CN214824253U - Passive operating platform for testing and parameter-adjusting of dynamic attitude of multi-rotor aircraft - Google Patents
Passive operating platform for testing and parameter-adjusting of dynamic attitude of multi-rotor aircraft Download PDFInfo
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- CN214824253U CN214824253U CN202120835942.7U CN202120835942U CN214824253U CN 214824253 U CN214824253 U CN 214824253U CN 202120835942 U CN202120835942 U CN 202120835942U CN 214824253 U CN214824253 U CN 214824253U
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Abstract
The utility model discloses a passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment, which relates to the technical field of unmanned aerial vehicle test and comprises a fixed base on which a rotatable universal load test part is arranged; a parameter information display part is arranged in the fixed base, and the parameter information display part is a control, measurement and parameter information display system of a built-in system; the utility model discloses can be to many rotor unmanned aerial vehicle of each type, use this test operation panel, can be within limited controllable scope with many rotor unmanned aerial vehicle retrains, effectively reduce the probability that causes danger to external environment and personnel, and many rotors are the true flight situation on equipment simultaneously and do not receive any degree of freedom restriction completely, many rotor unmanned aerial vehicle's start flight state and gesture and when true scene normal flight identical, many rotor unmanned aerial vehicle still can carry out the roll, motor-driven actions such as every single move and driftage.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle tests technical field, concretely relates to passive form operation panel that is used for many rotor crafts dynamic attitude test to transfer parameter.
Background
At present, in the research, design, production, equipment and debugging process of many rotor unmanned aerial vehicle aircraft, need test, regulation, observation and design to the static mechanism characteristic and the dynamic characteristic parameter of specific aircraft. The design and debugging process is often complicated, and designers or debuggers are required to continuously test and fly a specific developed model in the aspects of aircraft stability, energy consumption, control performance and the like, and the test efficiency determines the determination time of a parameter and the overall research and development setting time of the model. Many rotor unmanned aerial vehicle is an aerospace vehicle, consequently is a device that possesses higher dangerous operating factor, when design and test flight tester design and test flight, has just increased more uncertainties for the operation of many rotor unmanned aerial vehicle equipment, and test flight test process and result probably possess danger more, more can cause unmanned aerial vehicle test flight fryer or cause loss and threat to surrounding environment personnel.
And the same education training trade field at many rotor unmanned aerial vehicle, at learning operation, flight training and examination stage, the student who learns many rotor unmanned aerial vehicle flight principle and control technical skill often can cause the damage for equipment, causes the threat to personnel's environment on every side simultaneously. Many rotor unmanned aerial vehicle study personnel knowledge mastery level and learning ability often are jagged, and education and training mechanism receive the student's quantity of training more, cause the probability of loss and danger will be bigger.
Two kinds of current techniques, a system that is partial to unmanned aerial vehicle system analog simulation, the mode through unmanned aerial vehicle graphical modeling, analysis by simulation and computer language is moved, and whole system experiences comparatively boring, and especially lower to the mechanical system of unmanned aerial vehicle body and the audio-visual perception of each part component, is unfavorable for understanding and teaching and the study of unmanned aerial vehicle and unmanned aerial vehicle application system at preliminary entry stage.
In addition, the unmanned aerial vehicle is connected with the equipment platform through a connecting rope, and then tests the unmanned aerial vehicle under the environmental conditions of different wind speeds and directions through the mooring takeoff of the unmanned aerial vehicle and the external environment of artificial manufacturing. The unmanned aerial vehicle system has the advantages that the unmanned aerial vehicle still needs to normally take off in a real environment, the unmanned aerial vehicle faces more unknown factors when being tested in different environments, the test system is huge and complex, and most importantly, the expensive unmanned aerial vehicle system still faces larger flight faults and equipment loss risks when being tested.
Disclosure of Invention
The utility model is directed to the above-mentioned problem, a passive form operation panel that is used for many rotor crafts dynamic attitude test to transfer parameter is provided, has solved how better problem of testing many rotor unmanned aerial vehicle.
The utility model adopts the technical proposal that: a passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment comprises a fixed base, a parameter information display part and a rotatable universal load test part;
the fixed base is provided with a rotatable universal load testing part;
and a parameter information display part is arranged in the fixed base, and the parameter information display part is a control, measurement and parameter information display system of a built-in system.
Furthermore, the rotatable universal load testing component comprises a fixed connecting block, a turntable base, a transverse turntable, a longitudinal turntable, a universal turntable and a counterweight adjusting device; a chassis is arranged on the fixed base, a fixed connecting block is arranged on the chassis, and a turntable base is rotatably connected to the fixed connecting block;
the unmanned aerial vehicle load testing device is characterized in that a longitudinal rotary table is connected to the rotary table base, a transverse rotary table is connected to the longitudinal rotary table in a rotating mode, a universal rotary table is connected to the transverse rotary table in a rotating mode, a balance weight adjusting device is arranged at the bottom of the universal rotary table, and an unmanned aerial vehicle load to be tested is mounted at the top of the universal rotary table.
Furthermore, the turntable base is rotatably connected with the fixed connecting block through a thrust ball bearing.
Furthermore, universal carousel includes tray and support arm, the support arm is connected with the tray through first bolt, the support arm both ends are rotated with horizontal carousel through first ball bearing and are connected, first ball bearing installs in first bearing fixing support, first bearing fixing support is connected with horizontal carousel, and the unmanned aerial vehicle load that awaits measuring is installed in the tray top.
Furthermore, the counterweight adjusting device comprises a screw rod and a counterweight block, the bottom of the supporting arm is in threaded connection with the screw rod, and the other end of the screw rod is in threaded connection with the counterweight block.
Further, through second bolted connection between horizontal carousel and the vertical carousel, horizontal carousel inboard is installed second bearing fixing support, install second ball bearing in the second bearing fixing support, the second bolt runs through second ball bearing and horizontal carousel lateral wall respectively and is connected with vertical carousel, and second bolt and second ball bearing, second bolt and vertical carousel are interference fit.
Furthermore, the second bolt penetrates through the second ball bearing, the lateral wall of the transverse turntable and the lateral wall of the longitudinal turntable respectively and is connected with a matched nut.
The utility model has the advantages that:
the utility model provides a passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment, which can be used for various types of multi-rotor unmanned aerial vehicles, four-axis, six-axis, eight-axis rotorcraft and other types, the model of the operating platform can be matched with the types of the machines with different sizes, the test operating platform can constrain the multi-rotor unmanned aerial vehicle within a limited controllable range no matter in the design of a prototype, the initial test stage or the later learning, training, operation and flying stage, the probability of danger to the external environment and personnel is effectively reduced, meanwhile, the real flying condition of the multi-rotor unmanned aerial vehicle on the equipment is not limited by any degree of freedom, the starting flying state and attitude of the multi-rotor unmanned aerial vehicle are completely the same as the real scene during normal flying, the multi-rotor unmanned aerial vehicle can still carry out the maneuvering actions of rolling, pitching, yawing and the like, the real flying state which is constrained by certain conditions is completely different from the computer simulation environment, the flight state and the feeling can enable an operator to more intuitively and clearly feel the action state during operation and the real-time correlation condition of the multi-rotor aircraft;
in the educational and teaching environment, the utility model can be used for better demonstration and teaching indoors, the teaching efficiency of the unmanned aerial vehicle system and the cognitive level of students are improved, and the potential risks of the unmanned aerial vehicle equipment to the surrounding environment and the human body can be greatly reduced; and the utility model provides a many rotor unmanned aerial vehicle aircraft need test, adjust, observe and the process equipment of stereotyping to the static mechanism characteristic and the dynamic characteristic parameter of specific aircraft in research, design, production, equipment and debugging process, designs and tests, can accelerate the efficiency of unmanned aerial vehicle design test greatly, reduces the loss probability of equipment.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a schematic view of the working state of the present invention;
FIG. 3 is a schematic structural view of the universal turntable of the present invention;
fig. 4 is a schematic view of the installation of the second bearing fixing support of the present invention;
fig. 5 is a schematic view of the installation of the first bearing fixing support of the present invention.
Reference numerals:
the test device comprises a base, a parameter information display part, a base plate, a fixed connecting block, a thrust ball bearing, a turntable base, a transverse turntable, a second ball bearing, a load of an unmanned aerial vehicle to be tested, a longitudinal turntable, a universal turntable, a first ball bearing and a counterweight adjusting device, wherein the parameter information display part is 2, the base plate is 3, the fixed connecting block is 4, the thrust ball bearing is 5, the turntable base is 6, the transverse turntable is 7, the second ball bearing is 8, the load of the unmanned aerial vehicle to be tested is 9, the longitudinal turntable is 10, the universal turntable is 11, the first ball bearing is 12, and the counterweight adjusting device is 13;
81-second bearing fixing support, 82-second bolt, 83-nut;
111-tray, 112-supporting arm, 113-first bolt, 114-first bearing fixing support;
131-screw and 132-counterweight.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Referring to fig. 1 to 5, a passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment comprises a fixed base 1, a parameter information display part 2 and a rotatable universal load test part;
a rotatable universal load testing component is arranged on the fixed base 1; the system is used for simulating the load 9 environment of the unmanned aerial vehicle to be tested; the rotatable universal load testing component comprises a fixed connecting block 4, a turntable base 6, a transverse turntable 7, a longitudinal turntable 10, a universal turntable 11 and a counterweight adjusting device 13; the fixed base 1 is connected with a chassis 3, a fixed connecting block 4 is arranged on the chassis 3, and a turntable base 6 is rotatably connected to the fixed connecting block 4, so that the turntable base 6 can freely rotate;
the turntable base 6 is connected with a longitudinal turntable 10, the longitudinal turntable 10 is driven to move through the movement of the turntable base 6, and the longitudinal turntable 10 is rotatably connected with a transverse turntable 7 to realize the free rotation of the transverse turntable 7; a universal turntable 11 is rotationally connected in the transverse turntable 7, so that the universal turntable 11 can freely rotate; the unmanned aerial vehicle load to be tested 9 is arranged at the top of the universal turntable 11; preferably, the universal turntable 11 comprises a tray 111 and a support arm 112, the support arm 112 is connected with the tray 111 through a first bolt 113, two ends of the support arm 112 are rotatably connected with the transverse turntable 7 through first ball bearings 12, the support arm 112 is used for installing the tray 111 and realizing free rotation of the tray 111, the first ball bearings 12 are installed in first bearing fixing supports 114, the first bearing fixing supports 114 are connected with the transverse turntable 7, and the unmanned aerial vehicle load to be tested 9 is installed at the top of the tray 111; the unmanned aerial vehicle load 9 to be tested can be selected from single-shaft unmanned aerial vehicles, two-shaft unmanned aerial vehicles, four-shaft unmanned aerial vehicles, six-shaft unmanned aerial vehicles and eight-shaft unmanned aerial vehicles;
the bottom of the universal rotary table 11 is provided with a counterweight adjusting device 13, preferably, the counterweight adjusting device 13 comprises a screw 131 and a counterweight block 132, the bottom of the support arm 112 is screwed with the screw 131, the other end of the screw 131 is screwed with the counterweight block 132, and counterweight adjustment is performed according to loads of unmanned aerial vehicles with different weights;
the fixed base 1 is internally provided with a parameter information display part 2, and the parameter information display part 2 is a control, measurement and parameter information display system of a built-in system.
The utility model provides a passive operating platform for testing and adjusting parameters of dynamic attitude of a multi-rotor aircraft, when in use, an unmanned aerial vehicle load 9 to be tested is selected as a four-axis unmanned aerial vehicle, and the four-axis unmanned aerial vehicle is arranged at the top of a tray 111;
when the system starts to work, the platform base 1 is started, the parameter information display system is waited for finishing information display initialization, when the parameter information display system is finished, the initialization prompt can start flight test, and a student or a tester starts the unmanned aerial vehicle of the four-axis system by using external wireless control equipment or autonomous programmed control equipment to start flight test;
because the load 9 of the unmanned aerial vehicle to be tested is fixed on the universal rotary table 11, the unmanned aerial vehicle can rotate with a first degree of freedom in space by taking the first ball bearing 12 as an axis, and the transverse rotary table 7 directly connected with the universal rotary table 11 is rotatably connected onto the longitudinal rotary table 10, so that the universal rotary table 11 and the transverse rotary table 7 can rotate with a second degree of freedom in space around the rotary connection position of the longitudinal rotary table 10 and the transverse rotary table 7;
the unmanned aerial vehicle load to be tested 9, the universal rotary table 11, the longitudinal rotary table 10 and the transverse rotary table 7 are mutually connected and then fixed on the rotary table base 6, the rotary table base 6 is rotationally connected with the fixed connecting block 4, and the rotary table base 6 can rotate; therefore, the unmanned aerial vehicle load 9 to be tested can move in three degrees of freedom in space, a student or a tester can safely test and observe the unmanned aerial vehicle load 9 to be tested in a limited range, and various action angle parameters and lift force information of the unmanned aerial vehicle load 9 to be tested can be displayed on the parameter information display system at the same time.
The utility model discloses an in the embodiment, rotate through thrust ball bearing 5 between carousel base 6 and the fixed connection piece 4 and be connected, further make things convenient for carousel base 6's rotation.
In an embodiment of the present invention, the transverse rotating disk 7 is connected to the longitudinal rotating disk 10 by the second bolt 82, the inner side of the transverse rotating disk 7 is fixedly provided with the second bearing fixing support 81, the second ball bearing 8 is fixedly arranged in the second bearing fixing support 81, the side wall of the transverse rotating disk 7 is provided with a through hole, the aperture size of the through hole is larger than the rod diameter size of the second bolt 82, the second bolt 82 respectively penetrates through the through holes on the side walls of the second ball bearing 8 and the transverse rotating disk 7 to be connected to the longitudinal rotating disk 10, the head of the second bolt 82 is not in contact with the second bearing fixing support 81, the second bolt 82 is not in contact with the through hole, the second bolt 82 and the second ball bearing 8, the second bolt 82 and the longitudinal rotating disk 10 are in interference fit, rotation between the transverse rotating disk 7 and the longitudinal rotating disk 10 is facilitated, the second bolt 82 respectively penetrates through the second ball bearing 8, the through hole on the side wall of the transverse rotating disk 7 and the side wall of the longitudinal rotating disk 10 are connected to the matching nut 83, the connection relation between the second bolt 82 and the longitudinal rotary table 10 is further strengthened, the fit relation between the second bolt 82 and the longitudinal rotary table 10 is interference fit, no movement relation exists between the second bolt and the longitudinal rotary table, and the nut 83 cannot rotate after being installed.
The utility model provides a passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment, which can be used for various types of multi-rotor unmanned aerial vehicles, four-axis, six-axis, eight-axis rotorcraft and other types, the model of the operating platform can be matched with the types of the machines with different sizes, the test operating platform can constrain the multi-rotor unmanned aerial vehicle within a limited controllable range no matter in the design of a prototype, the initial test stage or the later learning, training, operation and flying stage, the probability of danger to the external environment and personnel is effectively reduced, meanwhile, the real flying condition of the multi-rotor unmanned aerial vehicle on the equipment is not limited by any degree of freedom, the starting flying state and attitude of the multi-rotor unmanned aerial vehicle are completely the same as the real scene during normal flying, the multi-rotor unmanned aerial vehicle can still carry out the maneuvering actions of rolling, pitching, yawing and the like, the real flying state which is constrained by certain conditions is completely different from the computer simulation environment, the flight state and the feeling can enable an operator to more intuitively and clearly feel the action state during operation and the real-time correlation condition of the multi-rotor aircraft;
in the educational and teaching environment, the utility model can be used for better demonstration and teaching indoors, the teaching efficiency of the unmanned aerial vehicle system and the cognitive level of students are improved, and the potential risks of the unmanned aerial vehicle equipment to the surrounding environment and the human body can be greatly reduced; and the utility model provides a many rotor unmanned aerial vehicle aircraft need test, adjust, observe and the process equipment of stereotyping to the static mechanism characteristic and the dynamic characteristic parameter of specific aircraft in research, design, production, equipment and debugging process, designs and tests, can accelerate the efficiency of unmanned aerial vehicle design test greatly, reduces the loss probability of equipment.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (7)
1. A passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment is characterized by comprising a fixed base (1), a parameter information display part (2) and a rotatable universal load test part;
a rotatable universal load testing component is arranged on the fixed base (1);
the fixed base (1) is internally provided with a parameter information display part (2), and the parameter information display part (2) is a control, measurement and parameter information display system of a built-in system.
2. The passive operating platform for multi-rotor aircraft dynamic attitude test tuning according to claim 1, wherein the rotatable universal load testing component comprises a fixed connection block (4), a turntable base (6), a transverse turntable (7), a longitudinal turntable (10), a universal turntable (11), and a counterweight adjustment device (13); a chassis (3) is arranged on the fixed base (1), a fixed connecting block (4) is arranged on the chassis (3), and a turntable base (6) is rotatably connected to the fixed connecting block (4);
be connected with vertical carousel (10) on carousel base (6), vertical carousel (10) internal rotation is connected with horizontal carousel (7), horizontal carousel (7) internal rotation is connected with universal carousel (11), universal carousel (11) bottom is equipped with counter weight adjusting device (13), and the unmanned aerial vehicle load of awaiting measuring (9) is installed in universal carousel (11) top.
3. The passive operating platform for multi-rotor aircraft dynamic attitude testing parameter adjustment according to claim 2, wherein the turntable base (6) is rotatably connected with the fixed connecting block (4) through a thrust ball bearing (5).
4. The passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment according to claim 2, wherein the universal rotary table (11) comprises a tray (111) and a support arm (112), the support arm (112) is connected with the tray (111) through a first bolt (113), two ends of the support arm (112) are rotatably connected with the transverse rotary table (7) through a first ball bearing (12), the first ball bearing (12) is installed in a first bearing fixing support (114), the first bearing fixing support (114) is connected with the transverse rotary table (7), and an unmanned aerial vehicle load (9) to be tested is installed on the top of the tray (111).
5. The passive operating platform for multi-rotor aircraft dynamic attitude test parameter adjustment according to claim 4, wherein the counterweight adjusting device (13) comprises a screw (131) and a counterweight (132), the screw (131) is screwed at the bottom of the support arm (112), and the counterweight (132) is screwed at the other end of the screw (131).
6. The passive operating platform for multi-rotor aircraft dynamic attitude testing parameter adjustment according to claim 2, wherein the transverse rotating disk (7) is connected with the longitudinal rotating disk (10) through a second bolt (82), a second bearing fixing support (81) is installed on the inner side of the transverse rotating disk (7), a second ball bearing (8) is installed in the second bearing fixing support (81), the second bolt (82) penetrates through the second ball bearing (8) and the side wall of the transverse rotating disk (7) to be connected with the longitudinal rotating disk (10) respectively, and the second bolt (82) and the second ball bearing (8), the second bolt (82) and the longitudinal rotating disk (10) are in interference fit.
7. The passive operating platform for multi-rotor aircraft dynamic attitude testing tuning according to claim 6, wherein the second bolt (82) is connected with a matching nut (83) through the second ball bearing (8), the lateral turntable (7) side wall and the longitudinal turntable (10) side wall respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120835942.7U CN214824253U (en) | 2021-04-22 | 2021-04-22 | Passive operating platform for testing and parameter-adjusting of dynamic attitude of multi-rotor aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120835942.7U CN214824253U (en) | 2021-04-22 | 2021-04-22 | Passive operating platform for testing and parameter-adjusting of dynamic attitude of multi-rotor aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701660A (en) * | 2022-04-14 | 2022-07-05 | 昆山小莫智能科技有限公司 | Multi-rotor unmanned aerial vehicle debugging device and debugging method thereof |
| CN117058947A (en) * | 2023-09-12 | 2023-11-14 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
-
2021
- 2021-04-22 CN CN202120835942.7U patent/CN214824253U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114701660A (en) * | 2022-04-14 | 2022-07-05 | 昆山小莫智能科技有限公司 | Multi-rotor unmanned aerial vehicle debugging device and debugging method thereof |
| CN117058947A (en) * | 2023-09-12 | 2023-11-14 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
| CN117058947B (en) * | 2023-09-12 | 2024-03-15 | 广州天海翔航空科技有限公司 | Half-simulation flight training system and method for fixed-wing unmanned aerial vehicle |
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