CN105783820A - Helicopter level displacement sensor zero adjustment device and zero adjustment method - Google Patents
Helicopter level displacement sensor zero adjustment device and zero adjustment method Download PDFInfo
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- CN105783820A CN105783820A CN201610156568.1A CN201610156568A CN105783820A CN 105783820 A CN105783820 A CN 105783820A CN 201610156568 A CN201610156568 A CN 201610156568A CN 105783820 A CN105783820 A CN 105783820A
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- displacement transducer
- helicopter
- bar displacement
- bar
- rod assembly
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/02—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring length, width, or thickness
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- General Physics & Mathematics (AREA)
- Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
Abstract
The invention relates to the design of a helicopter fly-by-wire flight control system and especially relates to a helicopter level displacement sensor zero adjustment device and a zero adjustment method. The helicopter level displacement sensor zero adjustment device is used for carrying out zero adjustment on a level displacement sensor in the helicopter fly-by-wire flight control system, and comprises a length-adjustable pull level assembly, wherein one end of the pull level assembly is connected with an operating lever system of a helicopter, and the other end is connected with the level displacement sensor and used for carrying out zero adjustment on the level displacement sensor. The helicopter level displacement sensor zero adjustment method is used for realizing absolute zero adjustment of the level displacement sensor for measuring control input of a driver; and the method is convenient to operate and higher in zero adjustment precision.
Description
Technical field
The present invention relates to the design of helicopter fly-by-wire flight control system, particularly to a kind of helicopter bar displacement transducer balancing controls and adjusting zero method.
Background technology
Tradition flight control system adopts mechanical handling to add the form that control increasing is steady, and pilot inputs is directly acted on to propeller pitch angle by the mechanical passage that leverage connects, and bar displacement transducer collection is handled input signal and acted the effect controlling enhancing through demand model.Owing to bar displacement transducer signal is for controlling the superposition of output, only adopt the relative value's signal handling input during use, it is not necessary to carry out absolute zero position adjustment.
Fly-by-wire flight control system eliminates the mechanical linkage of stick rear end, and the manipulation input of driver only relies on the measurement of bar displacement transducer, and flight control computer gathers bar sensor signal, calculates voting rear drive steering wheel again through control law and produces corresponding propeller pitch angle.Corresponding with traditional mechanical leverage, sensor acquisition zero handles input corresponding neutral position propeller pitch angle, gathers opposed polarity and inputs corresponding different size of propeller pitch angle with the manipulation of size.Therefore, for fly-by-wire flight control system, accurately measure manipulation input signal most important.For ensureing that bar displacement transducer Gather and input signal is correctly reliable, it need to be carried out absolute zero position adjustment, and ensure that the error of zero is within scope of design.
Summary of the invention
A kind of helicopter bar displacement transducer balancing controls and adjusting zero method are it is an object of the invention to provide, it is possible to bar displacement transducer is carried out absolute zero position adjustment.
The technical scheme is that
A kind of helicopter bar displacement transducer balancing controls, for the bar displacement transducer in helicopter fly-by-wire flight control system is returned to zero, including:
Length-adjustable rod assembly, one end is connected with the stick leverage of described helicopter, the other end and described bar displacement transducer, for described bar displacement transducer is returned to zero.
Optionally, described rod assembly includes:
Bar body；
Head rod, the one end with the axis identical with described bar body, described head rod one end and described bar body is threaded connection, and the other end of described head rod is connected with the stick leverage of described helicopter by bearing；
Second connecting rod, the other end with the axis identical with described bar body, described second connecting rod one end and described bar body is threaded connection, and the other end of described second connecting rod is connected with described bar displacement transducer by bearing.
Optionally, described rod assembly also include with the use of lock washer and locking nut, be separately positioned on described bar body and described head rod and the junction with described second connecting rod.
Optionally, described helicopter bar displacement transducer balancing controls also include:
Bar displacement transducer zeroing device, is connected with described bar displacement transducer, is used for measuring described rod assembly and is in during predetermined length the output voltage values corresponding to described bar displacement transducer.
Present invention also offers the adjusting zero method of a kind of helicopter bar displacement transducer balancing controls, comprise the steps:
Step one, is connected one end of described rod assembly with the stick leverage of described helicopter, and the other end is connected with described bar displacement transducer；
Step 2, regulates described rod assembly to predetermined length, completes the zeroing to described bar displacement transducer.
Optionally, the adjusting zero method of described helicopter bar displacement transducer balancing controls also includes:
Step 3, when being in predetermined length by the bar displacement transducer zeroing device described rod assembly of measurement, the output voltage values corresponding to described bar displacement transducer, and judge whether described output voltage values is within the scope of scheduled voltage；If within the scope of described scheduled voltage, then complete the zeroing to described bar displacement transducer；Otherwise, step 4 is carried out；
Step 4, returns the length readjusting described rod assembly in step 2, until the output voltage values of described bar displacement transducer is within the scope of described scheduled voltage.
Optionally, in step 2, the predetermined length of described rod assembly refers to that stick leverage is when reference position, to the distance of described bar displacement transducer.
Optionally, in described step 2, it is by regulating the head rod at the axial two ends of described bar body or the second connecting rod regulates the length of described rod assembly.
Invention effect:
The helicopter bar displacement transducer balancing controls of the present invention and adjusting zero method, for the absolute zero position adjustment to the bar displacement transducer measuring pilot control input, the method is easy to operate, zeroing degree of accuracy is high, can ensure that ground service quickly, accurately realizes adjusting work, shorten the adjustment cycle, alleviate operation easier.
Accompanying drawing explanation
Fig. 1 is the structural representation of helicopter displacement transducer balancing controls of the present invention；
Fig. 2 is the structural representation of helicopter displacement transducer balancing controls king-rod displacement transducer of the present invention.
Detailed description of the invention
For making purpose of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has the element of same or like function from start to finish.Described embodiment is a part of embodiment of the present invention, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is illustrative of, it is intended to is used for explaining the present invention, and is not considered as limiting the invention.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " orientation or the position relationship of the instruction such as " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " be based on orientation shown in the drawings or position relationship; be for only for ease of the description present invention and simplifying and describe; rather than instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that limiting the scope of the invention.
Below in conjunction with accompanying drawing 1 to Fig. 2, helicopter bar displacement transducer balancing controls of the present invention and adjusting zero method are described in further details.
The invention provides a kind of helicopter bar displacement transducer balancing controls, for the bar displacement transducer 2 in helicopter fly-by-wire flight control system is returned to zero；Balancing controls include length-adjustable rod assembly, and one end of rod assembly is connected with the stick leverage of helicopter, the other end and bar displacement transducer 2, for bar displacement transducer 2 is returned to zero.
The helicopter displacement transducer balancing controls of the present invention, for the absolute zero position adjustment to the bar displacement transducer measuring pilot control input, easy to operate, zeroing degree of accuracy is high, can ensure that ground service quickly, accurately realizes adjusting work, shorten the adjustment cycle, alleviate operation easier.
In the helicopter displacement transducer balancing controls of the present invention, rod assembly can adopt multiple applicable structure as required；In the present embodiment, rod assembly can include the parts such as bar body 11, head rod the 12, second connecting rod 14, lock washer 15 and locking nut 16.
Bar body 11 is a polished rod, and axial two ends offer female thread respectively in axial direction.
Head rod 12 has the axis identical with bar body 11, and one end (near one end of bar body 11, the right-hand member in Fig. 1) of head rod 12 offers the external screw thread that the female thread with bar body 11 matches；One end (left end in Fig. 1) of this end of head rod 12 (right-hand member in Fig. 1) and bar body 11 is threaded connection, and the other end of head rod 12 is connected with the stick leverage (not shown) of helicopter by bearing 13.
Second connecting rod 14 has the axis identical with bar body 11, and one end (near one end of bar body 11, the left end in Fig. 1) of the second connecting rod 14 offers the external screw thread that the female thread with bar body 11 matches；The other end (right-hand member in Fig. 1) of second this end of connecting rod 14 (left end in Fig. 1) and bar body 11 is threaded connection, and the other end of the second connecting rod 14 is connected with bar displacement transducer 2 by bearing 13.Further, so that the length adjustment more convenient and quicker of rod assembly, can the rotation direction of the female thread at axial for bar body two ends be set on the contrary, after head rod 12 and the second connecting rod 14 installation, only just can be realized the length adjustment of rod assembly by rotating tension bar body 11, it is not necessary to head rod 12 and second other ends of connecting rod 14 are removed.
With the use of lock washer 15 and locking nut 16 be separately positioned on the junction of bar body 11 and head rod 12 and bar body 11 and the second connecting rod 14, during for being elongated to the length of needs when rod assembly, the head rod 12 on rod assembly and the second connecting rod 14 are fixed.
The helicopter displacement transducer balancing controls of the present invention are by screwing in and screwing out its two ends head rod 12 and the second connecting rod 14 simultaneously, it is achieved bar displacement transducer 2 is checking for zero, and range of accommodation is big and is prone to flight crew's operation.
The helicopter displacement transducer balancing controls of the present invention also include bar displacement transducer zeroing device；The multiple applicable zeroing device that bar displacement transducer zeroing device can be currently known, bar displacement transducer zeroing device is connected with bar displacement transducer 2, further, is be connected with the displacement transducer plug 21 on bar displacement transducer 2 by cable；Bar displacement transducer zeroing device is in during predetermined length the output voltage values corresponding to bar displacement transducer 2 for measuring rod assembly, operator can by judging that output voltage values judges that whether bar displacement transducer is at absolute zero position, again through judged result, rod assembly length is carried out feedback regulation so that zeroing accuracy is higher.
The adjusting zero method additionally providing a kind of helicopter bar displacement transducer balancing controls of the present invention, comprises the steps:
Step one, is connected one end of rod assembly with the stick leverage of helicopter, and the other end is connected with bar displacement transducer 2.Certainly, before bar displacement transducer is checking for zero, needs the appointment position being first installed on aircraft by bar displacement transducer 2, then adjustable drawbar assembly is linked between displacement transducer 2 and linkage when band arbor holds and do not lock.
Step 2, adjusting yoke assembly, to predetermined length, completes the zeroing to bar displacement transducer 2.Wherein, the predetermined length of rod assembly refers to stick leverage (do not operate, when head does not input, the theoretical basis value of the rod assembly length of calculating) when reference position, to the distance of the connecting rocker arm of bar displacement transducer 2；On stick leverage, generally it is provided with connecting rocker arm for cylinder lever connecting rod assembly.
The helicopter displacement transducer adjusting zero method of the present invention is easy to operate, and zeroing degree of accuracy is high, can ensure that ground service quickly, accurately realizes adjusting work, shorten the adjustment cycle, alleviate operation easier.
After above-mentioned zeroing (is equivalent to machine zero), rod assembly length ideal can meet bar displacement transducer 2 and be in zero-bit, but due to the existence of mechanical clearance and alignment error on machine, for meeting error of zero requirement, also need to carry out further accurate electronic zero-setting；Therefore, the adjusting zero method of the helicopter bar displacement transducer balancing controls of the present invention also includes:
Step 3, when being in predetermined length by bar displacement transducer zeroing device measurement rod assembly, the output voltage values (being again zero-bit output voltage values) corresponding to bar displacement transducer 2, and judge whether output voltage values is within the scope of scheduled voltage；If within the scope of scheduled voltage, then complete the zeroing to bar displacement transducer 2；Otherwise, step 4 is carried out.Wherein, scheduled voltage scope refers in reference value within next scope, it is possible to carries out the setting value being suitable for as required, is within preferred reference value ± 50mv in the present embodiment.It addition, under the voltage excitation signals effect of bar displacement transducer zeroing device, bar displacement transducer 2 can export the voltage signal of relation proportional to lever displacement and show at zeroing device display window, judges to facilitate.
Step 4, returns the length readjusting rod assembly in step 2, until bar displacement transducer returns to zero, the output voltage values of the bar displacement transducer 2 that device records is within the scope of scheduled voltage.Pull out the connection of bar displacement transducer zeroing device and bar displacement transducer 2 after electronic zero-setting, the lock washer at rod assembly two ends and locking nut are locked, completes bar displacement transducer 2 checking for zero
In step 2, be the head rod 12 by the axial two ends of adjusting yoke body 11 and or the flexible length regulating described rod assembly of the second connecting rod 14；Can only adjust one of them or adjustment two simultaneously is stretched.
A kind of helicopter displacement transducer adjusting zero method of the present invention, is mainly used in the absolute zero position adjustment to the bar displacement transducer 2 measuring pilot control input.Can be used for after machine upper boom displacement transducer 2 is installed for the first time checking for zero and follow-up take a flight test troubleshooting time inspection adjustment.By adjusting the length of the rod assembly being connected between bar displacement transducer 2 connecting rocker arm and stick linear system time checking for zero, it is ensured that bar displacement transducer 2 zero-bit output voltage values is within the range of error of designing requirement.After rod assembly machine zero coarse zero, reading total null voltage value by bar displacement transducer zeroing device and carry out electrically accurately zeroing, now fine-tuning band handle position of bearings guarantee total null voltage is within designing requirement range of error, and zeroing accuracy is high.
The above; being only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, any those familiar with the art is in the technical scope that the invention discloses; the change that can readily occur in or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with described scope of the claims.
Claims (8)
1. helicopter bar displacement transducer balancing controls, for the bar displacement transducer (2) in helicopter fly-by-wire flight control system is returned to zero, it is characterised in that including:
Length-adjustable rod assembly, one end is connected with the stick leverage of described helicopter, the other end and described bar displacement transducer (2), for described bar displacement transducer (2) is returned to zero.
2. helicopter bar displacement transducer balancing controls according to claim 1, it is characterised in that described rod assembly includes:
Bar body (11)；
Head rod (12), there is the axis identical with described bar body (11), one end of described head rod (12) one end and described bar body (11) is threaded connection, and the other end of described head rod (12) is connected with the stick leverage of described helicopter by bearing (13)；
Second connecting rod (14), there is the axis identical with described bar body (11), the other end of described second connecting rod (14) one end and described bar body (11) is threaded connection, and the other end of described second connecting rod (14) is connected with described bar displacement transducer (2) by bearing (13).
3. helicopter bar displacement transducer balancing controls according to claim 2, it is characterized in that, described rod assembly also include with the use of lock washer (15) and locking nut (16), be separately positioned on described bar body (11) and described head rod (12) and the junction with described second connecting rod (14).
4. helicopter bar displacement transducer balancing controls according to claim 1, it is characterised in that also include:
Bar displacement transducer zeroing device, is connected with described bar displacement transducer (2), is used for measuring described rod assembly and is in during predetermined length the output voltage values corresponding to described bar displacement transducer (2).
5. the adjusting zero method of the helicopter bar displacement transducer balancing controls according to any one of claim 1-4, it is characterised in that comprise the steps:
Step one, is connected one end of described rod assembly with the stick leverage of described helicopter, and the other end is connected with described bar displacement transducer (2)；
Step 2, regulates described rod assembly to predetermined length, completes the zeroing to described bar displacement transducer (2).
6. the adjusting zero method of helicopter bar displacement transducer balancing controls according to claim 5, it is characterised in that also include:
Step 3, when being in predetermined length by the bar displacement transducer zeroing device described rod assembly of measurement, the output voltage values corresponding to described bar displacement transducer (2), and judge whether described output voltage values is within the scope of scheduled voltage；If within the scope of described scheduled voltage, then complete the zeroing to described bar displacement transducer (2)；Otherwise, step 4 is carried out；
Step 4, returns the length readjusting described rod assembly in step 2, until the output voltage values of described bar displacement transducer (2) is within the scope of described scheduled voltage.
7. the adjusting zero method of helicopter bar displacement transducer balancing controls according to claim 6, it is characterized in that, in step 2, the predetermined length of described rod assembly refers to that stick leverage is when reference position, to the distance of described bar displacement transducer (2).
8. the adjusting zero method of helicopter bar displacement transducer balancing controls according to claim 6, it is characterized in that, in described step 2, be by regulate the head rod (12) at described bar body (11) axially two ends and or the second connecting rod (14) regulate the length of described rod assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610156568.1A CN105783820A (en) | 2016-03-18 | 2016-03-18 | Helicopter level displacement sensor zero adjustment device and zero adjustment method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610156568.1A CN105783820A (en) | 2016-03-18 | 2016-03-18 | Helicopter level displacement sensor zero adjustment device and zero adjustment method |
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| CN105783820A true CN105783820A (en) | 2016-07-20 |
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| CN201610156568.1A Pending CN105783820A (en) | 2016-03-18 | 2016-03-18 | Helicopter level displacement sensor zero adjustment device and zero adjustment method |
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Cited By (6)
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| CN106547234A (en) * | 2016-09-30 | 2017-03-29 | 中国科学院长春光学精密机械与物理研究所 | A kind of aircraft electric steering engine regulator control system and regulation and control method |
| CN109211165A (en) * | 2018-08-02 | 2019-01-15 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of pressurized strut displacement sensor embedded locking structure |
| CN109307471A (en) * | 2018-11-13 | 2019-02-05 | 福建福清核电有限公司 | A kind of nuclear power station main feed pump axial displacement sensor zero point scaling method |
| CN109870078A (en) * | 2017-12-05 | 2019-06-11 | 北京自动化控制设备研究所 | A kind of servo-operated mechanism mechanical zero and electrical null position registration method of adjustment |
| CN114455094A (en) * | 2020-10-30 | 2022-05-10 | 北京机械设备研究所 | Miniature precision zero setting device and zero setting method based on T-shaped guide rail |
| CN114455094B (en) * | 2020-10-30 | 2024-06-11 | 北京机械设备研究所 | Miniature precise zeroing device and zeroing method based on T-shaped guide rail |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109211165A (en) * | 2018-08-02 | 2019-01-15 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of pressurized strut displacement sensor embedded locking structure |
| CN109211165B (en) * | 2018-08-02 | 2021-03-26 | 中国航空工业集团公司西安飞行自动控制研究所 | Built-in locking structure of actuator cylinder displacement sensor |
| CN109307471A (en) * | 2018-11-13 | 2019-02-05 | 福建福清核电有限公司 | A kind of nuclear power station main feed pump axial displacement sensor zero point scaling method |
| CN109307471B (en) * | 2018-11-13 | 2020-08-21 | 福建福清核电有限公司 | Zero calibration method for displacement sensor of main water supply pump shaft of nuclear power station |
| CN114455094A (en) * | 2020-10-30 | 2022-05-10 | 北京机械设备研究所 | Miniature precision zero setting device and zero setting method based on T-shaped guide rail |
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Application publication date: 20160720 |