CN112607005B - Attitude control mechanism of aircraft without control surface - Google Patents
Attitude control mechanism of aircraft without control surface Download PDFInfo
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- CN112607005B CN112607005B CN202011539434.0A CN202011539434A CN112607005B CN 112607005 B CN112607005 B CN 112607005B CN 202011539434 A CN202011539434 A CN 202011539434A CN 112607005 B CN112607005 B CN 112607005B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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Abstract
The invention discloses a control surface-free aircraft attitude control mechanism, and particularly relates to the technical field of aircraft attitude control. The device solves the problems of complex and unstable operation caused by the traditional adoption of a slide rail and a hinge in the wing to control the flight attitude, has a simple and feasible control structure, can keep the rudder effect to achieve the optimal flight effect, can automatically monitor the state of the aircraft in real time, further can finish the purpose of automatically adjusting the flight attitude to the abnormal state, ensures the course accuracy, further can ensure the intelligent operation and control work of the aircraft, and has good popularization value.
Description
Technical Field
The invention relates to the technical field of aircraft attitude control, in particular to an aircraft attitude control mechanism without a control surface.
Background
With the continuous development of aviation technology, aircrafts are involved in various fields, such as military, reconnaissance and monitoring, communication relay, electronic countermeasure and the like, civil, geodetic measurement, environmental monitoring and the like, scientific research, atmospheric research, sampling and monitoring of nuclear biochemical pollution areas and the like, and along with the expansion of the application field of aircrafts, people have greater and greater demands on aircrafts which are simple in structure and easy to control.
The conventional control surface is mostly adopted by the existing aircraft to control the flight attitude of the aircraft, but the aircraft is controlled by the slide rails and the hinges in the wings when flying at high altitude, so that the structure is complex, the control efficiency cannot reach the optimal effect, in the prior art, the position of the aircraft is controlled by holding the handle in the control process of the flight of the aircraft, and the aircraft is manually adjusted when the flight of the aircraft is inclined, so that the operation is more complicated, and in view of the above, the aircraft attitude control mechanism in the prior art needs to be improved.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides an attitude control mechanism of an aircraft without a control surface, and the invention aims to solve the technical problems that: the conventional control surface is adopted by the existing aircraft to control the flight attitude of the aircraft, but the aircraft is controlled by the slide rails and the hinges in the wings when flying at high altitude, so that the structure is complex, the control efficiency cannot reach the optimal effect, and in the prior art, the position of the aircraft is controlled by holding the handle in the control process of the flight of the aircraft, and the aircraft is manually adjusted when the flight of the aircraft is deflected, so that the operation is complicated.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a no control surface aircraft attitude control mechanism, includes the aircraft, the lower surface of aircraft and the last fixed surface of controller are connected, the left surface and the right flank of aircraft respectively with the opposite face fixed connection of four universal shells, the internal surface of universal shell is provided with universal ball, the upper surface of universal ball and the lower fixed surface of motor are connected, the output shaft of motor and the lower fixed surface of flight leaf are connected.
The outer surface of the universal ball is provided with a plurality of meshing grooves, part of the meshing grooves are meshed with the toothed plate, the left side face and the back face of the toothed plate are fixedly connected with one end of the first electric push rod and one end of the second electric push rod respectively, the other end of the first electric push rod is fixedly connected with the right side face of the first guide block, and the lower surface of the universal shell is fixedly connected with the upper surface of the shell.
First guide way has been seted up to shells inner wall's left surface, first guide block sliding connection is in first guide way, the second guide way has been seted up at shells inner wall's the back, sliding connection has the second guide block in the second guide way, the front and the second electric putter other end fixed connection of second guide block.
As a further scheme of the invention: the controller comprises a path planning unit, the output end of the path planning unit is electrically connected with the input end of a processing chip, the output end of the processing chip is electrically connected with the input end of a comparison module, the comparison module can compare collected information of a period of time, flying position information of the aircraft and attitude information of the aircraft in the flying process with data information under normal conditions, so that whether the flying state of the aircraft is abnormal or not can be known in real time, the input end of the comparison module is electrically connected with the output end of an information collection unit, the output end of the comparison module is electrically connected with an alarm module and the input end of an automatic adjustment unit, the alarm module can be used for carrying out alarm reminding on the abnormal information of the compared result data, further, a controller can check the condition of the aircraft in time, and the output end of the automatic adjustment unit is electrically connected with the input end of a data storage module, the data storage module can store various data information and perform induction, classification and sorting for subsequent orderly checking work, and is in bidirectional electric connection with the processing chip.
As a further scheme of the invention: the input end of the processing chip is electrically connected with the output end of the information input module, the information input unit is an instruction and data input device for operating the aircraft, the established route data can be input into a data storage module for storage and storage so as to establish a comparison basis for the real-time data acquisition of the flight of the aircraft, the input end of the processing chip is electrically connected with the output end of the storage battery, the storage battery can store the electric energy input by the solar energy collecting module, for the power supply requirement of the aircraft, the input end of the storage battery is electrically connected with the output end of the solar energy collecting module, the solar energy collecting module can convert the heat radiation energy of the solar light into electric energy, therefore, the power supply work of the aircraft can be guaranteed, and the solar energy is a renewable novel energy source which can be recycled, so that the aims of energy conservation and environmental protection can be fulfilled.
As a further scheme of the invention: the processing chip is electrically connected with the wireless transmission module in a two-way mode, the wireless transmission module is a network which can realize interconnection of various communication devices without wiring, so that the communication connection of an aircraft and a control end can be kept, the aircraft is ensured to be in normal control work, the input end of the wireless transmission module is electrically connected with the output end of the comparison module, the wireless transmission module is electrically connected with the terminal query display module in a two-way mode, the terminal query display module can display flight data information of the aircraft and feedback data information, and therefore the purpose of viewing and knowing the flight state of the aircraft in real time can be achieved.
As a further scheme of the invention: the route planning unit comprises a route establishing module and a route time position calculating module, the output ends of the route establishing module and the route time position calculating module are electrically connected with the input end of the processing chip, the route creation module may input the route location of the desired flight into the data storage module for storage, the route time position calculation module may input the positions reached by the normal flight of the aircraft during each period of time into the data storage for storage management, the route establishing module and the route time and position calculating module can establish a basis for the subsequent comparison work of the real-time collected data, the input end of the data storage module is electrically connected with the output end of the image acquisition module, the image acquisition module can transmit images of the aircraft in the flight process to the data storage module in real time, and the data storage module is inquired through the terminal to check the video information in real time.
As a further scheme of the invention: the information acquisition unit includes time acquisition module, big dipper orientation module and levelness measurement sensor, time acquisition module, big dipper orientation module and levelness measurement sensor's output is connected with the input electricity of contrast module, time acquisition module can gather in real time the time that consumes in the aircraft flight process, big dipper orientation module can fix a position in real time the position of aircraft, and it can obtain the position information that the aircraft flies in a period with the cooperation of time acquisition module, levelness measurement sensor can the attitude information of real-time supervision aircraft flight in-process to can ensure whether the aircraft flies according to planning the route.
As a further scheme of the invention: the automatic adjusting unit comprises four groups of first electric push rod adjusting modules and four groups of second electric push rod adjusting modules, the output ends of the four groups of first electric push rod adjusting modules and the output ends of the four groups of second electric push rod adjusting modules are electrically connected with the input end of the data storage module, and the input ends of the four groups of first electric push rod adjusting modules and the input ends of the four groups of second electric push rod adjusting modules are electrically connected with the output end of the comparison module.
As a further scheme of the invention: the upper surface of aircraft and solar panel's lower fixed surface are connected, the lower surface of controller and the upper surface fixed connection of camera, the surface of motor and the internal surface fixed connection of cell-shell.
As a further scheme of the invention: third guide way has all been seted up to shells inner wall's front and the right flank of inner wall, sliding connection has a third guide block, the place ahead in the third guide way the back and the right side of third guide block the left surface of third guide block respectively with the one end fixed connection of two telescopic links, two the other end of telescopic link respectively with the front and the right flank fixed connection of pinion rack.
The invention has the beneficial effects that:
1. the invention can monitor the flying state of the aircraft in real time by planning the route of the aircraft, inputting the position point reached in each period of time and then collecting the flying state of the aircraft, can know whether the flying abnormality exists in real time by matching and comparing the collected data information, can alarm the abnormal information to ensure the real-time understanding of the flying state, and can automatically control the first electric push rod or the second electric push rod to push the toothed plate to control the universal ball to carry out the angle swing work by the abnormal information controller, thereby achieving the work of adjusting the flying state of the aircraft, avoiding the problems of complex operation and instability caused by the control of the flying posture by a slide rail and a hinge in the traditional wing, leading the control structure of the device to be simple and easy, and keeping the steering effect to achieve the optimal flying effect, and this device carries out real-time supervision through the automation to the state of aircraft, and then can accomplish the purpose of automatically regulated flight gesture to abnormal state, ensures course accuracy nature, further can ensure the work that the aircraft intellectuality was controlled, has good spreading value.
2. The invention ensures that the first guide block, the second guide block and the third guide block can slide in the first guide groove, the second guide groove and the third guide groove respectively and more stably to avoid the problem of sliding out by arranging the first guide block, the first guide groove, the second guide block, the second guide groove, the third guide block and the third guide groove in a T shape, ensures the supporting work of the first electric push rod and the second electric push rod, thereby ensuring the smooth operation of the state adjustment of the aircraft, ensures the normal movable work of the first electric push rod and the second electric push rod by arranging the telescopic rod, and simultaneously ensures the aim of supporting the toothed plate by matching the telescopic rod with the first electric push rod and the second electric push rod, the placing stability of the toothed plate is guaranteed.
3. According to the invention, the latticed shell is arranged, so that the latticed shell can be communicated with the outside air, the work of air exchange in the latticed shell is ensured, and the flying blades are prevented from rotating in a closed space, so that the normal flying work of the device can be ensured, and meanwhile, the latticed shell can cover the flying blades in a closed manner, so that the flying blades can be protected, and the good flying work of an aircraft can be ensured.
Drawings
FIG. 1 is a schematic cross-sectional view of the front view of the present invention;
FIG. 2 is a schematic cross-sectional view of the housing of the present invention from above;
FIG. 3 is a schematic diagram of a controller system of the present invention;
in the figure: the solar camera comprises an aircraft 1, a controller 2, a storage battery 3, a camera 4, a solar panel 5, a universal shell 6, a universal ball 7, a shell 8, a first electric push rod 9, a toothed plate 10, an engaging groove 11, a telescopic rod 12, a motor 13, a flight blade 14, a reticulated shell 15, a first guide groove 16, a first guide block 17, a second guide groove 18, a second guide block 19, a second electric push rod 20, a third guide block 21 and a third guide groove 22.
Detailed Description
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. 1-3, the invention provides a control plane-free aircraft attitude control mechanism, which comprises an aircraft 1, wherein the lower surface of the aircraft 1 is fixedly connected with the upper surface of a controller 2, the left side surface and the right side surface of the aircraft 1 are respectively fixedly connected with the opposite surfaces of four universal shells 6, universal balls 7 are arranged on the inner surfaces of the universal shells 6, the upper surfaces of the universal balls 7 are fixedly connected with the lower surface of a motor 13, and the output shaft of the motor 13 is fixedly connected with the lower surfaces of flight blades 14.
A plurality of meshing groove 11 has been seted up to universal ball 7's surface, part meshing groove 11 meshes with pinion rack 10, the left surface and the back of pinion rack 10 respectively with first electric putter 9's one end and second electric putter 20's one end fixed connection, through setting up first electric putter 9 and second electric putter 20, control first electric putter 9 and second electric putter 20 and carry out work, thereby can control universal ball 7 in proper order and control wobbling work, thereby can adjust the angle of flight leaf 14, further reach the purpose of adjusting aircraft 1 flight gesture, the other end of first electric putter 9 and the right flank fixed connection of first guide block 17, the lower surface of universal shell 6 and the upper surface fixed connection of casing 8.
The left side surface of the inner wall of the shell 8 is provided with a first guide groove 16, a first guide block 17 is connected in the first guide groove 16 in a sliding manner, the back surface of the inner wall of the shell 8 is provided with a second guide groove 18, a second guide block 19 is connected in the second guide groove 18 in a sliding manner, the first guide block 17, the first guide groove 16, the second guide block 19, the second guide groove 18, the third guide block 21 and the third guide groove 22 are arranged in a T shape, the first guide block 17, the first guide groove 16, the second guide block 19, the second guide groove 18, the third guide block 21 and the third guide groove 22 are all arranged in a T shape, so that the first guide block 17, the second guide block 19 and the third guide block 21 can slide in the first guide groove 16, the second guide groove 18 and the third guide groove 22 respectively more stably, the problem of sliding out is avoided, and the supporting work of the first electric push rod 9 and the second electric push rod 20 is ensured, therefore, the smooth state adjustment work of the aircraft 1 can be ensured, and the front surface of the second guide block 19 is fixedly connected with the other end of the second electric push rod 20.
As shown in fig. 1, the upper surface of aircraft 1 and solar panel 5's lower fixed surface are connected, the lower surface of controller 2 and the upper fixed surface of camera 4 are connected, the surface of motor 13 and the internal surface fixed connection of latticed shell 15, through setting up latticed shell 15, make latticed shell 15 circulate with the outside air, the work of the inside air exchange of latticed shell 15 has been ensured, it is rotatory in airtight space to avoid flying leaf 14, thereby can ensure the work of this device normal flight, latticed shell 15 can cover flying leaf 14 closed simultaneously, thereby can play the guard action to flying leaf 14, guarantee aircraft 1 carries out good flight work.
As shown in fig. 2, third guide way 22 has all been seted up to the front of casing 8 inner wall and the right flank of inner wall, sliding connection has third guide block 21 in third guide way 22, the back of the third guide block 21 in the place ahead and the left flank of right side third guide block 21 respectively with the one end fixed connection of two telescopic links 12, through setting up telescopic link 12, make telescopic link 12 can stretch out and draw back, ensure the normal activity work of first electric putter 9 and second electric putter 20, telescopic link 12 can support the mesh to pinion rack 10 with the cooperation of first electric putter 9 and second electric putter 20 simultaneously, guarantee pinion rack 10 stability in placement, the other end of two telescopic links 12 respectively with the front and the right flank fixed connection of pinion rack 10.
As shown in fig. 3, the controller 2 includes a route planning unit, an output terminal of the route planning unit is electrically connected to an input terminal of the processing chip, an output terminal of the processing chip is electrically connected to an input terminal of the comparison module, the comparison module can compare the acquired information of a period of time, the information of the position where the aircraft 1 flies, and the attitude information of the aircraft 1 during flying with the data information under normal conditions, so as to know whether the flying state of the aircraft 1 is abnormal in real time, an input terminal of the comparison module is electrically connected to an output terminal of the information acquisition unit, an output terminal of the comparison module is electrically connected to an input terminal of the alarm module and the automatic adjustment unit, the alarm module can be used to alarm and remind the data of the abnormal information after comparison, so that the control personnel can check the condition of the aircraft 1 in time, an output terminal of the automatic adjustment unit is electrically connected to an input terminal of the data storage module, the data storage module can store various data information and perform induction, classification and arrangement for subsequent orderly checking work, the data storage module is in bidirectional electric connection with the processing chip, the input end of the processing chip is in electric connection with the output end of the information input module, the information input unit is an instruction and data input device for operating the aircraft 1 to operate, the established route data can be input into the data storage module for storage and preservation, a comparison basis is established for the subsequent flying real-time data acquisition of the aircraft 1, the input end of the processing chip is in electric connection with the output end of the storage battery 3, the storage battery 3 can store the electric energy input by the solar energy acquisition module for the power supply requirement of the aircraft 1, the input end of the storage battery 3 is in electric connection with the output end of the solar energy acquisition module, and the solar energy acquisition module can convert the heat radiation energy of the solar light rays into electric energy, thereby ensuring the power supply work of the aircraft 1, and the solar energy is a renewable novel energy source which can be recycled, thereby achieving the purposes of energy saving and environmental protection, the processing chip is in bidirectional electric connection with the wireless transmission module, the wireless transmission module is a network which can realize the interconnection of various communication equipment without wiring, thereby being capable of keeping the communication connection of the aircraft 1 and the control end and ensuring the aircraft 1 to be in the normal control work, the input end of the wireless transmission module is electrically connected with the output end of the comparison module, the wireless transmission module is in bidirectional electric connection with the terminal query display module, the terminal query display module can display the flight data information and the feedback data information of the aircraft 1, thereby achieving the purpose of checking and knowing the flight state of the aircraft 1 in real time, the route planning unit comprises a route establishing module and a route time position calculating module, the output ends of the route establishing module and the route time position calculating module are electrically connected with the input end of the processing chip, the route establishing module can input the route position to be flown into the data storage module for storage, the route time position calculating module can input the position reached by the normal flying route of the aircraft 1 in each time into the data storage for storage and management, the route establishing module and the route time position calculating module can establish a basis for the comparison work of subsequent real-time collected data, the input end of the data storage module is electrically connected with the output end of the image collecting module, the image collecting module can transmit the image in the flying process of the aircraft 1 to the data storage module in real time, and the terminal query display module is used for real-time checking work of video information, the information collecting unit comprises a time collecting module, a Beidou positioning module and a levelness measuring sensor, the automatic adjusting unit comprises four groups of first electric push rod adjusting modules and four groups of second electric push rod adjusting modules, the output ends of the four groups of first electric push rod adjusting modules and the output ends of the four groups of second electric push rod adjusting modules are electrically connected with the input end of the comparison module, the time acquisition module can acquire the time consumed in the flight process of the aircraft 1 in real time, the Beidou positioning module can position the position of the aircraft 1 in real time, the position information of the aircraft 1 in a period of time can be obtained by matching with the time acquisition module, the levelness measuring sensor can monitor the attitude information of the aircraft 1 in the flight process in real time, whether the aircraft 1 flies according to a planned route can be ensured, the automatic adjusting unit comprises four groups of first electric push rod adjusting modules and four groups of second electric push rod adjusting modules, the output ends of the four groups of first electric push rod adjusting modules and the four groups of second electric push rod adjusting modules are electrically connected with the input end of the data storage module, and the input ends of the four groups of first electric push rod adjusting modules and the four groups of second electric push rod adjusting modules are electrically connected with the output end of the comparison module And the ends are electrically connected.
The working principle of the invention is as follows:
s1, when the aircraft needs to fly, a flying route position point is established through the route establishing module, the position reached by the aircraft 1 in each time period under the normal condition in the route is calculated through the route time position calculating module, the position is input into the controller 2 through the information recording module, the position is processed by the processing chip and then transmitted to the data storage module for storage management, then the motor 13 can be controlled to work, so that the motor 13 drives the flying blade 14 to rotate at a high speed, and then the attitude of the aircraft 1 is controlled to ascend through the control end, so that the aircraft 1 enters a flying state;
s2, in the flying process of the aircraft 1, the flying time of the aircraft 1, the arriving position of the time and the attitude of the aircraft 1 can be monitored through the time acquisition module, the Beidou positioning module and the levelness measuring sensor, the monitored information is transmitted to the comparison module, meanwhile, the data storage module can transmit the pre-input state information of the normal flying of the aircraft 1 to the processing chip, the processing chip transmits the state information to the comparison module, the comparison module matches and compares the normal data information with the monitored data information, if the comparison result is abnormal, the information is transmitted to the alarm module for alarm reminding, the result is transmitted to the terminal query display module through the wireless transmission module to display the understanding information, and meanwhile, the comparison module can transmit the information to the automatic adjusting unit;
s3, finally, the automatic regulating unit issues an adjusting command according to the flying state, and then the controller 2 automatically controls the first electric push rod 9 to work, then the toothed plate 10 is pushed to move, so that the toothed plate 10 pushes the universal ball 7 to swing angularly under the action of the meshing groove 11, so that the flying vane 14 swings angularly to adjust the flying attitude of the aircraft 1, and then the second electric push rod 20 is controlled to work, so that the second electric push rod 20 can control the toothed plate 10 to move, so that the toothed plate 10 can push the universal ball 7 to swing back and forth, and then the flying vane 14 can be controlled to perform angular adjustment work, and through the angular adjustment of the flying vane 14, and then the aircraft 1 can be controlled to keep the correct attitude to perform the work of route flying.
The points to be finally explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, and "upper," "lower," "left," and "right" are only used to indicate a relative positional relationship, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed;
secondly, the method comprises the following steps: in the drawings of the disclosed embodiments of the invention, only the structures related to the disclosed embodiments are referred to, other structures can refer to common designs, and the same embodiment and different embodiments of the invention can be combined with each other without conflict;
and finally: the above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that are within the spirit and principle of the present invention are intended to be included in the scope of the present invention.
Claims (9)
1. The utility model provides a no rudder face aircraft attitude control mechanism, includes aircraft (1), its characterized in that: the lower surface of the aircraft (1) is fixedly connected with the upper surface of the controller (2), the left side surface and the right side surface of the aircraft (1) are respectively fixedly connected with opposite surfaces of four universal shells (6), universal balls (7) are arranged on the inner surfaces of the universal shells (6), the upper surfaces of the universal balls (7) are fixedly connected with the lower surface of a motor (13), and an output shaft of the motor (13) is fixedly connected with the lower surfaces of the flying blades (14);
the outer surface of the universal ball (7) is provided with a plurality of meshing grooves (11), part of the meshing grooves (11) are meshed with a toothed plate (10), the left side surface and the back surface of the toothed plate (10) are fixedly connected with one end of a first electric push rod (9) and one end of a second electric push rod (20) respectively, the other end of the first electric push rod (9) is fixedly connected with the right side surface of a first guide block (17), and the lower surface of the universal shell (6) is fixedly connected with the upper surface of the shell (8);
first guide way (16) have been seted up to the left surface of casing (8) inner wall, first guide block (17) sliding connection is in first guide way (16), second guide way (18) have been seted up at the back of casing (8) inner wall, sliding connection has second guide block (19) in second guide way (18), the front and second electric putter (20) other end fixed connection of second guide block (19).
2. The attitude control mechanism of an aircraft without control surfaces according to claim 1, characterized in that: the controller (2) comprises a path planning unit, the output end of the path planning unit is electrically connected with the input end of a processing chip, the output end of the processing chip is electrically connected with the input end of a comparison module, the comparison module can compare collected information of a period of time, flying position information of the aircraft (1) and attitude information of the aircraft (1) in the flying process with data information under normal conditions, so that whether the flying state of the aircraft (1) is abnormal or not can be known in real time, the input end of the comparison module is electrically connected with the output end of an information collection unit, the output end of the comparison module is electrically connected with an alarm module and the input end of an automatic adjustment unit, the alarm module can be used for carrying out alarm reminding on the abnormal data information after comparison, and further a controller can check the condition of the aircraft (1) in time, the output end of the automatic adjusting unit is electrically connected with the input end of the data storage module, the data storage module can store various data information and perform induction, classification and sorting for subsequent orderly checking work, and the data storage module is electrically connected with the processing chip in a two-way mode.
3. The attitude control mechanism of an aircraft without control surfaces according to claim 2, characterized in that: the input end of the processing chip is electrically connected with the output end of the information input module, the information input unit is an instruction and data input device for operating the aircraft (1) to run, the established route data can be input into the data storage module for storage and storage, so as to establish a comparison basis for the subsequent real-time flight data acquisition of the aircraft (1), the input end of the processing chip is electrically connected with the output end of the storage battery (3), the storage battery (3) can store the electric energy input by the solar energy acquisition module for supplying power for the aircraft (1), the input end of the storage battery (3) is electrically connected with the output end of the solar energy acquisition module, the solar energy acquisition module can convert the heat radiation energy of the solar light into the electric energy, so that the power supply work of the aircraft (1) can be ensured, and the solar energy is a novel recyclable energy source, thereby achieving the purposes of energy conservation and environmental protection.
4. The attitude control mechanism of an aircraft without control surfaces according to claim 2, characterized in that: the processing chip is electrically connected with the wireless transmission module in a two-way mode, the wireless transmission module is a network which can realize interconnection of various communication devices without wiring, so that the communication connection of the aircraft (1) and the control end can be kept, the aircraft (1) is ensured to be in normal control work, the input end of the wireless transmission module is electrically connected with the output end of the comparison module, the wireless transmission module is electrically connected with the terminal query display module in a two-way mode, the terminal query display module can display flight data information of the aircraft (1) and feedback data information, and therefore the purpose of viewing the flight state of the aircraft (1) in real time can be achieved.
5. The attitude control mechanism of an aircraft without control surfaces according to claim 2, characterized in that: the route planning unit comprises a route establishing module and a route time and position calculating module, wherein the output ends of the route establishing module and the route time and position calculating module are electrically connected with the input end of a processing chip, the route establishing module can input the route position required to fly into a data storage module for storage, the route time and position calculating module can input the position reached by the route of the aircraft (1) in normal flight in each period of time into a data storage for storage and management, a basis can be established for the subsequent comparison work of real-time acquired data through the route establishing module and the route time and position calculating module, the input end of the data storage module is electrically connected with the output end of an image acquisition module, the image acquisition module can transmit the image of the aircraft (1) in the flight process to the data storage module in real time, and the video information is checked in real time through the terminal query display module.
6. The attitude control mechanism of an aircraft without control surfaces according to claim 2, characterized in that: the information acquisition unit includes time acquisition module, big dipper orientation module and levelness measurement sensor, time acquisition module, big dipper orientation module and levelness measurement sensor's output is connected with the input of contrast module electricity, time acquisition module can carry out real-time collection to the time that aircraft (1) flight in-process consumed, big dipper orientation module can carry out real-time location to the position of aircraft (1), and it can cooperate the position information of deriving aircraft (1) flight in a period with time acquisition module, levelness measurement sensor can real-time supervision aircraft (1) flight in-process attitude information to can ensure whether aircraft (1) fly according to planning route.
7. The attitude control mechanism of an aircraft without control surfaces according to claim 2, characterized in that: the automatic adjusting unit comprises four groups of first electric push rod adjusting modules and four groups of second electric push rod adjusting modules, the output ends of the four groups of first electric push rod adjusting modules and the output ends of the four groups of second electric push rod adjusting modules are electrically connected with the input end of the data storage module, and the input ends of the four groups of first electric push rod adjusting modules and the input ends of the four groups of second electric push rod adjusting modules are electrically connected with the output end of the comparison module.
8. The attitude control mechanism of an aircraft without control surfaces according to claim 1, characterized in that: the upper surface of aircraft (1) and the lower fixed surface of solar panel (5) are connected, the lower surface of controller (2) and the upper fixed surface of camera (4) are connected, the surface of motor (13) and the internal surface fixed connection of cell-shell (15).
9. The attitude control mechanism of an aircraft without control surfaces according to claim 1, characterized in that: third guide way (22) have all been seted up to the front of casing (8) inner wall and the right flank of inner wall, sliding connection has third guide block (21), the place ahead in third guide way (22) the back and the right side of third guide block (21) the left flank of third guide block (21) respectively with the one end fixed connection of two telescopic link (12), two the other end of telescopic link (12) respectively with the front and the right flank fixed connection of pinion rack (10).
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| CN207809781U (en) * | 2017-12-18 | 2018-09-04 | 酒泉水韵铧尖电子商务有限公司 | A kind of agricultural unmanned plane |
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