CN110562463A - Novel transition beam with stable structure system - Google Patents
Novel transition beam with stable structure system Download PDFInfo
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- CN110562463A CN110562463A CN201910956591.2A CN201910956591A CN110562463A CN 110562463 A CN110562463 A CN 110562463A CN 201910956591 A CN201910956591 A CN 201910956591A CN 110562463 A CN110562463 A CN 110562463A
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- crossbeam
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- framework
- missile
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- 230000007704 transition Effects 0.000 title claims abstract description 20
- 230000000087 stabilizing effect Effects 0.000 claims description 22
- 238000009434 installation Methods 0.000 claims description 6
- 239000011435 rock Substances 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 9
- 230000008569 process Effects 0.000 abstract description 9
- 230000007246 mechanism Effects 0.000 abstract description 4
- 239000000725 suspension Substances 0.000 abstract description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 239000003381 stabilizer Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006056 electrooxidation reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 244000005700 microbiome Species 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention relates to the field of aircraft outboard mounting switching equipment, and discloses a novel switching transition beam with a stable structure system. The invention solves the problem that the existing transfer transition beam is easy to cause the missile launcher to shake in the aircraft flight process or the missile launching process due to lack of an effective locking mechanism, thereby influencing the suspension stability of the missile launcher and the missile shooting precision.
Description
Technical Field
The invention relates to the field of aircraft outboard mounting switching equipment, in particular to a novel switching transition beam with a stable structure system.
Background
When the aircraft needs to hoist the missile launcher outside the cabin, the missile launcher cannot be directly hung on the general hanging beam of the aircraft body, a transfer transition beam is generally used to connect the missile launcher and the general hanging beam of the aircraft body, and the transfer transition beam can play a role in bearing and transmitting the catapulting acting force, the stopping force and the lateral force of a suspended object. The existing transfer transition beam is lack of an effective stop mechanism, so that the missile launcher easily shakes in the aircraft flight process or the missile launching process, and the suspension stability and the missile shooting precision of the missile launcher are affected.
Disclosure of Invention
Based on the technical problems, the invention provides a novel transfer transition beam with a stable structure system, and solves the problem that the existing transfer transition beam is easy to cause the missile launcher to shake in the airplane flying process or the missile launching process due to the lack of an effective locking mechanism, so that the suspension stability of the missile launcher and the missile shooting precision are influenced.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
The utility model provides a novel change over and cross cab apron with stable structure system, includes integrated into one piece's couple, the couple comprises the lifting hook that establishes by crossbeam and crossbeam lower extreme front and back both sides, both sides fixed mounting respectively around the crossbeam be used for hanging the preceding of roof beam linking to each other with the organism hang, hang after, both sides still are equipped with the dog that prevents general string roof beam and rock around the crossbeam.
When the device is used, the transfer transition beam is integrally hung under the general hanging beam of the airplane by using the front hanger and the rear hanger which are fixed with the cross beam, then the lifting lugs of the missile launcher are placed in the lifting hook grooves by using the missile hanging vehicle or other hanging devices, and the position of the missile launcher is slightly adjusted, so that the notch of the lifting lug is aligned with the lifting hook. In order to prevent the missile launcher from shaking, the missile launcher is stopped by using the stoppers arranged on the front side and the rear side of the beam. In addition, the cross beam and the lifting hook of the switching transition beam hook are integrally formed, and the hook is integral, stable and firm in structure.
As a preferred mode, the retainer is composed of two retaining assemblies which are oppositely arranged on the left side and the right side of the cross beam, each retaining assembly comprises a retaining arm, each retaining arm is divided into an installation part which is vertically parallel to the cross beam and a supporting part which is obliquely bent downwards to the side far away from the cross beam, the installation parts are fixedly connected with the cross beam through bolts, and the ends of the supporting parts are provided with stabilizing assemblies.
As a preferable mode, the stabilizing component comprises a threaded cylinder which penetrates through a through hole arranged at the end head of the supporting part and is vertically and fixedly connected with the supporting part, a screw rod is arranged in the threaded cylinder, the lower end of the screw rod extends out of the threaded cylinder, and the lower end of the screw rod is connected with the stabilizing disc.
As a preferable mode, the lower end of the screw is connected with the stabilizing disc through a spherical head arranged at the lower end of the screw.
Preferably, the cross member is fixed to the cavity of the frame by screws, and the hook and the stopper are extended out of the frame.
As a preferred mode, both ends all are equipped with the radome fairing around the skeleton, and the radome fairing passes through the carriage and butts joint with the skeleton end.
As a preferred mode, the framework is formed by assembling a right side plate and a left side plate.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention solves the problem that the existing transfer transition beam is easy to cause the missile launcher to shake in the aircraft flight process or the missile launching process due to lack of an effective locking mechanism, thereby influencing the suspension stability of the missile launcher and the missile shooting precision.
(2) The stop device comprises two stop components which are oppositely arranged on the left side and the right side of the cross beam, each stop component comprises a stop arm, each stop arm is divided into an installation part which is vertically parallel to the cross beam and a supporting part which is obliquely bent downwards to the side far away from the cross beam, the installation parts are fixedly connected with the cross beam through bolts, and the ends of the supporting parts are provided with stabilizing components. The front and rear stoppers of the beam contain four stopping components, the front and rear stoppers adopt a four-point stopping structural form, lifting stopping of the missile launching device and arm-holding constraint of the missile launching device can be realized by matching with the hook, and reaction force, stopping force and lateral force generated by missile launching are borne and transmitted.
(3) The stabilizing assembly comprises a threaded cylinder which penetrates through a through hole formed in the end head of the supporting part and is vertically and fixedly connected with the supporting part, a screw rod is arranged in the threaded cylinder, the lower end of the screw rod extends out of the threaded cylinder, and the lower end of the screw rod is connected with the stabilizing disc. The screw rod moves through rotation in the threaded cylinder, so that the position of the stabilizing disc can be adjusted by operating the screw rod, and the stabilizing disc can be stopped and pre-tightened by approaching the missile launching device.
(4) According to the invention, the lower end of the screw rod is connected with the stabilizing disc through the spherical head arranged at the lower end of the screw rod, and the spherical head can tightly press the stabilizing disc without rotating when the screw rod is rotated after the stabilizing disc is attached to the missile launching device, so that the pre-tightening effect is ensured.
(5) The lifting hook is fixed in the inner cavity of the framework through the cross beam through the screw, and the lifting hook and the retainer extend out of the framework. The framework can be paired with hooks. The stopper plays a certain protection role and improves the environmental adaptability of the product.
(6) The front end and the rear end of the framework are respectively provided with the fairing, and the fairings are butted with the end heads of the framework through the connecting frame. The fairing is streamline in shape, can adjust airflow, and is favorable for reducing the acting force of wind on the transition beam.
(7) The framework is formed by assembling the right side plate and the left side plate, so that the framework is convenient to mount.
Drawings
FIG. 1 is a schematic view of the present invention (with front fairing and right side panel removed)
Figure 2 is a schematic view of the hook and retainer assembly.
Fig. 3 is a schematic view of a hook structure.
FIG. 4 is a schematic view of the stop assembly.
FIG. 5 shows the screw and threaded barrel assembly.
Fig. 6 shows a schematic view of the structure of the stabilizer plate.
FIG. 7 is a schematic view of the skeletal structure.
FIG. 8 is a schematic view of a fairing configuration.
FIG. 9 is an isometric view of the present invention.
figure 10 is an isometric view of the invention.
The device comprises a connecting frame 1, a front hanger 2, a left side plate 3, a rear hanger 4, a fairing 5, a stopper 6, a mounting part 601, a supporting part 602, a screw 603, a threaded cylinder 604, a stabilizing disc 605, a spherical head 606, a hook 7, a beam 701, a hook 702 and a right side plate 8.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present disclosure more apparent, the technical solutions of the embodiments of the present disclosure will be described clearly and completely with reference to the drawings of the embodiments of the present disclosure. It is to be understood that the described embodiments are only a few embodiments of the present disclosure, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the described embodiments of the disclosure without any inventive step, are within the scope of protection of the disclosure.
Unless otherwise defined, technical or scientific terms used herein shall have the ordinary meaning as understood by one of ordinary skill in the art to which this disclosure belongs. The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather is used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element or item listed before the word covers the element or item listed after the word and its equivalents, but does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
Example 1
Referring to fig. 1-10, a novel transition beam with stable structure system that changes over, including integrated into one piece's couple 7, couple 7 comprises crossbeam 701 and the lifting hook 702 that establish in both sides around the crossbeam 701 lower extreme, and crossbeam 701 both sides are fixed mounting respectively before being used for hanging 2, the back is hung 4 with the general string roof beam of organism continuous that hang 2 before being used for, both sides around the crossbeam 701, still are equipped with stopper 6 that prevents general string roof beam and rock around the crossbeam 701.
In the embodiment, when the device is used, the transfer transition beam is integrally hung under a general hanging beam of an airplane by using the front hanger 2 and the rear hanger 4 which are fixed with the cross beam 701, then a missile hanging vehicle or other hanging devices are used for placing lifting lugs of the missile launching device into grooves of the lifting hooks 702, and the position of the missile launching device is slightly adjusted, so that the notch of the lifting lug is aligned with the lifting hooks 702. In order to prevent the missile launcher from shaking, the missile launcher is stopped by using stoppers 6 arranged on the front side and the rear side of the beam 701. In addition, the cross beam 701 of the transition beam hook 7 is integrally formed with the hook 702, and the hook 7 is in an integral structure and is stable and firm.
All metal materials in the invention have anticorrosion capability and surface protection measures, and can avoid electrochemical corrosion of different materials. The non-metallic material part is designed to reduce the abrasion and the damage caused by sunlight, microorganisms, humidity, extreme temperature, liquid fuel, lubricating grease and salt fog as much as possible, and the environmental adaptability of the product is improved.
Example 2:
Referring to fig. 1-10, a novel transition beam with stable structure system that changes over, including integrated into one piece's couple 7, couple 7 comprises crossbeam 701 and the lifting hook 702 that establish in both sides around the crossbeam 701 lower extreme, and crossbeam 701 both sides are fixed mounting respectively before being used for hanging 2, the back is hung 4 with the general string roof beam of organism continuous that hang 2 before being used for, both sides around the crossbeam 701, still are equipped with stopper 6 that prevents general string roof beam and rock around the crossbeam 701.
Furthermore, the stopper 6 is composed of two stopper assemblies oppositely arranged on the left side and the right side of the cross beam 701, each stopper assembly comprises a stopper arm which is divided into a mounting part 601 vertically parallel to the cross beam 701 and a supporting part 602 obliquely bent downwards to the side far away from the cross beam 701, the mounting part 601 is fixedly connected with the cross beam 701 through a bolt, and the end of the supporting part 602 is provided with a stabilizing assembly.
The stoppers 6 on the front side and the rear side of the beam 701 contain four stopping components, the front stopper 6 and the rear stopper 6 adopt a four-point stopping structural form, the lifting stopping of the missile launching device and the arm holding constraint of the missile launching device can be realized by matching with the hook 7, and the functions of bearing and transmitting the reaction force, the stopping force and the lateral force generated by missile launching are realized.
Furthermore, the stabilizing assembly comprises a threaded cylinder 604 which penetrates through a through hole arranged at the end of the supporting part 602 and is vertically and fixedly connected with the supporting part 602, a screw 603 is arranged in the threaded cylinder 604, the lower end of the screw 603 extends out of the threaded cylinder 604, and the lower end of the screw 603 is connected with the stabilizing disc 605.
The screw 603 is moved by rotation in the threaded barrel 604, so that the position of the stabilizer plate 605 can be adjusted by operating the screw 603, so that it can be locked and pretensioned against the projectile launching device.
Furthermore, the lower end of the screw 603 is connected with the stabilizing disc 605 through a spherical head 606 arranged at the lower end of the screw 603, and the spherical head 606 can compress the stabilizing disc 605 tightly after the stabilizing disc 605 is attached to the missile launching device, so that the screw 603 does not rotate when the screw 603 is rotated, and the pre-tightening effect is ensured.
Further, the beam 701 is fixed to the framework cavity by screws, and the hook 702 and the stopper 6 are extended out of the framework. The framework can be opposite to the hook 7. The stopper 6 plays a certain protection role, and improves the environmental adaptability of the product.
Furthermore, the front end and the rear end of the framework are respectively provided with a fairing 5, and the fairings 5 are in butt joint with the end head of the framework through the connecting frame 1. The fairing 5 is streamline in shape, can adjust airflow, and is favorable for reducing the acting force of wind on the transition beam.
Furthermore, the framework is formed by assembling the right side plate 8 and the left side plate 3, so that the framework is convenient to mount.
The other parts of this embodiment are the same as embodiment 1, and are not described herein again.
The above is an embodiment of the present invention. The embodiments and specific parameters in the embodiments are only used for clearly illustrating the verification process of the invention and are not used for limiting the patent protection scope of the invention, which is defined by the claims, and all the equivalent structural changes made by using the contents of the description and the drawings of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A novel transition beam with stable structure system that changes over which characterized in that: couple (7) including integrated into one piece, couple (7) constitute by lifting hook (702) that both sides were established around crossbeam (701) and crossbeam (701) lower extreme, both sides fixed mounting respectively around crossbeam (701) is used for hanging (2), hanging (4) after with the general string roof beam of organism continuous preceding hanging, both sides still are equipped with stopper (6) that prevent general string roof beam and rock around crossbeam (701).
2. The novel transfer beam with stabilized structural system of claim 1, wherein: the stop dog (6) comprises two relative stop components that set up in crossbeam (701) left and right sides, stop components includes the stop arm, the stop arm divide into with crossbeam (701) vertical parallel installation department (601) and to keeping away from crossbeam (701) a supporting part (602) of lateral tilt downward bending, installation department (601) pass through bolt and crossbeam (701) fixed connection, supporting part (602) end is equipped with stabilizing assembly.
3. A novel transfer beam with a stable structural system according to claim 2, characterized in that: the stabilizing assembly comprises a threaded cylinder (604) which penetrates through a through hole formed in the end of the supporting part (602) and is vertically and fixedly connected with the supporting part (602), a screw rod (603) is arranged in the threaded cylinder (604), the lower end of the screw rod (603) extends out of the threaded cylinder (604), and the lower end of the screw rod (603) is connected with a stabilizing disc (605).
4. A novel transfer beam with a stable structural system according to claim 3, characterized in that: the lower end of the screw (603) is connected with the stable disc (605) through a spherical head (606) arranged at the lower end of the screw (603).
5. A novel transfer beam with a stable structural system according to any one of claim 1, characterized in that: the beam (701) is fixed in the inner cavity of the framework through screws, and the hook (702) and the stopper (6) extend out of the framework.
6. The novel transfer beam with stabilized structural system of claim 5, wherein: both ends all are equipped with radome fairing (5) around the skeleton, radome fairing (5) dock with the skeleton end through link (1).
7. The novel transfer beam with stabilized structural system of claim 5, wherein: the framework is formed by assembling a right side plate (8) and a left side plate (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910956591.2A CN110562463A (en) | 2019-10-09 | 2019-10-09 | Novel transition beam with stable structure system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910956591.2A CN110562463A (en) | 2019-10-09 | 2019-10-09 | Novel transition beam with stable structure system |
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| Publication Number | Publication Date |
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| CN110562463A true CN110562463A (en) | 2019-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910956591.2A Pending CN110562463A (en) | 2019-10-09 | 2019-10-09 | Novel transition beam with stable structure system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024598A (en) * | 2019-12-26 | 2020-04-17 | 中国兵器工业第五九研究所 | A environmental test device for aircraft suspended structure |
| CN113732484A (en) * | 2021-09-30 | 2021-12-03 | 郑州郑飞机电技术有限责任公司 | Structure suitable for skeleton welding and welding method |
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| US6250195B1 (en) * | 1999-11-09 | 2001-06-26 | Northrop Grumman Corporation | Compact universal ejection/rail launching system |
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| CN117550073A (en) * | 2023-11-13 | 2024-02-13 | 吉林化工学院 | Hanger and aircraft |
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2019
- 2019-10-09 CN CN201910956591.2A patent/CN110562463A/en active Pending
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|---|---|---|---|---|
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| US6250195B1 (en) * | 1999-11-09 | 2001-06-26 | Northrop Grumman Corporation | Compact universal ejection/rail launching system |
| US20040011926A1 (en) * | 2002-07-22 | 2004-01-22 | Shay William F. | System and method for loading stores on an aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111024598A (en) * | 2019-12-26 | 2020-04-17 | 中国兵器工业第五九研究所 | A environmental test device for aircraft suspended structure |
| CN113732484A (en) * | 2021-09-30 | 2021-12-03 | 郑州郑飞机电技术有限责任公司 | Structure suitable for skeleton welding and welding method |
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