CN109443641A - A kind of system and method for fast tuning aircraft level - Google Patents
A kind of system and method for fast tuning aircraft level Download PDFInfo
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- CN109443641A CN109443641A CN201811642673.1A CN201811642673A CN109443641A CN 109443641 A CN109443641 A CN 109443641A CN 201811642673 A CN201811642673 A CN 201811642673A CN 109443641 A CN109443641 A CN 109443641A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000005259 measurement Methods 0.000 claims abstract description 25
- 239000000523 sample Substances 0.000 claims abstract description 3
- 238000012546 transfer Methods 0.000 claims description 26
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 26
- 238000006073 displacement reaction Methods 0.000 claims description 18
- 230000001360 synchronised effect Effects 0.000 claims description 9
- 230000003028 elevating effect Effects 0.000 description 11
- 238000005303 weighing Methods 0.000 description 6
- 230000005484 gravity Effects 0.000 description 5
- 230000033001 locomotion Effects 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 3
- 230000000007 visual effect Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000013523 data management Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
- G01M1/125—Determining position of centre of gravity of aircraft
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01G—WEIGHING
- G01G19/00—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups
- G01G19/02—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles
- G01G19/07—Weighing apparatus or methods adapted for special purposes not provided for in the preceding groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/02—Details of balancing machines or devices
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
本发明公开了一种快速调校飞机水平的系统及方法，包括三个升降装置、全站仪和控制柜；所述三个升降装置分别设置在飞机机轮下方且连接有伺服电机，初始位置与地面持平，移动方向为竖直方向；所述全站仪放置在地面上，探头朝向飞机的三个调水平点和设定的飞机基准点，并与控制柜连接，用于实时测量飞机的三个调水平点与飞机基准点的相对距离，并将测量数据发送给控制柜；控制柜与三个升降装置的伺服电机连接，控制三个升降装置的上升与下降。实现飞机水平状态快速调校，提高了工作效率，减小了测量误差，提高了测量精度，实现了飞机调校过程的自动化控制。
The invention discloses a system and method for quickly adjusting the level of an aircraft, comprising three lifting devices, a total station and a control cabinet; the three lifting devices are respectively arranged under the wheel of the aircraft and are connected with a servo motor. It is level with the ground, and the moving direction is the vertical direction; the total station is placed on the ground, the probe faces the three leveling points of the aircraft and the set aircraft reference point, and is connected to the control cabinet for real-time measurement of the aircraft's The relative distance between the three leveling points and the aircraft reference point, and the measurement data is sent to the control cabinet; the control cabinet is connected with the servo motors of the three lifting devices to control the ascent and descent of the three lifting devices. The rapid adjustment of the aircraft level state is realized, the work efficiency is improved, the measurement error is reduced, the measurement accuracy is improved, and the automatic control of the aircraft adjustment process is realized.
Description
Technical field
The invention belongs to aircraft weighting technical fields, are related to a kind of system and method for fast tuning aircraft level.
Background technique
When aircraft weight center of gravity measurement, the gross weight of aircraft is recorded when aircraft need to be adjusted to horizontality, then using winged
The center of gravity calculation formula of machine calculates the vertical and horizontal center of gravity of aircraft.Currently, when the center of gravity of airplane measures, level-off mode one
As be with jack type, i.e., with three jack stand aircrafts, then with the horizontality of level survey aircraft, if unhorizontal,
Then cooperated using level and jack by aircraft top level, the entire process for adjusting aircraft level is required to manually participate in, easily
Human error is generated, precision is low, and weighing process and inconvenience, and time-consuming, low efficiency, and automation, intelligence degree are low.
Summary of the invention
It is an object of the invention to overcome the above-mentioned prior art, a kind of system of fast tuning aircraft level is provided
And method, it realizes aircraft horizontality fast tuning, improves work efficiency, reduce measurement error, improve measurement accuracy,
Realize the automation control of aircraft calibration procedures.
In order to achieve the above objectives, the present invention is achieved by the following scheme:
A kind of system of fast tuning aircraft level, including three lifting devices, total station and control cabinet；
Three lifting devices are separately positioned below airplane wheel and are connected with servo motor, initial position and ground
Maintain an equal level, moving direction is vertical direction；
The total station is placed on the ground, and is popped one's head in towards three water transfer flat spots of aircraft and the aircraft reference point of setting,
And connect with control cabinet, for three water transfer flat spots of real-time measurement aircraft and the relative distance of aircraft reference point, and will measurement
Data are sent to control cabinet；
Control cabinet is connect with the servo motor of three lifting devices, controls the rise and fall of three lifting devices.
Preferably, three water transfer flat spots of aircraft are provided with the identical outstanding ruler of length, hang the nature hanging of ruler end.
Preferably, three lifting devices are provided with laser displacement sensor, and the probe court of laser displacement sensor divides into
It sets, the output end of laser displacement sensor and the input terminal of control cabinet connect.
Preferably, lifting device is all made of four screw synchronous lifting devices.
Further, three lifting devices are provided with the handwheel for controlling its height, and handwheel is connected by gear and lead screw
It connects.
Preferably, electronic platform scale is provided at the top of three lifting devices.
A kind of method of fast tuning aircraft level is included the following steps based on system described in above-mentioned any one；
Step 1, aircraft is moved into ranging region, wheel is respectively positioned on above lifting device, and is fixed；
Step 2, using the relative distance of three water transfer flat spots of total station survey aircraft and aircraft reference point, and will measurement
Data are sent to control cabinet；
Step 3, control cabinet is chosen with datum mark Relative vertical apart from maximum water transfer flat spot according to measurement data as mesh
Punctuate controls lifting device corresponding with other two water transfer flat spots and is gone up and down；
Step 4, step 2 and step 3 are repeated, until aircraft is in horizontality.
Preferably, in step 2, the end of the outstanding ruler of nature hanging and datum mark is opposite at total station survey water transfer flat spot
Distance.
Preferably, in step 3, Relative vertical distance of the control cabinet according to other two water transfer flat spots and target point, judgement
Lifting device direction of displacement and shift length, and the travel information command displacement distance fed back by laser displacement sensor.
Preferably, in step 4, when the Relative vertical distance between each water transfer flat spot is no more than 1mm, level leveling
Work is completed.
Compared with prior art, the invention has the following advantages:
By the present invention in that measured with the relative distance that total station exchanges level point and datum mark, and by measurement data
Be sent to control cabinet, control cabinet according to the data received, the lifting device that control three is arranged in below wheel rise or under
Drop, and then adjustment aircraft is horizontal, does not need manual operation, and then reduce human error, precision is high, and speed is fast, and it is high-efficient, it is real
The automation control of aircraft calibration procedures is showed.
Further, by the way that the outstanding ruler of equal length is arranged in water transfer flat spot and datum mark, the nature hanging of ruler end is hanged, makes to survey
The point of amount can extend to visual range, be convenient for measuring.
Further, control cabinet passes through the travel information command displacement distance that laser displacement sensor is fed back, and realizes adjustment
When accurate control.
Detailed description of the invention
Fig. 1 is adjustment system structural schematic diagram of the invention；
Fig. 2 is adjusting process flow chart of the invention.
Wherein: 1- electronic platform scale；2- elevating mechanism；3- servo motor；4- hoistable platform；5- laser displacement sensor；6-
Total station；7- control cabinet；8- handwheel.
Specific embodiment
The invention will be described in further detail with reference to the accompanying drawing:
The system of fast tuning aircraft level of the present invention is based on following equipment, including electronic platform scale 1, four screw synchronous are gone up and down
Device, total station subsystem, main control computer, control cabinet 7, cable and the wheel stopper for embedding application software.
The electronic platform scale 1, four screw synchronous lifting devices, total station subsystem pass through cable and answer with described embed
It is connected with the computer of software, the computer of embedded application software is placed in control cabinet 7, and application software includes the lifting control of scale body
Software, horizontal adjustment software and weight center of gravity software for calculation processed.
The electronic platform scale 1 mainly by upper scale body, lower scale body, four weighing sensors, a terminal box array at.Entirely
Electronic platform scale 1 is placed on the hoistable platform 4 at the top of four screw synchronous lifting devices, and lower scale body and hoistable platform 4 are connected.Electronic table
Scale 1 contains three altogether, respectively carrying front and back wheel, when installation, removes scale body upper table surface, three weighing platforms are mounted in ground and keep
Scale body upper table surface is concordant with grade level, moves to weighing platform Weighing Area convenient for aircraft；Wheel stopper is placed on scale body, is used for
Airplane wheel is limited, stabilization of the aircraft in leveling is kept.
There are three the four screw synchronous lifting device settings, respectively corresponds three electronic platform scales 1, and main includes that lifting is flat
Platform 4, elevating mechanism 2, servo motor 3, motor servo driver and PLC controller.Hoistable platform 4 is installed under electronic platform scale 1
Side, laser displacement sensor 5 are placed in 1 side of electronic platform scale.When work, laser displacement sensor 5 detects adjustable height, and in real time
The elevation information of transmission hoistable platform 4 gives scale body elevating control software as value of feedback, meanwhile, scale body elevating control software is sent
It instructs to PLC controller, PLC controller controls motor servo driver, and driving servo motor 3 drives the silk in elevating mechanism 2
Thick stick rotation, four screw synchronous rotation, converts rotational motion into linear motion, the final raising and lowering for realizing hoistable platform 4.
In addition, in elevating mechanism 2, the protective devices such as the travel switch limited up and down are set, when touch switch, hoistable platform 4 stops, and
Only allow to move backward, to guarantee platform safety movement in allowed limits.Simultaneously be furnished with handwheel 8, handwheel 8 by gear with
Lead screw connection is, it can be achieved that manually and automatically two kinds of control modes, and when being allocated to manual gear, staff can pass through handwheel 8 and rotate silk
Thick stick movement, when being allocated to automatic catch, directly controls driver by scale body elevating control software.
The full-automatic ranging subsystem of 3D is mainly thin and ranging software forms by total station 6, measurement hand.The total station
6 uses come card TS16 model.When work, total station 6 is placed in ground, can flatten automatically within the scope of certain angle, and pass through electricity
Cable is connect with control cabinet.When systematic survey, can the thin control of hand, can also directly capture feature on data processing terminal panel
Point, Survey Software automatic measurement as built in it.
As shown in Fig. 2, the specific steps of adjustment level are as follows:
Step 1, aircraft is moved into Weighing Area, the limit of wheel stopper is placed by wheel；
Step 2, three sections or the identical outstanding ruler one end of multiple lengths are fixed at the water transfer flat spot on airframe, hang the another of ruler
One end nature hanging, so that the water transfer flat spot on aircraft extends to visual range；
Step 3, outstanding ruler end and datum mark on aircraft are captured with total station 6, ranging software survey calculation is between the two
Distance, and calculated result is transmitted to the horizontal adjustment software of the aircraft in main control computer；
Step 4, the laser displacement sensor 5 in four screw synchronous lifting subsystem feeds back 4 height of hoistable platform and will be anti-
Feedback value is transmitted to the horizontal adjustment software of the aircraft in main control computer；
Step 5, the horizontal adjustment software of machine is according to the value of feedback of 3,4 steps, and judging aircraft, whether adjustment is horizontal；
Step 6, if meeting condition, aircraft adjustment is horizontal, and otherwise, scale body elevating control software sends instructions to elevator
Structure 2, hoistable platform 4 act；
Step 7, return step 3 circuit sequentially, until aircraft adjustment is horizontal.
The observing and controlling process and principle of aircraft fast tuning level: before measurement, by the identical outstanding ruler one of three sections or multiple lengths
End is fixed with the level-off point on airframe, other end nature hanging, so that the water transfer flat spot on aircraft extends to visual model
It encloses.When measurement, rangefinder is placed in ground, after its automatic leveling, opens the sky that laser beam is directed toward outstanding ruler nature hanging end
Between location point and datum mark, or from measurement hand thin panel or data processing terminal panel on directly capture on aircraft outstanding ruler end
End and datum mark, ranging software quickly calculates the two o'clock distance of capture as built in total station 6, realizes water transfer flat spot and base
The measurement of relative distance on schedule, measurement result are transmitted to scale body elevating control software eventually by its included communication interface.Step
In rapid 5, if the relative distance that total station 6 is measured is labeled as △ Xi (i=1,2,3), maximum value is labeled as △ Xmax in △ Xi,
If △ Xmax is target value when aircraft levels, each relative distance precision is 1mm when aircraft levels.Judgement, if | △ Xi- △ Xmax |
≤ 1mm, then point leveling is motionless, otherwise compares value of feedback and target value, it is soft that the difference of the two is sent to scale body elevating control
Part, scale body elevating control software judge after receiving the difference, if △ Xi- △ Xmax≤1mm, the water transfer flat spot are corresponding
Hoistable platform 4 rises, if △ Xi- △ Xmax > 1mm, the corresponding hoistable platform 4 of the water transfer flat spot declines, and sends instructions to
PLC controller, control driver driving servo motor 3 act, and hoistable platform 4 is gone up and down, and is as follows recycled and is judged, until value of feedback
Consistent with target value, three water transfer flat spots level locking, then aircraft level levels.
As embodiment of the present invention, the scheme further includes two modules of application software, i.e. data acquisition module
And data management module, two Module-embeddings, according to measurement result, realize computer and aircraft weighting system into computer application software
The human-computer interaction of system and data output.
The horizontal adjustment system of aircraft can carry out quickly horizontal adjustment to aircraft, meanwhile, four screw synchronous go up and down subsystem
Lead screw have lifting self-lock function, total station 6 measurement accuracy is high, can be flattened automatically according to surface state, environmental suitability is strong.
Therefore, aircraft level tune correcting delay precision is high, stability is good doing for the horizontal adjustment system of aircraft, and system is safe and reliable.
The above content is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme each falls within claims of the present invention
Protection scope within.
Claims (10)
1. a kind of system of fast tuning aircraft level, which is characterized in that including three lifting devices, total station (6) and control
Cabinet (7)；
Three lifting devices are separately positioned below airplane wheel and are connected with servo motor, and initial position is held with ground
Flat, moving direction is vertical direction；
The total station (6) is placed on the ground, and pops one's head in towards three water transfer flat spots of aircraft and the aircraft reference point of setting, and
It is connect with control cabinet (7), for three water transfer flat spots of real-time measurement aircraft and the relative distance of aircraft reference point, and will measurement
Data are sent to control cabinet (7)；
Control cabinet (7) is connect with the servo motor of three lifting devices, controls the rise and fall of three lifting devices.
2. a kind of system of fast tuning aircraft level according to claim 1, which is characterized in that three water transfer of aircraft
Flat spot is provided with the identical outstanding ruler of length, hangs the nature hanging of ruler end.
3. a kind of system of fast tuning aircraft level according to claim 1, which is characterized in that three lifting devices are equal
Be provided with laser displacement sensor (5), the probe of laser displacement sensor (5) is arranged downward, laser displacement sensor (5) it is defeated
The connection of the input terminal of outlet and control cabinet.
4. a kind of system of fast tuning aircraft level according to claim 1, which is characterized in that lifting device is all made of
Four screw synchronous lifting devices.
5. a kind of system of fast tuning aircraft level according to claim 4, which is characterized in that three lifting devices are equal
It is provided with the handwheel (8) for controlling its height, handwheel (8) is connect by gear with lead screw.
6. a kind of system of fast tuning aircraft level according to claim 1, which is characterized in that three lifting device tops
Portion is provided with electronic platform scale (1).
7. a kind of method of fast tuning aircraft level, is based on system as claimed in any one of claims 1 to 6, feature exists
In including the following steps；
Step 1, aircraft is moved into ranging region, wheel is respectively positioned on above lifting device, and is fixed；
Step 2, using the relative distance of three water transfer flat spots of total station (6) survey aircraft and aircraft reference point, and will measurement
Data are sent to control cabinet (7)；
Step 3, control cabinet (7) is chosen with datum mark Relative vertical apart from maximum water transfer flat spot according to measurement data as mesh
Punctuate controls lifting device corresponding with other two water transfer flat spots and is gone up and down；
Step 4, step 2 and step 3 are repeated, until aircraft is in horizontality.
8. a kind of method of fast tuning aircraft level according to claim 7, which is characterized in that in step 2, total station
(6) relative distance of the end of the outstanding ruler of nature hanging and datum mark at water transfer flat spot is measured.
9. a kind of method of fast tuning aircraft level according to claim 7, which is characterized in that in step 3, control cabinet
(7) according to the Relative vertical distance of other two water transfer flat spots and target point, judge lifting device direction of displacement and shift length,
And the travel information command displacement distance fed back by laser displacement sensor (5).
10. a kind of method of fast tuning aircraft level according to claim 7, which is characterized in that in step 4, when every
When Relative vertical distance between a water transfer flat spot is no more than 1mm, level leveling work is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811642673.1A CN109443641A (en) | 2018-12-29 | 2018-12-29 | A kind of system and method for fast tuning aircraft level |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811642673.1A CN109443641A (en) | 2018-12-29 | 2018-12-29 | A kind of system and method for fast tuning aircraft level |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461201A (en) * | 2020-11-18 | 2021-03-09 | 中航通飞华南飞机工业有限公司 | Airplane horizontal measurement method and system |
| CN114265421A (en) * | 2021-12-13 | 2022-04-01 | 中航贵州飞机有限责任公司 | Intelligent boresight system for airplane and using method |
| CN114370921A (en) * | 2021-12-23 | 2022-04-19 | 中国航天空气动力技术研究院 | A kind of aircraft flexible wing static load weighing equipment |
| CN114383776A (en) * | 2021-12-06 | 2022-04-22 | 中航贵州飞机有限责任公司 | Method for improving measurement accuracy of center of gravity of airplane |
| CN114563070A (en) * | 2022-03-08 | 2022-05-31 | 成都程航航空科技有限公司 | Weighing and transverse moving method for airplane |
| CN116266733A (en) * | 2021-12-16 | 2023-06-20 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Micro-displacement centering device based on magnetic fluid |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1334947A2 (en) * | 2001-11-02 | 2003-08-13 | Roberto Maggiori | Self leveling integrated lifting device |
| CN102519430A (en) * | 2011-12-06 | 2012-06-27 | 江西洪都航空工业集团有限责任公司 | Horizontal laser measurement system and method for airplane |
| CN103376193A (en) * | 2012-04-17 | 2013-10-30 | 波音公司 | System and method for ground vibration testing and weight and balance measurement |
| CN104390687A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Intelligent tester for weight and center of gravity of aircraft |
| CN105136391A (en) * | 2015-07-29 | 2015-12-09 | 中航电测仪器股份有限公司 | Method of measuring distance between ground force bearing points of plane and system |
| CN107102645A (en) * | 2016-02-22 | 2017-08-29 | 成都飞机工业（集团）有限责任公司 | A kind of aspect adjusting means |
| CN107884125A (en) * | 2017-12-23 | 2018-04-06 | 中航电测仪器股份有限公司 | A kind of aircraft weight center of gravity self-operated measuring unit and its control method |
-
2018
- 2018-12-29 CN CN201811642673.1A patent/CN109443641A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1334947A2 (en) * | 2001-11-02 | 2003-08-13 | Roberto Maggiori | Self leveling integrated lifting device |
| CN102519430A (en) * | 2011-12-06 | 2012-06-27 | 江西洪都航空工业集团有限责任公司 | Horizontal laser measurement system and method for airplane |
| CN103376193A (en) * | 2012-04-17 | 2013-10-30 | 波音公司 | System and method for ground vibration testing and weight and balance measurement |
| CN104390687A (en) * | 2014-11-26 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Intelligent tester for weight and center of gravity of aircraft |
| CN105136391A (en) * | 2015-07-29 | 2015-12-09 | 中航电测仪器股份有限公司 | Method of measuring distance between ground force bearing points of plane and system |
| CN107102645A (en) * | 2016-02-22 | 2017-08-29 | 成都飞机工业（集团）有限责任公司 | A kind of aspect adjusting means |
| CN107884125A (en) * | 2017-12-23 | 2018-04-06 | 中航电测仪器股份有限公司 | A kind of aircraft weight center of gravity self-operated measuring unit and its control method |
Non-Patent Citations (3)
| Title |
|---|
| 居玮: "飞机水平测量", 技术与市场, vol. 25, no. 11, pages 91 - 92 * |
| 廖美东: "飞机校平及机翼校装", 航空制造技术, no. 04, pages 44 * |
| 李欣;申蒸洋;: "浅谈大型飞机的水平测量", 科技创新与应用, no. 08, pages 296 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461201A (en) * | 2020-11-18 | 2021-03-09 | 中航通飞华南飞机工业有限公司 | Airplane horizontal measurement method and system |
| CN114383776A (en) * | 2021-12-06 | 2022-04-22 | 中航贵州飞机有限责任公司 | Method for improving measurement accuracy of center of gravity of airplane |
| CN114383776B (en) * | 2021-12-06 | 2023-05-05 | 中航贵州飞机有限责任公司 | Method for improving aircraft gravity center measurement accuracy |
| CN114265421A (en) * | 2021-12-13 | 2022-04-01 | 中航贵州飞机有限责任公司 | Intelligent boresight system for airplane and using method |
| CN116266733A (en) * | 2021-12-16 | 2023-06-20 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Micro-displacement centering device based on magnetic fluid |
| CN116266733B (en) * | 2021-12-16 | 2025-07-18 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | Micro-displacement centering device based on magnetic fluid |
| CN114370921A (en) * | 2021-12-23 | 2022-04-19 | 中国航天空气动力技术研究院 | A kind of aircraft flexible wing static load weighing equipment |
| CN114563070A (en) * | 2022-03-08 | 2022-05-31 | 成都程航航空科技有限公司 | Weighing and transverse moving method for airplane |
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Application publication date: 20190308 |