CN109850165A - Ejector seat vector device - Google Patents
Ejector seat vector device Download PDFInfo
- Publication number
- CN109850165A CN109850165A CN201610922425.7A CN201610922425A CN109850165A CN 109850165 A CN109850165 A CN 109850165A CN 201610922425 A CN201610922425 A CN 201610922425A CN 109850165 A CN109850165 A CN 109850165A
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- CN
- China
- Prior art keywords
- spring detent
- rocket
- ejector seat
- cable wire
- seat
- 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
Ejector seat vector device provided by the invention is made of ejector seat, rocket bag apparatus, spring detent mechanism, bracket, cable wire, guide wheel and operating-controlling mechanism etc..One end of rocket bag apparatus (2) is connected by hinge with the chair basin of ejector seat (1), the other end of rocket bag apparatus (2) is connected by hinge with spring detent mechanism (3), bracket (5) is by being hingedly coupled on the chair basin of ejector seat (1), guide wheel (6) and operating-controlling mechanism (7) are fixed on aircraft cockpit, the steel ball (4a) of cable wire (4) is clamped in spring detent mechanism (3), and the steel ball (4b) of cable wire (4) is placed in the spring detent (7a) of opening.The present invention can make ejector seat in abnormal situation, and the automatic angle for changing rocket pack thrust, makes ejector seat generate upward thrust, so that the ejection escape performance of seat is improved, to ensure the successful implementation of ejection escape before pop-up aircraft cockpit.
Description
Technical field:
The present invention relates to the ejector seat vector devices of pilot ejection lifesaving.
Background technique:
Rocket pack is fixedly mounted in its chair basin bottom part in the ejector seat of aircraft at present, and thrust caused by rocket pack only has
One fixed direction ramps seat after seat pops up aircraft cockpit, in normal condition that is, perpendicular to chair basin bottom part
Achievable ejection escape down.It is especially close at the aircraft elevation angle such as when aircraft lands and pull-up but in abnormal situation
Perpendicular to ground state when, rocket pack generate thrust be approximately parallel to ground, seat loses the power of rising, and liftoff
In the case that face is not high, it is bound to cause the failure of ejection escape.The sacrifice for destroying -15 comrades Zhang Chao touches unavoidably apart from distressed
Thought changes the direction of its thrust, seat is made to generate upward thrust if the thrust of rocket pack can be turned an angle at that time,
Then comrade Zhang Chao perhaps can be saved, and can successfully realize ejection escape.Because different from civilian technology, the present invention temporarily provides easy ejection
Seat vector device.
Summary of the invention:
The present invention is to solve ejector seat to change the thrust direction of rocket pack automatically when needed, generates seat upward
Thrust, to ensure the successful implementation of ejection escape.
In order to solve the above technical problems, ejector seat vector device by ejector seat, rocket bag apparatus, spring detent mechanism,
The composition such as cable wire, bracket, guide wheel and operating-controlling mechanism.One end of rocket bag apparatus is by hinge and ejector seat chair basin (similarly hereinafter) bottom
It is connected, the other end is fixed in chair basin bottom part with spring leaf and (is not shown in the figure, and is connected to spring detent mechanism with hinge
In rocket bag apparatus.Spring detent mechanism is made of spring detent and lasso, is usually tightened spring detent by lasso, is allowed to a cable wire one
The steel ball at end is clamped in spring detent.Bracket reaches turning for setting by being hingedly coupled on chair basin, to implement rocket bag apparatus
The length at angle, bracket is determined by the rocket bag apparatus corner set.Guide wheel is fixed on aircraft cockpit, required for reaching cable wire
It turns to.Operating-controlling mechanism is fixed on aircraft cockpit, is mainly made of spring detent and pressurized strut, and pressurized strut is more square using electromagnetic mechanism
Just, usually spring detent opens, and the other end steel ball of cable wire is disposed within to throw the reins to.When the elevation angle of aircraft reaches the angle of setting
When operating-controlling mechanism work, pressurized strut is slid by graphic arrow direction, and spring detent is tightened, the steel ball of cable wire is clamped in it is interior, such as
The elevation angle of aircraft restores normal, then pressurized strut sets back, and spring detent keeps opening.
Usually, since the spring detent of operating-controlling mechanism is in open configuration, the cable wire steel ball being placed in one is unfettered, therefore
It can carry out normal ejection escape program.When the aircraft elevation angle reaches the angle of setting, operating-controlling mechanism work, spring detent tightening will
The steel ball of cable wire is fixed on aircraft cockpit, when ejection sequence starting, while ejector seat rises, is clamped in spring detent machine
Cable wire steel ball in structure pulls downward on rocket bag apparatus, pulls the spring leaf (not shown) of fixed rocket bag apparatus, until
Interstage sleeve on bracket frees the lasso in spring detent mechanism, and spring detent opens automatically because losing constraint, discharges cable wire immediately
Steel ball, and its spring detent boss opened is blocked in the interstage sleeve lower end of bracket, so that rocket bag apparatus is reached the corner of setting, that is, is existed
Before seat pops up aircraft cockpit, it is automatically performed corner set by rocket bag apparatus, the thrust of rocket pack is by hinge and branch
Frame is transmitted to ejector seat, to make ejector seat obtain upward thrust, to realize the successful implementation of ejection escape.
Detailed description of the invention:
Attached drawing is the schematic diagram of ejector seat vector device of the present invention
In figure: 1- ejector seat；2- rocket bag apparatus；3- spring detent mechanism；3a- spring detent；3b- lasso；4- cable wire；
4a- is fixed on the steel ball of cable wire one end；4b- is fixed on the steel ball of the cable wire other end；5- bracket；5a- is fixed on bracket
Interstage sleeve；6- guide wheel；7- operating-controlling mechanism；7a- spring detent；7b- pressurized strut
Specific embodiment:
Ejector seat vector device shown in the drawings by ejector seat 1, rocket bag apparatus 2, spring detent mechanism 3, cable wire 4,
The composition such as bracket 5, guide wheel 6 and operating-controlling mechanism 7.
Rocket bag apparatus 2 in attached drawing, one end are connected by hinge with the chair basin of ejector seat 1, and the other end is by cutting with scissors
Chain is connected with spring detent mechanism 3, and spring detent mechanism 3 is made of spring detent 3a and lasso 3b.Bracket 5 is by hinge and ejector seat
1 chair basin is connected, and interstage sleeve 5a is fixed on bracket 5.Guide wheel 6 and operating-controlling mechanism 7 are fixed on aircraft cockpit, operating-controlling mechanism 7
It is made of spring detent 7a and pressurized strut 7b.The steel ball 4a of cable wire 4 is fixed in spring detent 3a by lasso 3b, the steel ball 4b of cable wire 4
It is placed in the spring detent 7a of opening.
When the elevation angle of aircraft reaches the angle of setting, the operating-controlling mechanism 7 for being fixed on aircraft cockpit works immediately, actuation
Cylinder 7b slides to graphic arrow direction, clamps steel ball 4b to tighten spring detent 7a, so that it is winged to be fixed on one end of cable wire 4
Base cabin, at this time such as starting ejection sequence, then due to the rising of seat, cable wire 4 is through its steel ball 4a and spring detent mechanism 3 by rocket
Bag apparatus pulls downward on after freeing the constraint (not shown) of spring leaf, until the interstage sleeve 5a of bracket 5 is by the set of spring detent mechanism 3
Circle 3b frees, and spring detent 3a opens the steel ball 4a of release cable wire 4 immediately, and blocks interstage sleeve 5a by the boss of the spring detent 3a opened
Lower end, so that rocket bag apparatus is reached the corner of setting, thus ejector seat pop up aircraft cockpit before, be automatically performed fire
Corner set by arrow bag apparatus makes ejector seat generate upward thrust immediately after popping up aircraft cockpit, to improve bullet
Penetrate the lifesaving performance of seat, it is ensured that the successful implementation of ejection escape.
Claims (3)
1. ejector seat vector device is by ejector seat (1), rocket bag apparatus (2), spring detent mechanism (3), cable wire (4), bracket
(5), guide wheel (6) and operating-controlling mechanism (7) composition, it is characterised in that: one end of rocket bag apparatus (2) is by hinge and ejector seat
(1) chair basin is connected, and the other end of rocket bag apparatus (2) is connected by hinge with spring detent mechanism (3), and bracket (5) is by cutting with scissors
For chain link on the chair basin of ejector seat (1), guide wheel (6) and operating-controlling mechanism (7) are fixed on aircraft cockpit, the steel ball of cable wire (4)
(4a) is clamped in spring detent mechanism (3), and the steel ball (4b) of cable wire (4) is placed in the spring detent (7a) of the operating-controlling mechanism (7) of opening
It is interior.
2. according to claim 1, spring detent mechanism (3) is made of spring detent (3a) and lasso (3b), it is characterised in that: lasso
(3b) is placed on spring detent (3a), and spring detent (3a) holding is made to close state.
3. according to claim 1, operating-controlling mechanism (7) is made of spring detent (7a) and pressurized strut (7b), it is characterised in that: manipulating
In mechanism (7) idle situation, pressurized strut (7b) is motionless, and spring detent (7a) keeps open configuration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610922425.7A CN109850165A (en) | 2016-10-18 | 2016-10-18 | Ejector seat vector device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610922425.7A CN109850165A (en) | 2016-10-18 | 2016-10-18 | Ejector seat vector device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109850165A true CN109850165A (en) | 2019-06-07 |
Family
ID=66887267
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610922425.7A Pending CN109850165A (en) | 2016-10-18 | 2016-10-18 | Ejector seat vector device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109850165A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846248A (en) * | 2020-07-27 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and unmanned aerial vehicle escape method |
| CN114537680A (en) * | 2022-03-11 | 2022-05-27 | 南京理工大学 | Catapult seat gas rudder type thrust vectoring nozzle |
| CN115027680A (en) * | 2022-06-22 | 2022-09-09 | 江苏大学 | Ejection seat using vector detonation propulsion and attitude correction method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3334847A (en) * | 1964-12-23 | 1967-08-08 | Saab Ab | Positioning and restraining means for ejection seat occupant |
| GB1217161A (en) * | 1967-03-17 | 1970-12-31 | James Martin | Improvements in vehicle ejection seats |
| US4236687A (en) * | 1979-05-24 | 1980-12-02 | The United States Of America As Represented By The Secretary Of The Navy | Ejection seat with pitch, roll and yaw control |
| US4787576A (en) * | 1986-09-29 | 1988-11-29 | The Boeing Company | Automatic multi-position G-protective ejection seat assembly |
| CN203603083U (en) * | 2013-11-12 | 2014-05-21 | 永康市原野工业产品设计有限公司 | Remote control folding type road warning sign |
| CN204383753U (en) * | 2014-11-26 | 2015-06-10 | 航宇救生装备有限公司 | A kind of new rocket ejection-seat compound type sparking mechanism |
| CN105620763A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Mounting angle adjustable structure of ejection seat |
-
2016
- 2016-10-18 CN CN201610922425.7A patent/CN109850165A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3334847A (en) * | 1964-12-23 | 1967-08-08 | Saab Ab | Positioning and restraining means for ejection seat occupant |
| GB1217161A (en) * | 1967-03-17 | 1970-12-31 | James Martin | Improvements in vehicle ejection seats |
| US4236687A (en) * | 1979-05-24 | 1980-12-02 | The United States Of America As Represented By The Secretary Of The Navy | Ejection seat with pitch, roll and yaw control |
| US4787576A (en) * | 1986-09-29 | 1988-11-29 | The Boeing Company | Automatic multi-position G-protective ejection seat assembly |
| CN203603083U (en) * | 2013-11-12 | 2014-05-21 | 永康市原野工业产品设计有限公司 | Remote control folding type road warning sign |
| CN105620763A (en) * | 2014-10-31 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Mounting angle adjustable structure of ejection seat |
| CN204383753U (en) * | 2014-11-26 | 2015-06-10 | 航宇救生装备有限公司 | A kind of new rocket ejection-seat compound type sparking mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111846248A (en) * | 2020-07-27 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and unmanned aerial vehicle escape method |
| CN114537680A (en) * | 2022-03-11 | 2022-05-27 | 南京理工大学 | Catapult seat gas rudder type thrust vectoring nozzle |
| CN115027680A (en) * | 2022-06-22 | 2022-09-09 | 江苏大学 | Ejection seat using vector detonation propulsion and attitude correction method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| DD01 | Delivery of document by public notice |
Addressee: Fei Shuifu Document name: Notification of Acceptance of Patent Application |
|
| DD01 | Delivery of document by public notice | ||
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190607 |
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| WD01 | Invention patent application deemed withdrawn after publication |