CN106017395A - Aircraft horizontal rudder surface angle measuring device - Google Patents
Aircraft horizontal rudder surface angle measuring device Download PDFInfo
- Publication number
- CN106017395A CN106017395A CN201610486698.1A CN201610486698A CN106017395A CN 106017395 A CN106017395 A CN 106017395A CN 201610486698 A CN201610486698 A CN 201610486698A CN 106017395 A CN106017395 A CN 106017395A
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- CN
- China
- Prior art keywords
- sucker
- compasses cutter
- suction disc
- cutter suction
- compasses
- 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.)
- Granted
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Magnetic Variables (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses an aircraft horizontal rudder surface angle measuring device, which comprises an arch block, a compass cutter suction disc, a connecting piece, a flat head rivet, a rectangular ring, a bonding belt, a plastic buckle in the shape of a Chinese character ''ri'', a cushion block, a transverse angle sensor, a vertical angle sensor and lead wires, wherein the transverse angle sensor is fixed inside the compass cutter suction disc, a fixing plate installed vertically is further arranged inside the compass cutter suction disc, the vertical angle sensor is vertically installed on the fixing plate, the connecting piece is fixed on the upper end surface of the compass cutter suction disc, one end of the rectangular ring is installed on the connecting piece through the flat head rivet, one end of the bonding belt sleeves the other end of the rectangular ring, the plastic buckle in the shape of a Chinese character ''ri'' is installed on the bonding belt, and the cushion block is installed inside the compass cutter suction disc. The aircraft horizontal rudder surface angle measuring device has the advantages of being reasonable in structural design, high in space utilization rate, convenient to use, light in weight, small in size, convenient to store, transport and use, and convenient in assembly and disassembly, effectively solving the problem of difficult installation and fixation of the sensors, and realizing angle measurement.
Description
Technical field
The present invention relates to aeronautical product technical field of angle detection, a kind of aircraft flat rudder face angle
Measurement apparatus.
Background technology
At present, flying to join timing signal carrying out aircraft, internal field and outfield are to the measurement of deflection angle of airplane control surface degree still
Use bevel protractor frock clamp, and visually measure after each rudder face is clamped.Owing to frock size is big,
Heavy, the position that aircraft front flap, rear wing flap, the secondary flap, tailplane, vertical fin etc. need to be measured is more,
Therefore installation difficulty, result in rudder face angular surveying inconvenience.Urgent needs one can conveniently carry out angle
The device that degree is measured.
Summary of the invention
In order to solve above-mentioned technical problem, the present invention provides a kind of aircraft flat rudder face angle measurement unit.
The present invention solves its technical problem and realizes by the following technical solutions:
A kind of aircraft flat rudder face angle measurement unit, including arch block, compasses cutter sucker, screw two, nut
One, connect sheet, thin flat head rivet, straight-flanked ring, bandage, plastics day word is buckled, cushion block, lateral angles sense
Device, vertical angular transducer and wire, described lateral angles sensor levels is fixed on the interior of compasses cutter sucker
Portion, the inside of compasses cutter sucker is additionally provided with the fixed plate that vertical direction is installed, and described vertical angular transducer erects
Directly be arranged in fixed plate, connect sheet by screw two, nut one coordinate to be fixed on compasses cutter sucker
On upper surface, one end of straight-flanked ring is arranged on connection sheet by thin flat head rivet, and one end of bandage is sleeved on
On the other end of straight-flanked ring, described plastics day word button be arranged on bandage, cushion block is arranged on compasses cutter sucker
Inside, arch block is arranged on the right side central of compasses cutter sucker, wire respectively with lateral angles sensor, perpendicular
Draw at arch block after angular transducer is connected.Lateral angles sensor of the present invention, vertical angle sensor
Device is sensor with data readout double-shaft tilt angle sensor, and its measurement of dip angle scope is :-30 °～30 °, and precision can be high
Reach 0.01 °.Meet aircraft each control surface deflection angle maximum magnitude-28 °～the requirement of 25 °, it is achieved that right
Horizontal tail or the angular surveying of vertical fin.
Described lateral angles sensor is fixed on the inside of compasses cutter sucker by the cooperation of screw one, nut two,
Circuit board copper pillar it is cased with on screw one.
The invention has the beneficial effects as follows:
The present invention has the advantages such as reasonable in design, space availability ratio be high, easy to use, light weight, chi
Very little little, it is simple to deposit, transport and use.Meanwhile, easy to loading and unloading, efficiently solve sensor and install fixing
The problem of difficulty, it is achieved that the measurement of angle.
Accompanying drawing explanation
The present invention is further described with embodiment below in conjunction with the accompanying drawings.
Fig. 1 is the front view of the present invention；
Fig. 2 is the plan structure schematic diagram that the present invention is connected with external receptor；
Fig. 3 is the I partial enlarged drawing of Fig. 1；
Fig. 4 is II partial enlarged drawing of Fig. 2.
Detailed description of the invention
In order to make the purpose of the present invention, technical scheme and beneficial effect clearer, below in conjunction with accompanying drawing,
Being described in detail the preferred embodiments of the present invention, the present invention will be further described, to facilitate technology
Personnel understand.
As shown in Figures 1 to 4, a kind of aircraft flat rudder face angle measurement unit, inhale including arch block 1, compasses cutter
Dish 4, screw 25, nut 1, connection sheet 7, thin flat head rivet 8, straight-flanked ring 9, bandage 10, plastics day
Word button 11, cushion block 12, lateral angles sensor 2, vertical angular transducer 15 and wire, described lateral angles
Sensor 2 is horizontally fixed on the inside of compasses cutter sucker 4, and the inside of compasses cutter sucker 4 is additionally provided with vertical direction peace
The fixed plate 16 of dress, described vertical angular transducer 15 is vertically installed in fixed plate 16, connects sheet 7 and passes through spiral shell
Follow closely 25, the coordinating to be fixed on the upper surface of compasses cutter sucker 4 of nut 1, one end of straight-flanked ring 9 is passed through
Thin flat head rivet 8 is arranged on connection sheet 7, and one end of bandage 10 is sleeved on the other end of straight-flanked ring 9, described
Plastics day, word button 11 was arranged on bandage 10, and cushion block 12 is arranged on the inside of compasses cutter sucker 4, and arch block 1 is pacified
Be contained in the right side central of compasses cutter sucker 4, wire respectively with lateral angles sensor 2, vertical angular transducer
15 be connected after at arch block 1 draw.Lateral angles sensor 2 of the present invention, vertical angular transducer 15 are number
Word output type double-shaft tilt angle sensor, its measurement of dip angle scope is :-30 °～30 °, precision may be up to
0.01°.Meet aircraft each control surface deflection angle maximum magnitude-28 °～the requirement of 25 °, it is achieved that to flat
Tail or the angular surveying of vertical fin.
Described lateral angles sensor 2 is fixed on compasses cutter sucker by the cooperation of screw 1, nut 2 13
The inside of 4, screw 1 is cased with circuit board copper pillar 14.
The upper end of compasses cutter sucker 4 is provided with sucker and plays group handle 17, during use, when compasses cutter sucker 4 is placed on
During surface of the work, operator can stir sucker and play group handle 17, make compasses cutter sucker 4 absorption tightly exist
On surface of the work, and then lateral angles sensor 2, vertical angular transducer 15 is utilized to be passed through by the signal of detection
Wire exports in external receptor, it is achieved that the measurement to angle.
Finally illustrate, preferred embodiment above only in order to technical scheme to be described and unrestricted,
Although the present invention being described in detail by above preferred embodiment, but those skilled in the art
Should be appreciated that and in the form and details it can be made various change, without departing from the present invention
Claims limited range.
Claims (2)
1. an aircraft flat rudder face angle measurement unit, including arch block (1), compasses cutter sucker (4),
Connect sheet (7), thin flat head rivet (8), straight-flanked ring (9), bandage (10), plastics day word buckle (11),
Cushion block (12), lateral angles sensor (2), vertical angular transducer (15) and wire, its feature exists
In: described lateral angles sensor (2) is horizontally fixed on the inside of compasses cutter sucker (4), and compasses cutter is inhaled
The inside of dish (4) is additionally provided with the fixed plate (16) that vertical direction is installed, described vertical angular transducer (15)
It is vertically installed in fixed plate (16), connects sheet (7) and be fixed on the upper surface of compasses cutter sucker (4),
One end of straight-flanked ring (9) is arranged in connection sheet (7) by thin flat head rivet (8), bandage (10)
One end is sleeved on the other end of straight-flanked ring (9), and described plastics day word button (11) is arranged on bandage (10)
On, cushion block (12) is arranged on the inside of compasses cutter sucker (4), and arch block (1) is arranged on compasses cutter and inhales
The right side central of dish (4), wire respectively with lateral angles sensor (2), vertical angular transducer (15)
Draw from arch block (1) after Xiang Lianing.
A kind of aircraft flat rudder face angle measurement unit the most according to claim 1, it is characterised in that: institute
State lateral angles sensor (2) and be fixed on compasses cutter by the cooperation of screw one (3), nut two (13)
The inside of sucker (4), screw one (3) is cased with circuit board copper pillar (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610486698.1A CN106017395B (en) | 2016-06-28 | 2016-06-28 | A kind of flat rudder face angle measurement unit of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610486698.1A CN106017395B (en) | 2016-06-28 | 2016-06-28 | A kind of flat rudder face angle measurement unit of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106017395A true CN106017395A (en) | 2016-10-12 |
| CN106017395B CN106017395B (en) | 2019-04-19 |
Family
ID=57085364
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610486698.1A Active CN106017395B (en) | 2016-06-28 | 2016-06-28 | A kind of flat rudder face angle measurement unit of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106017395B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108731706A (en) * | 2018-04-03 | 2018-11-02 | 烟台北方星空自控科技有限公司 | A kind of sensor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101963499A (en) * | 2010-07-21 | 2011-02-02 | 中国航空工业集团公司西安飞机设计研究所 | Tool and method for measuring deflection angle of airplane control surface |
| JP2011257275A (en) * | 2010-06-09 | 2011-12-22 | Alps Electric Co Ltd | Rotation angle sensor |
| US20150042321A1 (en) * | 2012-01-27 | 2015-02-12 | Kavlico Corporation | Rotary variable differential transformer (rvdt) sensor assembly with auxiliary output signal |
| CN104655082A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Airplane control plane deflection angle measuring system |
| CN204788330U (en) * | 2015-06-23 | 2015-11-18 | 中国人民解放军海军航空工程学院青岛校区 | Control surface sensor calibration clamp |
| CN205808389U (en) * | 2016-06-28 | 2016-12-14 | 国营芜湖机械厂 | A kind of aircraft flat rudder face angle measurement unit |
-
2016
- 2016-06-28 CN CN201610486698.1A patent/CN106017395B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011257275A (en) * | 2010-06-09 | 2011-12-22 | Alps Electric Co Ltd | Rotation angle sensor |
| CN101963499A (en) * | 2010-07-21 | 2011-02-02 | 中国航空工业集团公司西安飞机设计研究所 | Tool and method for measuring deflection angle of airplane control surface |
| US20150042321A1 (en) * | 2012-01-27 | 2015-02-12 | Kavlico Corporation | Rotary variable differential transformer (rvdt) sensor assembly with auxiliary output signal |
| CN104655082A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Airplane control plane deflection angle measuring system |
| CN204788330U (en) * | 2015-06-23 | 2015-11-18 | 中国人民解放军海军航空工程学院青岛校区 | Control surface sensor calibration clamp |
| CN205808389U (en) * | 2016-06-28 | 2016-12-14 | 国营芜湖机械厂 | A kind of aircraft flat rudder face angle measurement unit |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108731706A (en) * | 2018-04-03 | 2018-11-02 | 烟台北方星空自控科技有限公司 | A kind of sensor |
| CN108731706B (en) * | 2018-04-03 | 2020-08-07 | 烟台北方星空自控科技有限公司 | Sensor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106017395B (en) | 2019-04-19 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200331 Address after: 241000 room 01, building 01, Chengdong new city, Dongwan Road South, Jinger Road West and jingsan Road East, Wanyi Town, Wuhu County, Wuhu City, Anhui Province Patentee after: Wuhu Hangyi Integrated Equipment Co., Ltd Address before: 241000 Anhui Wanli Wuhu Airport Patentee before: WUHU STATE-OWNED FACTORY OF MACHINING |
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| TR01 | Transfer of patent right |