CN1373073A - Push vector helm - Google Patents
Push vector helm Download PDFInfo
- Publication number
- CN1373073A CN1373073A CN 01109111 CN01109111A CN1373073A CN 1373073 A CN1373073 A CN 1373073A CN 01109111 CN01109111 CN 01109111 CN 01109111 A CN01109111 A CN 01109111A CN 1373073 A CN1373073 A CN 1373073A
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- CN
- China
- Prior art keywords
- rudder
- helm
- push vector
- jet
- vector
- 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
A thrust vector rudder for the jet airplane with two parallel jet-engines is composed of hydraulic driver, universal joint, rotary axle and rudder plate. It is characterized by that the rotary axle of directional rudder is linked via universal joint with that of said thrust vector rudder positioned between the jet exhausts of said two jet-engines, and the hydraulic driver of directional rudder can drive both directional rudder and thrust vector rudder to change the airflow direction of jet exhausts.
Description
The present invention is a kind of push vector helm, is applicable to two send out and together on the jet plane, on aircrafts such as " destroying-6 ", " destroying-8 ".
At present, military fighter aircraft turns to all and realizes by the deflecting direction rudder, and aircraft is when spiraling with high angles of attack flight fast, and rudder face does not often satisfy the crossrange maneuvering of aircraft.Though some advanced aircraft installs the thrust vectoring device additional now,, be difficult on conventional airplane, installing because device and control are all very complicated.
The object of the invention is to provide a kind of push vector helm that improves aircraft crossrange maneuvering ability, and it can work in coordination with rudder kick, changes the nozzle air flow line, improves aircraft turning rate and alerting ability.
The present invention is achieved in that the push vector helm turning cylinder links to each other with the yaw rudder turning cylinder by universal-joint, the yaw rudder fluid pressure drive device drives the thrust vectoring rudder kick in the driving direction rudder kick, push vector helm changes single engine tail nozzle air flow line, turn to thereby assist yaw rudder to carry out, increase the aircraft crossrange maneuvering.
Simple in structure, convenient easily system that the present invention has, easy manipulation, reliability advantages of higher.
Fig. 1 is the push vector helm structural representation that connects transmission with universal-joint.
Fig. 2 is the push vector helm structural representation with meshed transmission gear.
1 couple of the present invention is further described below in conjunction with accompanying drawing, a kind of push vector helm.By the turning cylinder 2 of yaw rudder fluid pressure drive device 1 driving direction rudder 5, yaw rudder turning cylinder 2 links to each other with the turning cylinder 4 of push vector helm 6 by universal-joint 3; Push vector helm 6 is positioned in the middle of two nozzles that are close to 7, each turning cylinder is located by axis hole, direction of passage rudder fluid pressure drive device 1 drives yaw rudder 5 and push vector helm 6 deflections simultaneously, changes air flow line, strengthens the crossrange maneuvering of aircraft and the horizontal controllability of high-angle-of-attack flight.
Claims (2)
1, a kind of push vector helm, it is made up of yaw rudder fluid pressure drive device, universal-joint, steering shaft and rudder face, it is characterized in that: the yaw rudder turning cylinder links to each other with the push vector helm steering shaft by universal-joint, and the yaw rudder actuating device also drives push vector helm in the driving direction rudder; Push vector helm is positioned at two sending out in the middle of the nozzle.
2, according to claim 1, diaxon connects also available two gears mesh and replaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01109111 CN1373073A (en) | 2001-03-07 | 2001-03-07 | Push vector helm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01109111 CN1373073A (en) | 2001-03-07 | 2001-03-07 | Push vector helm |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1373073A true CN1373073A (en) | 2002-10-09 |
Family
ID=4657725
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01109111 Pending CN1373073A (en) | 2001-03-07 | 2001-03-07 | Push vector helm |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1373073A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104139858A (en) * | 2014-07-03 | 2014-11-12 | 余彩仙 | Disc type aircraft |
| WO2017121114A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Vector engine having rudders |
| CN109383789A (en) * | 2018-11-21 | 2019-02-26 | 南京航空航天大学 | High lift device and its application |
| CN112124563A (en) * | 2009-09-09 | 2020-12-25 | 威罗门飞行公司 | Elevon control system |
-
2001
- 2001-03-07 CN CN 01109111 patent/CN1373073A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124563A (en) * | 2009-09-09 | 2020-12-25 | 威罗门飞行公司 | Elevon control system |
| CN104139858A (en) * | 2014-07-03 | 2014-11-12 | 余彩仙 | Disc type aircraft |
| CN104139858B (en) * | 2014-07-03 | 2016-05-04 | 罗仙花 | Disc aircraft |
| WO2017121114A1 (en) * | 2016-01-14 | 2017-07-20 | 王佐良 | Vector engine having rudders |
| CN109383789A (en) * | 2018-11-21 | 2019-02-26 | 南京航空航天大学 | High lift device and its application |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |