CN202147842U - Locking mechanism in rudder deflection angle measuring device - Google Patents
Locking mechanism in rudder deflection angle measuring device Download PDFInfo
- Publication number
- CN202147842U CN202147842U CN201120240368U CN201120240368U CN202147842U CN 202147842 U CN202147842 U CN 202147842U CN 201120240368 U CN201120240368 U CN 201120240368U CN 201120240368 U CN201120240368 U CN 201120240368U CN 202147842 U CN202147842 U CN 202147842U
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- clamping plate
- axis
- sideslip
- output shaft
- rudder
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Abstract
The utility model relates to a locking mechanism in a rudder deflection angle measuring device, which comprises at least one pair of fixtures and angle output shafts, wherein the at least one pair of fixtures are used for being matched with a corresponding adjusting rudder wing in a clamping and rotation stopping way; the rotating axes of the angle output shafts are coaxial with a rotating axis of a corresponding rudder shaft; and a driving mechanism used for transmitting the rotating angle of the corresponding fixture to the angle output shaft in real time is arranged between each angle output shaft and the corresponding fixture. The utility model provides the locking mechanism in the rudder deflection angle measuring device, which can directly measure the parameters of the rotating angle of the rudder shaft without dismounting the adjusting rudder wing of an aircraft.
Description
Technical field
The utility model relates to the angle of rudder reflection proving installation that is used for aircraft rudder angle deviator, relates 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.
The utility model content
The purpose of the utility model is to provide a kind of and is 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, the technical scheme of the utility model is:
Catch gear in the 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; Be provided with between the described upper and lower clamping plate and be used to regulate its clamping plate bolt, nut locking mechanism in gap between the two; Described upper and lower clamping plate slidable fit also can be locked through described clamping plate bolt, nut locking mechanism on described axis of sideslip; 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.
The beneficial effect of the utility model 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; Because the adjusting rudder wing and corresponding rudderpost are rotations synchronously,, thereby reached the purpose that the rudderpost anglec of rotation is tested again so described angle output shaft has been exported the anglec of rotation of corresponding rudderpost in real time.The utility model 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 utility model 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 the 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.The bearing fit place of described upper and lower clamping plate and said axis of sideslip 16 is provided with train wheel bridge sleeve 22 and lower plate sleeve 23 respectively; Offer in the said upper and lower split sleeve to be provided with and be used for the through hole that said axis of sideslip 16 wears; After upper and lower clamping plate are locked through clamping plate bolt, 17 pairs of corresponding adjusting rudder wings 18 of nut locking mechanism; Upper and lower sleeve also produces predetermincd tension and locking through clamping plate bolt, 17 pairs of axiss of sideslip of nut locking mechanism 16 simultaneously; This moment, upper and lower sleeve just was connected with said axis of sideslip 16; Thereby the anglec of rotation that realizes upper and lower clamping 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 catch gear 10 is arranged at the angle of rudder reflection proving installation that is used for rudderpost 19 anglec of rotation parameter testings; Described angle of rudder reflection proving installation; Comprise the detent mechanism 1 that is used for aircraft 20 location; Described detent mechanism 1 has and cooperates with aircraft 20 outer peripheral faces to be measured and to the location cancave cambered surface 3 (or hole) of aircraft 20 location; Described detent mechanism 1 comprises locating piece 2; Also be provided with the rudderpost 19 identical position-limited troughs 4 that embed assembling that supply aircraft 20 to be measured on the described locating piece 2; The trough wall surface of said position-limited trough 4 has watt shape face of cylinder that when measuring, is used for the coaxial corresponding setting of the rotation axis of aircraft 20 rudderposts 19 to be measured; Described proving installation also comprises supporting seat 8, and described supporting seat 8 is provided with at least one and is used for measuring section 9 that rudderpost 19 anglecs of rotation are tested, and described each measuring section 9 is equipped with and is used for the corresponding catch gear 10 that the rudder wing 18 is locked of regulating; Described catch gear 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 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, the corresponding setting of axis coaxle on the axis of said angle output shaft 11 and watt shape face of cylinder of said position-limited trough 4, described location cancave cambered surface 3 (or hole) also is 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 exports the anglec of rotation of corresponding rudderpost 19 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 through adjusting locating piece bolt, nut locking mechanism 6 locating piece 2 are fallen, and respectively the anglec of rotation of three groups of rudderposts 19 are tested then.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 utility model can be locked 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 the catch gear 10 of the utility model, 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 embodiment of the utility model, 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; Be provided with between the described upper and lower clamping plate and be used to regulate its clamping plate bolt, nut locking mechanism in gap between the two; Described upper and lower clamping plate slidable fit also can be locked through described clamping plate bolt, nut locking mechanism on described axis of sideslip; 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 |
|---|---|---|---|
| CN201120240368U CN202147842U (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120240368U CN202147842U (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202147842U true CN202147842U (en) | 2012-02-22 |
Family
ID=45588910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120240368U Expired - Lifetime CN202147842U (en) | 2011-07-08 | 2011-07-08 | Locking mechanism in rudder deflection angle measuring device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202147842U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102343984A (en) * | 2011-07-08 | 2012-02-08 | 凯迈（洛阳）测控有限公司 | Locking mechanism in rudder deflection angle testing device |
| CN104315057A (en) * | 2014-10-08 | 2015-01-28 | 兰州飞行控制有限责任公司 | Rotating shaft circumferential limiting mechanism |
| CN107651215A (en) * | 2017-10-19 | 2018-02-02 | 北京电子工程总体研究所 | A kind of inclined indicator alignment error compensation method of rudder |
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
-
2011
- 2011-07-08 CN CN201120240368U patent/CN202147842U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102343984A (en) * | 2011-07-08 | 2012-02-08 | 凯迈（洛阳）测控有限公司 | Locking mechanism in rudder deflection angle testing device |
| CN102343984B (en) * | 2011-07-08 | 2014-01-01 | 凯迈（洛阳）测控有限公司 | Locking mechanism in rudder deflection angle testing device |
| CN104315057A (en) * | 2014-10-08 | 2015-01-28 | 兰州飞行控制有限责任公司 | Rotating shaft circumferential limiting mechanism |
| CN107651215A (en) * | 2017-10-19 | 2018-02-02 | 北京电子工程总体研究所 | A kind of inclined indicator alignment error compensation method of rudder |
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
| CN116986015B (en) * | 2023-09-28 | 2023-12-12 | 航天江南集团有限公司 | Steering engine detection device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20120222 Effective date of abandoning: 20140101 |
|
| RGAV | Abandon patent right to avoid regrant |