CN111959745A - Aircraft radome connecting lock structure and radome locking method - Google Patents
Aircraft radome connecting lock structure and radome locking method Download PDFInfo
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- CN111959745A CN111959745A CN202010645052.XA CN202010645052A CN111959745A CN 111959745 A CN111959745 A CN 111959745A CN 202010645052 A CN202010645052 A CN 202010645052A CN 111959745 A CN111959745 A CN 111959745A
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- lock
- radome
- handle
- joint
- locking
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The invention relates to an aircraft radome connecting lock structure and a radome locking method, wherein the connecting lock structure comprises a lock body, a lock seat and a joint, the joint is fixed on a radome, a threaded hole is formed in the joint, the lock body comprises a locking joint and a handle component, the front end of the locking joint is matched with the threaded hole of the joint, the rear end of the locking joint is hinged with the handle component, a quick-release lock is arranged on the handle component, the lock seat is fixed on an aircraft body, a positioning groove matched with the handle component is formed in the lock seat, and a limiting hole matched with the quick-release lock is formed in the bottom of the positioning groove. The lock body is connected with the connector on the radome through threads, so that the lock body can be quickly installed and detached, and is convenient to use and maintain.
Description
Technical Field
The invention relates to the technology of airplane structure design, in particular to a connecting lock for an airplane radome and a locking method for the radome.
Background
The aircraft radome is installed at the foremost part of the fuselage for radar system in the safety cover is not damaged or destroyed by external force, and in addition, as the important component part of the aircraft appearance, the radome also plays the effect of maintaining the aerodynamic appearance of the complete machine. The radome is required to be opened frequently during maintenance of the aircraft radar in daily life, so that a safe, reliable, rapid and convenient locking mechanism is required to be used for connecting the radome and an engine body structure, the flight safety of the aircraft is guaranteed, the operation flow can be simplified during ground maintenance, and the time for opening and closing the radome is saved.
The radar cover that uses on the present aircraft connects the lock and installs in organism inside more, for making the aircraft surface keep the smooth and smooth, is equipped with little flap above connecting the lock, when maintaining the radar at every turn, need open little flap earlier, opens the radar cover again and connects the lock, and the in-process generally needs two kinds of instruments to use, and the dismouting is inconvenient, influences maintenance efficiency.
Disclosure of Invention
According to the requirements for developing an aircraft radome and the problems in the prior art, the invention aims to provide the radome connecting lock capable of being quickly disassembled so as to improve the maintenance efficiency of an aircraft radar, reduce tools required in the disassembly and assembly process and achieve the purposes of being convenient and quick in disassembly and assembly of the radome and saving maintenance time.
The utility model provides an aircraft radome joint lock structure, contains lock body, lock seat and connects, its characterized in that, the joint fix on the radome, connect and have a screw hole, the lock body contain locking joint and handle components, the front end that the locking connects is a pin rod of outband screw thread, the external screw thread of this pin rod matches with the screw hole that connects, the rear end that the locking connects is the engaging lug, this engaging lug is articulated with handle components, the last quick-release lock that is equipped with of handle components, the lock seat fix on the aircraft organism, the constant head tank that has on the lock seat and matches with handle components, the bottom of constant head tank is equipped with the spacing hole that matches with the quick-release lock.
The application also provides an aircraft radome locking method, which is characterized by comprising the following contents: 1) the aircraft engine is characterized by comprising a connecting lock structure, a lock seat and a joint, wherein the joint is fixed on a radome and is provided with a threaded hole, the lock body comprises a locking joint and a handle assembly, the front end of the locking joint is a pin rod with external threads, the external threads of the pin rod are matched with the threaded hole of the joint, the rear end of the locking joint is a connecting lug, the connecting lug is hinged with the handle assembly, the handle assembly is provided with a quick-release lock, the lock seat is fixed on an aircraft body, the lock seat is provided with a positioning groove matched with the handle assembly, and the bottom of the positioning groove is provided with a limiting hole matched with the quick-release lock; 2) when the radome is locked, a pin rod at the front end of a locking joint of the lock body is connected with a threaded hole of a joint fixed on the radome, the radome is buckled at a proper position of the machine body, the position of the joint on the radome corresponds to the position of a lock seat fixed on the machine body, a handle assembly of the lock body is pressed into a positioning groove of the lock seat to be clamped, and finally the handle assembly and a limiting hole at the bottom of the positioning groove of the lock seat are locked through a quick-release lock on the handle assembly; 3) when the radome is opened, the quick-release lock is firstly opened to release the locking relation between the handle assembly and the lock seat positioning groove, then the handle assembly is separated from the lock seat positioning groove, the limit of the lock seat positioning groove on the handle assembly is released, the locking on the radome can be released, and the radome is opened.
The beneficial effect of this application lies in: the radar cover connecting lock has the advantages that the installation mode is simple, the opening and closing process is convenient and quick, and other special unlocking tools are not needed except a tool screwdriver; the connecting lock is connected with the connector on the radome through threads, so that the radome can be quickly mounted and dismounted, and the radome is convenient to use and maintain.
The present application will be described in further detail with reference to the accompanying drawings.
Drawings
FIG. 1 is a schematic view of an aircraft radome hitch lock assembly.
Fig. 2 is a schematic view of the locking state of the aircraft radome attachment lock.
Fig. 3 is a schematic view of an aircraft radome attachment lock in an open state.
Fig. 4 is a schematic diagram of the use state of the aircraft radome connection lock.
Fig. 5 is a cross-sectional structural schematic diagram of an airplane radome connection lock in a locking use state.
The numbering in the figures illustrates: the aircraft comprises a joint 1, a lock seat 2, a lock body 3, a bush 4, a bayonet 5, a lock nail joint 6, a nut 7, a connecting piece 8, a handle groove 9, a folding handle 10, a connecting shaft 11, a torsion spring 12, a quick-release lock 13, a groove 14, a positioning groove 15, a limiting hole 16, a radome 17 and an aircraft body 18.
Detailed Description
Referring to the drawings, the airplane radome junction lock structure of the application comprises a lock body 3, a lock seat 2 and a joint 1, wherein the joint 1 is fixed on a radome 17, a threaded hole is formed in the joint 1, in the implementation, a connecting hole is formed in the joint, and a bush 4 with an internal thread is pressed in the connecting hole to form the threaded hole of the joint. The lock body 3 contain locking joint 7 and handle assembly, the front end of locking joint 7 is a pin rod with external screw thread, the external screw thread of this pin rod matches with the screw hole that connects 1, the rear end of locking joint 7 is the engaging lug, this engaging lug passes through connecting axle 11 and is articulated with handle assembly, the last quick-release lock 13 that is equipped with of handle assembly, lock seat 2 fix on aircraft organism 18, there is constant head tank 15 with handle assembly matching on the lock seat 2, the bottom of constant head tank 15 is equipped with the spacing hole 16 that matches with quick-release lock 13.
In order to clamp and inlay the handle assembly in the positioning groove 15 of the lock base, a convex bayonet 5 is arranged on the side wall of the positioning groove 15 of the lock base, and a groove 14 corresponding to the bayonet 5 is arranged on the handle assembly.
In implementation, the handle assembly comprises a handle slot 9, a folding handle 10 and a connecting piece 8, the front end of the connecting piece 8 is a double lug, the rear end of the connecting piece 8 is a single lug, the front end of the connecting piece 8 is hinged with the rear end of the locking joint 7 through a connecting shaft 11, the rear end of the connecting piece 8 is hinged with the front end of the handle slot 9 through another connecting shaft 11, grooves 14 are formed in two side slot walls of the front end of the handle slot 9, the folding handle 10 is hinged with the rear end of the handle slot 9 through one connecting shaft 11, the folding handle 10 can be overturned and embedded in a slot cavity of the handle slot 9, a through hole of a quick-release lock 13 is formed in the bottom of the slot cavity of the handle slot 9, a torsion spring 12 is further arranged between the folding handle 10 and the handle slot 9, and the quick-release lock 13.
When the radome is locked, a pin rod at the front end of a locking joint 6 of the lock body 3 is connected with a threaded hole of a joint 1 fixed on the radome, then the radome 17 is buckled at a proper position of the airplane body 18, so that the position of the joint 1 on the radome 17 corresponds to the position of a lock seat 2 fixed on the airplane body 18, then a handle component of the lock body 3 is pressed into a positioning groove 15 of the lock seat 2 to be clamped, and finally the handle component is locked with a limiting hole 16 at the bottom of the positioning groove of the lock seat through a quick-release lock 13 on the handle component; when the radome is opened, the quick-release lock 13 is firstly opened to release the locking relation between the handle assembly and the lock seat positioning groove 15, then the handle assembly is separated from the lock seat positioning groove 15, the limit of the lock seat positioning groove 15 on the handle assembly is released, the locking on the radome can be released, and the radome is opened.
In the embodiment shown, when the radome junction lock is installed, the connector 1 and the lock base 2 are respectively fixed on the structures of the radome 17 and the airplane body 18. The locking nail joint 6 on the lock body 3 is screwed into the bush 4 on the joint 1 and is locked and prevented from loosening by the adjusting nut 7. Each movable component of the lock body 3 comprises a lock nail joint 6, a connecting piece 8, a handle groove 9 and a folding handle 10 which are hinged through three connecting shafts 11.
When the radar cover connecting lock is locked, firstly, the handle groove 9 is rotated to drive the connecting piece 8 to rotate, the bayonet 5 on the lock base 2 is clamped into the circular groove 14 at the front end of the handle groove 9 and is compressed, meanwhile, the handle groove 9 is rotated and placed into the positioning groove 15 of the lock base 2, then the folding handle 10 is rotated to compress the torsion spring 12, the folding handle 10 is overturned and placed into the handle groove 9, the quick-release lock 13 is slightly pressed down and rotated by 90 degrees by a screwdriver, the quick-release lock 13 and the limiting hole 16 on the lock base can be locked, the locking process is completed, and the radar cover 17 and the airplane body 18 are locked. At this time, the end surface of the quick release lock 13 is flush with the surface of the folding handle 10, indicating that the quick release lock 13 is in the locked state.
When the radar cover connecting lock is unlocked, the quick-release lock 13 is pressed down and rotated by 90 degrees by using a screwdriver, the limit of the lock base limiting hole 16 on the quick-release lock 13 is removed, the folding handle 10 rotates upwards due to the resilience of the torsion spring 12, then the folding handle 10 is pulled to drive the handle groove 9 and the connecting piece 8 to rotate, the circular groove 14 at the front end of the handle groove 9 is disengaged from the bayonet 5 on the lock base 2, and then the unlocking of the connecting mechanism is completed.
The specific installation mode is shown in fig. 4, the joint 1 is installed on the radome through a bolt or a rivet, and the lock seat 2 is installed on the machine body structure. When the lock body 3 is locked, the handle groove 9 is clamped and pressed with the bayonet 5 to ensure that the radome 17 is tensioned and fixed with the structure of the airplane body 18, and the quick-release lock 13 is connected with the limiting hole 16 of the lock base 2 to ensure that the movable assembly of the lock body 3 is not separated from the bayonet 5, so that the reliable connection of the radome 17 and the structure of the airplane body 18 is ensured.
Claims (7)
1. The utility model provides an aircraft radome joint lock structure, contains lock body, lock seat and connects, its characterized in that, the joint fix on the radome, connect and have a screw hole, the lock body contain locking joint and handle components, the front end that the locking connects is a pin rod of outband screw thread, the external screw thread of this pin rod matches with the screw hole that connects, the rear end that the locking connects is the engaging lug, this engaging lug is articulated with handle components, the last quick-release lock that is equipped with of handle components, the lock seat fix on the aircraft organism, the constant head tank that has on the lock seat and matches with handle components, the bottom of constant head tank is equipped with the spacing hole that matches with the quick-release lock.
2. An aircraft radome coupler lock structure as claimed in claim 1 wherein projecting detents are provided on the side walls of the seat positioning slot and recesses corresponding to the detents are provided on the handle assembly.
3. An aircraft radome coupler lock structure as claimed in claim 1 or 2, wherein the handle assembly comprises a handle slot, a folding handle and a coupler, the front end of the coupler is double-lug, the rear end of the coupler is single-lug, the front end of the coupler is hinged with the rear end connecting lug of the locking joint, the rear end of the coupler is hinged with the front end of the handle slot, the grooves are formed on the two side slot walls of the front end of the handle slot, the folding handle is hinged with the rear end of the handle slot, the folding handle can be rotatably embedded in the slot cavity of the handle slot, the through hole of the quick-release lock is formed at the bottom in the slot cavity of the handle slot, a compression spring is further arranged between the folding handle and the handle slot, and the quick-release lock is embedded in the folding handle.
4. An aircraft radome adapter lock structure as claimed in claim 3 wherein the pin shank externally threaded at the forward end of the locking adapter has a locking nut thereon.
5. An aircraft radome coupler lock structure as claimed in claim 3 wherein the adapter has a coupling hole and a bushing having an internal thread is press-fitted into the coupling hole to form a threaded hole of the adapter.
6. A method of using an aircraft radome coupler lock structure according to claim 3, comprising the steps of: 1) when the radome is locked, a pin rod at the front end of a locking joint of the lock body is connected with a threaded hole of the joint fixed on the radome, the radome is buckled at a proper position of the machine body, the joint position on the radome corresponds to the position of a lock seat fixed on the machine body, a handle assembly of the lock body is pressed into a positioning groove of the lock seat, grooves on two side groove walls at the front end of the handle groove are clamped with a bayonet lock on the side wall of the positioning groove of the lock seat, the folding handle is overturned and embedded in the handle groove, and the handle assembly is locked with a limiting hole at the bottom of the positioning groove of the lock seat through a quick-release lock on the folding handle; 2) when opening the radome, open earlier and unload the lock soon and remove the locking relation with handle components and lock seat constant head tank, compression spring makes folding handle pop out from the handle inslot, and the rethread folding handle pulls out lock seat constant head tank with whole handle components, removes the spacing of lock seat constant head tank to handle components, can remove the locking to the radome, opens the radome.
7. A method of locking an aircraft radome, comprising: 1) the aircraft engine is characterized by comprising a connecting lock structure, a lock seat and a joint, wherein the joint is fixed on a radome and is provided with a threaded hole, the lock body comprises a locking joint and a handle assembly, the front end of the locking joint is a pin rod with external threads, the external threads of the pin rod are matched with the threaded hole of the joint, the rear end of the locking joint is a connecting lug, the connecting lug is hinged with the handle assembly, the handle assembly is provided with a quick-release lock, the lock seat is fixed on an aircraft body, the lock seat is provided with a positioning groove matched with the handle assembly, and the bottom of the positioning groove is provided with a limiting hole matched with the quick-release lock; 2) when the radome is locked, a pin rod at the front end of a locking joint of the lock body is connected with a threaded hole of a joint fixed on the radome, the radome is buckled at a proper position of the machine body, the position of the joint on the radome corresponds to the position of a lock seat fixed on the machine body, a handle assembly of the lock body is pressed into a positioning groove of the lock seat to be clamped, and finally the handle assembly and a limiting hole at the bottom of the positioning groove of the lock seat are locked through a quick-release lock on the handle assembly; 3) when the radome is opened, the quick-release lock is firstly opened to release the locking relation between the handle assembly and the lock seat positioning groove, then the handle assembly is separated from the lock seat positioning groove, the limit of the lock seat positioning groove on the handle assembly is released, the locking on the radome can be released, and the radome is opened.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010645052.XA CN111959745B (en) | 2020-07-06 | 2020-07-06 | Aircraft radome connecting lock structure and radome locking method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010645052.XA CN111959745B (en) | 2020-07-06 | 2020-07-06 | Aircraft radome connecting lock structure and radome locking method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111959745A true CN111959745A (en) | 2020-11-20 |
| CN111959745B CN111959745B (en) | 2022-08-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010645052.XA Active CN111959745B (en) | 2020-07-06 | 2020-07-06 | Aircraft radome connecting lock structure and radome locking method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513841B1 (en) * | 2000-10-10 | 2003-02-04 | Hartwell Corporation | Blowout latch |
| CN201566832U (en) * | 2009-10-29 | 2010-09-01 | 江西洪都航空工业集团有限责任公司 | Connecting rod quick-release lock |
| US20120181797A1 (en) * | 2011-01-14 | 2012-07-19 | Zeljko Baic | Latching Mechanism |
| RU2012126868A (en) * | 2012-06-28 | 2014-01-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | LOCK OF ATTACHMENT OF THE BOW AIRCRAFT OF THE AIRPLANE |
| US20150267724A1 (en) * | 2014-03-19 | 2015-09-24 | Marathonnorco Aerospace, Inc. | Pull Then Lift Hold Open Rod Lock Mechanism |
| CN108058806A (en) * | 2017-11-16 | 2018-05-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome of fighter passes in and out hatch door |
-
2020
- 2020-07-06 CN CN202010645052.XA patent/CN111959745B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513841B1 (en) * | 2000-10-10 | 2003-02-04 | Hartwell Corporation | Blowout latch |
| CN201566832U (en) * | 2009-10-29 | 2010-09-01 | 江西洪都航空工业集团有限责任公司 | Connecting rod quick-release lock |
| US20120181797A1 (en) * | 2011-01-14 | 2012-07-19 | Zeljko Baic | Latching Mechanism |
| RU2012126868A (en) * | 2012-06-28 | 2014-01-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | LOCK OF ATTACHMENT OF THE BOW AIRCRAFT OF THE AIRPLANE |
| US20150267724A1 (en) * | 2014-03-19 | 2015-09-24 | Marathonnorco Aerospace, Inc. | Pull Then Lift Hold Open Rod Lock Mechanism |
| CN108058806A (en) * | 2017-11-16 | 2018-05-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome of fighter passes in and out hatch door |
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| Publication number | Publication date |
|---|---|
| CN111959745B (en) | 2022-08-09 |
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