CN204788330U - Rudder area sensor mark school anchor clamps - Google Patents
Rudder area sensor mark school anchor clamps Download PDFInfo
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- CN204788330U CN204788330U CN201520435255.0U CN201520435255U CN204788330U CN 204788330 U CN204788330 U CN 204788330U CN 201520435255 U CN201520435255 U CN 201520435255U CN 204788330 U CN204788330 U CN 204788330U
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- rudder face
- calibration
- rudder
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Abstract
The utility model discloses a rudder area sensor mark school anchor clamps, including the rudder face, sensor cartridge unit and rudder face press from both sides the unit. The sensor cartridge unit is including marking school sensor, sensor cartridge and adaptor, and mark school sensor sets firmly in sensor cartridge's inside, and the adaptor passes through the screw connection to be fixed on sensor cartridge's lateral wall, sets up threaded hole on the adaptor, the rudder face presss from both sides the unit personally experiences sth. Part of the body, compresses tightly knob, bulb stabilizer blade and switch knob including switching axle, anchor clamps, and the rudder face presss from both sides the clamping that the unit is used for aileron, wing flap or rudder. The utility model discloses can make things convenient for, swift clamping on the rudder face, and can realize nimble adjustment, through the actual pivoted angle displacement of mark school sensor measurements rudder face, fly to join rudder face angle displacement channel data with the aircraft and compare, the result that compares is used for marking the school aircraft and flies to join rudder face angle displacement passageway, has solved the convenience, swift has marked the technological problem in school to flying to join rudder face angle displacement passageway.
Description
Technical field
The utility model relates to a kind of sensor calibration fixture.
Background technology
Flight Data Record System for Aircraft (abbreviation FDR system) is the important equipment on aircraft, the confidence level of the manipulation such as the yoke recorded in FDR system, aileron, wing flap, yaw rudder displacement parameter and accuracy directly have influence on the application of flying quality, play an important role to the diagnosis and forecasting etc. of aircraft accident investigation, engineering maintenance guarantee, airplane fault.Therefore, need to carry out periodic calibration to FDR system data acquisition channel.
In the past, people generally used mechanical protractor and ruler to measure to yoke, rudder face angular displacement, rudder etc. the collection realizing flight data.Along with the development of aeronautical technology, in aircraft, FDR system manipulation displacement passage has all installed displacement transducer additional, and measuring accuracy is higher than mechanical protractor and ruler.In order to ensure the confidence level that sensor is recorded, with regard to needing, regular calibration is carried out to installed additional sensor.
Summary of the invention
The technical problems to be solved in the utility model is: provide a kind of rudder face sensor calibration fixture, to carry out calibration to rudder face sensor easily and efficiently.
The utility model solves the technical scheme that its technical matters adopts:
A kind of rudder face sensor calibration fixture, comprises rudder face, also comprises sensor box unit and rudder face folder unit; Described sensor box unit comprises calibration sensor, sensor box and adaptor, and calibration sensor is installed in the inside of sensor box, and described adaptor is connected by screw and is fixed on the sidewall of sensor box, and adaptor offers threaded hole; Described rudder face folder unit comprises Coupling Shaft, clamp body, compression knob, bulb leg and switch knob, and described rudder face folder unit is used for the clamping of aileron, wing flap or yaw rudder; Described clamp body is U-shaped structure, and its upper end has the first threaded hole, and middle part offers through hole and the second threaded hole; Described compression knob is provided with screw thread and carries out threaded engagement with described first threaded hole and is connected, and described compression knob carries out ball pivot by bulb and bulb leg and is connected, and the clamping of the bottom formation clamping rudder face of described bulb leg and described clamp body is right; One end of described Coupling Shaft is provided with screw thread and is formed with the threaded hole on adaptor and is threaded, and to be fixed in Coupling Shaft by sensor box unit, the other end of described Coupling Shaft coordinates with described through hole; Described switch knob is provided with screw thread and also and between the second threaded hole forms threaded engagement, sensor box unit can be locked by screwing in switch knob, by the angle of inclination of adjustable sensor box unit after back-out switch knob.
As improvement of the present utility model, described calibration sensor refers to three axle inertial sensors; Calibration sensor is connected with connector, for connection data process computer.
As further improvement of the utility model, in order to better fix and dismounting calibration sensor, described sensor box comprises sensor cartridge, sensor lid, and described calibration sensor is fixed in sensor cartridge inner bottom surface; Sensor lid forms removable being fixedly connected with sensor cartridge by screw.
Further improve as of the present utility model, in order to ensure the precision of sensor measurement, described sensor cartridge inner bottom surface has certain flatness, and is provided with mounting hole, and the mode for being connected by screw fixes calibration sensor.
Improving further again as of the present utility model, being conducive to clamping rudder face and in order to reduce the damage to aircraft surfaces in clamping process, described bulb leg is provided with rubber to increase friction.
Improve further as of the present utility model, better lock Coupling Shaft to be beneficial to switch knob, described Coupling Shaft is provided with annular groove again.
Improve further more again as of the present utility model, in order to avoid electromagnetic interference (EMI) is on the impact of sensor, the material of described sensor cartridge and sensor lid adopts aluminium alloy.
Also improve further as of the present utility model, in order to the wear-resisting of movement parts and life-span are considered, the material of described Coupling Shaft and switch knob adopts brass again.
Compared with prior art, the utility model has following features: the utility model can easily and efficiently clamping on rudder face, and can realize adjusting flexibly, by the angular displacement of the actual rotation of calibration sensor measurement rudder face, compared with flying to join rudder face angular displacement channel data with aircraft, result is relatively used for calibration aircraft and flies ginseng rudder face angular displacement passage, solves and joins to flying the technical barrier that rudder face angular displacement passage carries out calibration easily and efficiently.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of three-dimensional structure schematic diagram of rudder face sensor calibration fixture;
Fig. 2 is a kind of three-dimensional structure exploded perspective view of rudder face sensor calibration fixture;
Fig. 3 is the three-dimensional structure schematic diagram of clamp body;
Fig. 4 is the exploded perspective view of sensor box unit;
Fig. 5 is the three-dimensional structure schematic diagram after adjustment sensor box unit horizontal;
Embodiment
For making the object of the utility model embodiment, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, technical scheme in the utility model embodiment is clearly and completely described, obviously, described embodiment is the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
As illustrated in fig. 1 and 2, a kind of rudder face sensor calibration fixture, comprises rudder face 3, also comprises sensor box unit 1 and rudder face folder unit 2; Sensor box unit 1 comprises calibration sensor 11, sensor box 12 and adaptor 13, calibration sensor 11 is installed in the inside of sensor box 12, adaptor 13 be connected by screw be fixed on sensor box 12 sidewall on, adaptor 13 offers threaded hole 131; Rudder face folder unit 2 comprises Coupling Shaft 21, clamp body 22, compresses knob 23, bulb leg 24 and switch knob 25, and rudder face folder unit 2 is for the clamping of aileron, wing flap, yaw rudder etc.;
As shown in Figure 3, clamp body 22 is U-shaped structures, and its upper end has the first threaded hole 223, and middle part offers through hole 221 and the second threaded hole 222;
As illustrated in fig. 1 and 2, compression knob 23 is provided with screw thread and carries out threaded engagement with the first threaded hole 223 and is connected, compression knob 23 carries out ball pivot by bulb 231 and bulb leg 24 and is connected, and the clamping of the bottom formation clamping rudder face 3 of bulb leg 24 and clamp body 22 is right; Owing to adopting ball pivot thus can to vert certain angle, thus be well adapted to the surface that rudder face 3 tilts, as described in figures 1 and 5.One end of Coupling Shaft 21 is provided with screw thread and is formed with the threaded hole 131 on adaptor 13 and is threaded, and to be fixed in Coupling Shaft 21 by sensor box unit 1, the other end of Coupling Shaft 21 coordinates with through hole 221; Switch knob 25 is provided with screw thread and also and between the second threaded hole 222 forms threaded engagement, sensor box unit 1 can be locked by screwing in switch knob 25, by screwing out the angle of inclination of adjustable sensor box unit 1 after switch knob 25, as shown in Figure 5 be three-dimensional structure schematic diagram after adjustment sensor box unit horizontal.
The utility model can easily and efficiently clamping on rudder face, and can realize adjusting flexibly, by the angular displacement of the actual rotation of calibration sensor measurement rudder face, compared with flying to join rudder face angular displacement channel data with aircraft, result is relatively used for calibration aircraft and flies ginseng rudder face angular displacement passage, solves and joins to flying the technical barrier that rudder face angular displacement passage carries out calibration easily and efficiently.As improvement of the present utility model, calibration sensor refers to three axle inertial sensors, and this sensor electromagnetism interference, good stability, precision is high.
As further improvement of the utility model, in order to better fix and dismounting calibration sensor 11, as shown in Figure 4, sensor box 12 comprises sensor cartridge 121, sensor lid 122, and calibration sensor 11 is fixed in the inner bottom surface of sensor cartridge 121; Sensor lid 122 forms removable being fixedly connected with sensor cartridge 121 by screw.
Calibration sensor 11 is high precision instrument, and in order to ensure accuracy and the confidence level of calibration, calibration sensor 11 on even curface, calibration sensor 11 should be connected with connector 111, for connection data process computer when mounted.Further improve as of the present utility model, in order to ensure the precision of sensor measurement, sensor cartridge 121 inner bottom surface has certain flatness (machining precision is more than 6 grades), and be provided with mounting hole, mode for being connected by screw fixes calibration sensor 11, and the connector 111 of calibration sensor 11 is fixed on the rear wall of sensor cartridge 121.
As illustrated in fig. 1 and 2, improving further again as of the present utility model, being conducive to clamping rudder face and in order to reduce the damage to aircraft surfaces in clamping process, bulb leg 24 is provided with rubber 241 to increase friction.Improve further as of the present utility model, in order to be beneficial to switch knob 25 better locking Coupling Shaft 21, Coupling Shaft 21 is provided with annular groove again.Improve further more again as of the present utility model, in order to avoid electromagnetic interference (EMI) is on the impact of sensor, the material of sensor cartridge 121 and sensor lid 122 adopts aluminium alloy.Also improve further as of the present utility model, in order to the wear-resisting of movement parts and life-span are considered, the material of Coupling Shaft 21 and switch knob 25 adopts brass again.
Last it is noted that above embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (10)
1. a rudder face sensor calibration fixture, comprises rudder face (3), it is characterized in that: also comprise sensor box unit (1) and rudder face folder unit (2);
Described sensor box unit (1) comprises calibration sensor (11), sensor box (12) and adaptor (13), calibration sensor (11) is installed in the inside of sensor box (12), described adaptor (13) be connected by screw be fixed on sensor box (12) sidewall on, adaptor (13) offers threaded hole (131);
Described rudder face folder unit (2) comprises Coupling Shaft (21), clamp body (22), compresses knob (23), bulb leg (24) and switch knob (25), and described rudder face folder unit (2) is for the clamping of aileron, wing flap or yaw rudder;
Described clamp body (22) is U-shaped structure, and its upper end has the first threaded hole (223), and middle part offers through hole (221) and the second threaded hole (222); Described compression knob (23) is provided with screw thread and carries out threaded engagement with described first threaded hole (223) and is connected, described compression knob (23) is carried out ball pivot by bulb (231) and bulb leg (24) and is connected, and the clamping of bottom formation clamping rudder face (3) of described bulb leg (24) and described clamp body (22) is right; One end of described Coupling Shaft (21) is provided with screw thread and is formed with the threaded hole (131) on adaptor (13) and is threaded, to be fixed in Coupling Shaft (21) by sensor box unit (1), the other end of described Coupling Shaft (21) coordinates with described through hole (221);
Described switch knob (25) be provided with screw thread and and form threaded engagement between the second threaded hole (222), sensor box unit (1) can be locked by screwing in switch knob (25), by screwing out the angle of inclination of switch knob (25) adjustable sensor box unit (1) afterwards.
2. a kind of rudder face sensor calibration fixture as claimed in claim 1, is characterized in that: wherein said calibration sensor (11) refers to three axle inertial sensors; Calibration sensor (11) is connected with connector (111), for connection data process computer.
3. a kind of rudder face sensor calibration fixture as claimed in claim 1 or 2, it is characterized in that: wherein said sensor box (12) comprises sensor cartridge (121), sensor lid (122), described calibration sensor (11) is connected by screw and is fixed in sensor cartridge (121) inner bottom surface; Sensor lid (122) forms removable being fixedly connected with sensor cartridge (121) by screw.
4. a kind of rudder face sensor calibration fixture as claimed in claim 3, it is characterized in that: wherein said sensor cartridge (121) inner bottom surface has certain flatness, and being provided with mounting hole, the mode for being connected by screw fixes calibration sensor (11).
5. a kind of rudder face sensor calibration fixture as claimed in claim 1 or 2, is characterized in that: wherein said bulb leg (24) is provided with rubber (241).
6. a kind of rudder face sensor calibration fixture as claimed in claim 3, is characterized in that: wherein said bulb leg (24) is provided with rubber (241).
7. a kind of rudder face sensor calibration fixture as claimed in claim 4, is characterized in that: wherein said bulb leg (24) is provided with rubber (241).
8. a kind of rudder face sensor calibration fixture as claimed in claim 5, is characterized in that: wherein said Coupling Shaft (21) is provided with annular groove.
9. a kind of rudder face sensor calibration fixture as described in as arbitrary in claim 6 or 7 or 8, is characterized in that: the material of wherein said sensor cartridge (121) and sensor lid (122) adopts aluminium alloy.
10. a kind of rudder face sensor calibration fixture as claimed in claim 9, is characterized in that: the material of wherein said Coupling Shaft (21) and switch knob (25) adopts brass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520435255.0U CN204788330U (en) | 2015-06-23 | 2015-06-23 | Rudder area sensor mark school anchor clamps |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520435255.0U CN204788330U (en) | 2015-06-23 | 2015-06-23 | Rudder area sensor mark school anchor clamps |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204788330U true CN204788330U (en) | 2015-11-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520435255.0U Expired - Fee Related CN204788330U (en) | 2015-06-23 | 2015-06-23 | Rudder area sensor mark school anchor clamps |
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| CN (1) | CN204788330U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017395A (en) * | 2016-06-28 | 2016-10-12 | 国营芜湖机械厂 | Aircraft horizontal rudder surface angle measuring device |
| CN106767647A (en) * | 2015-11-24 | 2017-05-31 | 中航贵州飞机有限责任公司 | A kind of deflection angle of airplane control surface degree measurement apparatus |
| CN107554815A (en) * | 2016-06-23 | 2018-01-09 | 陕西飞机工业（集团）有限公司 | A kind of accurate measurement aircraft aileron tab aerofoil jump device |
| CN107655438A (en) * | 2017-09-13 | 2018-02-02 | 北京安达维尔测控技术有限公司 | A kind of measurement apparatus and its measuring method at aircraft rudder surface angle |
| CN110480547A (en) * | 2019-09-06 | 2019-11-22 | 北京精密机电控制设备研究所 | A kind of method and system of rudder face clamping tooling and its determining electromagnetic lock lock function |
| CN112461184A (en) * | 2020-11-10 | 2021-03-09 | 中航通飞华南飞机工业有限公司 | Water rudder deflection angle measuring device |
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
-
2015
- 2015-06-23 CN CN201520435255.0U patent/CN204788330U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106767647A (en) * | 2015-11-24 | 2017-05-31 | 中航贵州飞机有限责任公司 | A kind of deflection angle of airplane control surface degree measurement apparatus |
| CN107554815A (en) * | 2016-06-23 | 2018-01-09 | 陕西飞机工业（集团）有限公司 | A kind of accurate measurement aircraft aileron tab aerofoil jump device |
| CN106017395A (en) * | 2016-06-28 | 2016-10-12 | 国营芜湖机械厂 | Aircraft horizontal rudder surface angle measuring device |
| CN107655438A (en) * | 2017-09-13 | 2018-02-02 | 北京安达维尔测控技术有限公司 | A kind of measurement apparatus and its measuring method at aircraft rudder surface angle |
| CN107655438B (en) * | 2017-09-13 | 2020-06-30 | 北京安达维尔测控技术有限公司 | Measuring device and measuring method for plane angle of airplane rudder |
| CN110480547A (en) * | 2019-09-06 | 2019-11-22 | 北京精密机电控制设备研究所 | A kind of method and system of rudder face clamping tooling and its determining electromagnetic lock lock function |
| CN110480547B (en) * | 2019-09-06 | 2021-05-04 | 北京精密机电控制设备研究所 | Control surface clamping tool and method and system for determining locking function of electromagnetic lock |
| CN112461184A (en) * | 2020-11-10 | 2021-03-09 | 中航通飞华南飞机工业有限公司 | Water rudder deflection angle measuring device |
| 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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151118 Termination date: 20180623 |