CN102343984A - Locking mechanism in rudder deflection angle testing device - Google Patents
Locking mechanism in rudder deflection angle testing device Download PDFInfo
- Publication number
- CN102343984A CN102343984A CN2011101913051A CN201110191305A CN102343984A CN 102343984 A CN102343984 A CN 102343984A CN 2011101913051 A CN2011101913051 A CN 2011101913051A CN 201110191305 A CN201110191305 A CN 201110191305A CN 102343984 A CN102343984 A CN 102343984A
- Authority
- CN
- China
- Prior art keywords
- axis
- clamping plate
- sideslip
- rudder
- output shaft
- 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
Links
Images
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 be used for the angle of rudder reflection proving installation of aircraft rudder angle deviator, relate in particular to the catch gear in a kind of angle of rudder reflection proving installation.
Background technology
Existing aircraft comprises body; For guarantee aircraft in flight course steadily and can adjust the horizontal flight angle of aircraft and vertical flying height at any time; Described body periphery is evenly equipped with four adjusting rudder wings that are respectively applied for 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 all is in the same plane.Also be rotatably equipped with two groups in the described body and be used to control corresponding every group of rudderpost of regulating the synchronous rotation of the rudder wing respectively.
Before aircraft is taken a flight test; Need test respectively the anglec of rotation parameter of said rudderpost; The test method of the anglec of rotation parameter of existing aircraft rudderpost is that the adjusting rudder wing with aircraft unloads, and directly links to each other with aircraft in-to-in circuit and tests the anglec of rotation of rudderpost.Workman's work capacity is bigger, and for some special aircraft, does not allow to regulate the rudder wing and unload, and therefore can't accomplish the test to rudderpost anglec of rotation parameter with existing technological means.
Summary of the invention
The object of the present invention is to provide and a kind ofly be used for that the angle of rudder reflection proving installation need not unload the adjusting rudder wing of aircraft and the catch gear that can directly test rudderpost anglec of rotation parameter.
In order to address the above problem, technical scheme of the present invention is:
Catch gear in a kind of angle of rudder reflection proving installation; Described catch gear comprises the angle output shaft that is used for only revolving with the clamping of the corresponding adjusting rudder wing at least one pair of clamp body of cooperating and rotation axis and the coaxial setting of rotation axis of corresponding rudderpost, is provided with the transmission device that is used for the anglec of rotation of corresponding clamp body is outputed in real time the angle output shaft between described each angle output shaft and the corresponding clamp body.
Described transmission device comprises the axis of sideslip that the rotation axis of line of centers and corresponding rudderpost is perpendicular; Thereby described clamp body comprises two to establishing and being used for the corresponding adjusting rudder of the clamping wing and the corresponding adjusting rudder the wing only train wheel bridge and the lower plate of the company of being rotated with; On described; Be provided with between the lower plate and be used to regulate 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 locks; Described angle output shaft fixed connection ends spinning and is assigned on the said axis of sideslip, and described angle output shaft is provided with the mouth that is used to insert the corresponding encoded device and the anglec of rotation that correspondence is regulated the rudder wing is outputed in real time the corresponding encoded device away from an end of said axis of sideslip.
The bearing fit place of described upper and lower clamping plate and said axis of sideslip is provided with upper and lower split sleeve respectively, offers in the said upper and lower split sleeve to be used for the through hole that said axis of sideslip wears.
Described upper and lower clamping plate are L type clamping plate, and the nut in described clamping plate bolt, the nut locking mechanism is a fly nut, and the corresponding position of described upper and lower clamping plate is equipped with and is used for the engaging lug that clamping plate bolt, fly nut assemble.
Described axis of sideslip is provided with away from an end of angle output shaft and is used for said upper and lower clamping plate along the spacing limiting stopper of moving axially of axis of sideslip.
Beneficial effect of the present invention is: clamp body and the locking of the cooresponding adjusting rudder wing; The anglec of rotation of regulating the rudder wing is outputed on the 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 rotations synchronously; 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.
Description of drawings
Fig. 1 is the present invention's structural representation of example in real time;
Fig. 2 is the running condition figure of Fig. 1;
Fig. 3 is the view at another visual angle of Fig. 2;
Fig. 4 is the structural representation of detent mechanism among Fig. 2;
Fig. 5 is the block diagram of Fig. 4;
Fig. 6 is the running condition figure of Fig. 2.
The specific embodiment
Embodiment is shown in Fig. 1 ~ 6: the catch gear 10 in a kind of angle of rudder reflection proving installation; Described catch gear 10 comprises the angle output shaft 11 that is used for only revolving with 18 clampings of the corresponding adjusting rudder wing at least one pair of clamp body of cooperating and rotation axis and the coaxial setting of rotation axis of corresponding rudderpost 19, is provided with the transmission device that is used for the anglec of rotation of corresponding clamp body is outputed in real time angle output shaft 11 between described each angle output shaft 11 and the corresponding clamp body.
Further; Described transmission device comprises the axis of sideslip 16 that the rotation axis of line of centers and corresponding rudderpost 19 is perpendicular; Thereby described clamp body comprises two to establishing and being used for the corresponding adjusting rudder of the clamping wing 18 and the corresponding adjusting rudder the wing 18 only train wheel bridge 14 and lower plate 15 of the company of being rotated with; Be provided with between the described upper and lower clamping plate and be used to regulate its clamping plate bolt, nut locking mechanism 17 in gap between the two, described upper and lower clamping plate slidable fit is on described axis of sideslip 16 and can lock through described clamping plate bolt, nut locking mechanism 17.Described upper and lower clamping plate are L shaped clamping plate, and the nut in described clamping plate bolt, the nut locking mechanism 17 is a fly nut, and the corresponding position of described upper and lower clamping plate is equipped with and is used for the engaging lug that clamping plate bolt, fly nut assemble.Described angle output shaft 11 only is connected, and spinning is assigned on the said axis of sideslip 16.On described; The bearing fit place of lower plate and said axis of sideslip 16 is provided with train wheel bridge sleeve 22 and lower plate sleeve 23 respectively; On said; Offer in the lower plate sleeve to be provided with and be used for the through hole that said axis of sideslip 16 wears; On; Lower plate is through 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 through the clamping plate bolt; 17 pairs of axiss of sideslip of nut locking mechanism 16 produce predetermincd tension and locking; On this moment; Lower sleeve just is connected with said axis of sideslip 16; Thereby in the realization; The anglec of rotation of lower plate is exported by axis of sideslip 16 in real time, realizes that finally the anglec of rotation of corresponding rudderpost 19 is exported by angle output shaft 11 in real time.Described axis of sideslip 16 is provided with away from an end of angle output shaft 11 and is used for said upper and lower clamping plate along the spacing limiting stopper 24 of moving axially of axis of sideslip 16.Described angle output shaft 11 is provided with the mouth that is used to insert corresponding encoded device 13 (or angular transducer) and the anglec of rotation that correspondence is regulated the rudder wing 18 is outputed in real time corresponding encoded device 13 away from an end of said axis of sideslip 16; Be connected through one section square pole transition between described deferent segment and the described axis of sideslip 16, begin to have the axially extended mating groove 24 of length direction on the outer peripheral face of said mouth along said angle output shaft 11.
This retaining mechanism 10 is arranged at the angle of rudder reflection testing arrangement that is used for rudderpost 19 anglec of rotation parameter testings; Described angle of rudder reflection testing arrangement; Comprise the detent mechanism 1 that is used for aircraft 20 location; Described detent mechanism 1 have cooperate with aircraft 20 outer peripheral faces to be measured and to the location cancave cambered surface 3(or the hole of aircraft 20 location); Described detent mechanism 1 comprises locating piece 2; Also be provided with the rudderpost 19 identical stopper slots 4 that embed assembling that supply aircraft 20 to be measured on the described locating piece 2; The trough wall surface of said stopper slot 4 has watt shape face of cylinder that when measuring, is used for the coaxial corresponding setting of the rotation of aircraft 20 rudderposts 19 to be measured; Described testing arrangement also comprises supporting seat 8; Described supporting seat 8 is provided with at least one and is used for test section 9 that rudderpost 19 anglecs of rotation are tested; Described each test section 9 is equipped with and is used for the corresponding retaining mechanism 10 that the rudder wing 18 is locked of regulating; Described retaining mechanism 10 comprises and is used for only revolving at least one pair of clamp body and the angle output shaft 11 that cooperates with 18 clampings of the corresponding adjusting rudder wing; Be provided with the transmission mechanism that is used for the anglec of rotation of corresponding clamp body is outputed in real time angle output shaft 11 between described each angle output shaft 11 and the corresponding clamp body; The corresponding setting of axis coaxle on the axis of said angle output shaft 11 and watt shape face of cylinder of said stopper slot 4, described location cancave cambered surface 3(or hole) also be arranged on the described locating piece 2.Described position-limited trough 4 has two and be arranged at the both sides of said location cancave cambered surface 3 (or holes) respectively, and described two position-limited troughs 4 are used for two adjacent rudderposts of aircraft 19 and coincide and embed assembling.
Described supporting seat 8 is a C shape supporting seat, and described measuring section 9 has three and be distributed on the described C shape supporting seat 8.The outer peripheral face of said supporting seat 8 is provided with and is used for its hard-wired supporting seat mounting plane 12, is provided with in the corresponding position of said supporting seat mounting plane 12 on the inner peripheral surface of said supporting seat 8 to be used for detent mechanism 1 hard-wired detent mechanism mounting plane 21.Described detent mechanism 1 is arranged on the described detent mechanism mounting plane 21 through screw; Described proving installation also comprises the positioning seat 5 that is used for locating piece 2 installations; The middle part of described locating piece 2 is rotated and is assemblied on the described positioning seat 5; Concretely; Spacing parallel arranging is provided with two engaging lugs 7 on the described positioning seat 5, and described locating piece 2 rotates and is assemblied between said two engaging lugs 7.Described location cancave cambered surface 3 is arranged at an end of said locating piece, and said locating piece 2 is away from being provided with locating piece bolt, nut locking mechanism 6 between end of locating cancave cambered surface and the described positioning seat 5.Described each measuring section 9 is equipped with coder 13, and during use, the deferent segment of said angle output shaft 11 cooperates with corresponding encoder 13 and the anglec of rotation of corresponding rudderpost 19 is exported in real time.
During use; Aircraft 20 is positioned in the location cancave cambered surface 3 on the described detent mechanism 1; 19 spacing cooperations of rudderpost on two position-limited troughs 4 of detent mechanism 1 and the aircraft 20; The rudderpost 19 of aircraft 20 is provided with the angle output shaft of corresponding measuring section 9 coaxial 11; Upper and lower clamping plate with three catch gears 10 clamp the cooresponding adjusting rudder wing 18 then; Clamp the back and locating piece 2 was fallen, respectively the anglec of rotation of three groups of rudderposts 19 is tested then through adjusting locating piece bolt, nut locking mechanism 6.Because rudderpost 19 rotates with the cooresponding adjusting rudder wing 18 respectively synchronously; And go up, clamping plate clamp with the cooresponding adjusting rudder wing 18 and axis of sideslip 16 and only revolve; So axis of sideslip 16 promptly is the anglec of rotation of cooresponding rudderpost 19 with respect to the swing angle degree of angle output shaft 11, the concrete anglec of rotation is through each measuring section 9 corresponding coder 13 real-time being transferred in the corresponding display equipment that are provided with.After detecting completion upper and lower clamping plate are removed, taken away and survey aircraft 20, get into next testing process.
The present invention can lock the adjusting rudder wing 18 of multiple different-thickness through the upper and lower clamping plate of catch gear; Guaranteed simultaneously through clamping plate bolt, nut locking mechanism 17 that upper and lower clamping plate are connected with the corresponding adjusting rudder wing 18 and axis of sideslip 16 respectively and only revolved, 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 detects completion, upper and lower clamping plate be moved along the sideskid guiding, make things convenient for the taking-up of aircraft 20 through adjustable clamp crab bolt, nut locking mechanism 17; Through catch gear 10 of the present invention, can under the situation that the adjusting rudder wing 18 is not dismantled, be rotated the angle parameter test to rudderpost 19, reduced working strength of workers, improved production efficiency.
In other embodiments of the invention, described transmission device can also be and the leading screw of said upper and lower clamping plate screw thread fit that the axis of sideslip 16 of this moment also is a screw thread fit with the matching relationship of said angle output shaft 11; Described measuring section 9 can be one or two also; Described upper and lower clamping plate can also have two, three or multi-disc respectively; Described location cancave cambered surface 3 also can separately be arranged on two pedestals with position-limited trough 4.
Claims (5)
1. the catch gear in the angle of rudder reflection proving installation; It is characterized in that: described catch gear comprises the angle output shaft that is used for only revolving with the clamping of the corresponding adjusting rudder wing at least one pair of clamp body of cooperating and rotation axis and the coaxial setting of rotation axis of corresponding rudderpost, is provided with the transmission device that is used for the anglec of rotation of corresponding clamp body is outputed in real time the angle output shaft between described each angle output shaft and the corresponding clamp body.
2. catch gear according to claim 1; It is characterized in that: described transmission device comprises the axis of sideslip that the rotation axis of line of centers and corresponding rudderpost is perpendicular; Thereby described clamp body comprises two to establishing and being used for the corresponding adjusting rudder of the clamping wing and the corresponding adjusting rudder the wing only train wheel bridge and the lower plate of the company of being rotated with; On described; Be provided with between the lower plate and be used to regulate 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 locks; Described angle output shaft fixed connection ends spinning and is assigned on the said axis of sideslip, and described angle output shaft is provided with the mouth that is used to insert the corresponding encoded device and the anglec of rotation that correspondence is regulated the rudder wing is outputed in real time the corresponding encoded device away from an end of said axis of sideslip.
3. catch gear according to claim 2 is characterized in that: the bearing fit place of described upper and lower clamping plate and said axis of sideslip is provided with upper and lower split sleeve respectively, offers in the said upper and lower split sleeve to be used for the through hole that said axis of sideslip wears.
4. catch gear according to claim 2; It is characterized in that: described upper and lower clamping plate are L type clamping plate; Nut in described clamping plate bolt, the nut locking mechanism is a fly nut, and the corresponding position of described upper and lower clamping plate is equipped with and is used for the engaging lug that clamping plate bolt, fly nut assemble.
5. catch gear according to claim 2 is characterized in that: described axis of sideslip is provided with away from an end of angle output shaft and is used for said upper and lower clamping plate along the spacing limiting stopper of moving axially of axis of sideslip.
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 true CN102343984A (en) | 2012-02-08 |
| CN102343984B CN102343984B (en) | 2014-01-01 |
Family
ID=45543128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110191305.1A Active CN102343984B (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102343984B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163626A (en) * | 2018-09-21 | 2019-01-08 | 湖南金翎箭信息技术有限公司 | A kind of zero adjuster and method of the Missile Actuator rudder wing |
| 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 (6)
| 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 |
| US20090019673A1 (en) * | 2007-07-16 | 2009-01-22 | Etablissements Caillau | Clamping Device with a Clamping Collar and a Positioning Piece |
| 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 |
| US20110062282A1 (en) * | 2008-05-05 | 2011-03-17 | Airbus Operations Gmbh | Fault-tolerant actuating system for adjusting flaps of an aircraft, comprising adjustment kinematics with a fixed pivot, and a method for monitoring an actuating system |
| 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 |
-
2011
- 2011-07-08 CN CN201110191305.1A patent/CN102343984B/en active Active
Patent Citations (6)
| 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 |
| US20090019673A1 (en) * | 2007-07-16 | 2009-01-22 | Etablissements Caillau | Clamping Device with a Clamping Collar and a Positioning Piece |
| 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 |
| US20110062282A1 (en) * | 2008-05-05 | 2011-03-17 | Airbus Operations Gmbh | Fault-tolerant actuating system for adjusting flaps of an aircraft, comprising adjustment kinematics with a fixed pivot, and a method for monitoring an actuating system |
| 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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163626A (en) * | 2018-09-21 | 2019-01-08 | 湖南金翎箭信息技术有限公司 | A kind of zero adjuster and method of the Missile Actuator rudder wing |
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102343984B (en) | 2014-01-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN202147842U (en) | Locking mechanism in rudder deflection angle measuring device | |
| CN204214627U (en) | Marine propulsion shafting whirling vibration test unit | |
| CN103921101B (en) | Large-scale heavy duty installation electromagnetical clutch mounting and adjusting frock and method | |
| CN102749193A (en) | Colouring examination method for high-precision central-driving bevel gear | |
| CN102343984A (en) | Locking mechanism in rudder deflection angle testing device | |
| CN110487158A (en) | A kind of shaft coupling centering detection device | |
| CN203464893U (en) | Adjustable gauge stand for coaxiality alignment of large couplings | |
| CN109046984B (en) | Guide vane angle linkage adjusting device | |
| CN108871769B (en) | Fixed involute spline pair fretting wear test device | |
| CN102126032B (en) | Device for precisely boring lug hole of hinge beam | |
| CN202267600U (en) | Rudder deflection angle testing device | |
| CN201455801U (en) | Rotary swinging device of high-precision small spherical grinder | |
| CN203705171U (en) | Gyroplane power test system | |
| CN201926593U (en) | Rotary bending fatigue test machine for aviation conduit component | |
| CN204085752U (en) | A kind of moment of friction aided measurement device | |
| CN103286357A (en) | Device for processing large-size flange surface | |
| CN103144075B (en) | For dismantling the device of the pump cover of automobile electric fuel pump | |
| CN105034422B (en) | A kind of tyre building machine tyre surface transmits ring | |
| CN205110441U (en) | Electrician's circle aluminium pole bar straightener | |
| CN204788219U (en) | Shafting fixing device of spare part tester | |
| CN203756925U (en) | Shaft end location adjusting device and mounting frame for rotation parts on shaft | |
| CN210175202U (en) | Quick location frock of inside casing paper indentation cutter | |
| CN209104487U (en) | A kind of synchronous winding device of screw for rectangular connector installation | |
| CN208042969U (en) | A kind of long shaft coupler concentricity calibration apparatus | |
| CN208860290U (en) | Capstan head roller bearing mounting surface flatness of contributing and mounting hole testing apparatus for verticality |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |