIED BY AN AIRCRAFT AND ASSOCIATED DEVICE | |
| CN110395402A (en) | The low disturbance unmanned aerial vehicle ejecting frame separating mechanism of one kind and separation method | |
| CN104527997B (en) | A kind of synchronous device for connecting and unlock satellite | |
| TW201834928A (en) | Hinge Mechanism For A Weight-Shifting Coaxial Helicopter | |
| CN109911208A (en) | A kind of monitoring based on thermal image analysis and drive alarm unmanned plane | |
| CN204988710U (en) | Unhook test device of mine slope manriding cars safety hook | |
| CN112432555B (en) | Ground throwing device for simulating airborne projectile launching | |
| RU2013147676A (en) | SYSTEMS AND METHODS OF STARTING AIRCRAFT | |
| CN110550220B (en) | Aerial photography unmanned aerial vehicle with falling protection function | |
| CN113353213A (en) | Intelligent multi-rotor-wing rescue throwing device and control method | |
| CN106494649B (en) | A kind of manned rocket release apparatus and its working method based on aerodynamic force | |
| CN104828668A (en) | Elevator adjusting-type centrifugation speed limiting device | |
| CN104417763A (en) | Convolution acceleration taking-off scheme | |
| CN103241383A (en) | Running takeoff auxiliary device for aircraft on round-tangent rails | |
| CN114506454B (en) | Onboard hanging object loading and unloading system and method | |
| CN204801769U (en) | Cableway flight experience system | |
| CN217100426U (en) | Intelligent multi-rotor wing rescue throwing device | |
| CN205857672U (en) | Anti-falling device of attached lifting scaffold | |
| CN105217036A (en) | Traction air-drop parachuting unit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110713 Termination date: 20141110 |
|
| EXPY | Termination of patent right or utility model |