CN204924516U - Integrated two -way measuring force device of aircraft - Google Patents
Integrated two -way measuring force device of aircraft Download PDFInfo
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- CN204924516U CN204924516U CN201520271673.0U CN201520271673U CN204924516U CN 204924516 U CN204924516 U CN 204924516U CN 201520271673 U CN201520271673 U CN 201520271673U CN 204924516 U CN204924516 U CN 204924516U
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Abstract
The utility model relates to an integrated two -way measuring force device of aircraft, specifically speaking is about measuring the measuring force device of driver when controing control stick (dish) awing, large -scale aircraft of mainly used and civilian airplane simply directly. An integrated two -way measuring force device of aircraft, the utility model is characterized in that, so sensor body design form is more special, sensor body structure appearance is as illustrated in figure. 4, adopt 2 Z character wheel spokes and 2 one character wheel spokes with this body strain of sensor roof beam, the foil gage is posted to both sides on 2 vertical roof beams of Z character wheel spoke, be used for measuring the horizontal power of manipulation, 2 two foil gages are posted to the both sides of an individual character wheel spoke, be used for measuring fore -and -aft control power, this sensor body one end and profile of tooth hub connection, other end plane is passed through the bolt and is connected with the control wheel.
Description
Technical field
The invention relates to a kind of aircraft integrated bi-directional device for measuring force, specifically, be about simple directly measure driver awing operate the joystick (dish) time device for measuring force, be mainly used in large aircraft and civil aircraft.
Background technology
Along with developing rapidly of observing and controlling robotization, electricity electric detecting technology is widely used and obtains develop rapidly, and widely applies in human being's production and practical experience of life.By to internal transportation machine measuring technique application analysis, steering force during direct measurement pilot control jociey stick (dish) is difficult to realize, and was all steering force during indirect utilization measurement mechanism measurement pilot control jociey stick (dish) in the past.This kind of measuring method has the following disadvantages:
1, measurement data is not direct, by the steering force indirectly converted time pilot control jociey stick (dish), causes measuring accuracy low;
2, the number of sensors needed is many, increases aircraft manufacturing cost and weight.
Traditional pilot control jociey stick (dish) force measuring device composition as shown in Figure 1.Primarily of sensor body, housing, signal conditioner, the compositions such as electric connector.This sensor can only be arranged in the pull bar of linkage, measurement form is more single, when pilot control jociey stick (dish), pilot control power passes to the sensor body on pull bar by transmission rocking arm, Sensor Elastic Element produces strain stress, then is transformed into resistance variations Δ R by strainometer, and Δ R is transformed into change in voltage Δ U by electric bridge, amplify through signal conditioner again and export, carry out record by aerial seeding vegetation.
For realizing power when directly measuring pilot control jociey stick (dish), improving measuring accuracy, reducing aircraft manufacturing cost, alleviating aircraft weight, the brand-new thinking of special employing devises the two-way device for measuring force of the inner integrated form of aircraft control stick.
Summary of the invention
(1) goal of the invention: the present invention is low in order to overcome traditional force measuring device precision, measurement form is single, aircraft manufacturing cost is high, aircraft weight heavily waits not enough, can the steering force in the horizontal course of survey aircraft, steering force on course can be indulged by survey aircraft again, the two-way device for measuring force of the inner integrated form of special invention jociey stick, the two-way device for measuring force of the inner integrated form of this type aircraft jociey stick, can directly apply to large, during medium duty delivery flight control system jociey stick (dish) power is measured or as large, medium duty delivery aircraft mechanical manoeuvring system jociey stick (dish) power measures beneficial reference.
(2) technical scheme:
In order to solve the problems of the technologies described above, the present invention is achieved by the following technical solutions:
A kind of aircraft integrated bi-directional device for measuring force, so sensor body design form is more special, sensor body construction profile as shown in Figure 4, sensor body strain beam is adopted 2 Z-shaped spokes and 2 character wheel spokes, foil gauge is posted in the both sides on 2 Z-shaped spoke vertical beams, for measuring lateral control power, two foil gauges are posted in the both sides of 2 character wheel spokes, for measuring fore-and-aft control power, this sensor body one end is connected with toothed shank, and other end plane is connected with control wheel by bolt.
(3) beneficial effect
Compared with prior art, the invention has the beneficial effects as follows:
1. achieve and directly measure pilot control jociey stick (dish) power, the transmission link in the middle of reducing, improve the measuring precision;
2. when realizing identical measurement function, reduce the installation quantity of sensor, reduce aircraft gross weight amount, lower production cost, reduce labor strength.
The integrated replacement tradition single-measurement mode of the two-way device for measuring force of the inner integrated form of this aircraft control stick, weight, cost, precision are all better than traditional approach.
Accompanying drawing explanation
Fig. 1 is: integrated form two-way device for measuring force installation site figure;
Fig. 2 is: the two-way device for measuring force composition diagram of integrated form;
Fig. 3 is: integrated form two-way device for measuring force sensor body front view;
Fig. 4 is: integrated form two-way device for measuring force sensor body Z-shaped structure diagram.
Embodiment
This aircraft control stick (dish) force measuring device fills use on the serial multi-aircraft of fortune 8, and through the accumulative use reaching thousands of pilot time.In order to solve the problems of the technologies described above, the present invention is achieved by the following technical solutions:
The design of installation site and installation form.Novel jociey stick (dish) force measuring device installation form is shown in Fig. 1.This force measuring device meets longitudinally simultaneously, lateral control power measures requirement, so select installation site more special, the fore-and-aft control power of driver can be experienced in this position, the lateral control power of driver can be experienced again, so select to be arranged on the junction that jociey stick (dish) force snesor is arranged on jociey stick and control wheel, this body profile of jociey stick (dish) force snesor is equal to certain part in system, for replacing this part of system, ensureing the requirement achieving the measurement of binary channels steering force under the prerequisite that weight does not increase.The power that driver rotates control wheel both experienced by this part, can experience again the power that driver moves jociey stick, and when driver rotates control wheel or moves jociey stick, this part is subject to the effect of two kinds of power simultaneously, realizes the measurement of longitudinal direction, lateral control power simultaneously.The two-way device for measuring force composition of the inner integrated form of aircraft control stick is shown in Fig. 2.The two-way device for measuring force of the inner integrated form of this aircraft control stick meets longitudinally simultaneously, lateral control power measures requirement.
A kind of aircraft integrated bi-directional device for measuring force, so sensor body design form is more special, sensor body construction profile as shown in Figure 4, sensor body strain beam is adopted 2 Z-shaped spokes and 2 character wheel spokes, foil gauge is posted in both sides on Z-shaped spoke (2) vertical beam, for measuring lateral control power, two foil gauges are posted in the both sides of one character wheel spoke (2), for measuring fore-and-aft control power, this sensor body one end is connected with toothed shank, and other end plane is connected with control wheel by bolt.
Spoke type block diagram form as shown in Figure 4, this version not only can survey normal stress but also can survey shearing, this kind of form pastes foil gauge in different strain faces, when pilot control aircraft, the fore-and-aft control power of driver can be measured, the lateral control power of driver can be measured again, the signal of direct acquisition pilot guidance jociey stick (longitudinal force) and control wheel (transverse force) size variation, the flexible member generation elastic deformation now on sensor and make strainometer on sensor produce resistance variations.Like this, the signal of strainometer resistance variations is converted to voltage signal and is transferred to signal conditioner by sensor.Signal conditioner amplify by a certain percentage be converted to control force, control wheel power voltage signal supply aerial seeding vegetation.
Claims (1)
1. an aircraft integrated bi-directional device for measuring force, it is characterized in that, sensor body strain beam adopts 2 Z-shaped spokes and 2 character wheel spokes, foil gauge is posted in both sides on 2 Z-shaped spoke vertical beams, for measuring lateral control power, two foil gauges are posted in the both sides of 2 character wheel spokes, for measuring fore-and-aft control power, this sensor body one end is connected with toothed shank, and other end plane is connected with control wheel by bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520271673.0U CN204924516U (en) | 2015-04-29 | 2015-04-29 | Integrated two -way measuring force device of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520271673.0U CN204924516U (en) | 2015-04-29 | 2015-04-29 | Integrated two -way measuring force device of aircraft |
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| Publication Number | Publication Date |
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| CN204924516U true CN204924516U (en) | 2015-12-30 |
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| CN201520271673.0U Active CN204924516U (en) | 2015-04-29 | 2015-04-29 | Integrated two -way measuring force device of aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151928A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft control force sensor |
| CN108151927A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft pedal force snesor |
-
2015
- 2015-04-29 CN CN201520271673.0U patent/CN204924516U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151928A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft control force sensor |
| CN108151927A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft pedal force snesor |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |