CN104197885A - Device and method for detecting aircraft down lock - Google Patents
Device and method for detecting aircraft down lock Download PDFInfo
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- CN104197885A CN104197885A CN201410471068.8A CN201410471068A CN104197885A CN 104197885 A CN104197885 A CN 104197885A CN 201410471068 A CN201410471068 A CN 201410471068A CN 104197885 A CN104197885 A CN 104197885A
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- platform
- down lock
- height
- aircraft down
- right cylinder
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Abstract
The invention relates to a device and a method for detecting an aircraft down lock. The device is composed of a height measurement device, a base and a platform, a handle, a measuring head and a control device are arranged on the height measurement device, the platform is mounted on the base, and a leading-in hole is formed in the platform. The method includes: disposing the annular platform on the base, inserting a cylinder I at the lower end of a to-be-measured aircraft down lock into the leading-in hole in the platform, and enabling the lower end face of a cylinder II of the to-be-measured aircraft down lock to be in close fit with the working face of the platform; adjusting the height of the measuring head on the height measurement device to enable the measuring head to be in contact with the working face of the platform, and setting the height as '0' through the control device; moving the measuring head upwards vertically to measure height values of a highest point and a lowest point of a fixing hole in the upper end of the down lock so as to obtain a height value of an axis of the fixing hole. The device is simple in structure, convenient to operate and accurate in measurement.
Description
Technical field
The present invention relates generally to a kind of pick-up unit and method being applied to aircraft down lock fixed orifice axis and rear end facet distance.
Background technology
Aircraft down lock is a vitals on aircraft, be illustrated in figure 1 a kind of aircraft down lock, the lower end of cylinder-shaped body (4-1) is provided with right cylinder III (4-5) and right cylinder I (4-2) successively, and upper end is for being provided with the right cylinder II (4-4) of fixed orifice (4-3).In the design of aircraft down lock, in order to ensure the installation quality of aircraft down lock, ensure that fixed orifice axis and rear end facet distance are crucial.Excessive cannot the installation of distance, too small generation gap, affects security.Therefore whether be the key of testing product quality to fixed orifice axis and rear end facet distance if meeting the requirements.Fixed orifice axis and rear end facet distance is the distance between fixed orifice axis and right cylinder III (4-5) and right cylinder I (4-2) joint face namely.Existing method is by hand steered that aircraft down lock is firmly vertical, then fixed orifice axis and the faceted distance in rear end are measured in manual operations, the problem existing is: well-known, conventionally the diameter of right cylinder I (4-2) is about Φ 40mm, the rear end facet end face weight less, that length is 60mm and aircraft down lock forming is heavier, therefore aircraft down lock astasia, location is forbidden to cause to measure and is forbidden; And the diameter that forms main body (4-1), right cylinder I (4-2), right cylinder II (4-4) and right cylinder III (4-5) is not etc., therefore residing two planes of fixed orifice axis and rear end facet are difficult to draw, and cause to measure and are forbidden.
Summary of the invention
In order to overcome the above problems, the invention provides one simple in structure, easy to operate, measure the device that detects accurately aircraft down lock.
Another object of the present invention is to provide a kind of by above-mentioned device Measurement accuracy aircraft down lock fixed orifice axis and the method for rear end facet distance.
The technical solution used in the present invention is: a kind of device that detects aircraft down lock, formed by height measuring device, base and platform, and height measuring device is provided with handle, gauge head and control device, and platform is arranged on base, and platform is provided with entrance hole.
Above-mentioned a kind of device that detects aircraft down lock, described platform is ring-type.
Above-mentioned a kind of device that detects aircraft down lock, the height of platform is greater than the height of the right cylinder I of aircraft down lock to be detected lower end; On platform, the aperture of entrance hole is less than the diameter of right cylinder III and is greater than the diameter of right cylinder I, and the depth of parallelism of the upper and lower plane of platform is 0.005mm, and the flatness of the workplace of platform is 0.005mm, and surface roughness Ra value is 0.4 μ m.
Above-mentioned a kind of device that detects aircraft down lock, the workplace hardness of platform is 60HRC, linear expansion coefficient is less than ± and 0.3 × 10
-6μ m.
Detect a method for aircraft down lock, utilize above-mentioned device, method is as follows:
1) annular platform is placed on base, the right cylinder I of aircraft down lock to be measured lower end is inserted in the entrance hole on platform, the lower surface of aircraft down lock right cylinder III to be measured and the workplace of platform closely cooperate;
2) height of gauge head on adjustment height measuring device, makes it to contact with the workplace of platform, by control device, this is highly set to " 0 ";
3) drive gauge head pan-up by handle, measure the height value of the highs and lows of the fixed orifice that is located at aircraft down lock to be measured upper end, calculate the height value of fixed orifice axis;
4) height value of fixed orifice axis is compared with design load, height value, in " design load ± 0.5mm " scope, is specification product.
The invention has the beneficial effects as follows: the present invention is owing to being provided with annular platform, when measurement, the right cylinder I of aircraft down lock lower end is inserted in entrance hole, the lower surface of right cylinder III is sitting on platform, and the workplace of the aircraft down lock rear end facet being made up of the plane between right cylinder I and right cylinder III just and on annular platform closely cooperates.Therefore utilize the workplace of annular platform that faceted down lock rear end standard flat is drawn, as measurement datum.Adopt contact measurement principle by gauge head, get final product Measurement accuracy.
The present invention can stablize clamping on platform by down lock to be measured, tested plane can be drawn again simultaneously, realizes Measurement accuracy.
Brief description of the drawings
Fig. 1 is a kind of structural representation of aircraft down lock.
Fig. 2 is the apparatus structure schematic diagram that the present invention detects aircraft down lock.
Embodiment
1 one kinds of embodiment detect the device of aircraft down lock
As shown in Figure 2, a kind of device that detects aircraft down lock, is made up of height measuring device (1), base (2) and annular platform (3).
Height measuring device (1) is provided with handle (1-1), gauge head (1-2) and control device (1-3).
It is upper that annular platform (3) is arranged on base (2), and annular platform (3) is provided with entrance hole (3-1).
The height of annular platform (3) is greater than the height of the right cylinder I (4-2) of aircraft down lock to be detected lower end; The aperture of the upper entrance hole (3-1) of platform (3) is less than the diameter of right cylinder III (4-5) and is greater than the diameter of right cylinder I (4-2), the depth of parallelism of the upper and lower plane of annular platform is 0.005mm, the flatness of the workplace of platform is 0.005mm, and surface roughness Ra value is 0.4 μ m.
Because the precision of the special annular platform of down lock is higher, so should consider the factor such as skin hardness, linear expansion coefficient in the time of selection material, avoid distortion and gauge head scratch surface and affect measuring accuracy.For avoiding in measuring process due to the special annular platform surface parameter of dynamometry influence power down lock, annular platform skin hardness should reach 60HRC, and linear expansion coefficient is less than ± and 0.3 × 10
-6μ m adopts 58% nickel steel material for this reason.
Adding man-hour, processing environment should be under (20 ± 1) DEG C environment, avoids material to bring the difficulty of measurement result correction because of thermal expansivity impact.
Processing technology comprises: heat treatment quenching and tempering, and icy processing, line cutting, numerical control plane mill, pincers worker is ground, inner circle mill etc.Because these ring-type rule are higher to upper and lower workplace geometric sense parameter request, so when in the end finishing, should be under (20 ± 1) DEG C environment, thickness, the upper and lower workplace depth of parallelism, top surface plane degree, upper surface roughness are detected with high-precision three coordinate measuring machine and precision length measurement instrument, roughness measuring instrument, until meet designing requirement.
2 one kinds of embodiment detect the method for aircraft down lock
Be illustrated in figure 1 a kind of aircraft down lock, the lower end of cylinder-shaped body (4-1) is provided with right cylinder III (4-5) and right cylinder I (4-2) successively, and upper end is for being provided with the right cylinder II (4-4) of fixed orifice (4-3).The diameter of main body (4-1) is 120mm; The diameter of right cylinder I (4-2) is Φ 40mm, and length is 60mm.In the time of design, the distance between this down lock fixed orifice axis and rear end facet (5) is H=304.8mm.
The present embodiment, taking detection aircraft down lock as shown in Figure 1 as example, describes.
For this reason, specifically being of a size of of design annular platform: annular platform external diameter Φ 200mm, internal diameter Φ 42mm, be ± 0.01mm of its tolerance, the thickness of annular platform should be greater than the height of down lock right cylinder I, design thickness is 70mm, tolerance is ± 0.005mm that upper and lower workplace depth of parallelism 0.005mm, because upper surface is using the reference field as measurement, top surface plane degree is designed to 0.005mm, and surface roughness Ra value is 0.4 μ m.
Height measuring device adopts Mahr817 type numeral altimeter.
Detection method is as follows:
1) annular platform (3) is placed on base (2), the right cylinder I of aircraft down lock to be measured lower end is inserted in the entrance hole (3-1) on platform (3), and the lower surface of aircraft down lock right cylinder III to be measured and the workplace of platform (3) closely cooperate;
2) gauge head (1-2) of adjustment Mahr817 type numeral altimeter highly, make it to contact with the workplace of annular platform (3), this is highly set to " 0 " by control device (1-3), the reference field by this height as measured parameter;
3) drive gauge head (1-2) pan-up by handle (1-1), utilize the axially bored line measurement function of Mahr817 numeral altimeter, utilize the gauge head of altimeter to find the highs and lows of fixed orifice, measuring height value, calculates the height value of fixed orifice axis;
4) height value of fixed orifice axis is compared with design load, height value, in " design load ± 0.5mm " scope, is specification product.
Claims (5)
1. one kind is detected the device of aircraft down lock, it is characterized in that: formed by height measuring device (1), base (2) and platform (3), height measuring device (1) is provided with handle (1-1), gauge head (1-2) and control device (1-3), it is upper that platform (3) is arranged on base (2), and platform (3) is provided with entrance hole (3-1).
2. a kind of device that detects aircraft down lock as claimed in claim 1, is characterized in that: described platform (3) is ring-type.
3. a kind of device that detects aircraft down lock as claimed in claim 2, is characterized in that: the height of platform (3) is greater than the height of the right cylinder I of aircraft down lock to be detected lower end; The aperture of the upper entrance hole (3-1) of platform (3) is less than the diameter of right cylinder III and is greater than the diameter of right cylinder I, the depth of parallelism of the upper lower plane of platform (3) is 0.005mm, the flatness of working platform face is 0.005mm, and surface roughness Ra value is 0.4 μ m.
4. a kind of device that detects aircraft down lock as claimed in claim 3, is characterized in that: the workplace hardness of platform is 60HRC, linear expansion coefficient is less than ± and 0.3 × 10
-6μ m.
5. detect a method for aircraft down lock, it is characterized in that utilizing the arbitrary described device of claim 1-4, method is as follows:
1) annular platform (3) is placed on base (2), the right cylinder I of aircraft down lock to be measured lower end is inserted in the entrance hole (3-1) on platform (3), and the lower surface of aircraft down lock right cylinder III to be measured and the workplace of platform (3) closely cooperate;
2) adjust the above height of gauge head (1-2) of height measuring device (1), make it to contact with the workplace of platform (3), this is highly set to " 0 " by control device (1-3);
3) drive gauge head (1-2) pan-up by handle (1-1), measure the height value of the highs and lows of the fixed orifice that is located at aircraft down lock to be measured upper end, calculate the height value of fixed orifice axis;
4) height value of fixed orifice axis is compared with design load, height value, in " design load ± 0.5mm " scope, is specification product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471068.8A CN104197885A (en) | 2014-09-16 | 2014-09-16 | Device and method for detecting aircraft down lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471068.8A CN104197885A (en) | 2014-09-16 | 2014-09-16 | Device and method for detecting aircraft down lock |
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| Publication Number | Publication Date |
|---|---|
| CN104197885A true CN104197885A (en) | 2014-12-10 |
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ID=52083213
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410471068.8A Pending CN104197885A (en) | 2014-09-16 | 2014-09-16 | Device and method for detecting aircraft down lock |
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| CN (1) | CN104197885A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111993315A (en) * | 2020-08-31 | 2020-11-27 | 湛江德利车辆部件有限公司 | Clamping device and detection method |
-
2014
- 2014-09-16 CN CN201410471068.8A patent/CN104197885A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111993315A (en) * | 2020-08-31 | 2020-11-27 | 湛江德利车辆部件有限公司 | Clamping device and detection method |
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Application publication date: 20141210 |
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| WD01 | Invention patent application deemed withdrawn after publication |