CN214397270U - Time domain aircraft nacelle locking structure - Google Patents
Time domain aircraft nacelle locking structure Download PDFInfo
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- CN214397270U CN214397270U CN202022482746.4U CN202022482746U CN214397270U CN 214397270 U CN214397270 U CN 214397270U CN 202022482746 U CN202022482746 U CN 202022482746U CN 214397270 U CN214397270 U CN 214397270U
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- joint
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- pipe fitting
- connecting pipe
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Abstract
The utility model belongs to the technical field of aircraft structural design, in particular to time domain aircraft nacelle locking structure. The rotation of the shaft is controlled through a handle, the shaft drives a four-bar mechanism consisting of the single-lug connector, the first connector, the pipe fitting and the second connector to move, the lock hook rotates, and the locking and throwing of the time domain pod is realized through two clamping grooves of the mounting support. The relative positions of the handle and the lock hook and the movement stroke of the mechanism can be changed by adjusting the lengths of the connecting rod and the shaft, so that the adjustment is convenient, and the applicability is wide. The lock hook supports through two lock hook supports, directly locks nacelle towing ring, can not produce the friction with other parts and lead to falling lacquer, corrosion. Prevent through erection support, first spacing flange, second spacing flange that the subassembly from moving, ensure structural stability. The material used in the whole structure has good strength and rigidity, the standard part adopts a common part, and the use and maintenance cost is low.
Description
Technical Field
The utility model belongs to the technical field of aircraft structural design, in particular to time domain aircraft nacelle locking structure.
Background
The existing locking structure of the aircraft pod in the time domain adopts two locking hooks to lock hanging shafts on two sides of the pod, the locking hooks are L-shaped, the upper portion of each locking hook extends into the interior of the aircraft body and is provided with a handle, the lower portion of each locking hook is limited through a baffle, and a layer of pipe fitting is arranged outside each locking hook for positioning. The structure is only suitable for the situation that the nacelle is arranged at the lower part of the fuselage, the two lock hooks need to be moved to the handles by an operator, and the two handles are operated simultaneously, so that the operation is inconvenient. The lock hook frequently rubs with the baffle, easily falls the lacquer, produces the corrosion.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a middle time domain aircraft nacelle locking structure who adopts four-bar linkage optimizes the locking mode, improves structural stability, avoids the part corrosion, is convenient for adjust simultaneously, and extensive applicability is general, and is easy and simple to handle, maintains and use cost hangs down.
In order to solve the technical problem, the utility model discloses the technical scheme who adopts is:
a time domain aircraft pod lockout structure comprising: the device comprises a handle, a mounting support, a shaft, a first joint, a pipe fitting, a second joint, a latch hook support and a latch hook;
one end of the shaft is connected with the handle, the other end of the shaft is connected with the fixed end of the first joint, and the first joint and the shaft form an angle of 90 degrees;
two ends of the pipe fitting are respectively connected with the free end of the first joint and the free end of the second joint; the pipe fitting, the first joint and the second joint form a four-bar linkage structure;
the fixed end of the second joint is connected with one end of the lock hook;
the mounting support is fixed in the machine body; the shaft penetrates through the mounting support and can freely rotate;
the lock hook support is fixed on the surface of the pod platform; the lock hook penetrates through the lock hook support and can rotate freely.
Further, the structure further includes: a stopper; two clamping grooves are formed in the mounting support and correspond to the switching states of the locking hooks respectively; one end of the retainer is connected with the handle, and the other end of the retainer is matched with the clamping groove to be used for opening and closing the locking hook.
Further, the structure further includes: a first limiting flange; the first limiting flange is in a hollow cylinder shape with flange edges at two sides, and is sleeved on the shaft and riveted with the shaft; and flange edges on two sides of the first limiting flange are respectively positioned on two sides of the mounting support to prevent the shaft from moving.
Further, the structure further includes: a second limiting flange; the second limiting flange is in a hollow cylinder shape with flange edges at two sides, and is sleeved on the locking hook and riveted with the locking hook; and flange edges on two sides of the second limiting flange are respectively positioned on two sides of the locking hook support to prevent the locking hook from moving.
Furthermore, the structure also comprises two single-lug joints, and two ends of the pipe fitting are respectively provided with one single-lug joint; the pipe fitting is connected with the free end of the first joint and the free end of the second joint through the two single lug joints.
Further, the pipe includes: the connecting device comprises a first connecting pipe, a second connecting pipe and a threaded shaft; the first connecting pipe and the second connecting pipe are provided with internal threads in opposite directions, and two ends of the threaded shaft are respectively provided with external threads matched with the internal threads of the first connecting pipe and the second connecting pipe; the first connecting pipe and the second connecting pipe are connected through the threaded shaft, and the length of the pipe fitting is adjusted.
The utility model discloses a 1 control shaft 4 of a handle rotates, and axle 4 drives the four-bar linkage motion that monaural joint 5, first joint 9, pipe fitting 10, second connect 11 to constitute, and latch hook 7 rotates, realizes locking and throwing the time domain nacelle through two draw-in grooves of erection support 3. Compared with the prior art, the operation is convenient by only one handle, and the handle 1 can be installed at the operator seat without the movement of the operator. The relative positions of the handle 1 and the latch hook 7 and the movement stroke of the mechanism can be changed by adjusting the lengths of the connecting rod and the shaft 4, so that the adjustment is convenient, and the applicability is wide. The lock hook 7 is supported by the two lock hook supports 6, directly locks the nacelle towing ring, and cannot rub with other parts to cause paint falling and corrosion. Prevent through erection support 3, first spacing flange 8, second spacing flange 12 that the subassembly from moving, ensure structural stability. The material used in the whole structure has good strength and rigidity, the standard part adopts a common part, and the use and maintenance cost is low.
Drawings
FIG. 1 is a schematic diagram of a time domain aircraft pod lockout architecture;
FIG. 2 is a schematic view of the internal structure of the fuselage;
FIG. 3 is a schematic view of a nacelle platform configuration;
the device comprises a handle 1, a stop 2, a mounting support 3, an axis 4, a single lug joint 5, a latch hook support 6, a latch hook 7, a first limiting flange 8, a first joint 9, a pipe fitting 10, a second joint 11 and a second limiting flange 12.
Detailed Description
The technical solution of the present invention will be further explained with reference to the accompanying drawings and the detailed description.
A time domain aircraft pod lockout structure, as shown in fig. 1, comprising: handle 1, stopper 2, erection support 3, axle 4, monaural joint 5, latch hook support 6, latch hook 7, first spacing flange 8, first joint 9, pipe fitting 10, second joint 11, second spacing flange 12. The shaft 4 is connected with the first joint 9, the second joint 11 and the lock hook 7 through split pins to serve as a rack, the first joint 9 and the second joint 11 serve as side link rods, the pipe fitting 10 is riveted with the single lug joint 5 to serve as a connecting rod, and the side link rods are connected with the connecting rod through bolts serving as shafts to form a four-bar mechanism. The handle 1 is connected with the shaft 4 through a cotter pin, is connected with the stop 2 through a spring and a flat head shaft, and the locking hook 7 is fixed through a locking hook support 6. When the locking device is operated, the handle 1 rotates to control the four-bar mechanism to move after the retainer 2 is lifted up, so that the aim of controlling the locking hook 7 to be opened/closed is achieved, and the retainer 2 is clamped in two clamping grooves of the mounting support 3 and respectively corresponds to the opening/closing state of the locking hook 7. Two clamping grooves of the mounting support 3, the first limiting flange 8 and the second limiting flange 12 are used for preventing the components from moving in a string mode, and the structural stability is ensured.
As shown in fig. 2, the erection supports 3 are mounted on the fuselage internal stringer structure, and the shaft 4 passes through the fuselage skin and is secured by the erection supports 3 and the skin stiffening structure. As shown in fig. 3, the latch hook support 6 is installed on the lower surface of the nacelle platform outside the fuselage, and the structure can be moved by adjusting the lengths of the side link and the link in the four-bar linkage. The operator can directly operate the seat to control the retraction of the nacelle outside the fuselage.
The nacelle locking structure design is verified by strength, seaworthiness, process and the like, and various performance requirements are met.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A time domain aircraft pod lockout structure, characterized by: the structure includes: the device comprises a handle, a mounting support, a shaft, a first joint, a pipe fitting, a second joint, a latch hook support and a latch hook;
one end of the shaft is connected with the handle, the other end of the shaft is connected with the fixed end of the first joint, and the first joint and the shaft form an angle of 90 degrees;
two ends of the pipe fitting are respectively connected with the free end of the first joint and the free end of the second joint; the pipe fitting, the first joint and the second joint form a four-bar linkage structure;
the fixed end of the second joint is connected with one end of the lock hook;
the mounting support is fixed in the machine body; the shaft penetrates through the mounting support and can freely rotate;
the lock hook support is fixed on the surface of the pod platform; the lock hook penetrates through the lock hook support and can rotate freely.
2. A time domain aircraft pod lockout structure as claimed in claim 1, wherein: the structure further includes: a stopper;
two clamping grooves are formed in the mounting support and correspond to the switching states of the locking hooks respectively; one end of the retainer is connected with the handle, and the other end of the retainer is matched with the clamping groove to be used for opening and closing the locking hook.
3. A time domain aircraft pod lockout structure as claimed in claim 2, wherein: the structure further includes: a first limiting flange;
the first limiting flange is in a hollow cylinder shape with flange edges at two sides, and is sleeved on the shaft and riveted with the shaft; and flange edges on two sides of the first limiting flange are respectively positioned on two sides of the mounting support to prevent the shaft from moving.
4. A time domain aircraft pod lockout structure as claimed in claim 2, wherein: the structure further includes: a second limiting flange;
the second limiting flange is in a hollow cylinder shape with flange edges at two sides, and is sleeved on the locking hook and riveted with the locking hook; and flange edges on two sides of the second limiting flange are respectively positioned on two sides of the locking hook support to prevent the locking hook from moving.
5. A time domain aircraft pod lockout structure as claimed in claim 1, wherein:
the structure also comprises two single-lug joints, and two ends of the pipe fitting are respectively provided with one single-lug joint; the pipe fitting is connected with the free end of the first joint and the free end of the second joint through the two single lug joints.
6. A time domain aircraft pod lockout structure as claimed in claim 1, wherein: the pipe fitting includes: the connecting device comprises a first connecting pipe, a second connecting pipe and a threaded shaft; the first connecting pipe and the second connecting pipe are provided with internal threads in opposite directions, and two ends of the threaded shaft are respectively provided with external threads matched with the internal threads of the first connecting pipe and the second connecting pipe; the first connecting pipe and the second connecting pipe are connected through the threaded shaft, and the length of the pipe fitting is adjusted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022482746.4U CN214397270U (en) | 2020-10-30 | 2020-10-30 | Time domain aircraft nacelle locking structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022482746.4U CN214397270U (en) | 2020-10-30 | 2020-10-30 | Time domain aircraft nacelle locking structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214397270U true CN214397270U (en) | 2021-10-15 |
Family
ID=78034564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022482746.4U Active CN214397270U (en) | 2020-10-30 | 2020-10-30 | Time domain aircraft nacelle locking structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214397270U (en) |
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2020
- 2020-10-30 CN CN202022482746.4U patent/CN214397270U/en active Active
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