CN213502954U - Unmanned aerial vehicle transverse wind torque test rack - Google Patents
Unmanned aerial vehicle transverse wind torque test rack Download PDFInfo
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- CN213502954U CN213502954U CN202022593848.3U CN202022593848U CN213502954U CN 213502954 U CN213502954 U CN 213502954U CN 202022593848 U CN202022593848 U CN 202022593848U CN 213502954 U CN213502954 U CN 213502954U
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Abstract
When the unmanned aerial vehicle is in a wind field environment, in order to realize hovering or flat flying, the tilting disk of the unmanned aerial vehicle controls the tip plane to tilt for a certain angle, so that the horizontal component of the lift force offsets the influence of transverse wind resistance. However, the maximum inclination angle of the swashplate is limited by the structural design, and therefore, for a given structural design, accurate measurement of the transverse wind induced torque is required in order to determine the maximum acceptable intensity of sudden wind disturbance under hover conditions and the maximum acceptable incoming flow velocity under level flight conditions. The utility model provides an unmanned aerial vehicle lateral wind moment of torsion test rack, including chassis subassembly, fuselage simulation frame subassembly and pivot subassembly. Wherein, the relative position between fuselage simulation frame subassembly and the pivot subassembly can be adjusted, but fuselage simulation frame subassembly bodily rotation. The utility model discloses can adapt to the rotor size that unmanned aerial vehicle is different, different rotor rotational speed and different crosswind wind speed, can the accurate torque value that measures and arouse by the crosswind.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, concretely relates to unmanned aerial vehicle transverse wind moment of torsion test rack.
Background
When the unmanned aerial vehicle is in a wind field environment, in order to realize hovering or flat flying, the tilting disk of the unmanned aerial vehicle controls the tip plane to tilt for a certain angle, so that the horizontal component of the lift force offsets the influence of transverse wind resistance. The maximum inclination angle of the tilting disk is limited by the structural design, so for a given structural design scheme, in order to determine the maximum acceptable sudden wind disturbance intensity under the hovering condition and the maximum acceptable incoming flow speed under the level flight condition, the torque caused by the transverse wind needs to be accurately measured.
Disclosure of Invention
The utility model discloses the technical problem that will solve is: the utility model provides an unmanned aerial vehicle transverse wind moment of torsion test rack, under the rotor size that unmanned aerial vehicle is different, different rotor rotational speed and the different transverse wind speed circumstances, can accurately measure the moment of torsion that the transverse wind arouses.
The technical scheme of the utility model is that: the utility model provides an unmanned aerial vehicle transverse wind moment of torsion test rack which characterized in that, including chassis subassembly, fuselage simulation frame subassembly and pivot subassembly. The chassis assembly is tightly connected with the rotating shaft assembly, the body simulation frame assembly is tightly connected with the rotating shaft assembly, the relative position between the body simulation frame assembly and the rotating shaft assembly can be adjusted, and the body simulation frame assembly can integrally rotate.
Further, the chassis component comprises a vertical rod, a horizontal supporting rod, a vertical rod connecting rod, a base longitudinal rod, a base transverse rod, a large corner piece, a small corner piece and a gland. The vertical rods are arranged in the vertical direction, and the horizontal support rods, the vertical rod connecting rods, the base longitudinal rods and the base transverse rods are all arranged in the horizontal direction; the vertical rods are connected with the horizontal support rods, the vertical rods are connected with the vertical rod connecting rods, and the vertical rods are connected with the longitudinal rods of the base through large-angle pieces so as to keep the verticality of the mutually connected positions; the base longitudinal rod and the base transverse rod, the base longitudinal rod and the upright rod connecting rod, and the base longitudinal rod and the horizontal supporting rod are connected by small angle pieces so as to keep the verticality of the mutual connection positions. The end parts of the horizontal supporting rod and the base longitudinal rod are all inserted with a gland.
Furthermore, the large angle piece and the small angle piece are connected with each rod piece by adopting bolts and nuts for fastening; the material of the gland is plastic.
Further, the fuselage simulation frame subassembly includes montant, ring flange, switching dish, balancing weight, counter weight briquetting, baffle. One side of the flange plate is mounted at one end of the vertical rod, the baffle plate is mounted at the other end of the vertical rod, the two vertical rods, the flange plate and the baffle plate form a surrounding structure, and the two vertical rods are parallel to each other; the other side of the flange plate is connected with a switching plate, and the switching plate is connected with the unmanned aerial vehicle; the counterweight block and the counterweight pressing block are fixedly connected, the counterweight block and the counterweight pressing block are arranged between the flange plate and the baffle plate, and the counterweight pressing block and the vertical rod are connected by bolts and nuts; the relative position of the balancing weight, the flange plate and the baffle plate can be adjusted through bolts and nuts.
Furthermore, the side surface of the vertical rod is marked with length scales.
Furthermore, the rotating shaft assembly comprises a rotating shaft, a bearing seat, a bearing, a coupler, a torque tester, a mounting bracket, a rotating shaft sleeve and a shaft sleeve cover plate. The two sides of the rotating shaft are respectively provided with a bearing and a bearing seat, the inner ring of the bearing is limited by the rotating shaft, and the outer ring of the bearing is limited by the bearing seat; the bearing block is arranged on the underframe assembly; two ends of the rotating shaft are respectively connected with a coupler, wherein one end of the coupler is connected with the torque tester, and the other end of the coupler is suspended and used for calibration and calibration of the torque tester; the torque tester is arranged on the mounting bracket, and the mounting bracket is arranged on the underframe assembly; the middle part of the rotating shaft is provided with a rotating shaft sleeve and a shaft sleeve cover plate, and the rotating shaft sleeve and the shaft sleeve cover plate are fastened on the rotating shaft.
Further, the bearing is a self-aligning ball bearing; a key groove plane is arranged on the cylindrical surface of the rotating shaft and is attached to the plane of the shaft sleeve cover plate; the coupler comprises a square hole-to-round hole body and a hoop.
Furthermore, the bearing seat is installed on the pole setting of chassis subassembly, and the installing support is installed on the horizontal support pole of chassis subassembly.
Further, the vertical rods are connected with the machine body simulation frame assembly through bolts and nuts; the relative position between the vertical rod and the rotary shaft sleeve can be adjusted through a bolt and a nut.
Further, the bolt and the nut are respectively a butterfly bolt and a slider nut.
The utility model has the advantages that: through adjusting the relative position between fuselage simulation frame subassembly and the pivot subassembly to and the relative position of adjusting balancing weight and ring flange, baffle, make fuselage simulation frame subassembly and unmanned aerial vehicle constitute the focus behind whole and the coincidence of the rotation center of pivot, realize the whole rotational balance after fuselage simulation frame subassembly is connected with unmanned aerial vehicle. The utility model discloses can adapt to the rotor size that unmanned aerial vehicle is different, different rotor rotational speed and different crosswind wind speed, can the accurate torque value that measures and arouse by the crosswind.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive work.
Fig. 1 is an overall structure diagram of the present invention.
Fig. 2 is a structural view of the underframe assembly of the present invention.
Fig. 3 is a structure diagram of the body simulation frame assembly of the present invention.
Fig. 4 is a structure view of the rotating shaft assembly of the present invention.
FIG. 5 is a schematic view of a thumb bolt and slider nut configuration.
In the figure: 1 chassis subassembly, 10 poles, 11 horizontal support pole, 12 pole connecting rods, 13 base vertical poles, 14 base horizontal poles, 15 big corner fittings, 16 little corner fittings, 17 butterfly bolts, 18 slider nuts, 19 glands, 2 fuselage simulation frame subassemblies, 20 montants, 21 ring flange, 22 switching dish, 23 balancing weights, 24 counter weight briquetting, 25 baffles, 3 pivot subassemblies, 30 pivots, 31 bearing seats, 32 bearings, 33 shaft couplings, 331 square hole switching round hole body, 332 staple bolt, 34 moment of torsion tester, 35 installing supports, 36 rotation axle sleeves, 37 axle sleeve apron, 4 unmanned aerial vehicles.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
The present invention will be described in further detail with reference to the accompanying drawings, please refer to fig. 1 to 5.
As shown in figure 1, the overall structure diagram of the transverse wind torque test bench for the unmanned aerial vehicle comprises an underframe assembly (1), a fuselage simulation frame assembly (2) and a rotating shaft assembly (3). Wherein, the chassis component (1) is tightly connected with the rotating shaft component (3), the machine body simulation frame component (2) is tightly connected with the rotating shaft component (3), the relative position between the machine body simulation frame component (2) and the rotating shaft component (3) can be adjusted, and the machine body simulation frame component (2) can integrally rotate.
Further, as shown in fig. 2, the underframe assembly (1) comprises a vertical rod (10), a horizontal support rod (11), a vertical rod connecting rod (12), a base vertical rod (13), a base cross rod (14), a large angle piece (15), a small angle piece (16) and a gland (19). The vertical rods (10) are arranged in the vertical direction, and the horizontal support rods (11), the vertical rod connecting rods (12), the base longitudinal rods (13) and the base transverse rods (14) are all arranged in the horizontal direction; the vertical rods (10) and the horizontal supporting rods (11), the vertical rods (10) and the vertical rod connecting rods (12) and the vertical rods (10) and the base longitudinal rods (13) are connected by large-angle pieces (15) so as to ensure the verticality of the mutual connection positions; the vertical base rods (13) and the horizontal base rods (14), the vertical base rods (13) and the vertical rod connecting rods (12) and the vertical base rods (13) and the horizontal supporting rods (11) are connected through small corner pieces (16) to ensure the perpendicularity of the connecting positions. The large angle piece (15) and the small angle piece (16) are connected with each rod piece by fastening a butterfly bolt (17) and a slide block nut (18). The schematic structural diagram of the butterfly bolt (17) and the slider nut (18) is shown in fig. 5. The end parts of the horizontal supporting rod (11) and the base vertical rod (13) are inserted with the gland (19). The gland (19) is a plastic piece.
Further, as shown in fig. 3, the fuselage simulation frame assembly (2) includes a vertical rod (20), a flange (21), an adapter plate (22), a counterweight (23), a counterweight block (24), and a baffle (25). One side of the flange plate (21) is arranged at one end of the vertical rod (20), the baffle plate (25) is arranged at the other end of the vertical rod (20), the two vertical rods (20), the flange plate (21) and the baffle plate (25) form a surrounding structure, and the two vertical rods (20) are parallel to each other; the side surface of the vertical rod (20) is marked with length scales. The other side of the flange plate (21) is connected with an adapter plate (22), and the adapter plate (22) is connected with the unmanned aerial vehicle (4); the balancing weight (23) is fixedly connected with the balancing weight pressing block (24), the balancing weight (23) and the balancing weight pressing block (24) are arranged between the flange plate (21) and the baffle plate (25), and the balancing weight pressing block (24) is connected with the vertical rod (20) through a butterfly bolt (17) and a sliding block nut (18); the sliding block nut (18) can slide in the sliding groove of the vertical rod (20), and the relative positions of the balancing weight (23), the flange plate (21) and the baffle plate (25) can be adjusted through the butterfly bolt (17) and the sliding block nut (18).
Further, as shown in fig. 4, the rotating shaft assembly (3) includes a rotating shaft (30), a bearing seat (31), a bearing (32), a coupling (33), a torque tester (34), a mounting bracket (35), a rotating shaft sleeve (36), and a shaft sleeve cover plate (37). The bearing (32) and the bearing seat (31) are respectively installed on two sides of the rotating shaft (30), the bearing (32) is a self-aligning ball bearing, the inner ring of the bearing (32) is limited by the rotating shaft (30), and the outer ring of the bearing (32) is limited by the bearing seat (31); the bearing seat (31) is arranged on the underframe assembly (1); two ends of the rotating shaft (30) are respectively connected with a coupler (33), wherein the coupler (33) at one end is connected with a torque tester (34), and the coupler (33) at the other end is suspended and used for calibrating and calibrating the torque tester (34); the coupler (33) comprises a square hole-to-round hole body (331) and a hoop (332). The torque tester (34) is arranged on the mounting bracket (35), and the mounting bracket (35) is arranged on the underframe assembly (1); the middle part of the rotating shaft (30) is provided with a rotating shaft sleeve (36) and a shaft sleeve cover plate (37), a key groove plane is arranged on the cylindrical surface of the rotating shaft (30), the key groove plane is attached to the plane of the shaft sleeve cover plate (37), and the rotating shaft sleeve (36) and the shaft sleeve cover plate (37) are fastened on the rotating shaft (30).
Furthermore, the bearing seat (31) is arranged on the vertical rod (10) of the underframe assembly (1), and the mounting bracket (35) is arranged on the horizontal supporting rod (11) of the underframe assembly (1).
Furthermore, the vertical rod (20) is connected with the rotating shaft sleeve (36) by a butterfly bolt (17) and a sliding block nut (18); the sliding block nut (18) can slide in a sliding groove of the vertical rod (20), and the relative position between the vertical rod (20) and the rotating shaft sleeve (36) can be adjusted through the butterfly bolt (17) and the sliding block nut (18).
The utility model discloses the test order of unmanned aerial vehicle transverse wind moment of torsion test rack is: fix screw on adapter plate (22) with unmanned aerial vehicle (4) earlier, then adjust balancing weight (23) and ring flange (21) through butterfly bolt (17) and slider nut (18), the relative position of baffle (25), the relative position between montant (20) and rotation axle sleeve (36) is adjusted through butterfly bolt (17) and slider nut (18) rethread, make fuselage simulation frame subassembly (2) and unmanned aerial vehicle (4) constitute the focus behind the whole and the coincidence of the centre of rotation of pivot (30), realize fuselage simulation frame subassembly (2) and unmanned aerial vehicle (4) and be connected the whole rotation balance of back. After balance adjustment, a standard torque instrument is used for calibrating and calibrating the torque tester (34) through the suspended coupler (33), then transverse wind with different wind speeds is applied, different unmanned aerial vehicle rotors are replaced and different rotor rotating speeds are set, and a torque value caused by the transverse wind is accurately measured through the torque tester (34).
The utility model has the advantages that: through adjusting the relative position between fuselage simulation frame subassembly (2) and pivot subassembly (3) to and the relative position of adjusting balancing weight (23) and ring flange (21), baffle (25), make fuselage simulation frame subassembly (2) and unmanned aerial vehicle (4) constitute the focus behind the whole and the coincidence of the rotation center of pivot (30), realize fuselage simulation frame subassembly (2) and unmanned aerial vehicle (4) and be connected the whole balance behind. The utility model discloses can adapt to the rotor size of unmanned aerial vehicle (4) difference, the rotor rotational speed of difference and the different transverse wind speed, can the accurate torque value that causes by the transverse wind that measures.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (9)
1. An unmanned aerial vehicle transverse wind torque test bench is characterized by comprising an underframe assembly, a machine body simulation frame assembly and a rotating shaft assembly; the chassis assembly is tightly connected with the rotating shaft assembly, the body simulation frame assembly is tightly connected with the rotating shaft assembly, the relative position between the body simulation frame assembly and the rotating shaft assembly can be adjusted, and the body simulation frame assembly can integrally rotate.
2. The unmanned aerial vehicle transverse wind torque test bench of claim 1, wherein the underframe assembly comprises a vertical rod, a horizontal support rod, a vertical rod connecting rod, a base longitudinal rod, a base cross rod, a large corner fitting, a small corner fitting, and a gland; the vertical rods are arranged in the vertical direction, and the horizontal support rods, the vertical rod connecting rods, the base longitudinal rods and the base transverse rods are all arranged in the horizontal direction; the vertical rods are connected with the horizontal supporting rods, the vertical rods are connected with the vertical rod connecting rods, and the vertical rods are connected with the base longitudinal rods through the large angle pieces so as to keep the verticality of the mutual connection positions; the base longitudinal rod and the base transverse rod, the base longitudinal rod and the upright rod connecting rod and the base longitudinal rod and the horizontal supporting rod are connected by the small angle piece so as to keep the verticality of the mutual connection positions; the end parts of the horizontal supporting rod and the base longitudinal rod are all inserted into the gland.
3. The unmanned aerial vehicle transverse wind torque test bench of claim 2, wherein the connection of the large corner fitting, the small corner fitting and each rod piece is fastened by bolts and nuts; the gland is made of plastic.
4. The unmanned aerial vehicle transverse wind torque test bench of claim 1, wherein the fuselage simulation frame assembly comprises a vertical rod, a flange plate, a transfer plate, a counterweight block, and a baffle plate; one side of the flange plate is mounted at one end of the vertical rod, the baffle plate is mounted at the other end of the vertical rod, the two vertical rods, the flange plate and the baffle plate form a surrounding structure, and the two vertical rods are parallel to each other; the other side of the flange plate is connected with the adapter plate, and the adapter plate is connected with the unmanned aerial vehicle; the counterweight block and the counterweight pressing block are fixedly connected, the counterweight block and the counterweight pressing block are installed between the flange plate and the baffle plate, and the counterweight pressing block and the vertical rod are connected by bolts and nuts; the relative positions of the balancing weight, the flange plate and the baffle plate can be adjusted through bolts and nuts.
5. The unmanned aerial vehicle transverse wind torque test stand of claim 4, wherein the side of the vertical rod is marked with length scales.
6. The unmanned aerial vehicle transverse wind torque test bench of claim 1, wherein the rotating shaft assembly comprises a rotating shaft, a bearing seat, a bearing, a coupling, a torque tester, a mounting bracket, a rotating shaft sleeve and a shaft sleeve cover plate; the bearing and the bearing seat are respectively arranged on two sides of the rotating shaft, the inner ring of the bearing is limited by the rotating shaft, and the outer ring of the bearing is limited by the bearing seat; the bearing block is arranged on the underframe assembly; the two ends of the rotating shaft are respectively connected with the coupler, one end of the coupler is connected with the torque tester, and the other end of the coupler is suspended and used for calibration and calibration of the torque tester; the torque tester is arranged on the mounting bracket, and the mounting bracket is arranged on the underframe assembly; the middle part of the rotating shaft is provided with the rotating shaft sleeve and the shaft sleeve cover plate, and the rotating shaft sleeve and the shaft sleeve cover plate are fastened on the rotating shaft.
7. The unmanned aerial vehicle transverse wind torque test bench of claim 6, wherein the bearing is a self-aligning ball bearing; a key groove plane is arranged on the cylindrical surface of the rotating shaft and is attached to the plane of the shaft sleeve cover plate; the coupler comprises a square hole-to-round hole body and a hoop.
8. The unmanned aerial vehicle transverse wind torque test bench of claim 4, wherein the vertical rod and the rotating shaft assembly are connected by the bolt and the nut; the relative position between the vertical rod and the rotating shaft assembly can be adjusted through the bolt and the nut.
9. The unmanned aerial vehicle transverse wind torque test bench of any one of claims 3 or 4, wherein the bolts and nuts are wing bolts and slider nuts, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022593848.3U CN213502954U (en) | 2020-11-11 | 2020-11-11 | Unmanned aerial vehicle transverse wind torque test rack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022593848.3U CN213502954U (en) | 2020-11-11 | 2020-11-11 | Unmanned aerial vehicle transverse wind torque test rack |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213502954U true CN213502954U (en) | 2021-06-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022593848.3U Active CN213502954U (en) | 2020-11-11 | 2020-11-11 | Unmanned aerial vehicle transverse wind torque test rack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213502954U (en) |
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2020
- 2020-11-11 CN CN202022593848.3U patent/CN213502954U/en active Active
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