CN205209615U - Controllable formula aircraft weighting device - Google Patents
Controllable formula aircraft weighting device Download PDFInfo
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- CN205209615U CN205209615U CN201521000183.3U CN201521000183U CN205209615U CN 205209615 U CN205209615 U CN 205209615U CN 201521000183 U CN201521000183 U CN 201521000183U CN 205209615 U CN205209615 U CN 205209615U
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Abstract
The utility model provides a controllable formula aircraft weighting device, a structural design technical field of aircraft surface equipment is related to, be used for aircraft weight, eliminate the yawing force in the centrobaric measurement process, the chassis, the jack sliding tray is the integrated into one piece structure, jack sliding tray bottom be provided with with jack fixing base assorted slip track, be provided with side force transducer in jack sliding tray inboard, the jack chassis is fixed in on the slip track in the jack sliding tray, hydraulic pressure sleeve top is provided with weighing sensor, the number of pass is according to the line connection side force transducer is through signal transmission cable junction the jack chassis, through show accuse device monitoring side force transducer and adjust the motion of jack chassis in the jack sliding tray, yawing force among the elimination aircraft weighing process. The utility model provides a controllable formula aircraft weighting device reduces or even eliminates the yawing force and to complete quick -witted weight, the influence of focus measuring, improved aircraft weight, centrobaric measurement accuracy by a wide margin, simple structure, and it is convenient to make.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to a kind of controllable type weighing machine for aircraft.
Background technology
Aircraft weight, center of gravity are the important design parameter in airplane design, the restriction that in aircraft flight, center of gravity is limit before and after must meeting, and when taking off and land, center of gravity of airplane degree of accuracy directly will affect flight safety.Therefore in the manufacture of aircraft, repacking and overhaul, all must carry out experiment of weighing to aircraft, provide the parameter such as weight, center of gravity accurately.At present, China mainly uses jack type aircraft weight, center of gravity measurement system, by by aircraft jack-up, leveling aircraft, reads the reading of LOAD CELLS, thus completes the experiment of weighing of aircraft.
General jack type weight, center of gravity measurement system are that a set of load cells is contained in lifting jack head, and by lifting jack top sensor, sensor support aircraft is weighed to aircraft.But because the factors such as fuselage, wing distortion and aspect adjustment all can produce side force at the Sensor section of measuring system in aircraft weight, center of gravity measurement process, this side force will directly affect the degree of accuracy of aircraft weight and center of gravity measurement.As can be seen here, how effectively reducing for jack type weighing system or eliminate side force to the impact of measurement result will be the key factor improving aircraft weight, center of gravity measurement system accuracies.
At present, the method reducing side force in aircraft weighting equipment mainly contains: one, reduce side force impact (referring to Chen Kehang, Wang Wenjian " Developing Application of New Generation of Portable Airplane Weighing System ", " new technology new instrument " the 19th volume the 5th phase in 1999) by increasing sliding platform under jack base; Two, the patent No. is that the utility model patent of ZL201420141747.4 discloses a kind of size by improving lifting jack and LOAD CELLS socket part, and part reduces side force.But, such scheme only reduces side force to a certain extent, undesirable to elimination side force effect on the one hand, accuracy requirement cannot be met, the method such as increasing sliding platform is not only subject to the restriction of sliding platform size, and the friction force be present between sliding platform and lifting jack surface of contact also can affect the effect reducing side force; Side force impact cannot in real time, be initiatively eliminated on the other hand according to measurement result.
The technical matters needing now solution badly how to design a kind of weighing machine for aircraft, to solve the technological deficiency existed in above-mentioned prior art.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provides a kind of simple and reasonable controllable type weighing machine for aircraft.
The purpose of this utility model is achieved through the following technical solutions: a kind of controllable type weighing machine for aircraft, carry out effectively controlling in real time for the weight of aircraft in aircraft testing process, the side force of center of gravity measurement, mainly comprise following ingredient: base, comprise chassis, lifting jack sliding tray, wherein, chassis, lifting jack sliding tray are formed in one structure, be provided with the sliding rail matched with lifting jack holder bottom lifting jack sliding tray, inside lifting jack sliding tray, be provided with load cells; Load cells, is arranged at along sliding rail direction inside lifting jack sliding tray; Lifting jack, is hydraulic-pressure sleeve lifting jack, comprises lifting jack chassis, and lifting jack chassis is fixed on the sliding rail in lifting jack sliding tray, and sleeve top is provided with LOAD CELLS; Display control device, integrated by display device, calibration apparatus, by data line connection side force snesor, connect described lifting jack chassis by signal-transmitting cable; Described load cells is monitored and side force in aircraft weighting process is eliminated in the motion regulating lifting jack chassis in lifting jack sliding tray by described display control device.
In such scheme preferably, chassis is circular, and the lifting jack sliding tray concentric mated with chassis, sliding rail direction is diameter of a circle direction, place, chassis.
In above-mentioned either a program preferably, chassis is rectangle, and sliding rail direction was the rectilinear direction at the center of chassis rectangle.
In above-mentioned either a program preferably, load cells is evenly arranged along lifting jack sliding tray inner circumferential.
In above-mentioned either a program preferably, the quantity of load cells is at least two.In aircraft weighting process, two contrary direction force in the rectilinear direction that the direction of side force is at least airplane motion, so the quantity of load cells is at least two.
In above-mentioned either a program preferably, the trough rim of lifting jack sliding tray is provided with through hole, data line, Signal transmissions electricity is through through hole connection side force snesor, lifting jack chassis respectively.
In above-mentioned either a program preferably, the trough rim of lifting jack sliding tray is provided with through hole, data line is through through hole connection side force snesor, and the upper edge that signal-transmitting cable walks around lifting jack sliding tray is connected with lifting jack chassis.
The beneficial effect of controllable type weighing machine for aircraft provided by the utility model is, make real-time adjustment by the direction of side force in the load cells determination aircraft weighting process on lifting jack sliding tray and size, reduce even to eliminate side force to the impact of whole machine weight, center of gravity measurement, significantly improve the measuring accuracy of aircraft weight, center of gravity, structure is simple, easily manufactured, device stability is high, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the structural representation of the preferred embodiment according to controllable type weighing machine for aircraft of the present utility model;
Fig. 2 is for the assembling schematic diagram of aircraft weighting according to the structure embodiment illustrated in fig. 1 of controllable type weighing machine for aircraft of the present utility model.
Reference numeral:
101-aircraft, 102-LOAD CELLS, 103-hydraulic-pressure sleeve, 201-chassis, 202-lifting jack sliding tray, 203-load cells, 204-lifting jack chassis, 205-display device, 206-calibration apparatus, 207-data line, 208-signal-transmitting cable.
Embodiment
The purpose of this utility model mainly provides a kind of novel weighing device, the controllable type weighing machine for aircraft adopting the utility model to provide directly can read the measurement registration of two orthogonal directionss, then initiatively eliminate side force by driving mechanism provided by the invention, improve the precision of aircraft weight, center of gravity measurement result.
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.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.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
As Figure 1-Figure 2, the controllable type weighing machine for aircraft that the utility model provides, carry out effectively controlling in real time for the weight of aircraft in aircraft testing process, the side force of center of gravity measurement, it is characterized in that, comprise: base, comprise chassis 201, lifting jack sliding tray 202, wherein, chassis 201, lifting jack sliding tray 202 are formed in one structure, be provided with the sliding rail matched with lifting jack holder bottom lifting jack sliding tray 202, inside lifting jack sliding tray 202, be provided with load cells 203; Load cells 203, is arranged at along sliding rail direction inside lifting jack sliding tray 202; Lifting jack, is hydraulic-pressure sleeve lifting jack, comprises lifting jack chassis 204, and lifting jack chassis 204 is fixed on the sliding rail in lifting jack sliding tray 202, and hydraulic-pressure sleeve 103 top is provided with LOAD CELLS 102; Display control device, integrated by display device 205, calibration apparatus 206, connect described load cells 203 by data line 207, connect described lifting jack chassis 204 by signal-transmitting cable 208; Described load cells 203 is monitored and side force in aircraft weighting process is eliminated in the motion regulating described lifting jack chassis 204 in lifting jack sliding tray 202 by described display control device.
In technique scheme, it will be appreciated by persons skilled in the art that lifting jack is divided into mechanic jacks and hydraulic jack two kinds, principle is had nothing in common with each other.From principle, hydraulic jack based on principle be pascal's principle, that is: liquid pressure is everywhere consistent, like this, in the system of balance, above smaller piston, applied pressure is smaller, and on large piston, applied pressure is also larger, can keep the static of liquid like this.So by the transmission of liquid, the different pressure on different end can be obtained, so just can reach an object converted.We common to hydraulic jack be exactly make use of this principle to reach the transmission of power.The lifting jack adopted in the controllable type weighing machine for aircraft that the utility model provides is hydraulic jack, and select the lifting jack being provided with chassis 204, in the convenient lifting jack sliding tray 202 be positioned in technique scheme, the scope of the motion of restriction lifting jack.Select hydraulic jack more can improve the precision of aircraft weight, center of gravity measurement.
Be understandable that, the display control device in technique scheme comprises display device 205, calibration apparatus 206, and respectively by data line 207 connection side force snesor 203, connects lifting jack chassis 204 by signal-transmitting cable 208.What display device 205 showed is the pressure load amount of load cells 203, learns that lifting jack is subject to the side force from which direction by pressure load.Adjusting gear is transferred to lifting jack chassis 204 by signal-transmitting cable 208 by calibration apparatus 206, lifting jack chassis 204 is provided with drive unit, make the moving on rails of lifting jack chassis 204 in lifting jack sliding tray 202, be adjusted to load cells 203 stressed be 0 or each load cells 203 stressed equal, or two load cells 203 stressed equal on same straight line.
Chassis 201 can be circular, and lifting jack sliding tray 202 concentric mated with chassis 201, sliding rail direction is diameter of a circle direction, place, chassis 201.The edge on lifting jack chassis 204 is equal to the edge of lifting jack sliding tray 202 to adopt the design of this kind of mode to ensure, in the inner side of the trough rim of lifting jack sliding tray 202, load cells 203 is set, can measure the induction of multidirectional side force, the direction of measurement is more, more accurately.Chassis 201 also can be designed to rectangle, and sliding rail direction was the rectilinear direction at the center of chassis 201 rectangle.Ensure that lifting jack chassis is equal to the distance on relative both sides, more convenient test.But be subject to the restriction of profile, the angle that the mode on more circular chassis 201 is measured is less.
Load cells 203 is evenly arranged along lifting jack sliding tray 202 inner circumferential, ensures that lifting jack chassis 204 is equal to the distance of each load cells 203, at least to being that the move distance of the load cells 203 on same straight line of lifting jack chassis 204 is equal.Match with above-mentioned either type, the mode that lifting jack sliding tray 20 is offered through hole also can be several as follows: the trough rim of 1) lifting jack sliding tray 202 is provided with through hole, and data line 207, signal-transmitting cable 208 connect described load cells 203, lifting jack chassis 204 respectively through same through hole; 2) trough rim of lifting jack sliding tray 202 is provided with through hole, and data line 207, signal-transmitting cable 208 connect described load cells 203, lifting jack chassis 204 respectively through different through holes.3) data line 207 is through through hole connection side force snesor 203, and the upper edge that signal-transmitting cable 208 walks around lifting jack sliding tray 202 is connected with lifting jack chassis 204.Wherein be understandable that, data line 207 is for transferring in display control device by the pressure signal of load cells 203, signal-transmitting cable 208, for the control signal of control device is transferred to lifting jack chassis 204 by display control device, regulates lifting jack chassis 204 orbital motion, eliminates side force.
More than be described in detail in conjunction with controllable type weighing machine for aircraft specific embodiment of the present utility model, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of controllable type weighing machine for aircraft technical scheme of the present utility model.
Claims (7)
1. a controllable type weighing machine for aircraft, carries out effectively controlling in real time for the weight of aircraft in aircraft testing process, the side force of center of gravity measurement, it is characterized in that, comprising:
Base, comprise chassis (201), lifting jack sliding tray (202), wherein, chassis (201), lifting jack sliding tray (202) are formed in one structure, and lifting jack sliding tray (202) bottom is provided with the sliding rail matched with lifting jack holder;
Load cells (203), is arranged at lifting jack sliding tray (202) inner side along sliding rail direction;
Lifting jack, comprise lifting jack chassis (204), hydraulic-pressure sleeve (103), described lifting jack chassis (204) is fixed on the sliding rail in lifting jack sliding tray (202), and hydraulic-pressure sleeve (103) top is provided with LOAD CELLS (102);
Display control device, by display device (205) and calibration apparatus (206) integrated, connect described load cells (203) by data line (207), connect described lifting jack chassis (204) by signal-transmitting cable (208);
Monitor described load cells (203) by described display control device, and regulate the motion of described lifting jack chassis (204) in described lifting jack sliding tray (202), eliminate side force in aircraft weighting process.
2. controllable type weighing machine for aircraft as claimed in claim 1, it is characterized in that, described chassis (201) is circular, described lifting jack sliding tray (202) is mated and concentric with described chassis (201), and described sliding rail direction is diameter of a circle direction, described chassis (201) place.
3. controllable type weighing machine for aircraft as claimed in claim 1, it is characterized in that, described chassis (201) are rectangle, and described sliding rail direction is on the straight line at center crossing described chassis (201) rectangle.
4. controllable type weighing machine for aircraft as claimed in claim 1, it is characterized in that, described load cells (203) is evenly arranged along described lifting jack sliding tray (202) inner circumferential.
5. controllable type weighing machine for aircraft as claimed in claim 4, it is characterized in that, the quantity of described load cells (203) is at least two.
6. controllable type weighing machine for aircraft as claimed in claim 1, it is characterized in that, the trough rim of described lifting jack sliding tray (202) is provided with through hole, and data line (207), signal-transmitting cable (208) connect described load cells (203), described lifting jack chassis (204) respectively through through hole.
7. controllable type weighing machine for aircraft as claimed in claim 1, it is characterized in that, the trough rim of described lifting jack sliding tray (202) is provided with through hole, data line (207) connects described load cells (203) through through hole, and the upper edge that signal-transmitting cable (208) walks around described lifting jack sliding tray (202) is connected with described lifting jack chassis (204).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521000183.3U CN205209615U (en) | 2015-12-04 | 2015-12-04 | Controllable formula aircraft weighting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521000183.3U CN205209615U (en) | 2015-12-04 | 2015-12-04 | Controllable formula aircraft weighting device |
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| CN205209615U true CN205209615U (en) | 2016-05-04 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248299A (en) * | 2016-07-11 | 2016-12-21 | 上海卫星装备研究所 | A kind of based on multi-dimensional force barycenter test system |
| CN106706212A (en) * | 2016-12-16 | 2017-05-24 | 燕山大学 | Aircraft center-of-mass measurement device capable of realizing automatic detection and eliminating yawing force |
| CN107651604A (en) * | 2016-07-26 | 2018-02-02 | 沈阳市松陵工具厂 | A kind of hydraulic means system of main wheel jack |
| CN109271690A (en) * | 2018-09-04 | 2019-01-25 | 沈阳飞机工业（集团）有限公司 | The design method of aircraft weighting elimination lateral force sensors |
| CN109855712A (en) * | 2019-01-09 | 2019-06-07 | 山东太古飞机工程有限公司 | Auxiliary mould during a kind of spacing in aircraft weighting technique is fixed |
| CN110182385A (en) * | 2018-12-11 | 2019-08-30 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of lateral force eliminating device of aircraft jack-up system |
-
2015
- 2015-12-04 CN CN201521000183.3U patent/CN205209615U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106248299A (en) * | 2016-07-11 | 2016-12-21 | 上海卫星装备研究所 | A kind of based on multi-dimensional force barycenter test system |
| CN107651604A (en) * | 2016-07-26 | 2018-02-02 | 沈阳市松陵工具厂 | A kind of hydraulic means system of main wheel jack |
| CN106706212A (en) * | 2016-12-16 | 2017-05-24 | 燕山大学 | Aircraft center-of-mass measurement device capable of realizing automatic detection and eliminating yawing force |
| CN109271690A (en) * | 2018-09-04 | 2019-01-25 | 沈阳飞机工业（集团）有限公司 | The design method of aircraft weighting elimination lateral force sensors |
| CN110182385A (en) * | 2018-12-11 | 2019-08-30 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of lateral force eliminating device of aircraft jack-up system |
| CN109855712A (en) * | 2019-01-09 | 2019-06-07 | 山东太古飞机工程有限公司 | Auxiliary mould during a kind of spacing in aircraft weighting technique is fixed |
| CN109855712B (en) * | 2019-01-09 | 2023-09-01 | 山东太古飞机工程有限公司 | Distance centering auxiliary tool for airplane weighing process |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20201028 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |
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| TR01 | Transfer of patent right |