CN203929051U - A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance - Google Patents
A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance Download PDFInfo
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- CN203929051U CN203929051U CN201420193327.0U CN201420193327U CN203929051U CN 203929051 U CN203929051 U CN 203929051U CN 201420193327 U CN201420193327 U CN 201420193327U CN 203929051 U CN203929051 U CN 203929051U
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- wire rope
- bar
- spiral arm
- flange
- running clearance
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- 125000006850 spacer group Chemical group 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000012360 testing method Methods 0.000 abstract description 5
- 230000007704 transition Effects 0.000 abstract description 5
- 238000011161 development Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000010923 batch production Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000000069 prophylactic effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Abstract
The utility model belongs to airplane ground test field, particularly relates to a kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance.The utility model is comprised of base, pin bar, oblique fulcrum bar, spiral arm, wire rope and force cell.After wire rope is connected with aircraft rudder surface, adjust the ring flange on pin bar, when just tightening, plugs by wire rope stop pin, unclamp the holding screw on spiral arm, the loading nut of tightening on slide block stretches out its slide block from spiral arm, wire rope is tightened gradually, and when the power output size of force cell reaches predetermined value, rudder face has loaded.The utility model low cost of manufacture, is used simple to operately, can realize the continuous loading to rudder face; Launch and draw in conveniently, after drawing in, volume is little, is convenient to transition transportation.
Description
Technical field
The invention belongs to aircraft rudder surface running clearance fields of measurement, particularly relates to a kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance.
Background technology
Owing to there is error in aircraft manufacturing and assembling, after the accumulation of error in the rudder face gap that rotates, when rudder face running clearance is excessive, not only can affect control accuracy and the flight quality of aircraft, when serious, also can bring out mesomerism, cause catastrophic effect, so before aircraft first-fly, must complete the measurement of rudder face running clearance, in prophylactic repair during one's term of military service, also will measure rudder face running clearance.
The batch production of development and the model aircraft of payment in the past, before dispatching from the factory or generally adopt during one's term of military service monoblock type to load, measure integration apparatus to measure rudder face running clearance, equipment volume used is large, development cost is high and transportation inconvenience.Along with advanced technology checking aircraft is towards Rapid Trial-Manufacture future development, development, the test of current advanced technology checking aircraft present the features such as aircraft type is many, monotype aircraft development sortie is few, take a flight test on remote airport, two wires, must adopt simple effectively rudder face running clearance measuring method and the loading equipemtn of being convenient to transition transportation.
For reducing development cost, shortening the lead time, and meet the how rudder face running clearance such as manufacturing plant and test field measurement requirement, need to invent the folding mechanical load equipment that the adaptation simple, with low cost of a kind of principle is measured for aircraft rudder surface running clearance.
Summary of the invention
The object of the invention is: the object of the invention be to provide a kind of easily, cheaply, be convenient to the rudder face loading equipemtn of transition transportation, the mechanical load while measuring for the horizontally disposed rudder face running clearance such as aircraft evelvator, aileron.
Technical scheme of the present invention is:
A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance, it is characterized in that, this equipment is by base 11, pin bar 12, oblique fulcrum bar 13, spiral arm 14, wire rope 15 and force cell 16 form, the lower end of the lower end of pin bar 12 and oblique fulcrum bar 13 and base 11 are hinged, the upper end of the upper end of pin bar 12 and oblique fulcrum bar 13 and spiral arm 14 are hinged, the second hinge 18 of the first hinge 17 of the upper end of pin bar 12 and the upper end of oblique fulcrum bar 13 is mutually vertical, wire rope 15 one end are connected with force cell 16, successively through the first pulley 144, after the second pulley 145 and the 3rd pulley 146, wire rope 15 other ends are fixed on the flange 121 on pin bar 12, rotary flange 121 can make wire rope 15 tighten or loosen, and inserts spacer pin 122 rear flanges 121 and rotates and will be limited,
The 3rd pulley 146 is arranged on slide block 143 one end, on slide block 143 other ends, is processed with external thread, and by the loading nut 142 on adjusting slider 143, slide block 143 can slide on spiral arm 14, has a holding screw 141 on described spiral arm 14.
The first described hinge 17 and the second hinge 18 are comprised of quick-release bolt and fast removing nut.
The scalable adjusting of length of pin bar 12, oblique fulcrum bar 13 and spiral arm 14.
On flange holder 123 on pin bar 12, by 90 °, be distributed with 2 apertures, on flange 121, be evenly equipped with 6 apertures, flange 121 with can insert spacer pin 122 restriction flanges 121 after aperture on flange holder 123 aligns and rotate.
Advantage of the present invention is:
With low cost.The present invention mainly adopts general square steel section bar, and only a small amount of part needs machining, and agent structure adopts welding, cheap for manufacturing cost; The force cell of selecting is widely used LOAD CELLS on market, and purchase cost is cheap.
Load level and smooth.The present invention loads nut 142 by adjusting slowly stretches out slide block 143, and wire rope tightens to realize the loading to rudder face gradually, owing to loading nut 142, can rotate continuously, therefore can realize level and smooth loading.
Easy and simple to handle.The present invention is simple in structure, only needs 1 open-ended spanner and 1 interior square head wrench to regulate and to load by finishing equipment, simple to operate, easy-to-use, can be between general assembly factory building, test and the inferior multiple occasion of outfield open-air atmosphere use.
Be convenient to transportation.After the present invention is folding, length is no more than respectively 1.2 meters, 0.8 meter and 0.35 meter, after employing specialized package case packing, can, by various ways transitions such as civil aviaton's shipping, transportation by railroad and transport by roads, be particularly suitable for outfield and army and use.
The invention has the beneficial effects as follows:
Described rudder face loading equipemtn is measured for the rudder face running clearance of inside and outside of certain unmanned plane, and equipment operating is easy, loading is level and smooth, and cheap for manufacturing cost, transition is transported flexibly, effectively reduces the experimentation cost of certain unmanned plane.
Accompanying drawing explanation
Fig. 1 is the axis side views such as folding mechanical load equipment of measuring for aircraft rudder surface running clearance;
Fig. 2 is the composition schematic diagram of pin bar;
Fig. 3 is the composition schematic diagram of spiral arm;
Fig. 4 is that loading equipemtn is used view;
Fig. 5 is folding process and the folding rear view of loading equipemtn.
Wherein, 1 is loading equipemtn, and 2 is rudder face, and 3 is rudder face clamp.
11 is base, and 12 is pin bar, and 13 is oblique fulcrum bar, and 14 is spiral arm, and 15 is wire rope, and 16 is force cell, and 17 is the first hinge, and 18 is the second hinge; 121 is that flange, 122 is that spacer pin, 123 is flange holder, and 141 is that holding screw, 142 is loading nut, and 143 is slide block, and 144 is that the first pulley, 145 is that the second pulley, 146 is the 3rd pulley.
Embodiment
Below use of the present invention is described in further details.
Described mechanical load equipment, has and launches and folding two states, deployed condition as shown in Figure 1, folding process and folding after state as shown in Figure 5, when folding, pin bar 12 and spiral arm 14 draw in and are fixed on base 11, oblique fulcrum bar 13 draws in and is fixed on pin bar 12.
Described loading equipemtn, its principle is, connect devices on aircraft rudder surface, adjust ring flange wire rope is just tightened, then tighten loading nut, in the process that slide block stretches out, wire rope is tightened gradually, the power being carried on rudder face increases gradually, and when loading force reaches re-set target, loading completes.Concrete use step of the present invention is:
A: connect loading equipemtn, clamp and aircraft rudder surface by Fig. 6;
B: rotary flange, when wire rope is just tightened, plug spacer pin;
C: unclamp holding screw, slowly tighten loading nut, slide block is fixedly slowly stretched out in spiral arm, wire rope is tightened gradually, and loading force increases gradually;
D: when sensor reading reaches goal-selling value, loading completes;
E: press the plan process unloading of aforesaid operations, remove loading equipemtn;
F: fold the present invention by folding step, pack into after Special packaging box and properly preserve.
Folding step of the present invention is Fig. 5:
I step: draw base 11 and spiral arm 14 in;
II step: the spiral arm 14 after dismounting is drawn in, is fixed on base 11;
III step: draw pin bar 12 in, be fixed on base 11;
IV step: draw oblique fulcrum bar 13 in, be fixed on pin bar 12.
Claims (4)
1. a folding mechanical load equipment of measuring for aircraft rudder surface running clearance, it is characterized in that, this equipment is by base (11), pin bar (12), oblique fulcrum bar (13), spiral arm (14), wire rope (15) and force cell (16) form, the lower end of the lower end of pin bar (12) and oblique fulcrum bar (13) and base (11) are hinged, the upper end of the upper end of pin bar (12) and oblique fulcrum bar (13) and spiral arm (14) are hinged, first hinge (17) of the upper end of pin bar (12) is mutually vertical with second hinge (18) of the upper end of oblique fulcrum bar (13), wire rope (15) one end is connected with force cell (16), successively through the first pulley (144), after the second pulley (145) and the 3rd pulley (146), wire rope (15) other end is fixed on the flange (121) on pin bar (12), rotary flange (121) can make wire rope (15) tighten or loosen, and inserts spacer pin (122) rear flange (121) and rotates and will be limited,
The 3rd pulley (146) is arranged on slide block (143) one end, on slide block (143) other end, be processed with external thread, by the loading nut (142) on adjusting slider (143), slide block (143) can, in the upper slip of spiral arm (14), have a holding screw (141) on described spiral arm (14).
2. a kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance as claimed in claim 1, is characterized in that, described the first hinge (17) and the second hinge (18) are comprised of quick-release bolt and fast removing nut.
3. a kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance as claimed in claim 1, is characterized in that the scalable adjusting of length of pin bar (12), oblique fulcrum bar (13) and spiral arm (14).
4. a kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance as described in one of claim 1-3, it is characterized in that, flange holder (123) on pin bar (12) is above distributed with 2 apertures by 90 °, on flange (121), be evenly equipped with 6 apertures, flange (121) with can insert spacer pin (122) restriction flange (121) after aperture on flange holder (123) aligns and rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420193327.0U CN203929051U (en) | 2014-04-21 | 2014-04-21 | A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420193327.0U CN203929051U (en) | 2014-04-21 | 2014-04-21 | A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203929051U true CN203929051U (en) | 2014-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420193327.0U Expired - Lifetime CN203929051U (en) | 2014-04-21 | 2014-04-21 | A kind of folding mechanical load equipment of measuring for aircraft rudder surface running clearance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203929051U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443430A (en) * | 2014-12-12 | 2015-03-25 | 北京航星机器制造有限公司 | Test set for unfolding of folding control surface |
| CN105352409A (en) * | 2015-11-02 | 2016-02-24 | 安徽江淮汽车股份有限公司 | Commutator rotating clearance test workbench and test method |
| CN106767373A (en) * | 2016-11-24 | 2017-05-31 | 兰州飞行控制有限责任公司 | A kind of angular displacement steering wheel mechanic transmission clearance measuring method |
| CN107672822A (en) * | 2017-08-28 | 2018-02-09 | 西北工业大学 | Aircraft active face movement measuring device and method |
| CN111252265A (en) * | 2018-12-03 | 2020-06-09 | 江西洪都航空工业集团有限责任公司 | Control surface clearance test equipment |
| CN113071706A (en) * | 2021-03-31 | 2021-07-06 | 成都飞机工业（集团）有限责任公司 | Aircraft control surface clearance measuring device |
| CN113443168A (en) * | 2021-06-11 | 2021-09-28 | 江西洪都航空工业股份有限公司 | Device for fixedly detecting clearance of control surface of airplane |
-
2014
- 2014-04-21 CN CN201420193327.0U patent/CN203929051U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443430A (en) * | 2014-12-12 | 2015-03-25 | 北京航星机器制造有限公司 | Test set for unfolding of folding control surface |
| CN104443430B (en) * | 2014-12-12 | 2017-04-05 | 北京航星机器制造有限公司 | Fold rudder face and launch test device |
| CN105352409A (en) * | 2015-11-02 | 2016-02-24 | 安徽江淮汽车股份有限公司 | Commutator rotating clearance test workbench and test method |
| CN105352409B (en) * | 2015-11-02 | 2018-07-10 | 安徽江淮汽车集团股份有限公司 | Commutator running clearance test table and test method |
| CN106767373A (en) * | 2016-11-24 | 2017-05-31 | 兰州飞行控制有限责任公司 | A kind of angular displacement steering wheel mechanic transmission clearance measuring method |
| CN107672822A (en) * | 2017-08-28 | 2018-02-09 | 西北工业大学 | Aircraft active face movement measuring device and method |
| CN111252265A (en) * | 2018-12-03 | 2020-06-09 | 江西洪都航空工业集团有限责任公司 | Control surface clearance test equipment |
| CN113071706A (en) * | 2021-03-31 | 2021-07-06 | 成都飞机工业（集团）有限责任公司 | Aircraft control surface clearance measuring device |
| CN113443168A (en) * | 2021-06-11 | 2021-09-28 | 江西洪都航空工业股份有限公司 | Device for fixedly detecting clearance of control surface of airplane |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |