CN106564613A - Mounting device and method for large-pulling-force return parallel-connection spring for weapon bay door of aircraft - Google Patents
Mounting device and method for large-pulling-force return parallel-connection spring for weapon bay door of aircraft Download PDFInfo
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- CN106564613A CN106564613A CN201510644961.0A CN201510644961A CN106564613A CN 106564613 A CN106564613 A CN 106564613A CN 201510644961 A CN201510644961 A CN 201510644961A CN 106564613 A CN106564613 A CN 106564613A
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- spring
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- sliding sleeve
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Abstract
The invention belongs to the field of designs of a releasing mechanism of an aircraft, and particularly relates to a mounting device and mounting method for a large-pulling-force return parallel-connection spring for a weapon bay door of the aircraft. For a long time, a mounting method of manual stretching is generally used to assemble a small-scale pulling force parallel-connection spring in a stretching state on the aircraft. According to the mounting device for the large-pulling-force return parallel-connection spring for the weapon bay door of the aircraft, provided by the invention, the mounting of a steel rope supporting seat is positioned by the two times of stretching of a parallel-connection spring when the parallel-connection spring is in two working states. Through the adoption of the mounting device disclosed by the invention, the stretching and the assembling of the large-pulling-force return parallel-connection spring of the aircraft are performed, and are visual to observe and convenient to adjust; and the labor intensity is reduced, the assembling efficiency is improved, and the assembling quality of products is improved.
Description
Technical field
The invention belongs to aircraft throwing mechanism design field, and in particular to a kind of for the big of aircraft weapon hatch door
Pulling force return spring erecting device and installation method.
Background technology
For a long time, for pulling force small-sized on aircraft, simultaneously spring is assembled generally in a stretched state with manual drawing
Installation method is stretched, its method is：First, one end of simultaneously spring is fixed on a part, then will simultaneously with handss
Spring stretching is fixed on another part, adjusts the pretension of simultaneously spring afterwards, and regulation finishes rear and spring and installs
Into.But it is for more than the big pulling force spring outside manpower stretchy scope, clearly not all right in this way
, so must be by force-extension confined state and conformal assembling.
Using and spring stretching and erecting device stretching and install simultaneously spring, can coefficient of elasticity is big, pretension it is big
And spring be conveniently installed on precalculated position, but also can meet and spring succeeding stretch assembling will
Ask.
The content of the invention
The technical problem to be solved is：A kind of big pulling force return for aircraft weapon hatch door is provided
And spring erecting device, positioned by the succeeding stretch of simultaneously spring and spring cable wire bearing under two working conditions
Install.
To solve above-mentioned technical problem, the technical scheme is that：
A kind of big pulling force return for aircraft weapon hatch door spring erecting device, including drawing mechanism and guarantor's type
Mechanism；
The drawing mechanism include leading screw, handwheel, threaded retainers seat, curved handle latch, forked standard, push rod,
Slide, movable block, platform and big band shoulder nut；Wherein threaded retainers seat, forked standard and slide pass through hexagonal
Bolt, pad, nut and straight pin are sequentially fixed on platform；Leading screw is coordinated by trapezoidal thread with handwheel
Fix together and by threaded retainers seat supports；One end of push rod is connected with leading screw by curved handle latch,
The other end sequentially passes through the hole of slide and movable block, and solid with movable block by big band shoulder nut and holding screw
It is fixed to connect；
Bao Xing mechanisms include curved handle latch, small band shoulder nut, termination block piece, to component, bolt, alignment pin,
Guide rod, sliding sleeve and guide pin bushing；Wherein described sliding sleeve is welded to connect with one end of the guide pin bushing, and the guide rod is passed through
Sliding sleeve and guide pin bushing and it is slidably connected, is threaded in one end of the guide rod, which passes through small band shoulder nut and institute
State termination block piece to be fixedly connected, the other end of guide pin bushing is threaded, which passes through small band shoulder nut with relative end
First speed part is fixedly connected；It is described that component is connected with the top of termination block piece by bolt, and can fix described
Big pulling force return spring.
A kind of utilization said apparatus carry out the installation method of big pulling force return spring, comprise the following steps：
1) simultaneously spring is fixed on by termination block piece and the zoarium to component composition by the nut block piece at simultaneously spring two ends
On；By the distance between groove on the end face of adjustment end first speed part and platform, it is determined that and spring it is initial
Position；
2) handwheel on threaded retainers seat is rotated, the leading screw on threaded retainers seat is rotated, guarantor's type machine is driven
The stretching of on structure and spring；
3) quarter when simultaneously spring is stretched to first state specified location, i.e., described in the block piece of termination on end face and platform
When distance is L1 between line, the position of first through hole is determined on guide rod according to the third through-hole on sliding sleeve and processed
Sliding sleeve and guide rod are fixed by the first through hole afterwards with alignment pin；
4) remove the curved handle latch for connection end block piece and movable block, and for connection end block piece and
The curved handle latch of forked standard；
5) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the first of simultaneously spring
The installation of part cable wire bearing on state reconciliation aircraft；
6) aircraft is removed into by the Bao Xing mechanisms and is arranged in the groove of movable block and forked standard again, and with curved
Handle latch is fixed；
7) 2), when simultaneously spring is stretched to the second state specified location, i.e., termination block piece is described for repeat step
Apart from L2 between groove on end face and platform, then determine on guide rod that second leads to according to the third through-hole on sliding sleeve
The position in hole simultaneously processes second through hole, fixes sliding sleeve and guide rod with alignment pin afterwards；
9) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the second of simultaneously spring
The installation of another part cable wire bearing on state reconciliation aircraft；
10) simultaneously spring will be installed on aircraft by the second state.
Beneficial effects of the present invention are：The stretching and assembling of the big pulling force return of aircraft spring are carried out using the present invention,
Observation is directly perceived, convenient to adjust, and reduces labor intensity, improves efficiency of assembling, improves the assembling of product
Quality.
Description of the drawings
Fig. 1 is the front view of erecting device of the present invention；
Fig. 2 is the top view of erecting device of the present invention；
B-B views of the Fig. 3 for Fig. 2；
Fig. 4 is the left view of erecting device of the present invention；
Fig. 5 is erecting device of the present invention spring drawing value.
Wherein, 1- leading screws, 2- handwheels, 3- threaded retainers seats, 4- curved handle latches, 5- forked standards, 6- push rods,
The big band shoulder nut of 7- slides, 8- movable blocks, 9- platforms, 10-, 11- small band shoulder nuts, 12- terminations block piece, 13-
To component, 14- bolts, 15- alignment pins, 16- guide pin bushings, 17- struts, 18- guide rods, 19- spring, 20- nuts
Block piece, 21- holding screws, 22- hex bolts, 23- pads, 24- nuts, 25- straight pins, 26- first lead to
Hole, the second through holes of 27-, 28- third through-holes
Specific embodiment
Below in conjunction with the accompanying drawings the specific embodiment of the present invention is described further.
Refer to Fig. 1, a kind of big pulling force return for aircraft weapon hatch door spring erecting device, including stretching
Mechanism and Bao Xing mechanisms；
The drawing mechanism include leading screw 1, handwheel 2, threaded retainers seat 3, curved handle latch 4, forked standard 5,
Push rod 6, slide 7, movable block 8, platform 9 and big band shoulder nut 10；Wherein threaded retainers seat 3, fork
Seat 5 and slide 7 are sequentially fixed at platform by hex bolts 22, pad 23, nut 24 and straight pin 25
On 9；Leading screw 1 is combined together by trapezoidal thread with handwheel 2 and supports solid by threaded retainers seat 3
It is fixed；One end of push rod 6 is connected with leading screw 1 by curved handle latch 4, and the other end sequentially passes through slide 7 and moves
The hole of motion block 8, and be fixedly connected with movable block 8 by big band shoulder nut 10 and holding screw 21；
Bao Xing mechanisms include curved handle latch 4, small band shoulder nut 11, termination block piece 12, to component 13, bolt
14th, alignment pin 15, guide rod 16, sliding sleeve 17 and guide pin bushing 18；Wherein described sliding sleeve 17 and the guide pin bushing 18
One end be welded to connect, the guide rod 16 passes through sliding sleeve 17 and guide pin bushing 18 and is slidably connected, in the guide rod
16 one end is threaded, and which is passed through small band shoulder nut 11 and is fixedly connected with the termination block piece 12, guide pin bushing
18 other end is threaded, and which is passed through small band shoulder nut 11 and is fixedly connected with relative termination block piece 12；
It is described that component 13 is connected with the top of termination block piece 12 by bolt 14, and the big pulling force time can be fixed
Position spring.
A kind of utilization said apparatus carry out the installation method of big pulling force return spring, comprise the following steps：
1) termination block piece 12 simultaneously will be fixed on and to component by spring 19 by the nut block piece 20 at simultaneously 19 two ends of spring
On the zoarium of 13 compositions；By the distance between groove on the end face of adjustment end first speed part 12 and platform 9,
It is determined that and spring initial position；
2) handwheel 2 on threaded retainers seat 3 is rotated, the leading screw 1 on threaded retainers seat 3, band is rotated
In Dong Bao types mechanism and spring 19 is stretched；
3) when simultaneously spring is stretched to first state specified location, i.e., end face and platform 9 described in termination block piece 12
On groove between distance when being L1, determine first on guide rod 16 according to the third through-hole 28 on sliding sleeve 17
The position of through hole 26 simultaneously processes the first through hole 26, afterwards will be sliding sleeve 17 and guide rod 16 solid with alignment pin 15
It is fixed；
4) the curved handle latch 4 for connection end block piece 12 and movable block 8 is removed, and is used for connection end
The curved handle latch 4 of block piece 12 and forked standard 5；
5) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the first of simultaneously spring
The installation of part cable wire bearing on state reconciliation aircraft；
6) aircraft is removed into by the Bao Xing mechanisms and is arranged in the groove of movable block 8 and forked standard 5 again, and
Fixed with curved handle latch 4；
7) repeat step 2), when and spring be stretched to the second state specified location when, i.e. termination block piece 12
Apart from L2 between groove on the end face and platform 9, then determine according to the third through-hole 28 on sliding sleeve 17
The position of the second through hole 27 second through hole 27 is processed on guide rod 16, afterwards with alignment pin 15 by sliding sleeve
17 and guide rod 16 fix；
9) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the second of simultaneously spring
The installation of another part cable wire bearing on state reconciliation aircraft；
10) simultaneously spring will be installed on aircraft by the second state.
The invention discloses a kind of innovation of and spring stretching erecting device big-and-middle-sized for aircraft.Solve big-and-middle
The problem that type spring stretching are wasted time and energy when installing, its mesopore 1 and hole 2 only need to be prepared when using first time,
It is follow-up just to press hole 1 and the stretching of 2 position of hole using simultaneously spring.
Claims (2)
1. a kind of big pulling force return for aircraft weapon hatch door spring erecting device, it is characterised in that：The dress
Put including drawing mechanism and Bao Xing mechanisms；
The drawing mechanism include leading screw (1), handwheel (2), threaded retainers seat (3), curved handle latch (4),
Forked standard (5), push rod (6), slide (7), movable block (8), platform (9) and big band shoulder nut (10)；
Wherein threaded retainers seat (3), forked standard (5) and slide (7) by hex bolts (22), pad (23),
Nut (24) and straight pin (25) are sequentially fixed on platform (9)；Leading screw (1) is led to handwheel (2)
Cross trapezoidal thread to be combined together and support fixation by threaded retainers seat (3)；The one of push rod (6)
End is connected with leading screw (1) by curved handle latch (4), and the other end sequentially passes through slide (7) and movable block (8)
Hole, and be fixedly connected with movable block (8) by big band shoulder nut (10) and holding screw (21)；
The Bao Xing mechanisms include curved handle latch (4), small band shoulder nut (11), termination block piece (12), right
Component (13), bolt (14), alignment pin (15), guide rod (16), sliding sleeve (17) and guide pin bushing (18)；
Wherein described sliding sleeve (17) is welded to connect with one end of the guide pin bushing (18), and the guide rod (16) passes through
Sliding sleeve (17) and guide pin bushing (18) and it is slidably connected, is threaded in one end of the guide rod (16), its
It is fixedly connected with the termination block piece (12) by small band shoulder nut (11), the other end of guide pin bushing (18)
It is threaded, which is passed through small band shoulder nut (11) and is fixedly connected with relative termination block piece (12)；It is described
Component (13) is connected with the top of termination block piece (12) by bolt (14), and can fix described big
Pulling force return spring.
2. it is a kind of to utilize the above-mentioned big pulling force return for aircraft weapon hatch door and spring erecting device carries out big pulling force
The installation method of return spring, it is characterised in that comprise the following steps：
1) termination block piece (12) simultaneously will be fixed on by spring (19) by the nut block piece (20) at simultaneously spring (19) two ends
On the zoarium constituted to component (13)；By the end face of adjustment end first speed part (12) and platform (9)
On the distance between groove, it is determined that and spring initial position；
2) handwheel (2) on threaded retainers seat (3) is rotated, the silk on threaded retainers seat (3) is rotated
Thick stick (1), drives the stretching of in Bao Xing mechanisms and spring (19)；
3) when and spring be stretched to first state specified location when, i.e. termination block piece (12) end face and platform
(9), when distance is L1 between the groove on, determines according to the third through-hole (28) on sliding sleeve (17) and lead
The position of first through hole (26) the first through hole (26) is processed on bar (16), afterwards with alignment pin (15)
Will be sliding sleeve (17) and guide rod (16) fixed；
4) the curved handle latch (4) for connection end block piece (12) and movable block (8), Yi Jiyong are removed
In the curved handle latch (4) of connection end block piece (12) and forked standard (5)；
5) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the first of simultaneously spring
The installation of part cable wire bearing on state reconciliation aircraft；
6) aircraft is removed into by the Bao Xing mechanisms and is arranged on the groove of movable block (8) and forked standard (5) again
In, and it is fixed with curved handle latch (4)；
7) repeat step 2), when and spring be stretched to the second state specified location when, i.e. termination block piece (12)
The end face and platform (9) on groove between distance (L2), then according to the 3rd on sliding sleeve (17)
Through hole (28) determines on guide rod (16) position of the second through hole (27) and processes second through hole (27),
Afterwards will be sliding sleeve (17) and guide rod (16) fixed with alignment pin (15)；
9) the Bao Xing mechanisms are taken out, moves on aircraft and spring installed position, with the second of simultaneously spring
The installation of another part cable wire bearing on state reconciliation aircraft；
10) simultaneously spring will be installed on aircraft by the second state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510644961.0A CN106564613B (en) | 2015-10-08 | 2015-10-08 | A kind of big pulling force return for aircraft weapon hatch door and spring mounting device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510644961.0A CN106564613B (en) | 2015-10-08 | 2015-10-08 | A kind of big pulling force return for aircraft weapon hatch door and spring mounting device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106564613A true CN106564613A (en) | 2017-04-19 |
| CN106564613B CN106564613B (en) | 2019-01-25 |
Family
ID=58507144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510644961.0A Active CN106564613B (en) | 2015-10-08 | 2015-10-08 | A kind of big pulling force return for aircraft weapon hatch door and spring mounting device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106564613B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10249751A (en) * | 1997-03-05 | 1998-09-22 | Fujita Auto Kogyo Kk | Coil spring compressing tool for automobile shock absorber |
| US6434807B1 (en) * | 2000-08-02 | 2002-08-20 | Paul Begin | Apparatus for removing and replacing coil springs and fasteners |
| CN102744602A (en) * | 2012-07-04 | 2012-10-24 | 江苏森源电气股份有限公司 | Energy storage spring mounting device |
| CN202684857U (en) * | 2012-06-28 | 2013-01-23 | 中国重汽集团福建海西汽车有限公司 | Spring tool |
| CN203887808U (en) * | 2014-06-18 | 2014-10-22 | 国家电网公司 | Spring assembling tool |
| CN104772619A (en) * | 2015-04-21 | 2015-07-15 | 浙江华丰电动工具有限公司 | Assembly machine for swing arm and tension spring of awning |
| CN204686815U (en) * | 2015-05-05 | 2015-10-07 | 马夸特开关(上海)有限公司 | Spring assembling device |
-
2015
- 2015-10-08 CN CN201510644961.0A patent/CN106564613B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10249751A (en) * | 1997-03-05 | 1998-09-22 | Fujita Auto Kogyo Kk | Coil spring compressing tool for automobile shock absorber |
| US6434807B1 (en) * | 2000-08-02 | 2002-08-20 | Paul Begin | Apparatus for removing and replacing coil springs and fasteners |
| CN202684857U (en) * | 2012-06-28 | 2013-01-23 | 中国重汽集团福建海西汽车有限公司 | Spring tool |
| CN102744602A (en) * | 2012-07-04 | 2012-10-24 | 江苏森源电气股份有限公司 | Energy storage spring mounting device |
| CN203887808U (en) * | 2014-06-18 | 2014-10-22 | 国家电网公司 | Spring assembling tool |
| CN104772619A (en) * | 2015-04-21 | 2015-07-15 | 浙江华丰电动工具有限公司 | Assembly machine for swing arm and tension spring of awning |
| CN204686815U (en) * | 2015-05-05 | 2015-10-07 | 马夸特开关(上海)有限公司 | Spring assembling device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106564613B (en) | 2019-01-25 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |