CN208000102U - A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device - Google Patents
A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device Download PDFInfo
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- CN208000102U CN208000102U CN201820117135.XU CN201820117135U CN208000102U CN 208000102 U CN208000102 U CN 208000102U CN 201820117135 U CN201820117135 U CN 201820117135U CN 208000102 U CN208000102 U CN 208000102U
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- rocking arm
- vernier
- bias signal
- horizontal tail
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Abstract
A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, belongs to test, field of measuring technique, it includes pedestal, rocking arm operating angle measuring mechanism, rocking arm extreme angles measuring mechanism;The pedestal is positioned on horizontal plane, pedestal one end install rocking arm operating angle measuring mechanism, the pedestal other end install rocking arm extreme angles measuring mechanism, in the base between position setting workpiece install bushing;The rocking arm operating angle measuring mechanism is equipped with vernier angle scale and vernier angle scale fixed seat, and the vernier angle scale fixed seat is wedge-shaped holder structure, and groove and output shaft locating slot for installing vernier angle scale are arranged in vernier angle scale fixed seat;The vernier angle scale is placed in the groove of vernier angle scale fixed seat, and is fixed by pressing plate.The utility model realizes being reliably fixed for detected workpiece, and can accurately read the rotation angle value of rocking arm, has achieved the purpose that improve testing result accuracy, has ensured aircraft security flight.
Description
Technical field
The utility model is related to a kind of angle measurement units, especially a kind of to be examined for aircraft horizontal tail degree of bias signal mechanism
The angle measurement unit of survey belongs to test, field of measuring technique.
Background technology
As shown in attached drawing 1, Fig. 2, a kind of aircraft horizontal tail degree of bias signal mechanism 1, it is equipped with rocking arm 1-1, the rocking arm 1-1
The output shaft 1-2 fixing assemblings of one end and aircraft horizontal tail degree of bias signal mechanism 1, the other end pass through pilot hole 1-3 and aircraft
Horizontal tail deflects executing agency's connection, and operation principle is to be passed to aircraft horizontal tail deflection angle information by rocking arm 1-1
Sensor, then aircraft horizontal tail deflection angle information is fed back to by steerable system by sensor, so that driver's accurate judgement flies
The state of flight of row device.
It, need to be to aircraft horizontal tail degree of bias signal mechanism when being overhauled to aircraft in order to ensure the reliability of aircraft manipulation
It is tested for the property, whether the information that rocking arm 1-1 actual rotational angles and sensor feedback are detected by related equipment is consistent, is
This needs aircraft horizontal tail degree of bias signal mechanism 1 being securely fixed, and accurately reads the rotational angle of rocking arm 1-1, simultaneously also
Corresponding corner measures when being in extreme position to rocking arm 1-1, therefore, design it is a kind of disclosure satisfy that above-mentioned requirements,
Angle measurement unit for the detection of aircraft horizontal tail degree of bias signal mechanism is imperative.
Utility model content
The utility model provides a kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, it is intended to by quilt
Being reliably fixed, accurately reading the technological means such as rocking arm rotation angle for detection workpiece, reaches and improves testing result accuracy, ensures
The purpose of aircraft security flight.
To achieve the above object, the utility model adopts the following technical solution:
A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, including pedestal, rocking arm operating angle measure
Mechanism, rocking arm extreme angles measuring mechanism;The pedestal is positioned on horizontal plane, and in pedestal one end, installation rocking arm operating angle is surveyed
Measuring mechanism, the pedestal other end install rocking arm extreme angles measuring mechanism, in the base between position setting workpiece install bushing;Institute
It states rocking arm operating angle measuring mechanism and is equipped with vernier angle scale and vernier angle scale fixed seat, the vernier angle scale fixed seat is
Groove and output shaft locating slot for installing vernier angle scale is arranged in wedge-shaped holder structure in vernier angle scale fixed seat;Institute
It states vernier angle scale to be placed in the groove of vernier angle scale fixed seat, and is fixed by pressing plate.
Above-mentioned aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, the rocking arm operating angle measuring mechanism is also
Equipped with link, described link one end passes through the dress on locking nail and the rocking arm of aircraft horizontal tail degree of bias signal to be detected mechanism
Distribution is fixedly connected, and the other end is fixed on the vernier scale back side of vernier angle scale, is arranged for reading vernier angle on link
Spend the long groove shape window of ruler measured value.
Above-mentioned aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, in the rocking arm operating angle measuring mechanism
In, vernier angle scale positioning convex platform is arranged in groove one end of the vernier angle scale fixed seat.
Two groups of bushings assembly are arranged on the pedestal for above-mentioned aircraft horizontal tail degree of bias signal mechanism detection angles measuring device
Hole, the workpiece installation bushing are fixed on the base with the cooperation of one of which bushing pilot hole.
Above-mentioned aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, the rocking arm extreme angles measuring mechanism are
Output shaft positioning bushing is arranged in the arch dial of corresponding 230 ° of central angles at the center location of the dial.
Above-mentioned aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, the rocking arm extreme angles measuring mechanism is also
Including the indicating hand component that can be fixedly mounted in rocking arm pilot hole.
The utility model is after adopting the above technical scheme, achieve following technological progress effect:
It is flat that aircraft is carried out using aircraft horizontal tail degree of bias signal described in the utility model mechanism detection angles measuring device
When tail degree of bias signal mechanism performance is tested, can install bushing and one group of bushing pilot hole cooperation on pedestal by workpiece first will wait for
The aircraft horizontal tail degree of bias signal mechanism of detection is fixed on the base, and is output it axis and is placed in output shaft locating slot, by rocking arm
Pilot hole passes through locking nail and link fixing assembling;Then drive rocking arm around output shaft by the vernier scale on vernier angle scale
Rotation, the stopping action at the rocking arm angular position of setting, record at this time to the corner of related equipment believe by sensor feedback
Breath, and rocking arm actual rotational angle that the corner information is shown with vernier angle scale is judged into the aircraft horizontal tail degree of bias to comparing with this
The reliability of signal mechanism work;In addition, when carrying out the measurement of rocking arm extreme angles, aircraft horizontal tail degree of bias news to be detected are adjusted
The installation direction of number mechanism makes workpiece installation bushing coordinate with another group of bushing pilot hole on pedestal, outputs it axis and be placed in quarter
In output shaft positioning bushing at scale center location, and it is equipped with indicating hand component in rocking arm pilot hole, rotate rocking arm and reads
The angle value is compared with standard value, judges to fly with this by its angle value indicated on dial in two extreme positions
Whether row device horizontal tail degree of bias signal mechanism rocking arm ultimate angle meets technology requirement.It can be seen that the utility model realize by
Detection workpiece is reliably fixed, and can accurately read the rotation angle value of rocking arm, has been reached raising testing result accuracy, has been protected
Demonstrate,prove the purpose of aircraft security flight.
Description of the drawings
Fig. 1 is carry-on horizontal tail degree of bias signal structural scheme of mechanism;
Fig. 2 is the side view of Fig. 1;
Fig. 3 is the utility model structure diagram;
Fig. 4 is the K direction views of Fig. 3;
Fig. 5 is the A direction views identified in Fig. 4;
Fig. 6 is the B direction views identified in Fig. 4;
Fig. 7 is pedestal, vernier angle scale fixed seat and workpiece installation bush structure and assembly relation schematic diagram;
Fig. 8 is connecting frame structure schematic diagram in rocking arm operating angle measuring mechanism;
Fig. 9 is that the utility model carries out aircraft horizontal tail degree of bias signal mechanism performance test schematic diagram;
Figure 10 is that the utility model carries out rocking arm extreme angles instrumentation plan.
Each list of reference numerals is in figure:
1, aircraft horizontal tail degree of bias signal mechanism, 1-1, rocking arm, 1-2, output shaft, 1-3, pilot hole;
2, aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, 2-1, pedestal, 2-1-1, bushing pilot hole, 2-
2, vernier angle scale fixed seat, 2-2-1, output shaft locating slot, 2-2-2, groove, 2-2-3, pressing plate, 2-2-4, vernier angle scale
Positioning convex platform, 2-3, vernier angle scale, 2-4, link, 2-4-1, long groove shape window, 2-5, locking nail, 2-6, workpiece installation lining
Set, 2-7, dial, 2-8, indicating hand component.
Specific implementation mode
Below in conjunction with the accompanying drawings and specific embodiment the utility model is described in further detail.
Referring to Fig. 3, Fig. 4, the utility model are a kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, it
Including pedestal 2-1, rocking arm operating angle measuring mechanism and rocking arm extreme angles measuring mechanism;The pedestal 2-1 is positioned over level
On face, rocking arm operating angle measuring mechanism is installed in the one end pedestal 2-1, rocking arm extreme angles measuring machine is installed in the pedestal other end
Structure, setting two groups of bushing pilot hole 2-1-1 of setting in position pass through when carrying out the measurement of rocking arm operating angle among pedestal 2-1
Workpiece is installed bushing 2-6 and one of which bushing pilot hole 2-1-1 and is coordinated aircraft horizontal tail degree of bias signal mechanism 1 to be detected
It is fixed on pedestal 2-1, when carrying out the measurement of rocking arm extreme angles, passes through workpiece and bushing 2-6 and another group of bushing assembly are installed
Aircraft horizontal tail degree of bias signal mechanism 1 to be detected is fixed on pedestal 2-1 by hole 2-1-1 cooperations.
Referring to Fig. 4, Fig. 5, Fig. 7, Fig. 8, aircraft horizontal tail degree of bias signal described in the utility model mechanism detection angles measure
Device 2, the rocking arm operating angle measuring mechanism are equipped with vernier angle scale 2-3, vernier angle scale fixed seat 2-2 and link 2-
4;The vernier angle scale fixed seat 2-2 is wedge-shaped holder structure, is arranged for installing vernier on vernier angle scale fixed seat 2-2
The groove 2-2-2 and output shaft locating slot 2-2-1 of bevel protractor;The vernier angle scale 2-3 is placed in vernier angle scale fixed seat 2-
In 2 groove 2-2-2, in the one end groove 2-2-2, setting vernier angle scale positioning convex platform 2-2-4, vernier angle scale 2-3 pass through pressure
Plate 2-2-3 is fixed;It is shaken by locking nail 2-5 and aircraft horizontal tail degree of bias signal to be detected mechanism 1 one end the link 2-4
Pilot hole 1-3 on arm 1-1 is fixedly connected, and the other end is fixed on the vernier scale back side of vernier angle scale 2-3, in link 2-4
The upper long groove shape window 2-4-1 being arranged for reading vernier angle scale measured value.
Referring to Fig. 4, Fig. 6, aircraft horizontal tail degree of bias signal described in the utility model mechanism detection angles measuring device 2, institute
The arch dial 2-7 that rocking arm extreme angles measuring mechanism is corresponding 230 ° of central angles is stated, in the center of circle of dial 2-7 position
It sets place's setting output shaft and positions bushing 2-7-1;The rocking arm extreme angles measuring mechanism further includes that can be fixedly mounted on rocking arm 1-1
Pilot hole 1-3 in indicating hand component 2-8.
Referring to Fig. 9, carried out using aircraft horizontal tail degree of bias signal described in the utility model mechanism detection angles measuring device 2
When 1 rocking arm operating angle of aircraft horizontal tail degree of bias signal mechanism measures, can bushing 2-6 and pedestal 2-1 be installed by workpiece first
Aircraft horizontal tail degree of bias signal mechanism 1 to be detected is fixed on pedestal 2-1 by upper one group of bushing pilot hole 2-1-1 cooperations, will
Its output shaft 1-2 is placed in the output shaft locating slot 2-2-1 of vernier angle scale fixed seat 2-2, by the pilot hole 1-3 of rocking arm 1-1
Pass through locking nail 2-5 and link 2-4 fixing assemblings;Then by vernier scale on vernier angle scale 2-3 drive rocking arm 1-1 around
Output shaft 1-2 rotation, at the rocking arm angular position of setting stopping act, record at this time sensor feedback to related equipment
Corner information, and rocking arm actual rotational angle that the corner information is shown with vernier angle scale is judged into aircraft to comparing with this
The reliability of horizontal tail degree of bias signal mechanism work.
Referring to Fig. 9, carried out using aircraft horizontal tail degree of bias signal described in the utility model mechanism detection angles measuring device 2
When 1 rocking arm extreme angles of aircraft horizontal tail degree of bias signal mechanism measure, aircraft horizontal tail degree of bias signal to be detected mechanism 1 is adjusted
Installation direction makes another group of bushing pilot hole on workpiece installation bushing 2-6 and pedestal 2-1 coordinate, outputs it axis 1-2 and be placed in quarter
In output shaft positioning bushing 2-7-1 at scale 2-7 center locations, and pointer set is equipped in the pilot hole 1-3 of rocking arm 1-1
Part 2-8 rotates rocking arm 1-1 and reads the angle value that its indicating hand component 2-8 is indicated in two extreme positions on dial 2-7,
The angle value is compared with standard value, judges whether aircraft horizontal tail degree of bias signal mechanism rocking arm ultimate angle meets with this
Technology requirement.
Claims (6)
1. a kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device, characterized in that the aircraft horizontal tail degree of bias
Signal mechanism detection angles measuring device (2) includes that pedestal (2-1), rocking arm operating angle measuring mechanism and rocking arm extreme angles are surveyed
Measuring mechanism;The pedestal (2-1) is positioned on horizontal plane, and rocking arm operating angle measuring mechanism is installed in the one end pedestal (2-1),
The pedestal other end installs rocking arm extreme angles measuring mechanism, and bushing (2-6) is installed in the intermediate position setting workpiece of pedestal (2-1);
The rocking arm operating angle measuring mechanism is equipped with vernier angle scale (2-3) and vernier angle scale fixed seat (2-2), the vernier angle
It is wedge-shaped holder structure to spend ruler fixed seat (2-2), is arranged for installing vernier angle scale in vernier angle scale fixed seat (2-2)
Groove (2-2-2) and output shaft locating slot (2-2-1);The vernier angle scale (2-3) is placed in vernier angle scale fixed seat (2-2)
Groove (2-2-2) in, and it is fixed to pass through pressing plate (2-2-3).
2. aircraft horizontal tail degree of bias signal according to claim 1 mechanism detection angles measuring device, characterized in that described
Rocking arm operating angle measuring mechanism is additionally provided with link (2-4), described link one end (2-4) by locking nail (2-5) with wait for
Pilot hole (1-3) on sense aircraft horizontal tail degree of bias signal mechanism (1) rocking arm (1-1) is fixedly connected, and the other end is fixed on trip
The long groove shape for reading vernier angle scale measured value is arranged in the vernier scale back side for marking bevel protractor (2-3) on link (2-4)
Window (2-4-1).
3. aircraft horizontal tail degree of bias signal according to claim 2 mechanism detection angles measuring device, characterized in that in institute
It states in rocking arm operating angle measuring mechanism, the one end groove (2-2-2) setting vernier angle of the vernier angle scale fixed seat (2-2)
Spend ruler positioning convex platform (2-2-4).
4. aircraft horizontal tail degree of bias signal according to claim 1 or 2 or 3 mechanism detection angles measuring device, feature
It is that two groups of bushing pilot holes (2-1-1) are set on the pedestal (2-1), the workpiece installation bushing (2-6) serves as a contrast with one of which
Set pilot hole (2-1-1) cooperation is fixed on pedestal (2-1).
5. aircraft horizontal tail degree of bias signal according to claim 4 mechanism detection angles measuring device, characterized in that described
Rocking arm extreme angles measuring mechanism is the arch dial (2-7) of corresponding 230 ° of central angles, in the center of circle of the dial (2-7)
Output shaft is set at position and positions bushing (2-7-1).
6. aircraft horizontal tail degree of bias signal according to claim 5 mechanism detection angles measuring device, characterized in that described
Rocking arm extreme angles measuring mechanism further includes the indicating hand component (2- that can be fixedly mounted in the pilot hole (1-3) of rocking arm (1-1)
8)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820117135.XU CN208000102U (en) | 2018-01-24 | 2018-01-24 | A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820117135.XU CN208000102U (en) | 2018-01-24 | 2018-01-24 | A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device |
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| Publication Number | Publication Date |
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| CN208000102U true CN208000102U (en) | 2018-10-23 |
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| CN201820117135.XU Active CN208000102U (en) | 2018-01-24 | 2018-01-24 | A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112325724A (en) * | 2020-10-09 | 2021-02-05 | 横店集团英洛华电气有限公司 | Door motor mounting plate position detection device |
| CN112407318A (en) * | 2020-10-30 | 2021-02-26 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting installation angle of shaft pin type fixed horizontal tail of helicopter |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
| CN113340264A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Method and device for debugging installation angle of aircraft attack angle sensor |
-
2018
- 2018-01-24 CN CN201820117135.XU patent/CN208000102U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113340264A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Method and device for debugging installation angle of aircraft attack angle sensor |
| CN113340264B (en) * | 2020-03-02 | 2023-03-14 | 中航西飞民用飞机有限责任公司 | Method and device for debugging installation angle of aircraft attack angle sensor |
| CN112325724A (en) * | 2020-10-09 | 2021-02-05 | 横店集团英洛华电气有限公司 | Door motor mounting plate position detection device |
| CN112325724B (en) * | 2020-10-09 | 2022-08-23 | 浙江联宜电机有限公司 | Door motor mounting plate position detection device |
| CN112407318A (en) * | 2020-10-30 | 2021-02-26 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting installation angle of shaft pin type fixed horizontal tail of helicopter |
| CN112960140A (en) * | 2021-03-15 | 2021-06-15 | 中国商用飞机有限责任公司 | Horizontal tail trim angle adjusting device |
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