CN203832761U - Control stick lateral loading device applicable to aircraft fatigue tests - Google Patents
Control stick lateral loading device applicable to aircraft fatigue tests Download PDFInfo
- Publication number
- CN203832761U CN203832761U CN201420188262.0U CN201420188262U CN203832761U CN 203832761 U CN203832761 U CN 203832761U CN 201420188262 U CN201420188262 U CN 201420188262U CN 203832761 U CN203832761 U CN 203832761U
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- CN
- China
- Prior art keywords
- control stick
- jociey stick
- fixed
- aircraft
- loading
- 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 - Lifetime
Links
- 238000009661 fatigue test Methods 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 abstract description 6
- 125000004122 cyclic group Chemical group 0.000 abstract description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 abstract 4
- 229910000831 Steel Inorganic materials 0.000 abstract 3
- 239000010959 steel Substances 0.000 abstract 3
- 238000004804 winding Methods 0.000 abstract 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a control stick lateral loading device applicable to aircraft fatigue tests. The control stick lateral loading device specifically comprises a control stick fixture (1), steel cables (2), pulleys (3), brace rods (4), loading devices (5), fixed lugs (6) and a pedestal (7), wherein both ends of the control stick fixture (1) are connected with the steel ropes (2), each steel cable (2) is connected with one end of the corresponding loading device after winding around the corresponding pulley (3), the other ends of the loading devices (5) are connected with the pedestal through the fixed plugs (6) which are fixed at two ends of the pedestal (7), and the pedestal is fixed on a seat sliding rail to meet the requirement of the control stick on left and eight cyclic loading; when in test processes, reloading is not needed, and thereby test cycles can be shortened; the whole device is mounted in a cabin with small occupied space, and no balance load is needed to be applied to an aircraft, thus being a great help to smooth progress of operating system fatigue tests.
Description
Technical field
The utility model relates to structure design and the application of aircraft fatigue experimental device, and a kind of jociey stick side direction force-input device that is applicable to aircraft fatigue test is provided especially.
Background technology
In airplane design technical field, in aircraft fatigue test, there is a kind of test situation need to apply to jociey stick the cyclic loading of side direction.Loading regime is in the past at aircraft external stability loading facilities, transfers loads on jociey stick by camber member.Due to cabin interior insufficient space, can only apply the load of single direction, reciprocal load needs the whole series to pull down, and is installed to an other side, has seriously delayed the progress of test.So need to design a kind of device, can, under the prerequisite that need not change the outfit, meet the requirement to jociey stick left and right CYCLIC LOADING.
People urgently wish to obtain a kind of jociey stick side direction force-input device that is applicable to aircraft fatigue test addressing the above problem.
Utility model content
The purpose of this utility model is to provide the good jociey stick side direction force-input device that is applicable to aircraft fatigue test of a kind of technique effect.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is constructed as follows: jociey stick fixture 1, cable wire 2, pulley 3, strut 4, loading facilities 5, fixing auricle 6 and base 7; Described jociey stick fixture 1 two ends are all connected with cable wire 2, described cable wire 2 is walked around pulley 3 and is connected with one end of loading facilities 5, the other end of loading facilities 5 is connected with base 7 by fixing auricle 6, described fixing auricle 6 is fixed on the two ends of base 7, described base 7 is fixed on seat slide, and setting height(from bottom) is as the criterion in same level with assurance device and load(ing) point, and described strut 4 is specially two, one end of strut 4 is fixed on base 7, and the other end is connected with pulley 3.The center of described jociey stick fixture 1 is identical to the distance of base 7 with the center of pulley 3.Pulley 3 and jociey stick fixture 1 should be with loading direction on same straight lines.
Described strut 4 is positioned at loading facilities 5 inner sides.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is in the time of right side loading facilities tension cable wire, and left side loading facilities is servo-actuated, and jociey stick is applied to load to the right; Reach after load peaks, left side loading facilities tension cable wire, right side loading facilities is servo-actuated, and jociey stick is applied to load left, so just can realize jociey stick is applied to the cyclic loading that left and right replaces.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is applicable to aircraft fatigue test, meets the requirement of jociey stick left and right CYCLIC LOADING; Coordinate with structural distortion, and need not change the outfit in process of the test.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is arranged on cabin interior, and base 6 is fixed on seat slide, and front end is installed pulley 3, by cable wire 2, jociey stick fixture 1 is connected with loading facilities 5; The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is course load by the load transfer of left and right directions;
The advantage of the described jociey stick side direction force-input device that is applicable to aircraft fatigue test is: meet the requirement of jociey stick left and right CYCLIC LOADING; In process of the test, do not need to change the outfit, can shorten the test period; Whole device is arranged on cabin interior, takes up room less, and does not need aircraft to apply balancing load, is very helpful for the tool that carries out smoothly of operating system fatigue test.
Brief description of the drawings
Fig. 1 is the jociey stick side direction force-input device structural representation that is applicable to aircraft fatigue test.
Detailed description of the invention
Embodiment 1
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is constructed as follows: jociey stick fixture 1, cable wire 2, pulley 3, strut 4, loading facilities 5, fixing auricle 6 and base 7; Described jociey stick fixture 1 two ends are all connected with cable wire 2, described cable wire 2 is walked around pulley 3 and is connected with one end of loading facilities 5, the other end of loading facilities 5 is connected with base by fixing auricle 6, described fixing auricle 6 is fixed on the two ends of base 7, described base 7 is fixed on seat slide, and setting height(from bottom) is as the criterion in same level with assurance device and load(ing) point, and described strut 4 is specially two, one end of strut 4 is fixed on base 7, and the other end is connected with pulley 3.The center of described jociey stick fixture 1 is identical to the distance of base 7 with the center of pulley 3.Pulley 3 and jociey stick fixture 1 should be with loading direction on same straight lines.
Described strut 4 is positioned at loading facilities 5 inner sides.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is in the time of right side loading facilities tension cable wire, and left side loading facilities is servo-actuated, and jociey stick is applied to load to the right; Reach after load peaks, left side loading facilities tension cable wire, right side loading facilities is servo-actuated, and jociey stick is applied to load left, so just can realize jociey stick is applied to the cyclic loading that left and right replaces.
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is applicable to aircraft fatigue test, meets the requirement of jociey stick left and right CYCLIC LOADING; Coordinate with structural distortion, and need not change the outfit in process of the test;
The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is arranged on cabin interior, and base 6 is fixed on seat slide, and front end is installed pulley 3, by cable wire 2, jociey stick fixture 1 is connected with loading facilities 5; The described jociey stick side direction force-input device that is applicable to aircraft fatigue test is course load by the load transfer of left and right directions;
The advantage of the described jociey stick side direction force-input device that is applicable to aircraft fatigue test is: meet the requirement of jociey stick left and right CYCLIC LOADING; In process of the test, do not need to change the outfit, can shorten the test period; Whole device is arranged on cabin interior, takes up room less, and does not need aircraft to apply balancing load, is very helpful for the tool that carries out smoothly of operating system fatigue test.
Claims (2)
1. a jociey stick side direction force-input device that is applicable to aircraft fatigue test, is characterized in that: described in be applicable to aircraft fatigue test jociey stick side direction force-input device be constructed as follows: jociey stick fixture (1), cable wire (2), pulley (3), strut (4), loading facilities (5), fixing auricle (6) and base (7), described jociey stick fixture (1) two ends are all connected with cable wire (2), described cable wire (2) is walked around pulley (3) and is connected with one end of loading facilities (5), the other end of loading facilities (5) is connected with base (7) by fixing auricle (6), described fixing auricle (6) is fixed on the two ends of base (7), described base (7) is fixed on seat slide, described strut (4) is specially two, one end of strut (4) is fixed on base (7), the other end is connected with pulley (3), the center of described jociey stick fixture (1) is identical to the distance of base (7) with the center of pulley (3).
2. the jociey stick side direction force-input device that is applicable to as claimed in claim 1 aircraft fatigue test, is characterized in that: described strut (4) is positioned at loading facilities (5) inner side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420188262.0U CN203832761U (en) | 2014-04-17 | 2014-04-17 | Control stick lateral loading device applicable to aircraft fatigue tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420188262.0U CN203832761U (en) | 2014-04-17 | 2014-04-17 | Control stick lateral loading device applicable to aircraft fatigue tests |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203832761U true CN203832761U (en) | 2014-09-17 |
Family
ID=51510636
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420188262.0U Expired - Lifetime CN203832761U (en) | 2014-04-17 | 2014-04-17 | Control stick lateral loading device applicable to aircraft fatigue tests |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203832761U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477378A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft longitudinal maneuvering limit limiting method and device thereof |
-
2014
- 2014-04-17 CN CN201420188262.0U patent/CN203832761U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477378A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft longitudinal maneuvering limit limiting method and device thereof |
| CN104477378B (en) * | 2014-11-19 | 2018-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft fore-and-aft control limit method for limiting and its device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140917 |
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| CX01 | Expiry of patent term |