CN205206991U - Thrust vector spray tube throat area adjustment mechanism - Google Patents
Thrust vector spray tube throat area adjustment mechanism Download PDFInfo
- Publication number
- CN205206991U CN205206991U CN201520994750.5U CN201520994750U CN205206991U CN 205206991 U CN205206991 U CN 205206991U CN 201520994750 U CN201520994750 U CN 201520994750U CN 205206991 U CN205206991 U CN 205206991U
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- CN
- China
- Prior art keywords
- cam
- throat area
- thrust
- spray tube
- adjustment sheet
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- Expired - Fee Related
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Abstract
The utility model provides a thrust vector spray tube throat area adjustment mechanism, it is main including the driving cam axle, cam 1, cam 2, convergence adjustment sheet connecting rod, the action roller, the cam slot hole, and a support, fixed roll, cam 1 is installed in driving cam axle vertical direction with cam 2, 1 lower extreme on the cam and fixed roll contact, 2 upper ends on the cam and activity roller contact, when the driving cam rotation of axes, rotary motion and the slip in the cam slot hole are done with cam 2 to cam 1, it removes to make the action roller promote convergence adjustment sheet connecting rod, promote the deflection of convergence adjustment sheet, realize the adjustment of thrust vector spray tube throat area. The utility model discloses the advantage is that mechanical structure is simple, has in the thrust vectoring nozzle size under the condition of close restraint, and this mechanism can guarantee thrust vectoring nozzle throat area and adjust necessary stroke under less transmission pressure angle, realizes the adjustment of spray tube throat area.
Description
Technical field
The utility model relates to a kind of jet engine thrust vector spray field, particularly relates to a kind of Thrust-vectoring Nozzle throat area controlling mechanism.
Background technique
At present, jet engine thrust vector spray is in conceptual phase, Thrust-vectoring Nozzle can increase substantially mobility and the agility of aircraft, research and develop a kind of mechanical structure simple, when vector spray size has strict restriction, can under less drive train pressure angle, ensure that vector spray throat area regulates necessary stroke, the mechanism realizing nozzle throat rea adjusting is necessary.
Summary of the invention
The purpose of this utility model is to provide a kind of Thrust-vectoring Nozzle throat area controlling mechanism.
A kind of Thrust-vectoring Nozzle throat area controlling mechanism, this mechanism mainly comprises drive cam shaft (1), cam 1(2), cam 2(3), convergence adjustment sheet connecting rod (4), action roller (5), cam elongated hole (6), support (7), fixed idler whell (8).
Cam 1 and cam 2 are arranged on drive cam shaft (1) Vertical direction, cam 1 lower end contacts with fixed idler whell (8), cam 2 upper end contacts with action roller (5), when airplane engine drives drive cam shaft (1) to rotate, cam 1 and cam 2 rotate and slip in cam elongated hole (6), make action roller (5) promote the movement of convergence adjustment sheet connecting rod (4), promote the deflection of convergence adjustment sheet, realize the adjustment of Thrust-vectoring Nozzle throat area.
Cam 1(2) and cam 2(3) be bolted together.
The utility model advantage is that mechanical structure is simple, and when vector spray size has strict restriction, this mechanism under less drive train pressure angle, can ensure that vector spray throat area regulates necessary stroke, realize the adjustment of nozzle throat area.
Accompanying drawing explanation
Below in conjunction with figure and mode of execution, the utility model is described in further detail.
Fig. 1 is structural representation of the present utility model.
Figure number explanation.
1 drive cam shaft, 2 cam 1,3 cam 2,4 convergence adjustment sheet connecting rods.
5 action rollers, 6 cam elongated holes, 7 supports, 8 fixed idler whells
Embodiment
With reference to figure 1, the utility model provides a kind of Thrust-vectoring Nozzle throat area controlling mechanism, and this mechanism mainly comprises drive cam shaft (1), cam 1(2), cam 2(3), convergence adjustment sheet connecting rod (4), action roller (5), cam elongated hole (6), support (7), fixed idler whell (8).
Cam 1 and cam 2 are arranged on drive cam shaft (1) Vertical direction, cam 1(2) and cam 2(3) be bolted together, cam 1 lower end contacts with fixed idler whell (8), cam 2 upper end contacts with action roller (5), when airplane engine drives drive cam shaft (1) to rotate, cam 1 and cam 2 rotate and slip in cam elongated hole (6), action roller (5) is made to promote the movement of convergence adjustment sheet connecting rod (4), promote the deflection of convergence adjustment sheet, realize the adjustment of Thrust-vectoring Nozzle throat area.
This mechanism's mechanical structure is simple, and when vector spray size has strict restriction, this mechanism under less drive train pressure angle, can ensure that vector spray throat area regulates necessary stroke, realize the adjustment of nozzle throat area.
Claims (2)
1. a Thrust-vectoring Nozzle throat area controlling mechanism, it is characterized in that: this mechanism mainly comprises drive cam shaft (1), cam 1(2), cam 2(3), convergence adjustment sheet connecting rod (4), action roller (5), cam elongated hole (6), support (7), fixed idler whell (8), cam 1 and cam 2 are arranged on drive cam shaft (1) Vertical direction, cam 1 lower end contacts with fixed idler whell (8), cam 2 upper end contacts with action roller (5), when airplane engine drives drive cam shaft (1) to rotate, cam 1 and cam 2 rotate and slip in cam elongated hole (6), action roller (5) is made to promote convergence adjustment sheet connecting rod (4) mobile, promote the deflection of convergence adjustment sheet, realize the adjustment of Thrust-vectoring Nozzle throat area.
2. a kind of Thrust-vectoring Nozzle throat area controlling mechanism as claimed in claim 1, is characterized in that: cam 1(2) and cam 2(3) be bolted together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520994750.5U CN205206991U (en) | 2015-12-06 | 2015-12-06 | Thrust vector spray tube throat area adjustment mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520994750.5U CN205206991U (en) | 2015-12-06 | 2015-12-06 | Thrust vector spray tube throat area adjustment mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205206991U true CN205206991U (en) | 2016-05-04 |
Family
ID=55844716
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520994750.5U Expired - Fee Related CN205206991U (en) | 2015-12-06 | 2015-12-06 | Thrust vector spray tube throat area adjustment mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205206991U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657043A (en) * | 2019-09-09 | 2020-01-07 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN111852685A (en) * | 2020-05-25 | 2020-10-30 | 北京动力机械研究所 | Designated limit position limiting device of linear motion component |
| CN113982777A (en) * | 2021-11-10 | 2022-01-28 | 南京航空航天大学 | Pneumatic thrust vectoring nozzle of two throats of linearization control |
| CN114776463A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Throat-adjustable invisible low-tail-resistance spray pipe |
-
2015
- 2015-12-06 CN CN201520994750.5U patent/CN205206991U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110657043A (en) * | 2019-09-09 | 2020-01-07 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN110657043B (en) * | 2019-09-09 | 2022-02-08 | 南京航空航天大学 | Mechanical disturbance type throat offset pneumatic vectoring nozzle |
| CN111852685A (en) * | 2020-05-25 | 2020-10-30 | 北京动力机械研究所 | Designated limit position limiting device of linear motion component |
| CN113982777A (en) * | 2021-11-10 | 2022-01-28 | 南京航空航天大学 | Pneumatic thrust vectoring nozzle of two throats of linearization control |
| CN114776463A (en) * | 2022-04-14 | 2022-07-22 | 中国航发沈阳发动机研究所 | Throat-adjustable invisible low-tail-resistance spray pipe |
| CN114776463B (en) * | 2022-04-14 | 2023-04-04 | 中国航发沈阳发动机研究所 | Throat-adjustable invisible low-tail-resistance spray pipe |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160504 Termination date: 20161206 |