CN220332944U - Wing load simulation device convenient for load adjustment - Google Patents
Wing load simulation device convenient for load adjustment Download PDFInfo
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- CN220332944U CN220332944U CN202321826852.7U CN202321826852U CN220332944U CN 220332944 U CN220332944 U CN 220332944U CN 202321826852 U CN202321826852 U CN 202321826852U CN 220332944 U CN220332944 U CN 220332944U
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- 238000004088 simulation Methods 0.000 title claims abstract description 33
- 230000000670 limiting effect Effects 0.000 claims abstract description 24
- 238000003825 pressing Methods 0.000 claims abstract description 18
- 238000001514 detection method Methods 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 7
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 abstract description 4
- 239000010959 steel Substances 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 16
- 238000000034 method Methods 0.000 description 10
- 230000005484 gravity Effects 0.000 description 9
- 230000001105 regulatory effect Effects 0.000 description 7
- 238000012360 testing method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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Abstract
The utility model discloses a wing load simulation device convenient for adjusting load, which comprises a movable load simulation structure serving as a bottom support, wherein one side above the movable load simulation structure is provided with a clamping limiting structure for limiting wing placement, the movable load simulation structure comprises a mounting plate with a plurality of universal wheels at the bottom, one side above the mounting plate is provided with a matching groove which is convenient for the supporting connection of parts of the clamping limiting structure, meanwhile, the mounting plate is provided with a movable connecting piece which is movably connected with a movable adjusting rod through a connecting seat, one end lower part of the movable adjusting rod is sequentially connected with an adjusting cylinder through the movable connecting piece, the other end of the movable adjusting rod is provided with an adjusting head with a mounting groove, and a pressing block for driving and adjusting is arranged below the adjusting head through a steel wire rope.
Description
Technical Field
The utility model relates to the technical field of wings, in particular to a wing load simulation device convenient for adjusting load.
Background
The wing is a component part of the whole aircraft, and the weight of the wing determines the flight life and service life effect of the whole aircraft, so that the wing needs to be subjected to load simulation experiment processing after manufacture to obtain effective and accurate load simulation data so as to ensure the flight life effect of the wing, the existing load simulation loading device generally adopts a direct loading mode, weights are suspended at the gravity center position of the wing to simulate the folding gravity load of the wing, the weights easily move and swing transversely along with the movement of the wing in the loading process, the stability and the load simulation precision of the testing process are affected, and the loading mode of the weights is difficult to simulate the actual gravity load data condition of the vertical position of the wing.
Disclosure of Invention
The utility model aims to provide a wing load simulation device convenient for adjusting load, aiming at overcoming the defects of the prior art, and solving the problems that the prior load simulation loading device proposed in the prior art generally adopts a direct loading mode, weights are hung at the gravity center position of a wing to simulate the folding gravity load of the wing, the weights easily move and swing transversely along with the movement of the wing in the loading process, the stability and the load simulation precision of the testing process are influenced, and the actual data condition of the gravity load at the vertical position of the wing is difficult to simulate by directly using the loading mode of the weights.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the wing load simulation device convenient for adjusting the load comprises a movable load simulation structure serving as a bottom support, wherein a clamping limiting structure for limiting the placement of a wing is arranged on one side above the movable load simulation structure;
the movable load simulation structure comprises a mounting plate with a plurality of universal wheels arranged at the bottom, a supporting groove which is convenient for supporting and connecting parts of the clamping limiting structure is formed in one side above the mounting plate, a movable connecting piece which is movably connected with the movable adjusting rod is arranged on the mounting plate through a connecting seat, and one end lower part of the movable adjusting rod is connected with the adjusting cylinder through the movable connecting piece.
Through adopting above-mentioned technical scheme, thereby through the universal wheel that sets up, play and remove static locking effect.
Preferably, the movable adjusting rod is provided with an adjusting head with an installing groove at the other end, a pressing block for driving and adjusting is arranged below the adjusting head through a steel wire rope, and a fixing plate for installing and arranging a driving cylinder is arranged at the inner side of the adjusting head through the installing groove.
Through adopting above-mentioned technical scheme, thereby through the wire rope that sets up play two-way connection setting effect.
Preferably, the output end of the driving cylinder is provided with an adjusting block, and a pressure detection module is arranged below the adjusting block.
Through adopting above-mentioned technical scheme, thereby play vertical drive regulation effect through the regulating block that sets up.
Preferably, the clamping limiting structure comprises a concave block seat with a connecting hole formed in the upper portion, the concave block seat is movably arranged with the pressing plate through a connecting pin, meanwhile, one side of the pressing plate is provided with a limiting hole penetrating through the connecting hole, and one side of the pressing plate is provided with a handle which is convenient for an operator to hold and adjust manually.
Through adopting above-mentioned technical scheme, thereby play activity regulation pressure material spacing effect through the clamp plate that sets up.
Preferably, the bottom of the concave block seat is provided with a matched block which is matched and connected with the matched groove, and the matched block and the matched groove are in sliding matched and connected.
Through adopting above-mentioned technical scheme, thereby set up and place the setting effect through the concave block seat that sets up.
Preferably, the matched grooves are provided with 1 group, and the matched grooves are symmetrically arranged on one side of the mounting plate.
Through adopting above-mentioned technical scheme, thereby play the supporting connection setting effect of sliding through the supporting groove of seting up.
Compared with the prior art, the utility model has the beneficial effects that: the wing load simulation device convenient for adjusting the load,
(1) The present case is by setting up: the clamping limiting structure is used for solving the problems that the existing load simulation loading device generally adopts a direct loading mode, weights are hung at the gravity center position of a wing to simulate folding gravity load of the wing, the weights are easy to move transversely and swing along with the movement of the wing in the loading process, stability and load simulation precision of the testing process are affected, when the wing needs load simulation, an operator manually places the wing in a concave block seat, when the wing is placed in the concave block seat, the operator manually adjusts the relative stress adjustment movement of the concave block seat, when the concave block seat is relatively adjusted to a corresponding interval distance, the operator manually utilizes a pressing plate to press and limit the upper part of the wing, at the moment, the connecting pin penetrates through a limiting hole to limit and fix the pressing plate, and therefore the situation is avoided after the whole wing is clamped and fixed;
(2) By setting up: the movable load simulation structure solves the problem that the loading mode of the weight is difficult to simulate the actual data condition of the gravity load at the vertical position of the wing, when the wing load is simulated, an operator controls the adjusting cylinder to work, the adjusting cylinder is used for carrying out load simulation on the upper part of the wing through the pressing block in the working process of the adjusting cylinder, when the force of the load is required to be adjusted, the operator controls the driving cylinder to work, the driving cylinder is driven to drive the adjusting block to synchronously bear force in the working process of the driving cylinder, when the adjusting block and the pressing block bear force, the pressure detection module displays the load pressure output by the driving cylinder on the controller, so that the operator can conveniently and intuitively check the wing load module data, and meanwhile, the situation is avoided by utilizing the arranged movable load simulation structure.
Drawings
FIG. 1 is a schematic diagram of a front cross-sectional structure of the present utility model;
FIG. 2 is a schematic diagram of the structure of the mounting plate, the universal wheel, the matching groove, the connecting seat, the movable connecting piece, the movable adjusting rod, the adjusting cylinder, the adjusting head, the steel wire rope, the pressing block, the driving cylinder, the adjusting block and the pressure detecting module;
FIG. 3 is a schematic view of the structure of the adjustment head and the mounting groove of the present utility model;
fig. 4 is a schematic view of a clamping and limiting structure of the present utility model.
In the figure: 1. a moving load simulation structure; 101. a mounting plate; 102. a universal wheel; 103. a mating groove; 104. a connecting seat; 105. a movable connecting piece; 106. a movable adjusting rod; 107. adjusting a cylinder; 108. adjusting the head; 109. a mounting groove; 1010. a wire rope; 1011. briquetting; 1012. a driving cylinder; 1013. an adjusting block; 1014. a pressure detection module; 2. clamping and limiting structures; 201. a concave block seat; 202. a pressing plate; 203. and (5) a matching block.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-4, the present utility model provides a technical solution: the utility model provides a wing load analogue means convenient to adjust load, as shown in fig. 1, fig. 2 and fig. 3, including the removal load analogue means 1 as bottom sprag, remove load analogue means 1 and be equipped with the mounting panel 101 of a plurality of universal wheels 102 including the bottom, and the supporting groove 103 that makes things convenient for the supporting connection setting of centre gripping limit structure 2 spare part is seted up to mounting panel 101 top one side, 1 group has been seted up to supporting groove 103, and supporting groove 103 sets up with mounting panel 101 one side symmetry, when 1 group is two through above-mentioned structure, so not only embody the practicality that the setting was seted up to above-mentioned structure, still embody the supporting connectivity and the relative sliding adjustability effect of atress that the setting was seted up to above-mentioned structure, and when having seted up 1 group by above-mentioned structure, also embody symmetry and the symmetry matching connectivity effect that the setting was seted up to above-mentioned structure, be equipped with the movable connection piece 105 that sets up with movable adjusting lever 106 swing joint through movable connection piece 105 and adjusting cylinder 107 are connected in proper order on mounting panel 101, wherein, above-mentioned spare part all adopts prior art spare part installation setting, when utilizing the installation setting of prior art spare part, when utilizing the installation setting of effective utilization and set up and play the regulation effect on the structure and play the structural rotation and effectively and play the regulation spare part simultaneously.
The scheme is further that the movable adjusting rod 106 other end is equipped with the adjusting head 108 of taking mounting groove 109, and adjusting head 108 below is equipped with the briquetting 1011 of drive regulation through wire rope 1010, simultaneously adjusting head 108 is equipped with the fixed plate that sets up the installation of drive cylinder 1012 through the mounting groove 109 inboard, wherein, above-mentioned spare part adopts prior art spare part installation setting equally, equally effectually play atress stretching and atress drive regulation effect when utilizing prior art spare part installation setting, briquetting 1011 adopts the briquetting 1011 of 10N pressure to install the setting simultaneously, so effectually to the preliminary 10N pressure load simulation detection effect of wing.
The scheme is further in turn, the output end of the driving cylinder 1012 is provided with the regulating block 1013, and the pressure detection module 1014 is arranged below the regulating block 1013, wherein the components are installed and arranged by adopting the prior art components, the driving regulating effect is also effectively achieved when the prior art components are installed and arranged, meanwhile, the components form the lifting regulating structure, and the load value effect is effectively changed and regulated by effectively gradually increasing the corresponding applied pressure when the lifting driving regulating structure formed by the components is utilized.
As shown in fig. 4, a clamping and limiting structure 2 for limiting wing placement is arranged on one side above the movable load simulation structure 1, the clamping and limiting structure 2 comprises a concave block seat 201 with a connecting hole formed in the upper side, the concave block seat 201 is movably arranged with a pressing plate 202 through a connecting pin, meanwhile, a limiting hole penetrating through the connecting hole is formed in one side of the pressing plate 202, a handle convenient for an operator to manually hold and adjust is arranged on one side of the pressing plate 202 in sequence, wherein the parts are installed and arranged in the prior art, the effects of opening and movably connecting are effectively achieved when the prior art parts are installed and arranged, and meanwhile, the concave block seat 201 is arranged in the concave block structure, so that the connecting hole is effectively penetrated and the limiting effect of movable adjustment is achieved for the pressing plate 202.
In the above scheme, the bottom of the concave block seat 201 is provided with a matching block 203 which is matched with the matching groove 103, and the matching block 203 and the matching groove 103 are in sliding matching connection.
In the above scheme, when the wing load simulation device is carried out, an operator manually holds the concave block seat 201 to apply relative thrust, at this moment, the concave block seat 201 drives the matched block 203 to move relatively with the matched groove 103 and the mounting plate 101 under stress, when the concave block seat 201 is adjusted at a corresponding interval distance, the operator manually places the wing on the concave block seat 201, meanwhile, the operator presses and limits the upper part of the wing through the grip, meanwhile, the connecting pin penetrates through the connecting hole and the limiting hole to limit the pressure plate 202, at this moment, the operator controls the adjusting cylinder 107 to work, the adjusting cylinder 107 drives the adjusting head 108, the steel wire rope 1010 and the pressure block 1011 to synchronously move under stress through the movable adjusting rod 106 in the working process, when the pressure block 1011 is in stressed contact with the upper center of the wing, the wing is stressed and bent, when the load force needs to be changed, the operator controls the driving cylinder 1012 to work, the adjusting block 1013 is driven to be in stressed contact with the pressure block 1011 in the working process, and the pressure detection module 1014 transmits detected pressure data to the display.
The terms "center," "longitudinal," "transverse," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used for descriptive simplicity and convenience only and not as an indication or implying that the apparatus or element being referred to must have a particular orientation, be constructed and operated for a particular orientation, based on the orientation or positional relationship illustrated in the drawings, and thus should not be construed as limiting the scope of the present utility model.
Although the present utility model has been described with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements and changes may be made without departing from the spirit and principles of the present utility model.
Claims (6)
1. The utility model provides a wing load simulation device convenient to adjust load, is including moving load simulation structure (1) as bottom sprag, its characterized in that: a clamping and limiting structure (2) for limiting the wing placement is arranged on one side above the movable load simulation structure (1);
the movable load simulation structure (1) comprises a mounting plate (101) with a plurality of universal wheels (102) arranged at the bottom, a supporting groove (103) which is convenient for supporting connection and setting of components of the clamping limiting structure (2) is formed in one side above the mounting plate (101), meanwhile, a movable connecting piece (105) which is movably connected with a movable adjusting rod (106) is arranged on the mounting plate (101) through a connecting seat (104), and one end lower part of the movable adjusting rod (106) is connected with an adjusting cylinder (107) through the movable connecting piece (105) in sequence.
2. A wing load simulator for facilitating load adjustment according to claim 1, wherein: the movable adjusting rod (106) other end is equipped with adjustment head (108) of taking mounting groove (109), and is equipped with briquetting (1011) of drive regulation through wire rope (1010) below adjustment head (108), and adjustment head (108) are equipped with the fixed plate to drive cylinder (1012) installation setting through mounting groove (109) inboard simultaneously.
3. A wing load simulator for facilitating load adjustment according to claim 2, wherein: an adjusting block (1013) is arranged at the output end of the driving cylinder (1012), and a pressure detection module (1014) is arranged below the adjusting block (1013).
4. A wing load simulator for facilitating load adjustment according to claim 1, wherein: the clamping limiting structure (2) comprises a concave block seat (201) with a connecting hole formed in the upper portion, the concave block seat (201) is movably arranged with the pressing plate (202) through a connecting pin, meanwhile, one side of the pressing plate (202) is provided with a limiting hole penetrating through the connecting hole, and one side of the pressing plate (202) is provided with a handle which is convenient for an operator to hold and adjust manually.
5. A wing load simulator for facilitating load adjustment according to claim 4, wherein: the bottom of the concave block seat (201) is provided with a matched block (203) which is matched and connected with the matched groove (103), and the matched block (203) and the matched groove (103) are in sliding matched and connected.
6. A wing load simulator for facilitating load adjustment according to claim 1, wherein: the matched grooves (103) are formed in 1 group, and the matched grooves (103) are symmetrically formed in one side of the mounting plate (101).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321826852.7U CN220332944U (en) | 2023-07-12 | 2023-07-12 | Wing load simulation device convenient for load adjustment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321826852.7U CN220332944U (en) | 2023-07-12 | 2023-07-12 | Wing load simulation device convenient for load adjustment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220332944U true CN220332944U (en) | 2024-01-12 |
Family
ID=89457016
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321826852.7U Active CN220332944U (en) | 2023-07-12 | 2023-07-12 | Wing load simulation device convenient for load adjustment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220332944U (en) |
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2023
- 2023-07-12 CN CN202321826852.7U patent/CN220332944U/en active Active
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