CN102343984B - Locking mechanism in rudder deflection angle testing device - Google Patents
Locking mechanism in rudder deflection angle testing device Download PDFInfo
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- CN102343984B CN102343984B CN201110191305.1A CN201110191305A CN102343984B CN 102343984 B CN102343984 B CN 102343984B CN 201110191305 A CN201110191305 A CN 201110191305A CN 102343984 B CN102343984 B CN 102343984B
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- 238000012360 testing method Methods 0.000 title claims abstract description 19
- 230000001105 regulatory effect Effects 0.000 claims abstract description 10
- 230000005540 biological transmission Effects 0.000 claims description 8
- 238000009987 spinning Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000001360 synchronised effect Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
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Abstract
The invention relates to a locking mechanism in a rudder deflection angle testing device, which comprises at least one pair of clamp bodies and angle output shafts, wherein the clamp bodies are used for being in clamping rotation-stopping fit with a corresponding regulating rudder wing; the rotation axial lines of the angle output shafts are coaxially arranged with the rotation axial line of a corresponding rudder shaft; and a driving mechanism which is used for outputting the rotation angle of the corresponding clamp body to the angle output shafts in real time is arranged between each angle output shaft and the corresponding clamp body. The invention provides the locking mechanism in the rudder deflection angle testing device, and by using the locking mechanism, the rotation angle parameters of the rudder shaft can be directly tested without disassembling the regulating rudder wing of an aircraft.
Description
Technical field
The present invention relates to the rudder deflection angle testing device for aircraft rudder angle deviator, relate in particular to the catch gear in a kind of rudder deflection angle testing device.
Background technology
Existing aircraft comprises body, for guarantee aircraft in flight course steadily and can adjust at any time the horizontal flight angle of aircraft and vertical flying height, described body periphery is evenly equipped with four adjusting rudder wings that are respectively used to control body horizontal flight angle and vertical flying height, described four adjusting rudder wings are divided into two groups, and the rudder aerofoil of described every group of rudder wing is all in same plane.Also be rotatably equipped with two groups in described body respectively for controlling corresponding every group of rudderpost of regulating rudder wing synchronous rotary.
Before aircraft is taken a flight test, need to test respectively the anglec of rotation parameter of described rudderpost, the test method of the anglec of rotation parameter of existing aircraft rudderpost is that the adjusting rudder wing of aircraft is unloaded, the anglec of rotation that directly with the circuit of aircraft inside, is connected to test rudderpost.Workman's work capacity is larger, and for some special aircraft, do not allow to regulate the rudder wing and unload, therefore with existing technological means, can't complete the test to rudderpost anglec of rotation parameter.
Summary of the invention
The object of the present invention is to provide a kind of catch gear that can directly be tested rudderpost anglec of rotation parameter for rudder deflection angle testing device need not unload the adjusting rudder wing of aircraft.
In order to address the above problem, technical scheme of the present invention is:
Catch gear in a kind of rudder deflection angle testing device, described catch gear comprises for the clamping of the corresponding adjusting rudder wing, only screwing the angle output shaft of at least one pair of clamp body of closing and rotation axis and the coaxial setting of the rotation axis of corresponding rudderpost, described each angle output shaft and be provided with the transmission device that outputs in real time the angle output shaft for the anglec of rotation by corresponding clamp body between clamp body accordingly.
Described transmission device comprises the axis of sideslip that the rotation axis of line of centers and corresponding rudderpost is perpendicular, described clamp body comprises that thereby two to establishing and for clamping the corresponding adjusting rudder wing and the corresponding adjusting rudder wing only train wheel bridge and the lower plate of the company of being rotated with, on described, between lower plate, be provided with for regulating its clamping plate bolt in gap between the two, nut locking mechanism, on described, the lower plate slidable fit is on described axis of sideslip and can pass through described clamping plate bolt, nut locking mechanism is locked, described angle output shaft fixed connection stops spinning and is assigned on described axis of sideslip, described angle output shaft is provided with for inserting the corresponding encoded device and the anglec of rotation that correspondence is regulated the rudder wing being outputed in real time to the mouth of corresponding encoded device away from an end of described axis of sideslip.
The bearing fit place of described upper and lower clamping plate and described axis of sideslip is provided with respectively upper and lower split sleeve, in described upper and lower split sleeve, offers the through hole worn for described axis of sideslip.
Described upper and lower clamping plate are the L-type clamping plate, and the nut in described clamping plate bolt, nut locking mechanism is fly nut, and the corresponding position of described upper and lower clamping plate is equipped with the engaging lug assembled for clamping plate bolt, fly nut.
Described axis of sideslip is provided with the limiting stopper spacing along moving axially of axis of sideslip for described upper and lower clamping plate away from an end of angle output shaft.
Beneficial effect of the present invention is: clamp body is locked with the corresponding adjusting rudder wing, the anglec of rotation of regulating the rudder wing is outputed on corresponding clamp body in real time, described clamp body exports the anglec of rotation to the angle output shaft again in real time, and then reached the purpose that the anglec of rotation that will regulate the rudder wing exports the angle output shaft in real time to, again because the adjusting rudder wing and corresponding rudderpost are synchronous rotaries, so described angle output shaft has been exported the anglec of rotation of corresponding rudderpost in real time, thereby reached the purpose that the rudderpost anglec of rotation is tested.The present invention need not unload the adjusting rudder wing of aircraft and directly aircraft is tested, and has reduced workman's work capacity, has improved production efficiency.
The accompanying drawing explanation
Fig. 1 is the present invention's structural representation of example in real time;
Fig. 2 is the use constitution diagram of Fig. 1;
Fig. 3 is the view at another visual angle of Fig. 2;
Fig. 4 is the structural representation of detent mechanism in Fig. 2;
Fig. 5 is the block diagram of Fig. 4;
Fig. 6 is the use constitution diagram of Fig. 2.
The specific embodiment
Embodiment is as shown in Fig. 1 ~ 6: the catch gear 10 in a kind of rudder deflection angle testing device, described catch gear 10 comprises for 18 clampings of the corresponding adjusting rudder wing, only screwing the angle output shaft 11 of at least one pair of clamp body of closing and rotation axis and the coaxial setting of the rotation axis of corresponding rudderpost 19, described each angle output shaft 11 and be provided with the transmission device that outputs in real time angle output shaft 11 for the anglec of rotation by corresponding clamp body between clamp body accordingly.
Further, described transmission device comprises the axis of sideslip 16 that the rotation axis of line of centers and corresponding rudderpost 19 is perpendicular, described clamp body comprises that thereby two to establishing and for clamping the corresponding adjusting rudder wing 18 and the corresponding adjusting rudder wing 18 only train wheel bridge 14 and the lower plate 15 of the company of being rotated with, between described upper and lower clamping plate, be provided with for regulating its clamping plate bolt, nut locking mechanism 17 in gap between the two, described upper and lower clamping plate slidable fit also can be locked by described clamping plate bolt, nut locking mechanism 17 on described axis of sideslip 16.Described upper and lower clamping plate are L shaped clamping plate, and the nut in described clamping plate bolt, nut locking mechanism 17 is fly nut, and the corresponding position of described upper and lower clamping plate is equipped with the engaging lug assembled for clamping plate bolt, fly nut.The described angle output shaft 11 only spinning that is connected is assigned on described axis of sideslip 16.On described, the bearing fit place of lower plate and described axis of sideslip 16 is provided with respectively train wheel bridge sleeve 22 and lower plate sleeve 23, on described, offer in the lower plate sleeve and be provided with the through hole worn for described axis of sideslip 16, on, lower plate is by the clamping plate bolt, after 17 pairs of corresponding adjusting rudder wings 18 of nut locking mechanism are locked, on, lower sleeve is simultaneously also by the clamping plate bolt, 17 pairs of axiss of sideslip of nut locking mechanism 16 produce predetermincd tension locking, now go up, lower sleeve just is connected with described axis of sideslip 16, thereby in realization, the anglec of rotation of lower plate is exported in real time by axis of sideslip 16, finally realize that the anglec of rotation of corresponding rudderpost 19 exported in real time by angle output shaft 11.Described axis of sideslip 16 is provided with the limiting stopper 24 spacing along moving axially of axis of sideslip 16 for described upper and lower clamping plate away from an end of angle output shaft 11.Described angle output shaft 11 is provided with for inserting corresponding encoded device 13(or angular transducer away from an end of described axis of sideslip 16) and the anglec of rotation that correspondence is regulated the rudder wing 18 is outputed in real time to the mouth of corresponding encoded device 13, be connected by one section square pole transition between described deferent segment and described axis of sideslip 16, start to have the axially extended mating groove 24 of length direction along described angle output shaft 11 on the outer peripheral face of described mouth.
This catch gear 10 is arranged to the rudder deflection angle testing device for rudderpost 19 anglec of rotation parameter testings, described rudder deflection angle testing device, comprise the detent mechanism 1 for aircraft 20 location, described detent mechanism 1 has location cancave cambered surface 3(or the hole that coordinates with aircraft 20 outer peripheral faces to be measured and aircraft 20 is located), described detent mechanism 1 comprises locating piece 2, also be provided with the identical position-limited trough 4 that embeds assembling of rudderpost 19 for aircraft 20 to be measured on described locating piece 2, the trough wall surface of described position-limited trough 4 has when measuring watt shape face of cylinder for the coaxial corresponding setting of the rotation axis with aircraft 20 rudderposts 19 to be measured, described proving installation also comprises supporting seat 8, described supporting seat 8 is provided with at least one measuring section 9 for rudderpost 19 anglecs of rotation are tested, described each measuring section 9 is equipped with for correspondence and regulates the catch gear 10 that the rudder wing 18 is locked, described catch gear 10 comprises for the corresponding adjusting rudder wing 18 clampings, only screwing at least one pair of clamp body and the angle output shaft 11 closed, be provided with the transmission device that outputs in real time angle output shaft 11 for the anglec of rotation by corresponding clamp body between described each angle output shaft 11 and corresponding clamp body, the corresponding setting of axis coaxle on the axis of described angle output shaft 11 and watt shape face of cylinder of described position-limited trough 4, described location cancave cambered surface 3(or hole) also be arranged on described locating piece 2.Described position-limited trough 4 have two and be arranged at respectively described location cancave cambered surface 3(or hole) both sides, described two position-limited troughs 4 two rudderposts adjacent for aircraft 19 coincide and embed assembling.
Described supporting seat 8 is C shape supporting seat, and described measuring section 9 has three and be distributed on described C shape supporting seat 8.The outer peripheral face of described supporting seat 8 is provided with for its hard-wired supporting seat mounting plane 12, on the inner peripheral surface of described supporting seat 8, in the corresponding position of described supporting seat mounting plane 12, is provided with for the hard-wired detent mechanism mounting plane 21 of detent mechanism 1.Described detent mechanism 1 is arranged on described detent mechanism mounting plane 21 by screw, described proving installation also comprises the positioning seat 5 of installing for locating piece 2, the middle part of described locating piece 2 is rotated and is assemblied on described positioning seat 5, concretely, on described positioning seat 5, spacing parallel arranging is provided with two engaging lugs 7, and described locating piece 2 rotates and is assemblied between described two engaging lugs 7.Described location cancave cambered surface 3 is arranged at an end of described locating piece, and described locating piece 2 is away between an end of locating cancave cambered surface and described positioning seat 5, being provided with locating piece bolt, nut locking mechanism 6.Described each measuring section 9 is equipped with coder 13, and during use, the deferent segment of described angle output shaft 11 coordinates and the anglec of rotation of corresponding rudderpost 19 is exported in real time with corresponding coder 13.
During use, aircraft 20 is positioned in the location cancave cambered surface 3 on described detent mechanism 1, two position-limited troughs 4 of detent mechanism 1 and spacing cooperation of rudderpost 19 on aircraft 20, the rudderpost 19 of aircraft 20 is arranged with the angle output shaft of corresponding measuring section 9 coaxial 11, then with the upper and lower clamping plate of three catch gears 10, the corresponding adjusting rudder wing 18 is clamped, by adjusting locating piece bolt, nut locking mechanism 6, locating piece 2 was fallen after clamping, then respectively the anglec of rotation of three groups of rudderposts 19 was tested.Due to rudderpost 19 respectively with the corresponding adjusting rudder wing 18 synchronous rotaries, and upper, clamping plate clamp with the corresponding adjusting rudder wing 18 and axis of sideslip 16 and only revolve, so axis of sideslip 16 is the anglec of rotation of corresponding rudderpost 19 with respect to the swing angle degree of angle output shaft 11, the concrete anglec of rotation is by corresponding real-time being transferred in corresponding display equipment of coder 13 arranged of each measuring section 9.After detection completes, upper and lower clamping plate are removed, taken away and survey aircraft 20, enter next testing process.
The present invention, by the upper and lower clamping plate of catch gear, can be locked the adjusting rudder wing 18 of multiple different-thickness; Guaranteed that by clamping plate bolt, nut locking mechanism 17 upper and lower clamping plate are connected and only revolve with the corresponding adjusting rudder wing 18 and axis of sideslip 16 respectively simultaneously, realized the real-time angle output of the rudder wing 19 to angle output shaft 11; Whole catch gear can not produce the power that applies to rudderpost 11; Can after aircraft 20 has detected, by adjustable clamp crab bolt, nut locking mechanism 17, make upper and lower clamping plate along the sideskid guiding movement, facilitate the taking-up of aircraft 20; By catch gear 10 of the present invention, can rudderpost 19 be rotated to the angle parameter test in the situation that the adjusting rudder wing 18 is not dismantled, reduced workman's labour intensity, improved production efficiency.
In other embodiments of the invention, described transmission device can also be and the leading screw of described upper and lower clamping plate screw thread fit that axis of sideslip 16 now is also screw thread fit with the matching relationship of described angle output shaft 11; Described measuring section 9 can be also one or two; Described upper and lower clamping plate can also have respectively two, three or multi-disc; Described location cancave cambered surface 3 and position-limited trough 4 also can separately be arranged on two pedestals.
Claims (4)
1. the catch gear in a rudder deflection angle testing device, it is characterized in that: described catch gear comprises for the clamping of the corresponding adjusting rudder wing, only screwing the angle output shaft of at least one pair of clamp body of closing and rotation axis and the coaxial setting of the rotation axis of corresponding rudderpost, be provided with the transmission device that outputs in real time the angle output shaft for the anglec of rotation by corresponding clamp body between described each angle output shaft and corresponding clamp body, described transmission device comprises the axis of sideslip that the rotation axis of line of centers and corresponding rudderpost is perpendicular, described clamp body comprises that thereby two to establishing and for clamping the corresponding adjusting rudder wing and the corresponding adjusting rudder wing only train wheel bridge and the lower plate of the company of being rotated with, on described, between lower plate, be provided with for regulating its clamping plate bolt in gap between the two, nut locking mechanism, on described, the lower plate slidable fit is on described axis of sideslip and can pass through described clamping plate bolt, nut locking mechanism is locked, described angle output shaft fixed connection stops spinning and is assigned on described axis of sideslip, described angle output shaft is provided with for inserting the corresponding encoded device and the anglec of rotation that correspondence is regulated the rudder wing being outputed in real time to the mouth of corresponding encoded device away from an end of described axis of sideslip.
2. catch gear according to claim 1, it is characterized in that: the bearing fit place of described upper and lower clamping plate and described axis of sideslip is provided with respectively upper and lower split sleeve, in described upper and lower split sleeve, offers the through hole worn for described axis of sideslip.
3. catch gear according to claim 1, it is characterized in that: described upper and lower clamping plate are the L-type clamping plate, nut in described clamping plate bolt, nut locking mechanism is fly nut, and the corresponding position of described upper and lower clamping plate is equipped with the engaging lug assembled for clamping plate bolt, fly nut.
4. catch gear according to claim 1, it is characterized in that: described axis of sideslip is provided with the limiting stopper spacing along moving axially of axis of sideslip for described upper and lower clamping plate away from an end of angle output shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110191305.1A CN102343984B (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110191305.1A CN102343984B (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle testing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102343984A CN102343984A (en) | 2012-02-08 |
| CN102343984B true CN102343984B (en) | 2014-01-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110191305.1A Expired - Fee Related CN102343984B (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle testing device |
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| CN (1) | CN102343984B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163626B (en) * | 2018-09-21 | 2023-09-26 | 湖南金翎箭信息技术有限公司 | Zero adjustment device and method for rudder wings of missile steering engine |
| CN112973012A (en) * | 2021-02-03 | 2021-06-18 | 李春平 | Body-building and body-shaping trainer for men, women, old and young |
| CN113933017A (en) * | 2021-09-29 | 2022-01-14 | 西安航天动力试验技术研究所 | Real-time measurement system and method for deployment angle of outer rudder of high-speed impact state aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2823629Y (en) * | 2005-08-24 | 2006-10-04 | 上海贝凯生物化工设备有限公司 | Normal closed hand-controlled locking mechanism |
| CN101397055A (en) * | 2008-10-21 | 2009-04-01 | 北京航空航天大学 | Shape adjusting apparatus for digital control flexible fixture |
| WO2009132684A1 (en) * | 2008-04-30 | 2009-11-05 | Esk Ceramics Gmbh & Co. Kg | Method for affixing a connection element to a work piece and component made from a work piece comprising a connection element affixed thereto |
| CN202147842U (en) * | 2011-07-08 | 2012-02-22 | 凯迈（洛阳）测控有限公司 | Locking mechanism in rudder deflection angle measuring device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2919039B1 (en) * | 2007-07-16 | 2012-12-28 | Caillau Ets | CLAMPING DEVICE WITH CLAMPING NECK AND POSITIONING PIECE |
| DE102008022092A1 (en) * | 2008-05-05 | 2009-11-19 | Airbus Deutschland Gmbh | Fault-tolerant control system for adjusting the flaps of an aircraft with adjustable kinematics with a fixed axis of rotation |
-
2011
- 2011-07-08 CN CN201110191305.1A patent/CN102343984B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2823629Y (en) * | 2005-08-24 | 2006-10-04 | 上海贝凯生物化工设备有限公司 | Normal closed hand-controlled locking mechanism |
| WO2009132684A1 (en) * | 2008-04-30 | 2009-11-05 | Esk Ceramics Gmbh & Co. Kg | Method for affixing a connection element to a work piece and component made from a work piece comprising a connection element affixed thereto |
| CN101397055A (en) * | 2008-10-21 | 2009-04-01 | 北京航空航天大学 | Shape adjusting apparatus for digital control flexible fixture |
| CN202147842U (en) * | 2011-07-08 | 2012-02-22 | 凯迈（洛阳）测控有限公司 | Locking mechanism in rudder deflection angle measuring device |
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| CN102343984A (en) | 2012-02-08 |
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Granted publication date: 20140101 |