CN105692422A - Detachable hoisting mechanism in end faces of cabin of warhead - Google Patents
Detachable hoisting mechanism in end faces of cabin of warhead Download PDFInfo
- Publication number
- CN105692422A CN105692422A CN201610090485.7A CN201610090485A CN105692422A CN 105692422 A CN105692422 A CN 105692422A CN 201610090485 A CN201610090485 A CN 201610090485A CN 105692422 A CN105692422 A CN 105692422A
- Authority
- CN
- China
- Prior art keywords
- warhead
- hoisting
- flap seat
- face
- detachable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
Abstract
The invention relates to a detachable hoisting mechanism in the end faces of a cabin of a warhead and belongs to the hoisting technology of missile warheads. The force bearing portions in a front end frame and a rear end frame of the warhead are each provided with two sets of hoisting seat mounting holes symmetrically. Hoisting seats are mounted in the positions of the hoisting seat mounting holes, and a hoisting hole is formed in the middle of each hoisting seat. The hoisting seats of the warhead are assembled on force bearing plates on the front end face and rear end face of the warhead through screws in the hoisting seat mounting holes. No hoisting hole needs to be formed in the outer surface of the warhead, so that the performance of the outer surface of the warhead is improved. No hoisting hole is needed, so that the butt-joint airtightness of cabin sections of the warhead is not influenced. Hoisted loads are dispersedly transmitted to structural force bearing faces in the butt-joint end faces of the warhead through the screws, so that the problem that the hoisting strength is insufficient due to one-point stress is solved. The thickening design of the end frames of the warhead is not needed. The scheme that the hoisting seats are detachable is adopted, so that the auxiliary mass of the warhead is not increased.
Description
Technical field
The present invention relates to detachable derricking gear in a kind of warhead nacelle end face, belong to missile armament lifting technology。
Background technology
The usual quality of missile armament is big, needs in use to arrange lifting eye seat in explosive assembly casing structure in process, realizes the lifting carrying of warhead。The lifting method of traditional warhead is by arranging lifting eye at warhead back or arranging lifting eye mode on interface frame, mating frame, by suspender bolt and warhead lifting eye mechanical connection, realizes the hoisting function of warhead。Which existence affects the shortcomings such as the sealing property of warhead appearance performance or cabin section docking end face。
Summary of the invention
The present invention is directed to the problems referred to above, purpose there are provided detachable derricking gear in a kind of warhead nacelle end face, has designed flap seat, has designed flap seat installing hole in warhead end face on force bearing plate, including warhead being played the design of flap seat mounting hole site, screw designs is installed。By installing bolts assemblies to force bearing plate in warhead end face, adopt the outside lifting tool such as hanging bolt and lifting rope can realize warhead and fast lift by crane。
To achieve these goals, the present invention adopts the following technical scheme that
Detachable derricking gear in a kind of warhead nacelle end face, in warhead front and back end frame, bearing position is respectively symmetrical arranged 2 groups and plays flap seat installing hole；
In the position playing flap seat installing hole, flap seat is installed, has risen and be provided with lifting eye in the middle part of flap seat；
Warhead rises flap seat has adopted the screw in flap seat installing hole to be assemblied on the force bearing plate of warhead front/rear end。
Frame place, front and back end of warhead is provided with end-face seal ring。
The quantity often having organized flap seat installing hole is 4。
Advantages of the present invention: the present invention, without arranging lifting eye at warhead outer surface, improves warhead outer surface performance；Without arranging lifting eye, affect warhead cabin section Butt sealing；Adopt screw sling load dispersion to be delivered in warhead docking end face inner structure load-carrying surface, improve single-point stress and cause the problems such as lifting intensity is not enough；Without warhead end frame is thickeied design；Play flap seat and adopt detachable scheme, the attached quality of warhead will not be increased。
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention；
Fig. 2 is A-A generalized section in Fig. 1。
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing 1,2:
(1), according to load load requirements, in warhead front and back end frame 1, bearing position is respectively symmetrical arranged 2 groups and plays flap seat installing hole 6, and front end face 2 groups plays flap seat and installs relation as shown in Figure 1。
(2), retrain according to warhead sling load demand and bulk, design four groups and play flap seat 5, design including a flap seat form construction design, lifting eye 4, play flap seat installing hole 6；And adopt high strength alloy steel processing to make four groups and play flap seat。
(3), warhead rises flap seat adopts 4 × 4 groups of screws 6 to be as shown in the figure assemblied on the force bearing plate 3 of warhead front/rear end。Front and back end frame 1 place of warhead is provided with end-face seal ring 2。
(4), warhead lifting time, the outside lifting tool such as suspender bolt, rise after flap seat is connected to position by lifting eye 4 and warhead, aspect can be implemented and lift by crane efficiently；
(5), warhead lifting is after task completes, and is dismantled by flap seat 5, can avoid the attached quality of increase warhead。
Claims (3)
1. detachable derricking gear in a warhead nacelle end face, it is characterised in that: in warhead front and back end frame (1), bearing position is respectively symmetrical arranged 2 groups and plays flap seat installing hole (6)；
In the position playing flap seat installing hole (6), flap seat (5) is installed, has played flap seat (5) middle part and be provided with lifting eye (4)；
Warhead rises flap seat has adopted the screw in flap seat installing hole (6) to be assemblied on the force bearing plate (3) of warhead front/rear end。
2. detachable derricking gear in warhead according to claim 1 nacelle end face, it is characterised in that: front and back end frame (1) place of warhead is provided with end-face seal ring (2)。
3. detachable derricking gear in warhead according to claim 1 nacelle end face, it is characterised in that: the quantity often having organized flap seat installing hole (6) is 4。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090485.7A CN105692422A (en) | 2016-02-18 | 2016-02-18 | Detachable hoisting mechanism in end faces of cabin of warhead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610090485.7A CN105692422A (en) | 2016-02-18 | 2016-02-18 | Detachable hoisting mechanism in end faces of cabin of warhead |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105692422A true CN105692422A (en) | 2016-06-22 |
Family
ID=56222376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610090485.7A Pending CN105692422A (en) | 2016-02-18 | 2016-02-18 | Detachable hoisting mechanism in end faces of cabin of warhead |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105692422A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184161A (en) * | 2021-04-29 | 2021-07-30 | 北京临近空间飞行器系统工程研究所 | Special-shaped shell bearing large axial pressure and hoisting structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3123402A (en) * | 1964-03-03 | Automobile safety belt anchor construction | ||
| US20070228235A1 (en) * | 2006-04-04 | 2007-10-04 | Nicholas Roccaforte | Duct hoisting bracket |
| CN101597011A (en) * | 2008-06-06 | 2009-12-09 | 中国海洋石油总公司 | Offshore wind powder tower hoisting appliance |
| CN202346581U (en) * | 2011-11-29 | 2012-07-25 | 北京新风机械厂 | Cantilever type sling |
| CN104743056A (en) * | 2015-02-11 | 2015-07-01 | 沪东中华造船(集团)有限公司 | Method for lifting ship aluminum alloy segments |
-
2016
- 2016-02-18 CN CN201610090485.7A patent/CN105692422A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3123402A (en) * | 1964-03-03 | Automobile safety belt anchor construction | ||
| US20070228235A1 (en) * | 2006-04-04 | 2007-10-04 | Nicholas Roccaforte | Duct hoisting bracket |
| CN101597011A (en) * | 2008-06-06 | 2009-12-09 | 中国海洋石油总公司 | Offshore wind powder tower hoisting appliance |
| CN202346581U (en) * | 2011-11-29 | 2012-07-25 | 北京新风机械厂 | Cantilever type sling |
| CN104743056A (en) * | 2015-02-11 | 2015-07-01 | 沪东中华造船(集团)有限公司 | Method for lifting ship aluminum alloy segments |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184161A (en) * | 2021-04-29 | 2021-07-30 | 北京临近空间飞行器系统工程研究所 | Special-shaped shell bearing large axial pressure and hoisting structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160622 |