CN218916509U - Self-lifting type aircraft weighing equipment and adjusting system - Google Patents
Self-lifting type aircraft weighing equipment and adjusting system Download PDFInfo
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- CN218916509U CN218916509U CN202221513092.XU CN202221513092U CN218916509U CN 218916509 U CN218916509 U CN 218916509U CN 202221513092 U CN202221513092 U CN 202221513092U CN 218916509 U CN218916509 U CN 218916509U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A40/00—Adaptation technologies in agriculture, forestry, livestock or agroalimentary production
- Y02A40/80—Adaptation technologies in agriculture, forestry, livestock or agroalimentary production in fisheries management
- Y02A40/81—Aquaculture, e.g. of fish
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Abstract
The utility model discloses self-lifting type aircraft weighing equipment and an adjusting system, wherein the self-lifting type aircraft weighing equipment comprises a telescopic adjusting component, a first bearing arm, a second bearing arm, a weighing sensor and a rolling component; the first bearing arm and the second bearing arm are respectively arranged at two sides of the telescopic adjusting assembly, and the relative position between the first bearing arm and the second bearing arm can be changed through the telescopic adjusting assembly; the rolling assembly is respectively connected with the first bearing arm and the second bearing arm, and the weighing sensor is arranged at the joint of the rolling assembly and the first bearing arm or the first bearing arm; when bearing, the device places the aircraft wheel set at the gap between the first bearing arm and the second bearing arm, adjusts the distance between the first bearing arm and the second bearing arm through the telescopic component, enables the first bearing arm and the second bearing arm to be in contact with the aircraft wheel set, and the aircraft wheel set is clamped and lifted by the first bearing arm and the second bearing arm.
Description
Technical Field
The utility model relates to the field of aircraft maintenance, in particular to self-lifting type aircraft weighing equipment and an adjusting system.
Background
The large unmanned aerial vehicle weighing work is a relatively common maintenance work. At present, the weighing equipment that more uses is platform type floor scale, needs jack-up unmanned aerial vehicle during the use, and the operation is comparatively loaded down with trivial details, and has certain risk, and factor of limitation is more, and current large-scale unmanned aerial vehicle bearing device can't carry out every single move angle adjustment simultaneously, and unmanned aerial vehicle can bring the error for measuring under the condition that rocks, simultaneously because large-scale unmanned aerial vehicle every single move angle is different in the measurement process, slightly moves and can appear the motion, and this operation personnel brings the risk.
Disclosure of Invention
The utility model aims at: to above-mentioned problem, provide a from aircraft weighing equipment and governing system of jacking formula, the complex operation when having solved among the prior art large-scale unmanned aerial vehicle and weighing, and there is the problem of certain risk, solved the problem that large-scale unmanned aerial vehicle bearing equipment can't carry out pitch angle regulation simultaneously.
The utility model is realized by the following scheme:
a self-lifting type aircraft weighing device comprises a telescopic adjusting assembly, a first bearing arm, a second bearing arm, a weighing sensor and a rolling assembly; the first bearing arm and the second bearing arm are respectively arranged at two sides of the telescopic adjusting assembly, and the relative position between the first bearing arm and the second bearing arm can be changed through the telescopic adjusting assembly; the rolling assembly is connected with the first bearing arm and the second bearing arm respectively, and the weighing sensor is arranged at the joint of the rolling assembly and the first bearing arm or the first bearing arm.
Based on the structure of the self-jacking type aircraft weighing equipment, the telescopic adjusting assembly comprises a sliding outer sleeve, a sliding inner cylinder, a hydraulic action cylinder and a hydraulic pedal; the sliding outer sleeve is sleeved at the outer side of the sliding inner cylinder, so that the sliding outer sleeve can move freely relative to the sliding inner cylinder; the telescopic rod of the hydraulic action cylinder is fixedly connected with the sliding inner cylinder, the body of the hydraulic action cylinder is fixedly connected with the sliding shell, and the hydraulic pedal is connected with the hydraulic action cylinder.
Based on the structure of the self-lifting type aircraft weighing equipment, the first bearing arm comprises a main beam, a sleeve and a rolling column; the main beam is sleeved in the sleeve, and the rolling column is arranged at a position between the main beam and the sleeve.
Based on the structure of the self-lifting type aircraft weighing equipment, the number of the rolling columns is at least 2 around the main beam at the position between the main beam and the sleeve.
Based on the structure of the self-lifting type aircraft weighing equipment, the sliding sleeve is connected with the main beam of the first bearing arm or the second bearing arm, and the sliding jacket is connected with the main beam on the opposite side.
Based on the structure of the self-lifting type aircraft weighing equipment, a Z-shaped mounting plate is arranged between the main beam and the weighing sensor.
Based on the structure of the self-lifting type aircraft weighing equipment, the maximum value of the width between the main beam of the first bearing arm and the main beam of the second bearing arm is not smaller than the diameter of an aircraft tire, and the minimum value is not smaller than the radius of the aircraft tire.
Based on the structure of the self-lifting type aircraft weighing equipment, the rolling assembly comprises a rolling wheel and a mounting plate; the mounting plate is arranged at the top of the rolling wheel, and mounting holes matched with the weighing sensors are formed in the mounting plate.
Based on the structure of the self-lifting type aircraft weighing equipment, the weighing sensor is provided with a first connecting hole connected with the rolling assembly and a second connecting hole connected with the Z-shaped mounting plate.
The scheme discloses a self-lifting type airplane weighing and adjusting system, which comprises a plurality of self-lifting type airplane weighing devices, wherein each self-lifting type airplane weighing device is contacted with one airplane wheel set.
In summary, due to the adoption of the technical scheme, the beneficial effects of the utility model are as follows:
1. through this device when bearing, place the space department between first arm and the second of accepting of aircraft wheelset, adjust the interval between first arm and the second of accepting through flexible adjusting part, make first arm and the second of accepting accept arm and aircraft wheelset contact, along with the interval between first arm and the second of accepting reduces, the aircraft wheelset is accepted the arm centre gripping and lifts by first arm and the second of accepting, when all aircraft wheelsets all lifted, can stabilize and accurately measure the weight of aircraft through weighing sensor.
2. In this scheme through setting up the rotor roller in the position between girder and sleeve, make it form and embrace a round roller structure, through the area of contact of sleeve increase weighing device and aircraft tire, protect aircraft tire, simultaneously with a plurality of settings of rotor roller between girder and sleeve, make the sleeve can more smooth rotate.
Drawings
FIG. 1 is a schematic view of the overall structure of the present utility model;
FIG. 2 is a schematic view of a rolling wheel structure in the utility model;
FIG. 3 is a schematic view of the structure of the first receiving arm according to the present utility model;
description of the drawings: 1. a telescoping adjustment assembly; 2. a first receiving arm; 3. a second receiving arm; 4. a weighing sensor; 5. a rolling assembly; 6. a Z-shaped mounting plate; 11. a sliding jacket; 12. sliding the inner cylinder; 13. a hydraulic action cylinder; 14. a hydraulic pedal; 21. a main beam; 22. a sleeve; 23. a rotating roller; 24. a rolling shaft; 41. a first connection hole; 42. a second connection hole; 51. a rolling wheel; 52. and (3) mounting a plate.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification (including any accompanying claims, abstract) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
In the description of the present utility model, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may include one or more of the feature, either explicitly or implicitly.
Example 1
As shown in fig. 1 and 3, the present utility model provides a technical solution:
a self-elevating aircraft weighing apparatus comprising at least, but not limited to, a telescoping adjustment assembly 1, a first receiving arm 2, a second receiving arm 3, a load cell 4, and a rolling assembly 5; the first bearing arm 2 and the second bearing arm 3 are respectively arranged at two sides of the telescopic adjusting assembly 1, and the relative position between the first bearing arm 2 and the second bearing arm 3 can be changed through the telescopic adjusting assembly 1; the rolling assembly 5 is respectively connected with the first bearing arm 2 and the second bearing arm 3, and the weighing sensor 4 is arranged at the joint of the rolling assembly 5 and the first bearing arm 2 or the first bearing arm 2.
Based on the above-mentioned structure, when bearing, place the aircraft wheelset in the first space department of accepting between arm 2 and the second and accept arm 3, adjust the first interval of accepting between arm 2 and the second and accept arm 3 through flexible adjusting part, make first accept arm 2 and the second accept arm 3 and aircraft wheelset contact, along with the first interval of accepting between arm 2 and the second and accept arm 3 reduces, the aircraft wheelset is accepted arm 2 and the second and accept arm 3 centre gripping and lift by first, when all aircraft wheelsets all lifted, can stabilize and accurately measure the weight of aircraft through weighing sensor 4.
As an example, the telescopic adjustment assembly may include a sliding outer sleeve 11, a sliding inner sleeve 12, a hydraulic action sleeve 13, and a hydraulic pedal 14; the sliding jacket 11 is sleeved on the outer side of the sliding inner cylinder 12, so that the sliding jacket 11 can move freely relative to the sliding inner cylinder 12; the telescopic rod of the hydraulic action cylinder 13 is fixedly connected with the sliding inner cylinder 12, the body of the hydraulic action cylinder 13 is fixedly connected with the sliding shell, and the hydraulic pedal 14 is connected with the hydraulic action cylinder 13.
With the above configuration, the amount of oil fed to and discharged from the hydraulic cylinder 13 can be adjusted by the hydraulic pedal 14, and the telescopic rod of the hydraulic cylinder 13 can be extended or shortened, so that the slide jacket 11 and the slide inner cylinder 12 can be displaced relatively, and the distance between the first receiving arm 2 and the second receiving arm 3 can be changed.
By way of example, the first receiving arm 2 and the second receiving arm 3 are similar in structure, again illustrated by the first receiving arm 2; the first receiving arm 2 may include a main beam 21, a sleeve 22, a rolling post 23; the main beam 21 is sleeved in the sleeve 22, the rolling column 23 is arranged at a position between the main beam 21 and the sleeve 22, and the rolling column 23 can rotate freely relative to the rolling shaft 24.
The number of rolling columns is at least 2 around the main beam 21 at a position between the main beam 21 and the sleeve 22.
Based on the above structure, through setting up the position between girder 21 and sleeve 22 with rolling post 23, make it form and embrace round roller structure, increase the area of contact of weighing device and aircraft tire through sleeve 22, protect aircraft tire, set up a plurality of settings of rolling post 23 between girder 21 and sleeve 22 simultaneously, make sleeve 22 can more smooth rotate.
As an example, the sliding inner cylinder 22 is connected to the main beam 21 of the first receiving arm 2 or the second receiving arm 3, and the sliding outer sleeve 11 is connected to the opposite main beam 21; the telescopic force of the telescopic adjusting component can be transmitted between the first bearing arm 2 and the second bearing arm 3, and stable width adjusting movement is carried out.
As an example, a Z-shaped mounting plate 52 may be provided between the main beam and the load cell 4, and the load cell 4 and the main beam are firmly connected by the Z-shaped mounting plate 52.
As an example, the width between the main beam 21 of the first receiving arm 2 and the main beam 21 of the second receiving arm 3 is not smaller than the diameter of the aircraft tire at the maximum and not smaller than the radius of the aircraft tire at the minimum.
Based on the structure, the maximum width of the distance between the main beams 21 of the first receiving arm 2 and the second receiving arm 3 is larger than the diameter of the aircraft tire, and the minimum width is approximately equal to the radius of the aircraft tire, so that the weighing device can stably clamp and lift the aircraft tire.
As an example, the rolling assembly 5 may include a rolling wheel 51 and a mounting plate 52; the mounting plate 52 is arranged at the top of the rolling wheel 51, mounting holes matched with the weighing sensors 4 are formed in the mounting plate 52, and the mounting plate 52 and the weighing sensors 4 are connected into a whole through the mounting holes.
The weighing sensor 4 is provided with a first connecting hole 41 connected with the rolling assembly 5 and a second connecting hole 42 connected with the Z-shaped mounting plate 526; the roller assembly, the load cell 4, and the main beam 21 are coupled as a unit through the first coupling hole 41 and the second coupling hole 42.
Through this scheme, can be steady contact and lift the aircraft wheelset, furthest reduces the damage to the aircraft wheelset, can accurately adjust the shrink length through flexible adjusting part, along with the regulation of shrink length, can accurately adjust the rigidity that lifts of aircraft wheelset, accomplish the back of lifting to the aircraft, realize the collection to aircraft gravity through weighing sensor 4.
Example 2
Based on the above embodiment 1, the present embodiment provides a self-lifting type aircraft weighing adjustment system, which includes a plurality of self-lifting type aircraft weighing devices, each self-lifting type aircraft weighing device contacts with one aircraft wheel set, and through the ground clearance which does not pass through the aircraft wheel set, the pitching degree adjustment of the whole aircraft can be realized, the bearing gesture of the aircraft is adjusted, and the stability and safety of bearing are ensured.
The working process of the scheme comprises the following steps:
1. all three weighing devices are in a full-extension state of the hydraulic actuator cylinder, and the distance between main beams 21 of the second receiving arms 3 of the first receiving arm 2 is the maximum width;
2. the three weighing devices are respectively arranged below the front landing gear, the left main landing gear and the right main landing gear, and the hydraulic pedal 14 is simultaneously operated, so that the self-lifting type airplane weighing device lifts the airplane wheels to a proper height;
3. and locking the weighing equipment, and stably reading weight data to finish weighing.
The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the utility model.
Claims (10)
1. A self-elevating aircraft weighing apparatus, characterized by: the device comprises a telescopic adjusting assembly, a first bearing arm, a second bearing arm, a weighing sensor and a rolling assembly; the first bearing arm and the second bearing arm are respectively arranged at two sides of the telescopic adjusting assembly, and the relative position between the first bearing arm and the second bearing arm can be changed through the telescopic adjusting assembly; the rolling assembly is connected with the first bearing arm and the second bearing arm respectively, and the weighing sensor is arranged at the joint of the rolling assembly and the first bearing arm or the first bearing arm.
2. A self-elevating aircraft weighing apparatus as set forth in claim 1, wherein: the telescopic adjusting assembly comprises a sliding outer sleeve, a sliding inner cylinder, a hydraulic action cylinder and a hydraulic pedal; the sliding outer sleeve is sleeved at the outer side of the sliding inner cylinder, so that the sliding outer sleeve can move freely relative to the sliding inner cylinder; the telescopic rod of the hydraulic action cylinder is fixedly connected with the sliding inner cylinder, the body of the hydraulic action cylinder is fixedly connected with the sliding shell, and the hydraulic pedal is connected with the hydraulic action cylinder.
3. A self-elevating aircraft weighing apparatus as set forth in claim 2, wherein: the first bearing arm comprises a main beam, a sleeve and a rolling column; the main beam is sleeved in the sleeve, and the rolling column is arranged at a position between the main beam and the sleeve.
4. A self-elevating aircraft weighing apparatus as set forth in claim 3 wherein: the number of the rolling columns is at least 2 around the girder at the position between the girder and the sleeve.
5. A self-elevating aircraft weighing apparatus as set forth in claim 4 wherein: the sliding inner cylinder is connected with the main beam of the first bearing arm or the second bearing arm, and the sliding outer sleeve is connected with the main beam on the opposite side.
6. A self-elevating aircraft weighing apparatus as set forth in claim 5, wherein: and a Z-shaped mounting plate is arranged between the main beam and the weighing sensor.
7. A self-elevating aircraft weighing apparatus as set forth in claim 6 wherein: the maximum value of the width between the main beam of the first bearing arm and the main beam of the second bearing arm is not smaller than the diameter of an aircraft tire, and the minimum value is not smaller than the radius of the aircraft tire.
8. A self-elevating aircraft weighing apparatus as set forth in claim 7 wherein: the rolling assembly comprises a rolling wheel and a mounting plate; the mounting plate is arranged at the top of the rolling wheel, and mounting holes matched with the weighing sensors are formed in the mounting plate.
9. A self-elevating aircraft weighing apparatus as set forth in claim 8, wherein: the weighing sensor is provided with a first connecting hole connected with the rolling assembly and a second connecting hole connected with the Z-shaped mounting plate.
10. A self-elevating aircraft weight adjustment system, characterized in that: a self-elevating aircraft weighing apparatus as claimed in any one of claims 1 to 9, each self-elevating aircraft weighing apparatus being in contact with one of the aircraft wheel sets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221513092.XU CN218916509U (en) | 2022-06-17 | 2022-06-17 | Self-lifting type aircraft weighing equipment and adjusting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221513092.XU CN218916509U (en) | 2022-06-17 | 2022-06-17 | Self-lifting type aircraft weighing equipment and adjusting system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218916509U true CN218916509U (en) | 2023-04-25 |
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ID=86045359
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221513092.XU Active CN218916509U (en) | 2022-06-17 | 2022-06-17 | Self-lifting type aircraft weighing equipment and adjusting system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218916509U (en) |
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2022
- 2022-06-17 CN CN202221513092.XU patent/CN218916509U/en active Active
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