CN106017395B - A kind of flat rudder face angle measurement unit of aircraft - Google Patents
A kind of flat rudder face angle measurement unit of aircraft Download PDFInfo
- Publication number
- CN106017395B CN106017395B CN201610486698.1A CN201610486698A CN106017395B CN 106017395 B CN106017395 B CN 106017395B CN 201610486698 A CN201610486698 A CN 201610486698A CN 106017395 B CN106017395 B CN 106017395B
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- Prior art keywords
- sucker
- compasses cutter
- compasses
- cutter
- bandage
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- 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)
- A Measuring Device Byusing Mechanical Method (AREA)
- Measuring Magnetic Variables (AREA)
Abstract
The invention discloses a kind of flat rudder face angle measurement units of aircraft, including arch block, compasses cutter sucker, connection sheet, thin flat head rivet, straight-flanked ring, bandage, plastics tri-glide, cushion block, lateral angles sensor, vertical angular transducer and conducting wire, lateral angles sensor levels are fixed on the inside of compasses cutter sucker, the inside of compasses cutter sucker is additionally provided with the fixed plate of vertical direction installation, vertical angular transducer is vertically installed in fixed plate, connection sheet is fixed on the upper surface of compasses cutter sucker, straight-flanked ring one end is mounted in connection sheet by thin flat head rivet, one end of bandage is sleeved on the other end of straight-flanked ring, plastics tri-glide is mounted on bandage, cushion block is mounted on the inside of compasses cutter sucker.The present invention has many advantages, such as that reasonable in design, space utilization rate is high, easy to use, and light weight, size is small, convenient for storage, transport and uses, easy to loading and unloading, efficiently solves the problems, such as that sensor installation is fixed difficult, realizes the measurement of angle.
Description
Technical field
The present invention relates to aeronautical product technical field of angle detection, specifically a kind of flat rudder face angle measurement dress of aircraft
It sets.
Background technique
Currently, internal field and outfield still use angle to the measurement of deflection angle of airplane control surface degree when progress aircraft flies ginseng calibration
Ruler frock clamp is spent, and is visually measured after being clamped to each rudder face.Since tooling size is big, heavy, aircraft front flap,
The position that wing flap, the secondary flap, tailplane, vertical fin etc. need to measure afterwards is more therefore difficult to install, and it is all to result in rudder face angle measurement
It is mostly inconvenient.Urgent need one kind can facilitate the device for carrying out angle measurement.
Summary of the invention
In order to solve the above technical problem, the present invention provides a kind of flat rudder face angle measurement units of aircraft.
The present invention solves its technical problem using following technical scheme to realize:
A kind of flat rudder face angle measurement unit of aircraft, including arch block, compasses cutter sucker, screw two, nut one, connection
It piece, thin flat head rivet, straight-flanked ring, bandage, plastics tri-glide, cushion block, lateral angles sensor, vertical angular transducer and leads
Line, the lateral angles sensor levels are fixed on the inside of compasses cutter sucker, and the inside of compasses cutter sucker is additionally provided with vertical side
To the fixed plate of installation, the vertical angular transducer is vertically installed in fixed plate, and connection sheet passes through screw two, nut one
To be fixed on the upper surface of compasses cutter sucker, one end of straight-flanked ring is mounted in connection sheet by thin flat head rivet, is tied up for cooperation
One end of band is sleeved on the other end of straight-flanked ring, and the plastics tri-glide is mounted on bandage, and cushion block is mounted on compasses cutter suction
The inside of disk, arch block are mounted on the right side central of compasses cutter sucker, and conducting wire is passed with lateral angles sensor, vertical angle respectively
Sensor is drawn from arch block after being connected.Lateral angles sensor of the present invention, vertical angular transducer are sensor with data readout twin shaft
Obliquity sensor, inclination angle measurement range are as follows: -30 °~30 °, precision may be up to 0.01 °.Meet each control surface deflection angle of aircraft
The requirement for spending -28 ° of maximum magnitude~25 °, realizes the angle measurement to horizontal tail or vertical fin.
The lateral angles sensor is fixed on the inside of compasses cutter sucker, screw by the cooperation of screw one, nut two
Circuit board copper pillar is cased on one.
The beneficial effects of the present invention are:
The present invention has many advantages, such as that reasonable in design, space utilization rate is high, easy to use, and light weight, size is small, is convenient for
Storage, transport and use.Meanwhile it is easy to loading and unloading, it efficiently solves the problems, such as that sensor installation is fixed difficult, realizes angle
Measurement.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and examples.
Fig. 1 is main view of the invention；
Fig. 2 is the overlooking structure diagram that the present invention is connect with external receiver；
Fig. 3 is the I partial enlarged view of Fig. 1；
Fig. 4 is II partial enlarged view of Fig. 2.
Specific embodiment
In order to keep the purpose of the present invention, technical scheme and beneficial effects clearer, below in conjunction with attached drawing, to the present invention
Preferred embodiment be described in detail, the present invention will be further described, to facilitate the technical staff to understand.
As shown in Figures 1 to 4, the flat rudder face angle measurement unit of a kind of aircraft, including arch block 1, compasses cutter sucker 4, spiral shell
Follow closely 25, nut 1, connection sheet 7, thin flat head rivet 8, straight-flanked ring 9, bandage 10, plastics tri-glide 11, cushion block 12, lateral angles
Sensor 2, vertical angular transducer 15 and conducting wire, the lateral angles sensor 2 are horizontally fixed on the interior of compasses cutter sucker 4
Portion, the inside of compasses cutter sucker 4 are additionally provided with the fixed plate 16 of vertical direction installation, and the vertical angular transducer 15 is vertically-mounted
In fixed plate 16, connection sheet 7 by the cooperation of screw 25, nut 1 to be fixed on the upper surface of compasses cutter sucker 4, square
One end of shape ring 9 is mounted in connection sheet 7 by thin flat head rivet 8, and one end of bandage 10 is sleeved on the other end of straight-flanked ring 9
On, the plastics tri-glide 11 is mounted on bandage 10, and cushion block 12 is mounted on the inside of compasses cutter sucker 4, and arch block 1 is mounted on
The right side central of compasses cutter sucker 4, conducting wire be connected respectively with lateral angles sensor 2, vertical angular transducer 15 after from arch
It is drawn at block 1.Lateral angles sensor 2 of the present invention, vertical angular transducer 15 are sensor with data readout double-shaft tilt angle sensor,
Inclination angle measurement range are as follows: -30 °~30 °, precision may be up to 0.01 °.Meet -28 ° of maximum magnitude of each control surface deflection angle of aircraft
~25 ° of requirement realizes the angle measurement to horizontal tail or vertical fin.
The lateral angles sensor 2 is fixed on the inside of compasses cutter sucker 4 by the cooperation of screw 1, nut 2 13,
Circuit board copper pillar 14 is cased on screw 1.
The upper end of compasses cutter sucker 4 is equipped with sucker and plays stirring hand handle 17, in use, when compasses cutter sucker 4 is placed on workpiece table
When face, operator can stir sucker and play stirring hand handle 17, make the absorption of compasses cutter sucker 4 tightly on the surface of the workpiece, in turn
It is output in external receiver using the signal that lateral angles sensor 2, vertical angular transducer 15 will test by conducting wire,
Realize the measurement to angle.
Finally, it is stated that preferred embodiment above is only used to illustrate the technical scheme of the present invention and not to limit it, although logical
It crosses above preferred embodiment the present invention is described in detail, however, those skilled in the art should understand that, can be
Various changes are made to it in form and in details, without departing from claims of the present invention limited range.
Claims (2)
1. a kind of flat rudder face angle measurement unit of aircraft, including arch block (1), compasses cutter sucker (4), connection sheet (7), flat head
Rivet (8), straight-flanked ring (9), bandage (10), plastics tri-glide (11), cushion block (12), lateral angles sensor (2), vertical angle
Sensor (15) and conducting wire, it is characterised in that: the lateral angles sensor (2) is horizontally fixed on the interior of compasses cutter sucker (4)
Portion, the inside of compasses cutter sucker (4) are additionally provided with the fixed plate (16) of vertical direction installation, and the vertical angular transducer (15) is perpendicular
It is directly mounted on fixed plate (16), connection sheet (7) is fixed on the upper surface of compasses cutter sucker (4), and one end of straight-flanked ring (9) is logical
It crosses thin flat head rivet (8) to be mounted on connection sheet (7), one end of bandage (10) is sleeved on the other end of straight-flanked ring (9), described
Plastics tri-glide (11) is mounted on bandage (10), and cushion block (12) is mounted on the inside of compasses cutter sucker (4), arch block (1) peace
Right side central mounted in compasses cutter sucker (4), conducting wire respectively with lateral angles sensor (2), vertical angular transducer (15) phase
It is drawn at Lian Houcong arch block (1).
2. the flat rudder face angle measurement unit of a kind of aircraft according to claim 1, it is characterised in that: the lateral angles pass
Sensor (2) is fixed on the inside of compasses cutter sucker (4) by the cooperation of screw one (3), nut two (13), covers on screw one (3)
There are 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 CN106017395A (en) | 2016-10-12 |
| CN106017395B true CN106017395B (en) | 2019-04-19 |
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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 |
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| CN (1) | CN106017395B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108731706B (en) * | 2018-04-03 | 2020-08-07 | 烟台北方星空自控科技有限公司 | Sensor |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5097800B2 (en) * | 2010-06-09 | 2012-12-12 | アルプス電気株式会社 | Rotation angle sensor |
| CN101963499B (en) * | 2010-07-21 | 2012-10-10 | 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 |
| CN104204719B (en) * | 2012-01-27 | 2017-05-31 | 卡夫利科公司 | Rotary Variable Differential transformer (RVDT) sensor cluster 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 | Rudder area sensor mark school anchor clamps |
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2016
- 2016-06-28 CN CN201610486698.1A patent/CN106017395B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| CN106017395A (en) | 2016-10-12 |
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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 |