CN111216922A - Lifting force testing device of cross dual-rotor helicopter - Google Patents
Lifting force testing device of cross dual-rotor helicopter Download PDFInfo
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- CN111216922A CN111216922A CN202010322484.7A CN202010322484A CN111216922A CN 111216922 A CN111216922 A CN 111216922A CN 202010322484 A CN202010322484 A CN 202010322484A CN 111216922 A CN111216922 A CN 111216922A
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- base
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- mounting plate
- arc
- positioning holes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The application discloses two rotor helicopter lift testing arrangement alternately includes: a rack; a sensor disposed on the gantry; the collector is in communication connection with the sensor; the mounting plate is arranged on the top of the sensor and connected with the sensor; the base plates are arranged on the mounting plate, and the mounting positions of the base plates on the mounting plate can be changed, so that the distance between different base plates can be changed; the rotary device comprises a base, a plurality of rotary bodies arranged on the base in a one-to-one mode, wherein the arrangement angles of the rotary bodies on the base can be changed, so that the included angles between power shafts connected to the rotary bodies and the mounting plates can be changed. The lifting force testing device of the cross double-rotor helicopter can realize the testing of the lifting force of the rotors of the cross double-rotor helicopter.
Description
Technical Field
The invention relates to the technical field of helicopters, in particular to a lifting force testing device of a cross double-rotor helicopter.
Background
The crossed double-rotor helicopter is provided with two pairs of rotors which are completely the same and have opposite rotating directions, the main shafts of the two rotors are not parallel and are respectively inclined towards the outside, and the transverse wheelbase is very small, so that the two pairs of rotors are crossed above the helicopter body. The size of the included angle between the two rotor main shafts and the size of the distance between the two rotor main shafts can influence the lift force, the resistance and the required power of the rotors, so that a group of proper included angles and distances are very necessary in the design process, but a device for testing the included angle and the distance between the two rotor main shafts does not exist in the prior art, and inconvenience is brought to the design of the crossed dual-rotor helicopter.
Disclosure of Invention
In view of this, the invention provides a device for testing the lift force of a cross dual-rotor helicopter, which can test the lift force of the rotors of the cross dual-rotor helicopter.
In order to achieve the purpose, the invention provides the following technical scheme:
a cross dual rotor helicopter lift testing arrangement includes:
a rack;
a sensor disposed on the gantry;
the collector is in communication connection with the sensor;
the mounting plate is arranged on the top of the sensor and connected with the sensor;
the base plates are arranged on the mounting plate, and the mounting positions of the base plates on the mounting plate can be changed, so that the distance between different base plates can be changed;
the rotary device comprises a base, a plurality of rotary bodies arranged on the base in a one-to-one mode, wherein the arrangement angles of the rotary bodies on the base can be changed, so that the included angles between power shafts connected to the rotary bodies and the mounting plates can be changed.
Preferably, among the above-mentioned cross double rotor helicopter lift test device, be provided with the recess on the base, the diapire of recess is the cambered surface diapire, the rotator can hold in the recess and have with the cambered surface rotation wall that the cambered surface diapire matches, the cambered surface rotation wall through with the contact of cambered surface diapire and rotate on the cambered surface diapire, realize the rotator and last the change of power shaft's the angle that sets up, and the cambered surface diapire with the centre of a circle of cambered surface rotation wall is the axle center of power shaft.
Preferably, in the above lifting force testing device for a cross twin-rotor helicopter, a plurality of first positioning holes are formed in the side wall of the groove, the connecting line of the first positioning holes is an arc line, and the arc line is concentric with the bottom wall of the arc line; the rotating body is provided with a plurality of second positioning holes which can be aligned with the first positioning holes, and the positioning piece can realize the positioning of the rotating body on the base by being inserted into the aligned first positioning holes and the aligned second positioning holes.
Preferably, among the above-mentioned double rotor helicopter lift testing arrangement that crosses, all first locating hole is in be many pitch arcs on the base and set up, all the centre of a circle of pitch arc is the same, and is located on the adjacent pitch arc first locating hole dislocation set.
Preferably, among the above-mentioned cross double rotor helicopter lift test device, every first screw hole has all been seted up on the bottom surface of base, set up a plurality of evenly distributed's second screw hole on the mounting panel, first screw hole is through with the difference the second screw hole is adjusted well and by bolted connection, can realize the base is in the setting of the different positions of mounting panel is in order to change the difference interval between the base.
Preferably, in the above-mentioned cross twin-rotor helicopter lift test apparatus, the sensor is a cantilever type tension-compression sensor.
Preferably, in the above-mentioned cross double rotor helicopter lift testing arrangement, the rack includes the support frame and sets up the welding frame on support frame top, the sensor is fixed to be set up on the welding frame.
Preferably, in the above-mentioned cross bispin helicopter lift test device, the bottom of support frame is provided with the rag connecting plate, be connected with rag bolt on the rag connecting plate.
Preferably, in the above-mentioned cross double rotor helicopter lift test device, the support frame forms fretwork form support through the concatenation of a plurality of aluminium alloy.
Preferably, in the above-mentioned cross double rotor helicopter lift test device, offer on the bottom surface of mounting panel and dodge the groove.
According to the lifting force testing device of the cross dual-rotor helicopter, the included angle between the two rotor main shafts of the cross dual rotor can be changed by changing the arrangement angle of the rotating body on the base, the distance between the two rotor main shafts of the cross dual rotor can be changed by changing the installation positions of the two bases on the installation plate, then the collector performs zero clearing operation, the lifting force generated by the rotor can be tested by driving the rotor to rotate through the transmission system and the power system of the cross dual-rotor helicopter, at the moment, the data collected by the collector is the lifting force generated by the rotor of the cross dual rotor helicopter, the structure is simple, the processing and the assembly are convenient, the research and development cost can be reduced, the operation is simple, and convenience is brought to the design of the cross dual rotor helicopter.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a lift force testing device of a cross twin-rotor helicopter provided in an embodiment of the present invention;
FIG. 2 is a schematic view of a structure of a lift testing device of a cross twin-rotor helicopter in cooperation with a bevel gear box;
FIG. 3 is a schematic structural view of the base and the rotating body;
FIG. 4 is a schematic view of the mounting plate;
fig. 5 is a structural schematic diagram of the gantry.
In the above fig. 1-5:
1-a gantry; 11-support frame, 12-welding frame;
2-a sensor;
3, mounting a plate; 311-a second threaded hole, 312-a connecting hole, 313-an avoidance groove;
4-a base; 411-a first positioning hole, 412-a first threaded hole;
5-a rotating body; 511-a second positioning hole;
6-bevel gearbox.
Detailed Description
The invention provides a device for testing the lift force of a cross double-rotor helicopter, which can test the lift force of the rotors of the cross double-rotor helicopter.
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 to 5, an embodiment of the present invention provides a lift testing device for a cross-twin-rotor helicopter, for testing the lift of a rotor of the cross-twin-rotor helicopter, where the lift testing device includes a rack 1, a sensor 2, a collector (not shown in the figure), a mounting plate 3, a base 4, and a rotator 5, where the rack 1 supports the sensor 2, the mounting plate 3, the base 4, the rotator 5, and other components of the lift testing device; the sensor 2 arranged on the rack 1 is in communication connection with the collector through a wire, the sensor 2 can sense the stress of the mounting plate 3, and the collector is used for converting a voltage signal in the sensor 2 into an analog signal and directly displaying the numerical value of the sensor 2 through software processing; the mounting plate 3 is arranged on the top of the sensor 2 and connected with the sensor 2; the bases 4 are arranged on the mounting plate 3, the number of the bases 4 is multiple, preferably two in the embodiment, and the mounting positions of the bases 4 on the mounting plate 3 can be changed, so that the distance between different bases 4 (namely two bases 4) can be changed; the rotating bodies 5 are arranged on the bases 4 one by one, namely the number of the rotating bodies 5 is the same as that of the bases 4, only one rotating body 5 is arranged on each base 4, the two bases 4 are preferred, so the rotating bodies 5 are also preferred, the arrangement angle of the rotating bodies 5 on the bases 4 can be changed, and the included angle between a power shaft connected to the rotating bodies 5 and the mounting plate 3 can be changed. Wherein, the power shaft refers to the input shaft of the bevel gear box 6 in the transmission system of the dual-rotor helicopter, namely the horizontally arranged shaft in fig. 2. The collector is an existing instrument.
As shown in fig. 3, it is preferable that a groove is formed in the base 4, a bottom wall of the groove is an arc bottom wall, the rotating body 5 can be accommodated in the groove, and the rotating body 5 has an arc rotating wall matched with the arc bottom wall, the arc rotating wall contacts with the arc bottom wall and rotates on the arc bottom wall, so that the rotating body 5 and a power shaft thereon can be changed in setting angle, and centers of the arc bottom wall and the arc rotating wall are both the axes of the power shaft. That is to say, rotator 5 can realize the rotation on base 4 through the contact of two cambered surfaces, cooperation, through rotating one or both of two rotators 5 that set up on two bases 4, just can change the contained angle between two power shafts for the lift testing arrangement that this embodiment provided can test the lift that two rotors produced under the condition of multiple different contained angles.
Moreover, as shown in fig. 3 and 4, a first threaded hole 412 is formed in the bottom surface of each base 4, a plurality of second threaded holes 311 are uniformly distributed in the mounting plate 3, and the first threaded holes 412 are aligned with different second threaded holes 311 and are connected by bolts, so that the base 4 can be arranged at different positions of the mounting plate 3, and the distance between different bases 4 can be changed. That is to say, by moving the base 4, the first threaded hole 412 on the base 4 can be aligned with different threaded holes in the plurality of second threaded holes 311 on the mounting plate 3, when the first threaded hole 412 is aligned with different second threaded holes 311, the setting position of the base 4 on the mounting plate 3 is changed accordingly, so that the adjustment of the distance between the two bases 4 can be realized, since the power shaft is set on the base 4 through the rotating body 5, the distance between the two bases 4 is changed, the adjustment of the distance between the two power shafts is realized, and then the first threaded hole 412 and the second threaded hole 311 which are aligned are connected through bolts, so that the lift force test can be performed. Through so setting up, can make the lift testing arrangement that this embodiment provided can test the lift that two rotors produced under the condition of multiple different intervals. Preferably, the first threaded holes 412 are plural to improve the connection stability between the base plate 4 and the mounting plate 3.
Specifically, as shown in fig. 3, a plurality of first positioning holes 411 are formed in the side wall of the groove, a connecting line of the plurality of first positioning holes 411 is an arc line, and the arc line is concentric with the bottom wall of the arc line; moreover, it is also preferable that all the first positioning holes 411 are arranged on the base 4 in a plurality of arcs, the centers of all the arcs are the same, and the first positioning holes 411 located on adjacent arcs are arranged in a staggered manner. That is, the two sides of the base 4 are provided with the first positioning holes 411, the first positioning holes 411 are arranged in two rows, and are symmetrically arranged on the two sides of the base 4, the first positioning hole 411 of the first row positioned above lags behind the first positioning hole 411 of the second row positioned below by one hole, and all the first positioning holes 411 are distributed on two arcs with the axis of the input shaft of the bevel gear box 6 as the center of a circle.
Correspondingly, as shown in fig. 3, the rotating body 5 is provided with a plurality of second positioning holes 511 capable of aligning with different first positioning holes 411, the arrangement manner of all the second positioning holes 511 on the rotating body 5 is the same as the arrangement manner of all the first positioning holes 411 on the base 4, and the positioning piece can realize the positioning of the rotating body 5 on the base 4 by being inserted into the aligned first positioning holes 411 and second positioning holes 511, that is, the included angle between the main axes of the two rotors of the crossed dual rotors can be adjusted by changing the combination of the first positioning holes 411 and the second positioning holes 511. Preferably, the first positioning hole 411 and the second positioning hole 511 are light holes, and the positioning member is a pin.
When the lifting force of the rotor wing is tested by using the lifting force testing device of the cross dual-rotor helicopter, the alignment combination of the first positioning hole 411 and the second positioning hole 511 is changed, the included angle between the two rotor wing spindles of the cross dual-rotor wing can be changed, the distance between the two rotor wing spindles of the cross dual-rotor wing can be changed by changing the alignment combination of the first threaded hole 412 and the second threaded hole 311, then, the zero clearing operation is carried out on the collector, the transmission system of the cross dual-rotor helicopter and the power system drive rotor wing to rotate, so that the lifting force can be tested, the lifting force generated by the rotor wing of the cross dual-rotor helicopter is collected by the collector, after the test is completely finished, the data is analyzed, and a group of proper included angles and distances is selected.
In this embodiment, the sensor 2 is preferably a cantilever type tension/compression sensor. The sensor 2 is preferably a cantilever type tension/compression sensor because it has a simple structure and is easy to test, and when it is mounted, the top end of the cantilever type tension/compression sensor is connected to the connection hole 312 of the mounting plate 3 by a bolt, and the bottom end of the cantilever type tension/compression sensor is connected to the welding frame 12 to be described later by a bolt. The top of cantilever type tension and compression sensor is the free end, and the bottom is the stiff end, and the collector carries out the zero clearing operation back, when lift produced, and the collector can be drawn and is pressed the sensor through the cantilever type and gather the lift value that corresponds contained angle, double-rotor wing interval between different double-rotor wings. The sensor 2 may have another configuration, such as an S-type sensor or a spoke-type sensor.
As shown in fig. 5, the gantry 1 preferably includes a support frame 11 and a welding frame 12 disposed at a top end of the support frame 11, and the sensor 2 is fixedly disposed on the welding frame 12. The welding frame 12 is arranged on the support frame 11, so that the overall firmness of the lift force testing device provided by the embodiment can be further improved, and the arrangement of the sensor 2 and the mounting plate 3 is facilitated.
Further, as shown in fig. 5, the support frame 11 is spliced by a plurality of aluminum profiles to form a hollow-out support, and meanwhile, the bottom of the support frame 11 is provided with a foundation connection plate which is connected with foundation bolts. The support frame 11 is spliced into a hollow support by aluminum profiles and corner pieces thereof, so that the rack 1 is easy to assemble, light in weight and practical. The setting of rag connecting plate 3 and rag bolt is favorable to the more firm setting of rack 1 subaerial.
As shown in fig. 1, 2 and 4, the mounting plate 3 of the present embodiment is further provided with an avoiding groove 313 on the bottom surface thereof. After the avoiding groove 313 is arranged, when an operator operates the mounting plate 3, the fingers can stretch into the avoiding groove 313 to more conveniently and firmly grasp the mounting plate 3, so that the mounting plate 3 can be conveniently carried and assembled.
The structures of all parts are described in a progressive mode in the specification, the structure of each part is mainly described to be different from the existing structure, and the whole and partial structures of the lift force testing device can be obtained by combining the structures of the parts.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The utility model provides a cross double rotor helicopter lift testing arrangement which characterized in that includes:
a rack;
a sensor disposed on the gantry;
the collector is in communication connection with the sensor;
the mounting plate is arranged on the top of the sensor and connected with the sensor;
the base plates are arranged on the mounting plate, and the mounting positions of the base plates on the mounting plate can be changed, so that the distance between different base plates can be changed;
the rotary device comprises a base, a plurality of rotary bodies arranged on the base in a one-to-one mode, wherein the arrangement angles of the rotary bodies on the base can be changed, so that the included angles between power shafts connected to the rotary bodies and the mounting plates can be changed.
2. The cross-rotor helicopter lift test device of claim 1 wherein the base has a recess, the bottom wall of the recess is an arc bottom wall, the rotor is receivable in the recess and has an arc rotating wall matching the arc bottom wall, the arc rotating wall is in contact with and rotates on the arc bottom wall to change the setting angle of the rotor and the power shaft thereon, and the centers of the arc bottom wall and the arc rotating wall are the axes of the power shaft.
3. The helicopter lift test apparatus of claim 2 wherein the side walls of the slot define a plurality of first positioning holes, the first positioning holes being connected by an arc that is concentric with the bottom wall of the arc; the rotating body is provided with a plurality of second positioning holes which can be aligned with the first positioning holes, and the positioning piece can realize the positioning of the rotating body on the base by being inserted into the aligned first positioning holes and the aligned second positioning holes.
4. The crossrotor helicopter lift test apparatus of claim 3 wherein all of the first positioning holes are positioned on the base in a plurality of arcs, all of the arcs having the same center of circle and positioned on adjacent arcs in a staggered configuration.
5. The helicopter lift test apparatus of claim 1 wherein each of the pedestals has a first threaded aperture formed in a bottom surface thereof, and the mounting plate has a plurality of second threaded apertures formed therein that are evenly distributed, the first threaded apertures being aligned with and bolted to different ones of the second threaded apertures to enable the pedestals to be positioned at different locations on the mounting plate to vary the spacing between different ones of the pedestals.
6. The crossrotor helicopter lift test apparatus of claim 1 wherein the sensors are cantilevered tension and compression sensors.
7. The cross-twin helicopter lift test apparatus of claim 1 where the gantry includes a support frame and a welded frame disposed at a top end of the support frame, the sensor being fixedly disposed on the welded frame.
8. The helicopter lift test apparatus of claim 7 wherein the bottom of the support frame is provided with a foot connection plate to which foot bolts are attached.
9. The helicopter lift test apparatus of claim 7 wherein the support frame is formed by a plurality of aluminum profiles that are joined together to form a hollow bracket.
10. The crossrotor helicopter lift test apparatus of claim 1 wherein the mounting plate has an evasion slot formed in a bottom surface thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010322484.7A CN111216922B (en) | 2020-04-22 | 2020-04-22 | Lifting force testing device of cross dual-rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010322484.7A CN111216922B (en) | 2020-04-22 | 2020-04-22 | Lifting force testing device of cross dual-rotor helicopter |
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| Publication Number | Publication Date |
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| CN111216922A true CN111216922A (en) | 2020-06-02 |
| CN111216922B CN111216922B (en) | 2020-07-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010322484.7A Active CN111216922B (en) | 2020-04-22 | 2020-04-22 | Lifting force testing device of cross dual-rotor helicopter |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308272A (en) * | 2013-05-30 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Non-planar dynamic testing device for aerodynamic performances of dual rotors |
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN207141409U (en) * | 2017-04-12 | 2018-03-27 | 北京建中数字科技有限公司 | Intersect twin-rotor helicopter and its machine driven system |
| WO2020013788A1 (en) * | 2018-07-13 | 2020-01-16 | Aselsan Elektroni̇k Sanayi̇ Ve Ti̇caret Anoni̇m Şi̇rketi̇ | Preflight test platform for rotary wing unmanned air vehicle |
| CN210284661U (en) * | 2019-07-19 | 2020-04-10 | 哈工大机器人（岳阳）军民融合研究院 | Rotor wing testing device |
-
2020
- 2020-04-22 CN CN202010322484.7A patent/CN111216922B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308272A (en) * | 2013-05-30 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Non-planar dynamic testing device for aerodynamic performances of dual rotors |
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN207141409U (en) * | 2017-04-12 | 2018-03-27 | 北京建中数字科技有限公司 | Intersect twin-rotor helicopter and its machine driven system |
| WO2020013788A1 (en) * | 2018-07-13 | 2020-01-16 | Aselsan Elektroni̇k Sanayi̇ Ve Ti̇caret Anoni̇m Şi̇rketi̇ | Preflight test platform for rotary wing unmanned air vehicle |
| CN210284661U (en) * | 2019-07-19 | 2020-04-10 | 哈工大机器人（岳阳）军民融合研究院 | Rotor wing testing device |
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| CN111216922B (en) | 2020-07-17 |
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