CN104340358B - A kind of servo tab mechanism for Aircraft Flight Test - Google Patents
A kind of servo tab mechanism for Aircraft Flight Test Download PDFInfo
- Publication number
- CN104340358B CN104340358B CN201310337389.4A CN201310337389A CN104340358B CN 104340358 B CN104340358 B CN 104340358B CN 201310337389 A CN201310337389 A CN 201310337389A CN 104340358 B CN104340358 B CN 104340358B
- Authority
- CN
- China
- Prior art keywords
- rocking arm
- gear ratio
- servo tab
- variable gear
- hold
- 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.)
- Expired - Fee Related
Links
Abstract
Technical field of aircraft structure design of the present invention, particularly relates to a kind of servo tab mechanism for Aircraft Flight Test.Mechanism is by hold-down support (1), variable gear ratio rocking arm (8), adjustable drawbar (6) and connector composition, wherein, bolt (5) hinge is passed through on the servo tab (4) of aircraft rudder surface (3) in one end of adjustable drawbar (6), the other end is installed in three length difference support arms of variable gear ratio rocking arm (8) by connecting bolt (7), rocking arm (8) is hinged on hold-down support (1) by rotating shaft connecting bolt (2), another support arm of rocking arm (8) is slidably attached in the elongated slot on hold-down support (1) by locking pin (9), by selecting the difference two in (8) three support arms of variable gear ratio rocking arm to carry out above-mentioned connection, adjust adjustable drawbar (6) again and be attached realizing the proving flight of the servo tab of different drive ratios.
Description
Technical field
Technical field of aircraft structure design of the present invention, particularly relates to a kind of servo tab mechanism for Aircraft Flight Test.
Background technology
The rudder face servo tab being currently used for Aircraft Flight Test is all to use a fixing gear ratio structure, as shown in Figure 1.But
Owing to Theoretical Calculation and practical flight there will be deviation, when Aircraft Flight Test, the gear ratio if there is design is unreasonable, aircraft with
The stick force of dynamic tab trim cannot meet the requirement of aircraft flight, then need to redesign gear ratio and servo tab, then
It is equipped with again, takes a flight test, therefore extend the Aircraft Flight Test cycle, reduce efficiency.
Summary of the invention
The technical problem to be solved in the present invention:
The present invention be directed to above-mentioned deficiency of the prior art, devise rudder face servo tab conversion equipment.Its objective is to provide
A kind of simple in construction, be beneficial to realize, structure member is few, it is little to take up room, can realize multiple gear ratio, be applicable to Aircraft Flight Test
Rudder face servo tab mechanism.
Technical scheme:
A kind of servo tab mechanism for Aircraft Flight Test, by hold-down support 1, variable gear ratio rocking arm 8, adjustable drawbar 6
And connector composition, wherein, one end of adjustable drawbar 6 by bolt 5 hinge on the servo tab 4 of aircraft rudder surface 3,
The other end is installed in three length difference support arms of variable gear ratio rocking arm 8 by connecting bolt 7, rocking arm 8
Being hinged on hold-down support 1 by rotating shaft connecting bolt 2, another support arm of rocking arm 8 is connected slidably by locking pin 9
It is connected in the elongated slot on hold-down support 1, by selecting the difference two in 8 three support arms of variable gear ratio rocking arm to carry out above-mentioned company
Connect, then adjust adjustable drawbar 6 and be attached realizing the proving flight of the servo tab of different drive ratios.
Beneficial effects of the present invention:
The present invention is widely used in aircraft rudder surface servo tab system, it is possible to meet at structure space smaller, it is achieved multiple biography
The Flight of dynamic ratio.: 1) a kind of new aircraft variable gear ratio servo tab mechanism for taking a flight test is provided；2) less
Construction weight loss；3) relatively small installing space；4) manufacture, assembly technology simple；5) gear ratio is realized adjustable；
6) easy to use, low cost；6) new machine development efficiency is improved.
Accompanying drawing explanation
Fig. 1 existing aircraft servo tab operating mechanism schematic diagram；
Fig. 2 is for the variable gear ratio servo tab structural scheme of mechanism taken a flight test；In figure: hold-down support 1, rotating shaft screw bolt
2, rudder face 3, tab 4, connecting bolt 5, adjustable drawbar 6, connecting bolt 7, variable gear ratio rocking arm 8,
Locking pin 9.
Detailed description of the invention
With embodiment, the present invention is explained as follows below in conjunction with the accompanying drawings:
Seeing accompanying drawing 2, this is a complete example structure figure of a kind of servo tab mechanism for Aircraft Flight Test.
One end of adjustable drawbar 6 is by bolt 5 hinge on the servo tab 4 of aircraft rudder surface 3, and the other end is installed to variable
On gear ratio rocking arm 8, and rocking arm 8 is fixed on bearing 1 by rotating shaft connecting bolt 2 and locking pin 9, thus constitutes one
Individual simple follower.When rudder face moves upward, variable gear ratio rocking arm is fixed, adjustable drawbar 6 and servo tab 4
Also can move upward therewith, but due to servo tab 4 and rudder face 3 hinge, cause adjustable drawbar 6 to push tab 4
The trend moved downward, and then tab 4 is deflected down relative to rudder face 3；Otherwise rudder face 3 moves downward, servo-actuated tune
Full wafer 4 upward deflects relative to rudder face 3.
When needs adjust servo tab gear ratio, disconnect the connecting bolt 7 of adjustable drawbar 6 and variable gear ratio rocking arm 8,
Pull down locking pin 9, variable gear ratio rocking arm 8 connecting bolt 2 around the shaft is rotated to the ratio position that need to verify, again
Locking pin 9 is installed fixed by variable gear ratio rocking arm 8, now servo tab 4 is fixed on and rudder face 3 neutral position,
Then adjust the length of adjustable drawbar 6 so that it is can be connected with variable gear ratio rocking arm 8, connecting bolt 7 is finally installed, i.e.
Can verify that new gear ratio servo tab.
Claims (1)
1., for a servo tab mechanism for Aircraft Flight Test, mechanism includes hold-down support (1) and servo tab (4)
, it is characterized in that, also include variable gear ratio rocking arm (8), adjustable drawbar (6) and connector, wherein, bolt (5) hinge is passed through on the servo tab (4) of aircraft rudder surface (3) in one end of adjustable drawbar (6), the other end is installed in three length difference support arms of variable gear ratio rocking arm (8) by connecting bolt (7), rocking arm (8) is hinged on hold-down support (1) by rotating shaft connecting bolt (2), another support arm of rocking arm (8) is slidably attached in the elongated slot on hold-down support (1) by locking pin (9), by selecting the difference two in (8) three support arms of variable gear ratio rocking arm to carry out above-mentioned connection, adjust adjustable drawbar (6) again and be attached realizing the proving flight of the servo tab of different drive ratios.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337389.4A CN104340358B (en) | 2013-08-05 | 2013-08-05 | A kind of servo tab mechanism for Aircraft Flight Test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310337389.4A CN104340358B (en) | 2013-08-05 | 2013-08-05 | A kind of servo tab mechanism for Aircraft Flight Test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104340358A CN104340358A (en) | 2015-02-11 |
| CN104340358B true CN104340358B (en) | 2016-09-14 |
Family
ID=52496959
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310337389.4A Expired - Fee Related CN104340358B (en) | 2013-08-05 | 2013-08-05 | A kind of servo tab mechanism for Aircraft Flight Test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104340358B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01229798A (en) * | 1988-03-09 | 1989-09-13 | Shin Meiwa Ind Co Ltd | Actuator mechanism for controlling rudder face with variable transmission ratio |
| DE10037318C2 (en) * | 1999-09-02 | 2002-10-10 | Daimler Chrysler Aerospace | Mechanism for actuating a compensation valve arranged in an aircraft wastewater discharge device |
| CZ2009560A3 (en) * | 2009-08-21 | 2011-05-25 | Ševcík@Milan | Continuously variable transmission |
| DE102009039967A1 (en) * | 2009-09-03 | 2011-03-10 | Airbus Operations Gmbh | Adjustment mechanism for the kinematic guidance of an adjusting body when it is adjusted to a supporting structural part, adjusting mechanism for kinematic adjustment of a high-lift body and high-lift system with such adjustment mechanism |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
-
2013
- 2013-08-05 CN CN201310337389.4A patent/CN104340358B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN104340358A (en) | 2015-02-11 |
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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 | ||
| 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: 20160914 Termination date: 20170805 |