CN110631420B - Airborne suspended object ejection mechanism - Google Patents
Airborne suspended object ejection mechanism Download PDFInfo
- Publication number
- CN110631420B CN110631420B CN201910905466.9A CN201910905466A CN110631420B CN 110631420 B CN110631420 B CN 110631420B CN 201910905466 A CN201910905466 A CN 201910905466A CN 110631420 B CN110631420 B CN 110631420B
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- CN
- China
- Prior art keywords
- rocker arm
- connecting rod
- launcher
- hinged
- suspended object
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
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- 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
Abstract
The invention provides an airborne suspended object ejection mechanism, which comprises a launcher framework, an actuating cylinder, a front rocker arm and a rear rocker arm, wherein the launcher framework is provided with a front rocker arm and a rear rocker arm; the launcher framework is connected with the launcher; one end of the front rocker arm is hinged with the launcher framework, and the other end of the front rocker arm is hinged with one end of the actuating cylinder; the other end of the actuating cylinder is hinged with the launcher framework; one end of the rear rocker arm is hinged with the launcher framework. The airborne suspended object launching mechanism provided by the invention can meet the requirements of compact structure and small occupied space, eliminates some unfavorable factors brought by a guide rail type launching device in the missile launching process, ensures that various performance indexes of the suspended object and the launching device meet the design requirements, and ensures that the suspended object and the launching frame are smoothly separated in the launching process.
Description
Technical Field
The invention relates to the field of structural design of aircraft launching devices, in particular to an airborne suspended object ejection mechanism.
Background
The matching device of the airplane mounted missile, rocket missile and launching device is called as suspended launching device, which is a special device for carrying and launching missile by airplane. The missile launching device is used as an important component of a missile weapon system and has the functions of launching, storing and supplying missiles. The basic task of the launching device is to carry and launch missiles, and the missiles are mainly used for enabling combat troops to hit targets according to preset requirements. Therefore, high reliability and precision are needed when transmitting. The design quality of the launching device has great influence on the precision and reliability of missile launching and the safety of the carrier.
Through the search of the prior art, the invention patent with application number 201410719286.9 discloses an integral rail type cube star launching device, which mainly comprises a rectangular frame, an unlocking mechanism, a spring mechanism and the like.
The rail type launching device is a launching device widely adopted by airborne missiles, and is provided with one or a group of rails for guiding the missiles to slide. However, the rail type launcher has some problems that: firstly, the harmful influence of gas flow on the aircraft during missile launching can cause the gas flow to possibly enter an aircraft air inlet channel to cause an aircraft engine to be flamed out; secondly, when the launching device is subjected to large dynamic load and inertia load, the friction force between the slide block and the guide rail of the missile is increased, and in order to launch the missile, the takeoff thrust is increased, which brings adverse effects on the dynamic and static strength of the launching device and increases the quality of the missile; and thirdly, when self-thrust launching is adopted, the bullet rack system can only be hung externally, so that the head-on resistance is increased. Thus limiting its range of application in airborne missile launching.
The ejection launching of the ejection launching device is to eject the suspended object by using the external force provided by the suspension device. After the suspension object leaves the carrier for a certain distance, a power device of the suspension object is started, and the suspension object flies in the air by means of the power of the suspension object. The ejection launching mode can effectively reduce some adverse factors brought by the guide rail type launching device in the missile launching process.
The higher the adaptability requirements of future high-tech wars on the development of airborne suspension launching devices, airplane performance and full weapon systems are, the higher the requirements are. Therefore, it is very urgent and meaningful to develop research work related to airborne suspension ejection mechanisms.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide an airborne suspended object ejection mechanism that solves one or more of the above mentioned problems.
According to one aspect of the invention, an airborne suspended object ejection mechanism is provided, which comprises a launcher framework, an actuating cylinder, a front rocker arm and a rear rocker arm; the launcher framework is connected with the launcher; one end of the front rocker arm is hinged with the launcher framework, and the other end of the front rocker arm is hinged with one end of the actuating cylinder; the other end of the actuating cylinder is hinged with the launcher framework; one end of the rear rocker arm is hinged with the launcher framework.
In some embodiments, a front rocker arm is pivotally connected to the front link system at one end and pivotally connected to the rear link system at the other end.
In some embodiments, the front synchronizing link system comprises a first synchronizing link, a second synchronizing link and a third synchronizing link, wherein the first synchronizing link is hinged with the front rocker arm and the second synchronizing link at the upper end and the lower end thereof respectively; the front and the back of the second synchronous connecting rod are respectively hinged with the first synchronous connecting rod and the third synchronous connecting rod; and the upper end and the lower end of the third synchronous connecting rod are respectively hinged with the second synchronous connecting rod and the rear rocker arm.
In some embodiments, a rear synchronization link system is further included, with one end hinged to the rear rocker arm and the other end hinged to the third synchronization link.
In some embodiments, the rear synchronization link system comprises a first rear rocker link, a second rear rocker link, wherein the first rear rocker link is hinged at its upper and lower ends to the second rear rocker link and the rear rocker, respectively; and the front and the back of the second rear rocker arm connecting rod are respectively hinged with the first rear rocker arm connecting rod and the launcher framework.
In some embodiments, the launcher frame further comprises a front hanger and a rear hanger, and the front hanger and the rear hanger are used for realizing connection of the launcher frame and a suspended object.
In some embodiments, a stop is further included and is connected to the first rear rocker link for limiting rearward movement of the rear hanger.
In some embodiments, a rear retainer block is also included and is coupled to the rear rocker arm.
In some embodiments, a catch latch is also included and is coupled to the first rear rocker link.
In some embodiments, a front retainer block is further included and is coupled to the front rocker arm.
The airborne suspended object launching mechanism provided by the invention can meet the requirements of compact structure and small occupied space, eliminates some unfavorable factors brought by a guide rail type launching device in the missile launching process, ensures that various performance indexes of the suspended object and the launching device meet the design requirements, and ensures that the suspended object and the launching frame are smoothly separated in the launching process.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of a airborne suspended object ejection launching device in a flying state;
fig. 2 is a schematic diagram of the ejection separation state of the airborne suspended object ejection and launching device.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention discloses a sliding bearing, in particular to an airborne suspended object ejection mechanism, which comprises a launcher framework 1, an actuating cylinder 2, a front rocker arm 3 and a rear rocker arm 9; the launcher framework is connected with the launcher; one end of the front rocker arm 3 is hinged with the launcher framework 1, and the other end of the front rocker arm is hinged with one end of the actuating cylinder 2; the other end of the actuating cylinder 2 is hinged with the launcher framework 1; one end of the rear rocker arm 9 is hinged with the launcher framework 1.
In addition, the swing arm mechanism also comprises a front connecting rod system, one end of which is hinged with the front swing arm 3, and the other end of which is hinged with the rear swing arm 9.
The front synchronization connecting rod system comprises a first synchronization connecting rod 5, a second synchronization connecting rod 6 and a third synchronization connecting rod 10, wherein the upper end and the lower end of the first synchronization connecting rod 5 are respectively hinged with the front rocker arm 3 and the second synchronization connecting rod 6; the front and the back of the second synchronous connecting rod 6 are respectively hinged with the first synchronous connecting rod 5 and the third synchronous connecting rod 10; and the upper end and the lower end of the third synchronous connecting rod 10 are respectively hinged with the second synchronous connecting rod 6 and the rear rocker arm 9.
In addition, the device also comprises a rear synchronous connecting rod system, wherein one end of the rear synchronous connecting rod system is hinged with the rear rocker arm 9, and the other end of the rear synchronous connecting rod system is hinged with the third synchronous connecting rod 10.
The rear synchronous connecting rod system comprises a first rear rocker arm connecting rod 7 and a second rear rocker arm connecting rod 8, wherein the first rear rocker arm connecting rod 7 is hinged to the second rear rocker arm connecting rod 8 and the rear rocker arm 9 from top to bottom; and the front and the back of the second rear rocker arm connecting rod 8 are respectively hinged with the first rear rocker arm connecting rod 7 and the launcher framework 1.
In addition, the launcher frame comprises a front hanger 17 and a rear hanger 14, and the front hanger and the rear hanger are used for realizing the connection between the launcher frame 1 and the hanging object 11.
And a stop block 12 connected with the first rear rocker arm connecting rod 7 and used for limiting the rear hanger 14 to move backwards. And a rear holding spring block 13 which is connected with the rear rocker arm 9. And the elastic catch 15 is connected with the first rear rocker arm connecting rod 7. And the front holding elastic block 16 is connected with the front rocker arm 3.
The airborne suspended object launching mechanism provided by the invention can meet the requirements of compact structure and small occupied space, eliminates some unfavorable factors brought by a guide rail type launching device in the missile launching process, ensures that various performance indexes of the suspended object and the launching device meet the design requirements, and ensures that the suspended object and the launching frame are smoothly separated in the launching process.
The specific implementation mode and the working principle are as follows:
as shown in fig. 1, the airborne suspended object launching mechanism provided by the present invention specifically comprises: the launcher framework 1 is fixedly connected with the launcher; the upper end of the actuating cylinder 2 is hinged with the launcher framework 1, and the lower end of the actuating cylinder is hinged with the front rocker arm 3; the front end and the rear end of the front rocker arm 3 are respectively hinged with the actuating cylinder 2 and the launcher framework 1; the limiting block is fixedly connected with the launcher framework 1 and impacts the second synchronous connecting rod 6 in the ejection process to play a limiting role; the upper end and the lower end of the first synchronous connecting rod 5 are respectively hinged with the second synchronous connecting rod 6 and the front rocker arm 3; the second synchronous connecting rod 6 is hinged with the first synchronous connecting rod 5 and the third synchronous connecting rod 10 in the front and back direction respectively and can only move back and forth in the launcher; the upper end and the lower end of the third synchronous connecting rod 10 are respectively hinged with the second synchronous connecting rod 6 and the rear rocker arm 9; the upper part and the lower part of the first rear rocker arm connecting rod 7 are respectively hinged with a second rear rocker arm connecting rod 8 and a rear rocker arm 9; the second rear rocker arm connecting rod 8 is hinged with the first rear rocker arm connecting rod 7 and the launcher framework 1 in the front and back directions respectively; the front and rear rocker arms 9 are respectively hinged with the first rear rocker arm connecting rod 7 and the launcher framework 1; the suspension 11 is connected with the launcher framework 1 through a front hanger 17 and a rear hanger 14; the stop block 12 is fixedly connected with the first rear rocker arm connecting rod 7 and used for limiting the rear hanging of the suspended object to move backwards; the rear hanger 14 is fixedly connected with the hanging object 11; the rear holding elastic block 13 is fixedly connected with the rear rocker arm 9; the elastic blocking hook 15 is fixedly connected with the first rear rocker arm connecting rod 7; the front holding elastic block 16 is fixedly connected with the front rocker arm; and the front hanger 17 is fixedly connected with the suspension object.
As shown in fig. 1, when the airborne suspended object ejection mechanism is in a flying state, the suspended object rear hanger 14 is located among the elastic catch 15, the rear elastic catch 13 and the stop block 12, the upper surface of the rear elastic catch 13 is in contact with the lower surface of the suspended object rear hanger 14, the elastic catch 15 and the stop block 12 limit the forward and backward movement of the suspended object, the suspended object front hanger 17 is located between the front elastic catch 16 and the front rocker groove, the upper surface of the front elastic catch 16 is in contact with the lower surface of the suspended object front hanger 17, and the forward and backward movement of the front hanger is not limited.
As shown in fig. 2, when the airborne suspended object ejection mechanism is in an ejection state, the actuator cylinder 2 generates an ejection force under the action of high-pressure gas, the front rocker arm 3 and the rear rocker arm 9 rotate around the rotating shaft through the first synchronous connecting rod, the second synchronous connecting rod 6 and the third synchronous connecting rod 10, the blocking elastic hook 15 and the stop block 12 always restrain the rear suspension 14 of the suspended object and keep parallel with the launcher framework 1, the front holding elastic block 16 and the rear holding elastic block 13 move backwards and upwards relative to the front suspension 17 and the rear suspension 14 along with the rotation of the front rocker arm and the rear rocker arm 9 until the distance between the front end of the blocking elastic hook 15 and the front end of the rear holding elastic block 13 is greater than the suspension hanging length, the front suspension 17 and the rear suspension 14 are separated from the launcher, and the ejection separation of the suspended object is realized.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (1)
1. An airborne suspended object ejection mechanism is characterized by comprising a launcher framework (1), an actuating cylinder (2), a front rocker arm (3) and a rear rocker arm (9);
wherein the launcher framework (1) is connected with the launcher;
one end of the front rocker arm (3) is hinged with the launcher framework (1), and the other end of the front rocker arm is hinged with one end of the actuating cylinder (2); the other end of the actuating cylinder (2) is hinged with the launcher framework (1);
one end of the rear rocker arm (9) is hinged with the launcher framework (1);
further comprising a front synchronization linkage system comprising a first synchronization linkage (5), a second synchronization linkage (6) and a third synchronization linkage (10), wherein,
the upper end and the lower end of the first synchronous connecting rod (5) are respectively hinged with the front rocker arm (3) and the second synchronous connecting rod (6);
the front and the back of the second synchronous connecting rod (6) are respectively hinged with the first synchronous connecting rod (5) and the third synchronous connecting rod (10);
the upper end and the lower end of the third synchronous connecting rod (10) are respectively hinged with the second synchronous connecting rod (6) and the rear rocker arm (9);
also comprises a rear synchronous connecting rod system, the rear synchronous connecting rod system comprises a first rear rocker arm connecting rod (7) and a second rear rocker arm connecting rod (8), wherein,
the upper part and the lower part of the first rear rocker arm connecting rod (7) are respectively hinged with a second rear rocker arm connecting rod (8) and the rear rocker arm (9);
the front and the back of the second rear rocker arm connecting rod (8) are respectively hinged with the first rear rocker arm connecting rod (7) and the launcher framework (1);
the launcher frame comprises a launcher framework (1) and a suspender (11), and is characterized by further comprising a front hanger (17) and a rear hanger (14) which are used for realizing the connection between the launcher framework (1) and the suspender (11);
the device also comprises a bullet-stopping hook (15) which is connected with the first rear rocker arm connecting rod (7);
the front rocker arm (3) is connected with the front rocker arm (16);
the rear suspension device also comprises a stop block (12) which is connected with the first rear rocker arm connecting rod (7) and used for limiting the rear suspension (14) to move backwards;
the rear support spring block (13) is connected with the rear rocker arm (9);
when the airborne suspended object ejection mechanism is in a flying state, the rear suspension (14) of the suspended object is positioned among the elastic stopping hook (15), the rear supporting elastic block (13) and the stop block (12), the upper surface of the rear supporting elastic block (13) is in contact with the lower surface of the rear suspension (14), the elastic stopping hook (15) and the stop block (12) limit the forward and backward movement of the suspended object, the front suspension (17) is positioned between the front supporting elastic block (16) and the front rocker groove, the upper surface of the front supporting elastic block (16) is in contact with the lower surface of the front suspension (17), and the forward and backward movement of the front suspension (17) is not limited;
when the airborne suspended object ejection mechanism is in an ejection state, under the action of high-pressure gas, the actuating cylinder (2) generates ejection force, the front rocker arm (3) and the rear rocker arm (9) rotate around a rotating shaft through the first synchronous connecting rod (5), the second synchronous connecting rod (6) and the third synchronous connecting rod (10), the bullet blocking hook (15) and the stopping block (12) always restrain the rear hanger (14) and keep parallel with the launcher framework (1), the front bullet holding block (16) and the rear bullet holding block (13) respectively move backwards and upwards relative to the front hanger (17) and the rear hanger (14) along with the rotation of the front rocker arm (3) and the rear rocker arm (9) until the distance between the bullet blocking hook (15) and the front end of the rear bullet holding block (13) is larger than the rear hanger length of a suspended object, and the front hanger (17), The rear hanger (14) is separated from the launching rack, so that the ejection separation of the suspended objects is realized.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910905466.9A CN110631420B (en) | 2019-09-24 | 2019-09-24 | Airborne suspended object ejection mechanism |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910905466.9A CN110631420B (en) | 2019-09-24 | 2019-09-24 | Airborne suspended object ejection mechanism |
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| CN110631420B true CN110631420B (en) | 2021-12-03 |
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| 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 |
| CN117309313B (en) * | 2023-11-29 | 2024-01-30 | 中国航空工业集团公司西安飞机设计研究所 | Ejection hanging frame model for simultaneous casting and continuous casting |
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