CN213934635U - Novel unmanned aerial vehicle attitude control device - Google Patents
Novel unmanned aerial vehicle attitude control device Download PDFInfo
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- CN213934635U CN213934635U CN202023230273.5U CN202023230273U CN213934635U CN 213934635 U CN213934635 U CN 213934635U CN 202023230273 U CN202023230273 U CN 202023230273U CN 213934635 U CN213934635 U CN 213934635U
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Abstract
The application discloses a novel unmanned aerial vehicle attitude control device, which relates to the technical field of unmanned aerial vehicles, and comprises an unmanned aerial vehicle body and a plurality of groups of electric control grid plate attitude control retaining devices, wherein each group of electric control grid plate attitude control retaining devices comprises a grid plate fixing plate fixed with the unmanned aerial vehicle body, a mounting side plate and a mounting plate, the lower end of the mounting plate is movably connected with a left movable grid plate and a right movable grid plate, the lower ends of 2 mounting side plates are movably connected with a front movable grid plate and a rear movable grid plate, and motion control mechanisms are respectively arranged between the mounting plate and the left movable grid plates and between the mounting side plates and the front movable grid plates as well as between the mounting side plates and the rear movable grid plates; automatically controlled grid tray attitude control is independent of flight rotor with attitude control outside, and flight rotor only undertakes flight power, and the stability and the gesture of aircraft keep handing over by automatically controlled grid tray control, have solved the problem that many rotor unmanned aerial vehicle bodily forms of flight rotor oar footpath restriction, are favorable to large-scale heavy load rotor unmanned aerial vehicle development.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, more specifically relates to a novel unmanned aerial vehicle attitude control device.
Background
The attitude adjusting and maintaining device is an important guarantee for the safe, stable and reliable flight of the aircraft, and is also a core key technology of the primary consideration of aircraft design and manufacture and the key test evaluation, and the performance and quality of the attitude adjusting and maintaining device is a primary mark for measuring the maneuverability of the aircraft and also determines the quality of the aircraft and the use reliability and safety of the aircraft.
The existing mainstream technology for controlling the attitude of the multi-rotor unmanned aerial vehicle is a non-control-plane mode, the attitude adjustment is realized by changing the speed of the rotor, the speed difference between the rotors generates a synthetic deflection force on a paddle surface, and the force acts on the center of the rotor to form a deflection moment, so that the aircraft is pushed to incline, pitch and turn, and the attitude adjustment and maintenance are further completed. The rotor wing is responsible for the propulsion power of the aircraft and the attitude adjustment and maintenance of the aircraft, so that when the speed of the rotor wing is changed, the moving speed and the height of the aircraft are inevitably lost, particularly under the condition of crosswind, the attitude adjustment is frequent, the moving speed of the aircraft is obviously slowed down, and the height is difficult to maintain.
And along with the grow of organism and the extension of rotor, the inertia of many rotor unmanned aerial vehicle rotors increases thereupon, and the hysteresis quality and the slow down nature of its attitude adjustment will bring the stability of aircraft and worsen gradually, even become invalid and can't use. This is also the main reason why multi-rotor aircraft cannot be made into unmanned aerial vehicles with heavy loads and large sizes. Many rotor unmanned aerial vehicle of industrial grade inherits the small and exquisite flexibility of little many rotor unmanned aerial vehicle, advantage convenient to use, for pertinence solve little many rotor unmanned aerial vehicle load capacity and range, the restricted problem during navigation, the power characteristic of aircraft has mainly been promoted (become electronic the oil machine), proper amplification has been carried out to the appearance structure and the rotor size of aircraft simultaneously, though flight principle and appearance structure are similar to little many rotor unmanned aerial vehicle, but flight attitude control is with the mechanism of keeping but with little many rotor unmanned aerial vehicle big dissimilarity. Firstly, as the body becomes larger and the rotors are lengthened, the rotary inertia of the rotors of the multi-rotor unmanned aerial vehicle is increased, the attitude adjustment is carried out by means of the speed difference between the rotors, and the stability of the aircraft is gradually deteriorated and even the aircraft fails to be used due to the hysteresis and the slowness of the aircraft; secondly, the utilization of the speed difference between the power rotors can cause power loss and load capacity reduction, and the reduction of flight performance such as lifting limit, speed, wind resistance and the like, which is not desirable on the industrial multi-rotor unmanned aerial vehicle. Especially, the takeoff weight of the industrial-grade multi-rotor unmanned aerial vehicle is more than 50kg, the diameter of a flying rotor exceeds 80cm, and the control and the maintenance of the attitude of the aircraft by applying the speed difference between power rotors can hardly be realized.
For an industrial unmanned aerial vehicle, the attitude is adjusted or maintained through the speed difference between the rotors by sacrificing the main lift force and the propulsive force to realize attitude transformation, so that the unmanned aerial vehicle is not cost-effective in economical efficiency and is not even feasible in technical aspect.
SUMMERY OF THE UTILITY MODEL
The purpose of this application lies in: in order to solve the problem that the traditional unmanned aerial vehicle realizes attitude transformation by sacrificing main lift and propulsive force through speed difference between rotors or keeping the attitude, a novel unmanned aerial vehicle attitude control device is disclosed, and the adjustment of the attitude of the aircraft is faster and better.
The following technical scheme is specifically adopted in order to achieve the purpose:
a novel unmanned aerial vehicle attitude control device comprises an unmanned aerial vehicle body, wherein a plurality of groups of electric control grid plate attitude control and maintaining devices are arranged on the side wall of the unmanned aerial vehicle body, the attitude control and maintenance device of the electric control grid plate comprises a grid plate fixing plate fixed with the unmanned aerial vehicle body, 1 mounting plate, 2 mounting side plates and corresponding movable grid plates, the device fixing plate, the 1 mounting plate and the 2 mounting side plates form a grid plate fixing frame, the lower end of the mounting plate is movably connected with a left movable grid plate and a right movable grid plate, the lower end of the mounting side plate is movably connected with a front movable grid plate and a rear movable grid plate, motion control mechanisms are arranged between the mounting plate and the left and right movable grid plates and between the mounting side plate and the front and rear movable grid plates, the motion control mechanisms are identical in structure, the motion control mechanisms control the left and right movable grid plates to deflect leftwards or rightwards, and the motion control mechanisms control the front and rear movable grid plates to deflect forwards or backwards.
By the scheme, the front movable grid plate and the rear movable grid plate control the pitching of the aircraft, and the left movable grid plate and the right movable grid plate control the inclination (rolling) of the aircraft. In the flying process, the flying control sends an attitude adjusting or maintaining instruction according to the flying state, the corresponding steering engine is controlled to control the corresponding grid plate to deflect or maintain the state through the motion control mechanism, the pneumatic effect on the corresponding grid plate is changed in a flowing mode, and the attitude of the aircraft is adjusted and maintained, so that the aircraft can fly safely, reliably and stably according to a preset air route.
The attitude control and maintenance device of the electric control grid plate controls the deflection of the left and right movable grid plates 4 or the front and back movable grid plates 3 through the motion control mechanism, the generated pneumatic deflection torque adjusts and maintains the attitude of the aircraft, the left and right movable grid plates 4 and the front and back movable grid plates 3 have large areas, the pneumatic effect is good, the response is fast, the deviation correction capability is strong, the attitude adjustment of the aircraft is faster and better, the attitude is easier to maintain, the problems of slow and unstable attitude adjustment of the large rotor unmanned aerial vehicle can be solved, the anti-crosswind capability of the rotor unmanned aerial vehicle can be improved, the range of the deflection angle is small, the electric energy requirement of the steering engine is low, and the weight reduction of the aircraft and the lengthening of a battery during use are facilitated; automatically controlled grid tray attitude control holding device separates out many rotor unmanned aerial vehicle attitude adjustment from the power rotor, the power rotor only undertakes aircraft motion (gos forward, retreat, climb, descend etc.) power, attitude adjustment shares by automatically controlled grid tray attitude control holding device with keeping, in order to realize the biggest efficiency of engine power, and the flight rotor only undertakes flight power, the stability and the attitude of aircraft keep handing over by automatically controlled grid tray control, the problem that the many rotor unmanned aerial vehicle bodily forms of flight rotor oar footpath restriction is also heavily loaded and is easily solved, be favorable to large-scale rotor unmanned aerial vehicle's development.
Furthermore, the motion control mechanism comprises a steering engine, a connecting rod and a movable rocker arm, the steering engine is arranged on the mounting plate and the mounting side plate, one end of the connecting rod is connected with the steering engine rocker arm, the other end of the connecting rod is connected with the movable rocker arm, and the movable rocker arm, the left movable grid plate, the right movable grid plate, the front movable grid plate and the rear movable grid plate are fixed through bolts.
Through the scheme, it drives the connecting rod through the steering wheel and removes, drive the movable rocker arm and remove then, about ordering about the activity grid tray with around the activity grid tray along articulated department deflection, and then change the air current and at the pneumatic effect that corresponds the activity grid tray, realize the adjustment and the maintenance of aircraft gesture, activity grid tray control mechanism design is dexterous, moreover, the steam generator is simple in structure, equipment such as steering wheel chooses for use conveniently, the preparation is easy, the practicality is good, the installation is in place and need not debug repeatedly, single steering wheel trouble does not influence the aircraft and uses, only reduce aircraft gesture adjustment and keep efficiency, the system reliability is good, and the security is high.
Furthermore, be equipped with the steering wheel rocking arm on the steering wheel, the holding tank has been seted up on the installation curb plate, the connecting rod be equipped with 2 and with steering wheel rocking arm both ends are connected, the activity rocking arm is the arc, both ends respectively with 2 the connecting rod is connected, activity rocking arm middle part is equipped with the fixed orifices.
Through above-mentioned scheme, set up the holding tank and be convenient for load the steering wheel and provide the rotation space for the steering wheel rocking arm, the activity rocking arm is the arc, rotates when the steering wheel rocking arm and drives 2 connecting rods and remove, makes the activity rocking arm to one side swing, and it adopts this kind of setting, and fixed effect is better, and overall structure is firm, and the operation is stable.
Furthermore, the mounting side plate, the movable grid plate and the grid plate fixing plate form a rectangular hopper-shaped structure.
Through the scheme, the front movable grid plate, the rear movable grid plate and the left movable grid plate and the right movable grid plate are conveniently adjusted, and the structure is simple.
Furthermore, the motion control mechanism comprises a steering engine and a steering engine rocker arm which are arranged on the mounting side plate, a connecting rod and a movable rocker arm, wherein the movable rocker arm, the left movable grid plate, the right movable grid plate, the front movable grid plate and the rear movable grid plate are fixed through bolts.
According to the scheme, the steering engine, the connecting rod, the movable rocker arm and the control steering engine are used for controlling the left movable grid plate, the right movable grid plate, the front movable grid plate and the rear movable grid plate to deflect, and posture adjustment is achieved through angular displacement of the movable grid plates.
The beneficial effect of this application is as follows:
1. the multi-rotor unmanned aerial vehicle attitude control system is simple in structure, the multi-rotor unmanned aerial vehicle attitude adjustment is separated from the power rotor by adopting an electric control grid plate technology, the power rotor only bears the power of the motion (advancing, retreating, climbing, descending and the like) of the aircraft, and the attitude adjustment and maintenance are shared by the electric control grid plate attitude control maintaining device, so that the maximum efficiency of the power of an engine is realized; the problem that the attitude of the large-rotor unmanned aerial vehicle is slowly and even unstable in adjustment is solved by utilizing large-area large-torque effect generated by the left and right movable grid plates and the front and rear movable grid plates; the left and right movable grid plates and the front and rear movable grid plates have quick response, strong deviation rectifying capability and easier posture maintenance, so that the crosswind resisting capability of the rotor unmanned aerial vehicle is enhanced; the flying rotor only bears flying power, the stability and the posture of the aircraft are kept under the control of the electric control grid plate, and the problem that the size of the multi-rotor unmanned aerial vehicle is limited by the propeller diameter of the flying rotor is solved, so that the development of a large heavy-load rotor unmanned aerial vehicle is facilitated;
2. compared with the pure electric rotor wing attitude control technology, the electric control grid plate attitude control and maintaining device has low electric energy requirement, and is favorable for the long-endurance flight of the aircraft under the condition of a given storage battery.
Drawings
FIG. 1 is a schematic view of the present application in an installed state;
FIG. 2 is a schematic structural view of the electronically controlled grid attitude control holding device of the present application;
fig. 3 is a schematic structural diagram of a rudder control mechanism in an embodiment of the present application.
Reference numerals: 1. a grid plate fixing plate; 2. installing a side plate; 21. mounting a plate; 3. front and rear movable grid plates; 4. a left movable grid plate and a right movable grid plate; 5. a steering engine; 6. a steering engine rocker arm; 7. a connecting rod; 8. a movable rocker arm; 9. a screw hole; 10. an unmanned aerial vehicle body; 11. a fixing hole; 12. and (6) accommodating the tank.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Example 1
As shown in fig. 1 and fig. 2, this embodiment provides a novel attitude control device for unmanned aerial vehicle, which comprises an unmanned aerial vehicle body 10, wherein 2 sets of electronic control grid plate attitude control retaining devices are arranged on the left and right side walls of the unmanned aerial vehicle body 10, each electronic control grid plate attitude control retaining device comprises a grid plate fixing plate 1 fixed with the unmanned aerial vehicle body 10, the grid plate fixing plate 1 is fixed with the unmanned aerial vehicle through bolts, screw holes 9 are arranged on the grid plate fixing plate 1, two mounting side plates 2 and 1 mounting plate 21 are vertically arranged on the grid plate fixing plate 1, one end of each of the two fixing side plates is connected with the grid plate fixing plate 1, the other end is connected with the mounting plate 21, the lower end of the mounting plate 21 is movably connected with a left and right movable grid plate 4, the lower end of each of the 2 mounting side plates 2 is movably connected with a front and rear movable grid plate 3, and movement control mechanisms are arranged between the mounting plate 21 and the left and right movable grid plates 4 and the mounting side plates 2 and the front and rear movable grid plates 3, the motion control mechanisms have the same structure, the motion control mechanisms connected with the left and right movable grid plates 4 control the left and right movable grid plates 4 to deflect leftwards and rightwards, and the motion control mechanisms connected with the front and rear movable grid plates 3 control the front and rear movable grid plates 3 to deflect forwards and backwards.
Therefore, the front and rear movable grid plates 3 control the pitching of the aircraft, the left and right movable grid plates 4 control the inclination (rolling) of the aircraft, in the flight process, the flight control sends out attitude adjustment or maintenance instructions according to the flight state, the corresponding steering engines 5 are operated to control the corresponding grid plates to deflect or maintain the state through the motion control mechanisms, the aircraft attitude is adjusted and maintained through changing the pneumatic effect on the corresponding grid plates through airflow, and therefore the aircraft can fly safely, reliably and stably according to a preset air route.
The attitude control and maintenance device of the electric control grid plate controls the deflection of the left and right movable grid plates 4 or the front and back movable grid plates 3 through the motion control mechanism, the generated pneumatic deflection torque adjusts and maintains the attitude of the aircraft, the left and right movable grid plates 4 and the front and back movable grid plates 3 have large areas, the pneumatic effect is good, the response is fast, the deviation correction capability is strong, the attitude adjustment of the aircraft is faster and better, the attitude is easier to maintain, the problems of slow and unstable attitude adjustment of the large rotor unmanned aerial vehicle can be solved, the anti-crosswind capability of the rotor unmanned aerial vehicle can be improved, the range of the deflection angle is small, the electric energy requirement of the steering engine is low, and the weight reduction of the aircraft and the lengthening of a battery during use are facilitated; automatically controlled grid tray attitude control holding device separates out many rotor unmanned aerial vehicle attitude adjustment from the power rotor, the power rotor only undertakes aircraft motion (gos forward, retreat, climb, descend etc.) power, attitude adjustment shares by automatically controlled grid tray attitude control holding device with keeping, in order to realize the biggest efficiency of engine power, and the flight rotor only undertakes flight power, the stability and the attitude of aircraft keep handing over by automatically controlled grid tray control, the problem that the many rotor unmanned aerial vehicle bodily forms of flight rotor oar footpath restriction is also heavily loaded and is easily solved, be favorable to large-scale rotor unmanned aerial vehicle's development.
Referring to fig. 2 and 3, the mounting plate 21, the mounting side plate 2, the grid plate fixing plate 1 and the corresponding movable grid plate form a rectangular hopper-shaped structure, and a motion control mechanism is arranged on the rectangular hopper-shaped structure so as to control the front and rear movable grid plates 3 and the left and right movable grid plates 4 to move to realize attitude control. The motion control mechanism comprises a steering engine 5, a steering engine rocker arm 6, a connecting rod 7 and a movable rocker arm 8, the steering engine 5 is arranged on the installation side plate 2 and the installation plate 21, one end of the connecting rod 7 is connected with the steering engine rocker arm 6, the other end of the connecting rod is connected with the movable rocker arm 8, and the movable rocker arm 8, the left movable grid plate 4, the right movable grid plate 4, the front movable grid plate 3 and the rear movable grid plate 3 are fixed through bolts through bolt holes 11. Steering wheel 5 is last to be provided with steering wheel rocking arm 6, sets up on installation curb plate 2 and the mounting panel 21 and has put holding tank 12, and connecting rod 7 is provided with 2 and one end and is connected with the 6 both ends of steering wheel rocking arm respectively, and movable rocking arm 8 is the arc, and both ends are connected with the 7 other ends of 2 connecting rods respectively, and 8 middle parts of movable rocking arm are provided with fixed orifices 11.
The containing groove 12 is arranged to facilitate the installation of the steering engine 5 and provide a moving space for the steering engine rocker arm 6, the movable rocker arm 8 is arc-shaped, when the steering engine 5 drives the steering engine rocker arm 6 to rotate to drive the connecting rods 7 to move, and the movable rocker arm 8 is driven to swing to one side, the arrangement is adopted, the fixing effect is better, the whole structure is stable, the operation is stable, the connecting rods 7 are driven to move through the steering engine 5, and then the movable rocker arm 8 is driven to move, so that the left and right movable grid plates 4 and the front and back movable grid plates 3 are driven to deflect along the hinged part, and the adjustment and maintenance of the attitude of the aircraft are realized by changing the pneumatic effect of airflow acting on the corresponding movable grid plates, the movable grid plate motion control mechanism is simple in design and manufacture, the structure is simple, the steering engine 5, the connecting rods 7 and other devices are convenient to select, the manufacture is easy, the practicability is good, the repeated debugging is not needed when the steering engine 5 is installed in place, the use of the aircraft is not influenced by the single steering engine 5, the aircraft attitude adjustment keeping efficiency is only reduced, the system reliability is good, and the safety is high.
Example 2
The structure of this embodiment is basically the same as that of embodiment 1, and the difference lies in that the motion control mechanism includes a telescopic screw rod (or an actuator cylinder) arranged on the mounting side plate 2 and the mounting plate 21, and further includes a control motor (not shown) for driving the telescopic screw rod (or the actuator cylinder) to operate, the telescopic screw rod (or the actuator cylinder) and the left and right movable grid plates 4 and the front and rear movable grid plates 3 are fixed by bolts, the left and right movable grid plates 4 and the front and rear movable grid plates 3 are driven to deflect by adopting the telescopic screw rod (or the actuator cylinder) and the control motor, and the posture adjustment is realized by the angular displacement of the movable grid plates.
The second purpose of this application provides an unmanned aerial vehicle attitude control method who is applied to above-mentioned novel unmanned aerial vehicle attitude control device.
An unmanned aerial vehicle attitude control method applied to the novel unmanned aerial vehicle attitude control device comprises the following steps:
s1; the control instruction of the steering engine 5 comes from aircraft flight control equipment, when the aircraft takes off, the power supply is switched on, and the aircraft flight control equipment controls the left and right movable grid plates 4 and the front and rear movable grid plates 3 to be in a suspension state until the aircraft reaches a preset height;
s2; when the aircraft enters horizontal flight, the aircraft flight control equipment still has no attitude adjustment instruction, the left and right movable grid plates 4 and the front and rear movable grid plates 3 are continuously in a suspension state, and the aircraft keeps a horizontal flight attitude;
s3: when crosswind pushes the aircraft to tilt leftwards, the aircraft flight control equipment sends a right rolling instruction, the steering engine 5 controls the steering engine rocker arm 6 to drive the connecting rod 7, the movable rocker arm 8 and the left and right movable grid plates 4 to deflect rightwards, and the left and right movable grid plates 4 deflect rightwards to offset the influence of the left wind; when crosswind pushes the aircraft to tilt rightwards, the aircraft flight control equipment sends a leftward rolling instruction, the steering engine 5 controls the steering engine rocker arm 6 to drive the connecting rod 7, the movable rocker arm 8 and the left and right movable grid plates 4 to deflect leftwards, the movable grid plates deflect leftwards to offset the influence of right-side wind, and the aircraft is enabled to fly in a preset course;
s4: when the aircraft needs to climb, the ground station sends a corresponding instruction, and the flight control equipment of the aircraft on the aircraft receives the instruction, then outputs and controls the steering engine 5 to operate the front and rear movable grid plates 3 to deflect forwards, so as to generate an upward deflection torque, push the aircraft head to face upwards, and the aircraft climbs until the ground station sends a leveling instruction, the front and rear movable grid plates 3 return to a suspension state, and the aircraft enters a level flight state;
s5: other attitude adjustment and maintenance such as landing, left rolling, right rolling and the like are similar in mode and same in principle, and are all the actions of controlling the corresponding left and right movable grid plates 4 and the front and back movable grid plates 3 by the aircraft flight control equipment steering engine 5, so that the aircraft is pushed to enter or maintain the designated or required attitude or flight state.
The ground station comprises a remote controller, a mobile phone and a PC computer. The working states of the aircraft comprise take-off, landing, left rolling, right rolling, strong wind, weak wind, damage of the left and right movable grid plates 4 or the front and rear movable grid plates 3 and failure of a single steering engine 5.
Compared with the pure electric rotor wing attitude control technology, the electric control grid plate attitude control and maintaining device has low electric energy requirement, and is favorable for the long-endurance flight of the aircraft under the condition of a given storage battery.
The implementation principle is as follows: the application adopts the electric control grid plate technology, and the adjustment and the maintenance of the attitude of the aircraft are realized by causing the left and right movable grid plates 4 and the front and rear movable grid plates 3 to deflect along the hinged part and further changing the pneumatic effect of airflow acting on the corresponding movable grid plates; the attitude adjustment of the multi-rotor unmanned aerial vehicle is separated from the power rotor, the flight rotor only bears the motion (advancing, retreating, climbing, descending and the like) power of the aircraft, and the attitude adjustment and maintenance are shared by the attitude control and maintenance device of the electric control grid plate so as to realize the maximum efficiency of the power of the engine; the large moment effect generated by the left and right movable grid plates 4 and the front and rear movable grid plates 3 in a large area is used for solving the problem that the attitude of the large-rotor unmanned aerial vehicle is slowly and even unstable; the left and right movable grid plates 4 and the front and rear movable grid plates 3 have fast response, strong deviation rectifying capability and easier posture maintenance, and the anti-crosswind capability of the rotor unmanned aerial vehicle is enhanced; the flight rotor only undertakes flight power, and the stability and the gesture of aircraft keep handing over by automatically controlled grid tray control, and the problem of flight rotor oar footpath restriction many rotor unmanned aerial vehicle bodily forms is also solved at a glance, is favorable to large-scale heavy load rotor unmanned aerial vehicle's development.
Claims (4)
1. A novel unmanned aerial vehicle attitude control device comprises an unmanned aerial vehicle body (10) and is characterized in that a plurality of groups of electric control grid plate attitude control retaining devices are arranged on the side wall of the unmanned aerial vehicle body (10), the electric control grid plate attitude control retaining devices are of a bucket-shaped structure and comprise a grid plate fixing plate (1) fixed with the unmanned aerial vehicle body (10), installation side plates (2) and an installation plate (21) are arranged on the grid plate fixing plate (1), 2 installation side plates (2) and 1 installation plate (21) form a fixing frame, the lower end of the installation plate (21) is movably connected with left and right movable grid plates (4), the lower end of the installation side plate (2) is movably connected with front and rear movable grid plates (3), and motion control mechanisms are arranged between the installation plate (21) and the left and right movable grid plates (4) and between the installation side plates (2) and the front and rear movable grid plates (3), the motion control mechanisms have the same structure, the motion control mechanisms control the left and right movable grid plates (4) to deflect leftwards or rightwards, and the motion control mechanisms control the front and rear movable grid plates (3) to deflect forwards or backwards.
2. The novel unmanned aerial vehicle attitude control device of claim 1, characterized in that, motion control mechanism includes steering wheel (5), connecting rod (7), movable rocker arm (8), steering wheel (5) are located installation curb plate (2) with on mounting panel (21), connecting rod (7) one end with steering wheel (5) are connected, the other end with movable rocker arm (8) are connected, movable rocker arm (8) with about movable grid tray (4) with around movable grid tray (3) all pass through the bolt fastening.
3. The novel unmanned aerial vehicle attitude control device of claim 2, characterized in that be equipped with steering wheel rocking arm (6) on steering wheel (5), installation curb plate (2) with holding tank (12) have been seted up on mounting panel (21), connecting rod (7) be equipped with 2 and with steering wheel rocking arm (6) both ends are connected, activity rocking arm (8) are the arc, both ends respectively with 2 connecting rod (7) are connected, activity rocking arm (8) middle part is equipped with fixed orifices (11).
4. The novel unmanned aerial vehicle attitude control device of claim 1, characterized in that the mounting plate (21) forms a rectangular hopper-shaped structure with the mounting side plate (2), the grid plate fixing plate (1) and the corresponding front and rear movable grid plates (3) and left and right movable grid plates (4).
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| CN202023230273.5U CN213934635U (en) | 2020-12-28 | 2020-12-28 | Novel unmanned aerial vehicle attitude control device |
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