CN205209734U - Balance installation base - Google Patents
Balance installation base Download PDFInfo
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- CN205209734U CN205209734U CN201521008463.9U CN201521008463U CN205209734U CN 205209734 U CN205209734 U CN 205209734U CN 201521008463 U CN201521008463 U CN 201521008463U CN 205209734 U CN205209734 U CN 205209734U
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- mounting seat
- balance
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- installation base
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Abstract
The utility model relates to an aircraft wind tunnel test technology field, in particular to balance installation base to at least, solve the inconvenient problem of torgue measurement balance installation. Balance installation base includes: installation base body, fixed mounting on full fuselage model, seted up on installation base body one with meet an emergency body shape assorted recess, the body of meeting an emergency is located the recess, and meets an emergency the body through first fixed part and installation base body fixed connection. The utility model discloses a balance installation base more convenient and fast ground meets an emergency body fixed mounting on full fuselage model in with the torgue measurement balance, in addition, the body of will meeting an emergency install with the body shape assorted recess of meeting an emergency, in the time of can preventing to test the installation base body lead to the fact the interference to the body of meeting an emergency to influence the accuracy of experimental result.
Description
Technical field
The utility model relates to aircraft wind-tunnel technique field, particularly a kind of balance mounting seat.
Background technology
The hinge moment of the rudder face of aircraft refers to the air torque that the air-flow flowing through rudder face is formed rudderpost.The catanator of aircraft is generally the deflection being controlled rudder face by mechanical transfer, in order to make control surface deflection to the position of needs, must overcome the hinge moment acted on rudderpost.
The rudder face of aircraft, as flaperon, elevating rudder, flying tail, yaw rudder, front wing etc., all needs to measure its aerodynamic quality in wind-tunnel, and wherein, the hinge moment of rudder face is the important evidence of design aircraft control system.Therefore, need to be measured accurately control surface hinge moment by wind tunnel test, during measurement, normally measured by such as three-component balance, four COMPONENT BALANCE etc.; Particularly, be provided with multiple balance beam be arranged in parallel along rudder face length direction interval, according to the distance between the stressing conditions on each balance that measurement obtains and balance, calculate with the product of distance the hinge moment obtaining rudder face by stressed.
Current a kind of torgue measurement balance, as depicted in figs. 1 and 2, comprises strain body 2, first fixed part 22, second fixed part 23 and foil gauge 21; First fixed part 22 one end is fixedly connected with full machine airframe models 14, and the other end is fixedly connected with one end of strain body 2; Second fixed part 23 one end is fixedly connected with one end away from the first fixed part 22 of strain body 2, and the other end is fixedly connected with rotating shaft 12; Foil gauge 21 is arranged on strain body 2 upper surface, for when straining body 2 and bending distortion occurring under rotating shaft 12 acts on, and the strain data of monitor strain body 2.
But being fixedly connected with full machine airframe models by means of only the first fixed part of above-mentioned torgue measurement balance, installs location inconvenience, and the first fixed part straining body easily comes in contact with full machine airframe models, thus affects the accuracy of strain data.
Summary of the invention
The purpose of this utility model there is provided a kind of balance mounting seat, installs inconvenient problem to solve torgue measurement balance.
The technical solution of the utility model is:
A kind of balance mounting seat, for the strain body being arranged in full machine airframe models torgue measurement balance is installed, wherein, operating surface model is arranged on wing-body model by axis of rotation, and one end of described rotating shaft extend in described full machine airframe models, described balance mounting seat comprises:
Mounting seat body, be fixedly mounted on described full machine airframe models, described mounting seat body offers a groove matched with described strain body shape, described strain body is positioned at described groove, and described strain body is fixedly connected with described mounting seat body by the first fixed part.
Optionally, described groove takes the shape of the letter U, the first fixed part of described strain body be bolted be arranged on the U-shaped bottom position place being positioned at described groove described mounting seat body on.
Optionally, the described mounting seat body being positioned at the U-shaped open end of described groove offers axis hole, described axis hole comprises two, be symmetricly set on the both sides of the U-shaped openend of described groove, and described axis hole and described rotating shaft clearance fit, described rotating shaft is fixedly connected with described strain body through after described axis hole.
The utility model has the advantage of:
Balance mounting seat of the present utility model, for the strain body in torgue measurement balance is fixedly mounted on full machine airframe models, makes torgue measurement balance install more convenient; In addition, mounting seat body offers a groove matched with strain body shape, is arranged in groove by strain body, when can prevent from testing, mounting seat body causes interference to strain body, thus affects the accuracy of experimental result.
Accompanying drawing explanation
Fig. 1 is and the structural representation of the utility model balance mounting seat with the torgue measurement balance matched;
Fig. 2 is the model in wind tunnel schematic diagram using the utility model balance mounting seat and torgue measurement balance;
Fig. 3 is the structural representation of the utility model balance mounting seat;
Fig. 4 is the structural representation after the utility model balance mounting seat coordinates with torgue measurement balance.
Embodiment
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.
Below in conjunction with accompanying drawing 1 to Fig. 4, the utility model balance mounting seat is described in further details.
The utility model provides a kind of balance mounting seat, for the strain body 2 in torgue measurement balance is fixedly mounted on full machine airframe models 14.
As depicted in figs. 1 and 2, torgue measurement balance is used for measuring the rudder face moment of operating surface model 11; Usually, rudder face torgue measurement test comprises the test model be arranged in wind-tunnel, and test model can comprise full machine airframe models 14 for simulating prototype fuselage, for simulating the wing-body model 13 of prototype wing and the operating surface model 11 for simulating prototype operation rudder face; In addition, operating surface model 11 is rotated by rotating shaft 12 to be arranged on wing-body model 13, and rotating shaft 12 extend in described full machine airframe models 14 towards full machine airframe models 14 direction.
Torgue measurement balance can comprise strain body 2 and foil gauge 21.Strain body 2 is arranged along perpendicular to rotating shaft 12 axis direction, one end of strain body 2 is fixedly connected with full machine airframe models 14 (as bending fulcrum), the other end is fixedly connected with rotating shaft 12, that is to say the bending that the other end of strain body 2 can carry out to a certain degree for fulcrum with its one end.
Foil gauge 21 is arranged on strain body 2 upper surface, for when straining body 2 and bending distortion occurring under rotating shaft 12 acts on, and the strain data of monitor strain body 2.Strain data again by obtaining can calculate rudder face moment, and structural principle is simple.
Further, the first fixed part 22 and the second fixed part 23 is also comprised in torgue measurement balance.First fixed part 22 one end is fixedly connected with full machine airframe models 14, and the other end is fixedly connected with one end of strain body 2.Second fixed part 23 one end is fixedly connected with one end away from the first fixed part 22 of strain body 2, and the other end offers the mounting hole 24 matched with rotating shaft 12, and rotating shaft 12 is fixedly mounted in mounting hole 24 by bolt (not shown).Further, the first fixed part 22 and strain body 2 are formed in one component, are bolted that to be arranged on full machine airframe models 14 inner.
Have the kink 25 of a U-shaped in the centre position of strain body 2, the U-shaped opening of kink 25 is towards the upper surface straining body 2.
Especially as shown in Figure 3 and Figure 4, balance mounting seat of the present utility model can comprise mounting seat body 3.Mounting seat body 3 can adopt multiple applicable planform, be fixedly mounted on full machine airframe models 14 by modes such as bolts, mounting seat body 3 offers one with the groove 31 of strain body 2 mating shapes, strain body 2 is positioned at groove 31, and strain body 2 is fixedly connected with mounting seat body 3 by the first fixed part 22.
In balance mounting seat of the present utility model, the strain body in torgue measurement balance can be fixedly mounted on full machine airframe models 14 more for convenience by mounting seat body 3; In addition, be arranged on by strain body 2 in groove 31, when can prevent from testing, mounting seat body 2 causes interference to strain body 2, thus affects the accuracy of experimental result.
Further, mounting seat body 3 obtains groove 31 and takes the shape of the letter U, strain body 2 the first fixed part be bolted be arranged on the U-shaped bottom position place being positioned at groove 31 mounting seat body 3 on.And, the mounting seat body 3 of U-shaped open end being positioned at groove 31 can also offer axis hole 32, axis hole 32 comprises two (matching with mounting hole 24 position on above-mentioned second fixed part 23), be symmetricly set on the both sides of the U-shaped openend of groove 31, and axis hole 32 and rotating shaft 12 clearance fit, second fixed part 23 is between two axis holes 32, stability is stronger, rotating shaft 12 is fixedly connected with strain body 2 through after axis hole 32, can prevent axis hole 32 countershaft 12 from causing interference on the one hand, affect test findings accuracy, on the other hand, rotating shaft 12 lateral deflection between these two axis holes 32 can also be limited.
The above; be only embodiment of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed within protection domain of the present utility model.
Claims (3)
1. a balance mounting seat, for the strain body (2) being arranged in full machine airframe models (14) torgue measurement balance is installed, wherein, operating surface model (11) is rotated by rotating shaft (12) to be arranged on wing-body model (13), and one end of described rotating shaft (12) extend in described full machine airframe models (14), it is characterized in that, described balance mounting seat comprises:
Mounting seat body (3), be fixedly mounted on described full machine airframe models (14), described mounting seat body (3) offers one with the groove (31) of described strain body (2) mating shapes, described strain body (2) is positioned at described groove (31), and described strain body (2) is fixedly connected with described mounting seat body (3) by the first fixed part (22).
2. balance mounting seat according to claim 1, it is characterized in that, described groove (31) takes the shape of the letter U, the first fixed part of described strain body (2) be bolted be arranged on the U-shaped bottom position place being positioned at described groove (31) described mounting seat body (3) on.
3. balance mounting seat according to claim 2, it is characterized in that, the described mounting seat body (3) being positioned at the U-shaped open end of described groove (31) offers axis hole (32), described axis hole (32) comprises two, be symmetricly set on the both sides of the U-shaped openend of described groove (31), and described axis hole (32) and described rotating shaft (12) clearance fit, described rotating shaft (12) is fixedly connected with described strain body (2) afterwards through described axis hole (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521008463.9U CN205209734U (en) | 2015-12-07 | 2015-12-07 | Balance installation base |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521008463.9U CN205209734U (en) | 2015-12-07 | 2015-12-07 | Balance installation base |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205209734U true CN205209734U (en) | 2016-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521008463.9U Active CN205209734U (en) | 2015-12-07 | 2015-12-07 | Balance installation base |
Country Status (1)
| Country | Link |
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| CN (1) | CN205209734U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768831A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of dummy vehicle rudder face connection combination apparatus |
-
2015
- 2015-12-07 CN CN201521008463.9U patent/CN205209734U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768831A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of dummy vehicle rudder face connection combination apparatus |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 |
|
| TR01 | Transfer of patent right |