CN107606992A - A kind of launching tube bonnet auto-reset method - Google Patents
A kind of launching tube bonnet auto-reset method Download PDFInfo
- Publication number
- CN107606992A CN107606992A CN201711065768.7A CN201711065768A CN107606992A CN 107606992 A CN107606992 A CN 107606992A CN 201711065768 A CN201711065768 A CN 201711065768A CN 107606992 A CN107606992 A CN 107606992A
- Authority
- CN
- China
- Prior art keywords
- bonnet
- detachable
- mounting seat
- launching tube
- upper mounting
- 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.)
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Abstract
The present invention relates to a kind of launching tube bonnet auto-reset method, it is related to lift-off technology field.The present invention using can automatically reset launching tube bonnet realize launching tube bonnet and automatically reset, firing box bonnet rebounding mechanism is engaged with guide frame, bonnet flange, detachable bonnet, realizes the resilience of firing box bonnet；During vehicle launch, detachable bonnet is in the presence of boost motor gaseous-pressure, compression rebound mechanism high temperature spring, make bonnet it is quick, it is reliable, safely open, realize that combustion gas stream row leads；After vehicle launch outlet, gaseous-pressure disappears, and detachable bonnet realizes resilience under the action of the spring, bonnet is recovered closed mode.
Description
Technical field
The present invention relates to lift-off technology field, and in particular to a kind of launching tube bonnet auto-reset method.
Background technology
In traditional detachable bonnet scheme, irrecoverable closed mode after bonnet is opened.Shared certainly in bullet more than one
Arrange in pathway emitter, after vehicle launch, if bonnet can not close, the combustion gas of adjacent position can be to having completed transmitting number
Position produces ablation；Also, the number of transmitting position can become jet exhaust passage, different hairs can be changed due to the increase of row's guide face product
The aircraft of the number of penetrating position goes out an inner trajectory.
The content of the invention
(1) technical problems to be solved
The technical problem to be solved in the present invention is：How to design a kind of satisfaction bullet more than one and share row's pathway emitter
The launching tube bonnet auto-reset method needed.
(2) technical scheme
In order to solve the above-mentioned technical problem, the invention provides it is a kind of using can automatically reset launching tube bonnet realize
Launching tube bonnet auto-reset method, it is described can automatically reset launching tube bonnet include detachable bonnet 8, bonnet flange 7,
Rebounding mechanism and guide frame 6；
The rebounding mechanism includes upper mounting seat 1, lower mounting seat 2, high temperature spring 3, cushion pad 4 and mandrel 5；Wherein, institute
Lower connecting base 2 is stated in firing box guide base, the upper mounting seat 1 is by bolt after firing box is detachable
On lid 8, mandrel 5 is located at the lower section centre position of upper mounting seat 1；High temperature spring 3 is used to provide screen resilience for rebounding mechanism, is enclosed on the heart
On axle 5, and row constraint is entered by the shaft hole matching of mandrel 5 and lower mounting seat 2；Cushion pad 4 is adhered in lower mounting seat 2, is used for
When detachable bonnet 8 is opened, reduce the impulsive force between upper mounting seat 1 and lower mounting seat 2；
The guide frame 6 is installed on bonnet flange 7；Detachable bonnet 8 is fixed by shear pin under original state
On bonnet flange 7, shear pin can be broken in the presence of boost motor gaseous-pressure so that the detachable energy of bonnet 8 and bonnet
Flange 7 separates, and moves downward；Detachable bonnet 8 can slide up and down under the constraint of guide frame 6, so as to rebounding mechanism
It can be engaged with guide frame 6, bonnet flange 7, detachable bonnet 8, realize the automatic multiple of the detachable bonnet 8 of firing box
Position；In the presence of boost motor gaseous-pressure, detachable bonnet 8 drives upper mounting seat 1 to may be such that after compressing high temperature spring 3
Mounting seat 1 contacts with cushion pad 4；
It the described method comprises the following steps：During vehicle launch, in the presence of boost motor gaseous-pressure, separate
Formula bonnet 8 drives upper mounting seat 1 to compress high temperature spring 3, until upper mounting seat 1 contacts with cushion pad 4, by gaseous-pressure under
Mounting seat 2 is delivered on firing box base；Detachable bonnet 8 is realized after being separated with bonnet flange 7 and opened, and realizes that combustion gas stream is arranged
Lead, after vehicle launch outlet, gaseous-pressure disappears, and detachable bonnet 8 is realized resilience in the presence of high temperature spring 3, made
Detachable bonnet 8 recovers closed mode, realizes the reset of detachable bonnet 8.
Preferably, the groove on the guide frame 6 and the male cooperation at the detachable both ends of bonnet 8 so that separable
Formula bonnet 8 can slide up and down under the constraint of guide frame 6.
Preferably, the high temperature spring 3 is made of high-temperature alloy material.
(3) beneficial effect
The present invention using can automatically reset launching tube bonnet realize launching tube bonnet and automatically reset, firing box bonnet returns
Play mechanism to be engaged with guide frame, bonnet flange, detachable bonnet, realize the resilience of firing box bonnet；Vehicle launch
During, detachable bonnet is in the presence of boost motor gaseous-pressure, compression rebound mechanism high temperature spring, make bonnet it is quick,
Reliably, safely open, realize that combustion gas stream row leads；After vehicle launch outlet, gaseous-pressure disappears, and detachable bonnet is in bullet
Resilience is realized under spring effect, bonnet is recovered closed mode.
Brief description of the drawings
Fig. 1 be the present invention a kind of launching tube bonnet auto-reset method in design can automatically reset launching tube bonnet
Middle rebounding mechanism schematic diagram；
Fig. 2 is that the present invention automatically resets bonnet original state and working state schematic representation in bonnet, and wherein left figure is initial
State, right figure are working condition.
Embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Embodiment is described in further detail.
As shown in figure 1, the utilization of the present invention can the launching tube bonnet realized of automatically reset launching tube bonnet automatically reset
In method, it is necessary first to design one kind can automatically reset launching tube bonnet, this can automatically reset launching tube bonnet by that can divide
Formed from formula bonnet, rebounding mechanism and guide frame, rebounding mechanism includes upper mounting seat 1, lower mounting seat 2, high temperature spring 3, slow
Rush pad 4, mandrel 5.Wherein upper mounting seat 1 is arranged on the detachable bonnet 8 of firing box by bolt, and mandrel 5 is located at upper installation
1 lower section centre position of seat, lower connecting base 2 are arranged in firing box guide base, and high temperature spring 3 is enclosed in mandrel 5, and passes through the heart
Axle 5 and the shaft hole matching of lower mounting seat 2 enter row constraint.High temperature spring 3 provides screen resilience for bonnet rebounding mechanism, is closed using high temperature
Golden material, and anti-yaw damper material is coated to protect spring on its surface, there is the property that elasticity is kept under high-temperature fuel gas stream effect
Energy.Cushion pad 4 is adhered in lower mounting seat 2, for when detachable bonnet 8 is opened, reducing upper mounting seat 1 and lower mounting seat
Impulsive force between 2.
As shown in Fig. 2 guide frame 6 is installed on bonnet flange 7；Detachable bonnet 8 passes through shearing under original state
Pin be fixed on bonnet flange 7, in the presence of boost motor gaseous-pressure shear pin be broken, may be such that detachable bonnet 8 with
Bonnet flange 7 separates, and moves downward；Groove and the male cooperation at the detachable both ends of bonnet 8 on guide frame 6 so that can
Separate type bonnet 8 can slide up and down under the constraint of guide frame 6.Firing box bonnet rebounding mechanism and guide frame 6, bonnet flange
7th, detachable bonnet 8 is engaged, and realizes automatically reseting for the detachable bonnet 8 of firing box.
Based on it is above-mentioned can the launching tube bonnet auto-reset method of the invention realized of automatically reset launching tube bonnet, bag
Include following steps：During vehicle launch, in the presence of boost motor gaseous-pressure, detachable bonnet 8 drives and installed
Seat 1 compresses high temperature spring 3, until upper mounting seat 1 contacts with cushion pad 4, gaseous-pressure is delivered into transmitting by lower mounting seat 2
In case guide base；Detachable bonnet 8 separates with bonnet flange 7, quick, reliable, safely open, and realizes that combustion gas stream is arranged
Lead.After vehicle launch outlet, gaseous-pressure disappears, and detachable bonnet 8 realizes resilience under the effect of spring 3, makes to separate
Formula bonnet 8 recovers closed mode, realizes the reset of detachable bonnet 8.
As can be seen that simple in construction, reliable operation of the invention, can ensure that detachable bonnet is reliably opened in transmitting
Open, and can quickly and reliably resilience after transmitting terminates；In the row's of sharing pathway emitter, this automatically reset transmitting
Cylinder bonnet makes to have completed launch mission bonnet holding closed state, and the launching tube for having completed launch mission can be protected from adjacent
Number secondary ablation of position combustion gas stream, improve device access times；Make the combustion gas pushing effect phase of different transmitting positions in emission process
Together, ensure that different shooting sequence aircraft go out an interior ballistic consistency.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (3)
- It is 1. a kind of using can the launching tube bonnet auto-reset method realized of automatically reset launching tube bonnet, it is characterised in that It is described can automatically reset launching tube bonnet include detachable bonnet (8), bonnet flange (7), rebounding mechanism and guide frame (6)；The rebounding mechanism includes upper mounting seat (1), lower mounting seat (2), high temperature spring (3), cushion pad (4) and mandrel (5)；Its In, the lower connecting base (2) is arranged in firing box guide base, and the upper mounting seat (1) is arranged on firing box by bolt On detachable bonnet (8), mandrel (5) is located at the lower section centre position of upper mounting seat 1；It is rebounding mechanism that high temperature spring (3), which is used for, Screen resilience is provided, is enclosed in mandrel (5), and row constraint is entered by the shaft hole matching of mandrel (5) and lower mounting seat (2)；Cushion pad (4) it is adhered in lower mounting seat (2), for when detachable bonnet (8) is opened, reducing upper mounting seat (1) and lower mounting seat (2) impulsive force between；The guide frame (6) is installed on bonnet flange (7)；Detachable bonnet (8) is consolidated by shear pin under original state It is scheduled on bonnet flange (7), shear pin can be broken in the presence of boost motor gaseous-pressure so that detachable bonnet (8) energy Separate, and move downward with bonnet flange (7)；Detachable bonnet (8) can slide up and down under the constraint of guide frame (6), So as to which rebounding mechanism can be engaged with guide frame (6), bonnet flange (7), detachable bonnet (8), realize that firing box can Separate type bonnet (8) automatically reset；In the presence of boost motor gaseous-pressure, detachable bonnet (8) drives upper mounting seat (1) it may be such that upper mounting seat (1) contacts with cushion pad (4) after compressing high temperature spring (3)；It the described method comprises the following steps：During vehicle launch, in the presence of boost motor gaseous-pressure, after detachable Cover (8) and drive upper mounting seat (1) compression high temperature spring (3), until upper mounting seat (1) contacts with cushion pad (4), by gaseous-pressure It is delivered to by lower mounting seat (2) on firing box base；Detachable bonnet (8) realizes unlatching after being separated with bonnet flange (7), Realize that combustion gas stream row leads, after vehicle launch outlet, gaseous-pressure disappears, work of the detachable bonnet (8) in high temperature spring (3) Resilience is realized under, detachable bonnet (8) is recovered closed mode, realizes the reset of detachable bonnet (8).
- 2. the method as described in claim 1, it is characterised in that groove and detachable bonnet on the guide frame (6) (8) male cooperation at both ends so that detachable bonnet (8) can slide up and down under the constraint of guide frame (6).
- 3. method as claimed in claim 1 or 2, it is characterised in that the high temperature spring (3) uses high-temperature alloy material system Into.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711065768.7A CN107606992B (en) | 2017-11-02 | 2017-11-02 | A kind of launching tube rear cover auto-reset method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711065768.7A CN107606992B (en) | 2017-11-02 | 2017-11-02 | A kind of launching tube rear cover auto-reset method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107606992A true CN107606992A (en) | 2018-01-19 |
| CN107606992B CN107606992B (en) | 2019-03-01 |
Family
ID=61084728
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711065768.7A Active CN107606992B (en) | 2017-11-02 | 2017-11-02 | A kind of launching tube rear cover auto-reset method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107606992B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4934241A (en) * | 1987-11-12 | 1990-06-19 | General Dynamics Corp. Pomona Division | Rocket exhaust deflector |
| US20060090635A1 (en) * | 2002-10-30 | 2006-05-04 | Lockheed Martin Corporation | Article comprising a canister closure with pressure-pulse release |
| CN106507887B (en) * | 2006-11-24 | 2011-08-24 | 上海机电工程研究所 | The hood-opening device of MISSILE LAUNCHING case |
| RU2537068C1 (en) * | 2013-09-02 | 2014-12-27 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Launching facility |
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
-
2017
- 2017-11-02 CN CN201711065768.7A patent/CN107606992B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4934241A (en) * | 1987-11-12 | 1990-06-19 | General Dynamics Corp. Pomona Division | Rocket exhaust deflector |
| US20060090635A1 (en) * | 2002-10-30 | 2006-05-04 | Lockheed Martin Corporation | Article comprising a canister closure with pressure-pulse release |
| CN106507887B (en) * | 2006-11-24 | 2011-08-24 | 上海机电工程研究所 | The hood-opening device of MISSILE LAUNCHING case |
| RU2537068C1 (en) * | 2013-09-02 | 2014-12-27 | Открытое акционерное общество "Завод им. В.А. Дегтярева" | Launching facility |
| CN105043166A (en) * | 2015-07-20 | 2015-11-11 | 北京理工大学 | Low-impact overall ejection type launching canister front cover |
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| Publication number | Publication date |
|---|---|
| CN107606992B (en) | 2019-03-01 |
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