CN216374971U - Four rotor unmanned aerial vehicle - Google Patents
Four rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN216374971U CN216374971U CN202123098437.8U CN202123098437U CN216374971U CN 216374971 U CN216374971 U CN 216374971U CN 202123098437 U CN202123098437 U CN 202123098437U CN 216374971 U CN216374971 U CN 216374971U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- quad
- rotor
- fuselage panel
- panel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 18
- 238000009826 distribution Methods 0.000 claims description 11
- 238000010276 construction Methods 0.000 claims description 2
- 230000004308 accommodation Effects 0.000 abstract description 7
- 238000013461 design Methods 0.000 abstract description 6
- 230000005611 electricity Effects 0.000 description 10
- 238000012546 transfer Methods 0.000 description 8
- 230000000875 corresponding effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 238000013473 artificial intelligence Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000084 colloidal system Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Images
Landscapes
- Toys (AREA)
Abstract
The utility model relates to the field of unmanned aerial vehicles, in particular to a quad-rotor unmanned aerial vehicle, which is provided with a body, rotors and a power supply; the fuselage is provided with a first fuselage panel, a second fuselage panel, a third fuselage panel and a wing arm; the fuselage panels are aligned with each other, the maximum surfaces of the fuselage panels are parallel to each other, the first fuselage panel is connected with the second fuselage panel at intervals through the first connecting piece and is connected with the third fuselage panel at intervals through the second connecting piece, and the first end of the wing arm is connected to the periphery of the first fuselage panel; the rotor wing is provided with a propeller and a driving piece; the propeller is connected with the second end of the wing arm through a driving piece; the power supply is connected with the driving piece. Through the fuselage board that designs three-layer interval and set up, the space between fuselage board and the fuselage board constitutes enough big device accommodation space, can satisfy the demand of carrying the great device of volume weight.
Description
Technical Field
The utility model relates to the field of unmanned aerial vehicles, in particular to a quad-rotor unmanned aerial vehicle.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by using a wireless remote control device and a self-contained program control device. The unmanned aerial vehicle can effectively utilize high-precision core technologies such as artificial intelligence, automatic driving, signal processing and the like, has the advantages of flexibility, high reliability, unmanned driving and the like, can be used for executing tasks which cannot be performed by human beings and have high difficulty, high risk and high content, and is widely applied to the fields of military affairs, logistics, natural environment investigation, science popularization, agriculture and the like.
Present unmanned aerial vehicle uses the compactness of structure as design criteria more, and the device accommodation space that leads to being used for devices such as holding machine-carried computers and sensors is less to can't carry on the great device of volume weight, and the great device of volume weight need be used to more scene, consequently need a great unmanned aerial vehicle of device accommodation space urgently.
SUMMERY OF THE UTILITY MODEL
The embodiment of the utility model discloses a quad-rotor unmanned aerial vehicle, which is used for solving the technical problem that an unmanned aerial vehicle in the prior art cannot carry devices with larger volume and weight due to small device accommodating space.
The utility model provides a quad-rotor unmanned aerial vehicle, which comprises:
a fuselage, a rotor, and a power source;
this fuselage includes: a first fuselage panel, a second fuselage panel, a third fuselage panel, and a wing arm;
the maximum surfaces of the fuselage plates are parallel to each other, the fuselage plates are aligned with each other, the first fuselage plate is connected with the second fuselage plate at intervals through a first connecting piece and is connected with the third fuselage plate at intervals through a second connecting piece, and the first end of the wing arm is connected to the periphery of the first fuselage plate;
the rotor comprises a propeller and a driving member;
the propeller is connected with the second end of the wing arm through the driving piece;
the power supply is electrically connected with the driving piece.
In a first possible implementation of the unmanned aerial vehicle, the body panel is a hollow structure.
In a second possible implementation of the drone, the connection is of cylindrical structure;
one end of the first connecting piece is vertically connected with the first largest surface of the first fuselage panel, and the other end of the first connecting piece is vertically connected with the opposite surface of the second fuselage panel;
one end of the second connecting piece is vertically connected with the second largest surface of the first machine body plate, and the other end of the second connecting piece is vertically connected with the opposite surface of the third machine body plate;
the opposite face is a face opposite to the first largest face or the second largest face.
In a third possible implementation of the drone, the drone further includes:
a foot rest connected with the wing arm;
the foot rest is of a hollow structure.
With reference to the third possible implementation of the drone, in a fourth possible implementation of the drone, the foot rest is disposed at one side of the second end that is close to the third fuselage panel;
the rotor is arranged on one side of the second end close to the second fuselage panel.
With reference to the fourth possible implementation of the drone, in a fifth possible implementation of the drone, the foot rest includes: the first vertical plate, the second vertical plate and the horizontal backing plate;
the first vertical plate and the second vertical plate are parallel to each other;
one end of the vertical plate is vertically connected with the second end, and the other ends of the vertical plate are mutually connected through the horizontal base plate;
the vertical plate is a hollow structure.
In a sixth possible implementation of the drone, the propeller comprises a hub and N blades, N being an integer greater than or equal to 2;
the blades are uniformly connected to the periphery of the hub;
the driving piece is a rotating motor;
the propeller hub is sleeved on a rotating shaft of the rotating motor.
In a seventh possible implementation of the drone, the number of arms is 4;
the wing arm is a square rod;
4 square rods are symmetrically distributed on two sides of the first machine body plate in a cross shape;
the first end is fixedly connected with the first machine body plate through a connecting plate.
In an eighth possible implementation, the drone further includes:
the distribution board, the flight control, the electric regulation and the receiver are arranged on the first machine body board;
the input end of the distribution board is connected with the power supply, and the output end of the distribution board is respectively connected with the electric controller and the flight control;
the electric controller is respectively connected with the driving piece and the flight control;
the flight control is connected to the receiver.
In a ninth possible implementation of the drone, the drone further includes:
onboard computers and sensors;
the onboard computer is connected with the sensor;
the onboard computer is connected with the power supply.
According to the technical scheme, the embodiment of the utility model has the following advantages:
the quad-rotor unmanned aerial vehicle provided by the utility model is provided with a body, rotors and a power supply; the fuselage is provided with a first fuselage panel, a second fuselage panel, a third fuselage panel and a wing arm; the fuselage panels are aligned with each other, the maximum surfaces of the fuselage panels are parallel to each other, the first fuselage panel is connected with the second fuselage panel at intervals through the first connecting piece and is connected with the third fuselage panel at intervals through the second connecting piece, and the first end of the wing arm is connected to the periphery of the first fuselage panel; the rotor wing is provided with a propeller and a driving piece; the propeller is connected with the second end of the wing arm through a driving piece; the power supply is connected with the driving piece. Through the fuselage board that designs three-layer interval and set up, the space between fuselage board and the fuselage board constitutes enough big device accommodation space, can satisfy the demand of carrying the great device of volume weight.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of a quad-rotor drone provided in an embodiment of the present invention;
fig. 2 is another schematic structural diagram of a quad-rotor drone provided in an embodiment of the present invention;
fig. 3 is another schematic structural diagram of a quad-rotor drone provided in an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a first fuselage panel provided in an embodiment of the utility model;
fig. 5 is a schematic structural view of a second fuselage panel provided in an embodiment of the utility model;
fig. 6 is a schematic structural view of a third fuselage panel provided in an embodiment of the utility model;
FIG. 7 is a schematic structural diagram of a connecting plate provided in an embodiment of the present invention;
wherein: 100-fuselage, 101-first fuselage plate, 102-second fuselage plate, 103-third fuselage plate, 104-wing arm, 105-first connector, 106-second connector, 107-connecting plate, 200-rotor, 210-propeller, 211-hub, 212-blade, 220-driver, 300-power supply, 400-foot rest, 401-horizontal backing plate, 402-first vertical plate, 403-second vertical plate, 500-distribution plate, 600-flight control and 700-electric regulation.
Detailed Description
The embodiment of the utility model discloses a quad-rotor unmanned aerial vehicle, which is used for solving the technical problem that an unmanned aerial vehicle in the prior art cannot carry devices with larger volume and weight due to small device accommodating space.
In order to make the objects, features and advantages of the present invention more obvious and understandable, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the embodiments described below 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.
In the description of the embodiments of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "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 in describing the embodiments of the present application and simplifying the description, but do not indicate or imply that the referred devices or elements must have specific orientations, be configured in specific orientations, and operate, and thus, should not be construed as limiting the embodiments of the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the embodiments of the present application, it should be noted that the terms "mounted," "connected," and "connected" are used broadly and are defined as, for example, a fixed connection, an exchangeable connection, an integrated connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection through an intermediate medium, and a communication between two elements, unless otherwise explicitly stated or limited. Specific meanings of the above terms in the embodiments of the present application can be understood in specific cases by those of ordinary skill in the art.
Present unmanned aerial vehicle uses the compactedness of structure as design criteria more, and the device accommodation space that leads to being used for devices such as holding machine-carried computer and sensor is less to can't carry on the great high performance device of volume weight, and the great device of volume weight need be used to more scene, consequently urgently needed a great unmanned aerial vehicle of device accommodation space.
Referring to fig. 1 to 7, a quad-rotor drone provided in an embodiment of the present invention includes:
The beneficial effects of this embodiment include: the unmanned aerial vehicle comprises a body plate, wherein the upper surface and the lower surface of the body plate can be used for fixing devices of the unmanned aerial vehicle, and three layers of body plates are arranged, namely, the body plate has enough device accommodating space and can carry devices with larger volume and weight; the large enough device accommodating space can accommodate a power supply with larger capacity, so that the unmanned aerial vehicle has larger power, the load capacity of the unmanned aerial vehicle can be improved, and the cruising ability of the unmanned aerial vehicle is also improved; the device accommodating space is an open space, so that the device can be quickly replaced, the mounting position can be adjusted according to different device combinations, the device accommodating space is optimally utilized, and the practicability and the universality are high; and fourthly, the open type device accommodating space enables each device to better dissipate heat.
Specifically, in order to further improve unmanned aerial vehicle's load carrying capacity and duration, design into hollow out construction with the fuselage board-carry out the fretwork of maximize to the fuselage board under the circumstances of guaranteeing that the fuselage board possess required intensity, so, unmanned aerial vehicle self weight has been reduced, when flying, be used for offsetting the electric energy that self gravity consumed and reduce, thereby the consumption rate of power electric energy has been reduced, duration has been improved, and simultaneously, under the invariable condition of unmanned aerial vehicle maximum take-off weight, unmanned aerial vehicle self weight has been reduced, unmanned aerial vehicle's that can carry weight has been increased promptly, unmanned aerial vehicle's load carrying capacity has been improved. In the present embodiment, the body panel is formed by hollowing out the middle region of the rectangular panel and cutting out the edge-ineffective region. In addition, in order to further reduce unmanned aerial vehicle self weight, the fuselage board adopts carbon fiber material to make for the fuselage board has lighter quality and higher toughness.
Specifically, in order to facilitate the processing and reduce the occupied space of the connecting piece as much as possible, the connecting piece is designed into a cylindrical structure; one end of the first connecting member 105 is vertically connected to the first largest face of the first body panel 101, and the other end is vertically connected to the opposite face of the second body panel 102; one end of the second connecting member 106 is vertically connected to the second largest face of the first body panel 101, and the other end is vertically connected to the opposite face of the third body panel 103; the opposing face is a face opposing the first largest face or the second largest face. In the present embodiment, the first connecting pieces 106 are provided with 6 pieces, wherein the lower ends of 4 pieces are vertically connected with four diagonal positions of the upper surface of the first fuselage panel 101, the upper ends are vertically connected with four diagonal positions of the lower surface of the second fuselage panel 102, and the other 2 pieces are respectively arranged between 2 diagonal first connecting pieces 101 which are far away from each other; the number of the second connecting pieces 106 is 4, the upper ends of the second connecting pieces 106 are vertically connected with four diagonal positions of the lower surface of the first body panel 101, and the lower ends of the second connecting pieces 106 are vertically connected with four diagonal positions of the upper surface of the third body panel 103; the upper and lower end faces of the first connecting piece 105 and the second connecting piece 106 are provided with threaded holes, correspondingly, the first body panel 101, the second body panel 102 and the third body panel 103 are provided with through holes at corresponding connecting positions, and screws are matched with the threaded holes of the connecting pieces after penetrating through the through holes to realize the relative fixation between the body panels and the connecting pieces.
Specifically, in order to avoid that the lower surface of the third fuselage plate 103 is in direct hard contact with the ground when the unmanned aerial vehicle lands, and the stability of the fuselage is damaged, a foot rest 400 connected with a wing arm 104 is arranged for the quad-rotor unmanned aerial vehicle; in order to reduce the weight of the foot rest 400, the foot rest 400 is a hollow structure, and in order to further reduce the weight of the foot rest 400, the foot rest 400 is made of a carbon fiber material. The foot rest 400 is arranged at the second end of the wing arm 104 on the side close to the third fuselage panel 103; the rotor 200 is disposed on a side of the second end of the wing arm 104 adjacent to the second fuselage panel 102. In the present embodiment, there are 4 foot rests 400, the foot rests 400 are disposed at the lower side of the outer end of the wing arm 104, and the rotor 200 is disposed at the upper side of the outer end of the wing arm 104; the foot rest 400 is provided with a horizontal base plate 401, a first hollow vertical plate 402 and a second hollow vertical plate 403, the maximum surfaces of the first vertical plate 402 and the second vertical plate 403 are parallel to each other, the maximum surfaces are hollow to the maximum extent under the condition of ensuring the strength of the foot rest, the upper ends of the first vertical plate 402 and the second vertical plate 403 are fixedly connected with the side surface of the outer end of the wing arm 104, so that the maximum surface of the vertical plate 401 is perpendicular to the lower surface of the wing arm 104, and the inner sides of the lower ends of the first vertical plate 402 and the second vertical plate 403 are connected with each other through the horizontal base plate 401; the vertical plate is a polygonal plate, the upper end of the vertical plate is larger, the lower end of the vertical plate is smaller, the upper end of the vertical plate is provided with a notch, the middle area of the maximum surface of the vertical plate is provided with a plurality of through holes to form a hollow part, and the through holes are arranged in a circular matrix; the horizontal backing plate 401 is a rectangular plate with four corners rounded.
Specifically, propeller 210 includes a hub 211 and N blades 212, N being an integer greater than or equal to 2; the blades 212 are uniformly connected around the hub; the driving member 220 is a rotating motor; the hub 211 is fitted over the shaft of the rotating electrical machine. In the present embodiment, a total of 4 propellers 210 are provided, each propeller 210 is provided with 3 blades 212, and the 3 blades 212 are uniformly connected to the outer wall of a cylindrical hub 211; the rotary motor is fixed to the upper surface of the outer end of the wing arm 104 with the shaft vertically upward, and the hollow region of the hub 211 is fitted with the shaft of the rotary motor. Because of the relatively high efficiency of direct current brushless motor, in this embodiment, adopt SmooX 2806 plus motor, the external diameter that shows the motor is 28 millimeters, and length is 6 millimeters, and the size of the key parameter kv value of motor multiplies the battery voltage and is the number of times that the motor idles per minute, and the unmanned aerial vehicle of little moment of torsion uses the motor that kv value is big, and the rotational speed is very fast, and the unmanned aerial vehicle that the wheelbase was answered needs great torsion, should use the motor that kv value is little, in this embodiment, chooses for use the motor of 1350 kv. The screw carries out the lectotype according to the rotating electrical machines, and the material is harder for being good, and the main parameter of screw is length and pitch, and two are the pitch-the distance that advances of rotatory round in the colloid behind the length two before the specification, in the embodiment of this application, chooses the screw of 7040 model for use, and length is 7.0 inches, and the pitch is 4.0 inches. High-power motor and paddle are selected, and the load capacity of the unmanned aerial vehicle is improved.
Specifically, 4 wing arms 104 are arranged, and the wing arms 104 are square rods; the 4 square rods are symmetrically distributed on two sides of the first machine body plate 101 in a cross shape; the first end of the wing arm 104 is fixedly connected to the first fuselage panel 101 by means of a connecting plate 107. In this embodiment, in order to reduce the weight of the unmanned aerial vehicle, the wing arms 104 are made of a carbon fiber material, the inner ends of 2 wing arms 104 are connected with the middle area of one longer side of the first fuselage panel 101, the inner ends of the other 2 wing arms 104 are connected with the middle area of the other longer side of the first fuselage panel 101, the largest surface of the wing arms 104 is parallel to the largest surface of the fuselage panel, 2 through holes are formed in the upper surface of the inner ends of the wing arms 104, 2 through holes are also formed in the corresponding positions of the first fuselage panel 101 and the connecting plate 107, the wing arms 104 are clamped between the first fuselage panel 101 and the connecting plate 107, bolts sequentially pass through the corresponding through holes in the connecting plate 107, the wing arms 104 and the first fuselage panel 101, and then the bolts are screwed into nuts, so that the wing arms 104 and the first fuselage panel 101 are relatively fixed; four corners of the connecting plate 107 are provided with convex square plates, and each convex area is provided with 2 through holes. The wing arm 104 is arranged at the center of the unmanned aerial vehicle to balance the weight of the whole body.
Specifically, the quad-rotor unmanned aerial vehicle further comprises a distribution board 500, a flight control 600, an electric tilt 700 and a receiver which are arranged on the first body board; the input end of the distribution board 500 is connected with the power supply 300, and the output end is respectively connected with the electronic controller 700 and the flight control 600; the electronic controller 700 is respectively connected with the driving part 210 and the flight controller 600; flight control 600 is coupled to a receiver. In this embodiment, the distribution board 500, the flight control 600, the electronic tilt 700, and the receiver are fixed on the upper surface of the first body panel 101, and the power supply 300 is fixed on the upper surface of the third body panel 103.
The power supply 300 uses a lithium battery, and has a high discharge rate, and the capacity of the battery multiplied by the discharge rate is the maximum current that can be achieved by the battery. The model airplane lithium battery is usually connected in series by a plurality of sheets, 3S represents that the number of battery cores of the battery is 3, the voltage of the battery is single-sheet voltage, generally 3.8V of standard voltage, 4.2V of full voltage and multiplied by the number of the battery cores. In this embodiment, select for use the 6S battery, rated voltage is 22.8V, and full voltage is 25.2V, because the model aeroplane and model ship lithium cell is that the multi-disc electricity core works simultaneously, for the damage that avoids each electric core unbalanced voltage to lead to, need use the balanced charging during the charging, measure the voltage of each electric core and carry out intelligent distribution current, let the voltage of several electric cores unanimous as far as. Select for use 6S battery, improve unmanned aerial vehicle' S duration and the efficiency of motor. The mode of adopting the battery to directly transmit the resolution edition is adopted to supply power for each electric appliance, thereby reducing the number of power supplies and simplifying the connection.
The flight control 600 is also called a flight controller, and is an element for assisting or fully autonomously performing cooperative control on other systems and components of the unmanned aerial vehicle in stages of takeoff, cruising, landing, and the like. The flight control system is generally used together with components such as an inertial measurement unit, a barometer, a magnetic compass and the like. In the flying process of the unmanned aerial vehicle, the flying height, the speed, the angle and the position information of the flying control perception unmanned aerial vehicle control different systems of the unmanned aerial vehicle to make corresponding actions according to a preset flying plan or a temporarily received flying instruction, the control surface and the like are adjusted for a fixed wing aircraft, the output power and the like of each power are adjusted for a multi-rotor aircraft, and therefore the purpose of changing the flying attitude is achieved. For development purposes, the design trend is to choose a PIXhawk4 flight control with a good open source community. In order to make the process more compact, in this embodiment, Pixhawk4 Mini is selected. Compared with the PIXhawk, the Pixhawk4 Mini has smaller volume, the size of the stack of 49.5mm 41.0mm2 sheets is larger, and the wiring mode is more reasonable. All wires are terminated at the 2' end of the PIX. And some interfaces (CAN, SPI and AUX ADC) which are not used are removed, so that the use is convenient. And a plurality of unreasonable devices are removed, and the hardware cost is reduced.
Electricity is transferred 700 to brushless motor driver, brushless motor does not have the brush, the three-phase alternating current of 3 120 degrees alternating current potentials of inside production need to be transferred to the production of electric power potential energy, the input protocol of electricity transfer is the pwm signal that the cycle is constituteed for 20 ms's high-low level, high level duration is 1ms to 2ms, corresponding 0 and full-scale signal, the high-low limit here can be set up through the calibration of electricity transfer, the calibration of electricity transfer is also in order to guarantee that four electricity transfers are the same to the sensitivity of signal, in this embodiment, choose for use to have full 60a electricity to transfer, for the four unification electricity transfers. The calibration mode is that the pulse width is set to be the highest when the power is turned on electrically, the pulse width is set to be the lowest when the prompt tone is finished. The warning tone finishes the calibration, and different manufacturers electrically tune the calibration sound differently, but they all follow the same protocol. Adopt four unification electricity to transfer, reduce electricity and transfer quantity, alleviateed unmanned aerial vehicle's weight promptly, improved unmanned aerial vehicle's load capacity and duration.
The receiver analyzes the remote controller signal and sends the remote controller signal to the flight control end, the receiver and the remote controller need to use the same protocol, and 3 protocols are common when the receiver interacts with the flight control: PWM, PPM, SBUS protocol. The method comprises the steps that PWM is a periodic signal composed of high and low levels, PPM is a protocol formed by combining PWM of a plurality of channels on one channel, SBUS uses a serial port to transmit information of each channel, SBUS has the characteristic of simple structure, communication can be completed only by two serial port lines, and in the embodiment, flight control uses an SBUS connection mode and the protocol to analyze and process signals of a receiver. The remote control and the receiver can be self-adaptive and are not specified. In this embodiment, a radio link remote controller and a corresponding receiver are selected.
Specifically, an airborne computer and a sensor can be carried on the quad-rotor unmanned aerial vehicle; the airborne computer is connected with the sensor; the airborne computer is connected with the power supply. In this embodiment, a magic description computer and an intel D435i camera are mounted on the unmanned aerial vehicle.
The four-rotor unmanned aerial vehicle provided by the utility model is described in detail above, and for a person skilled in the art, according to the idea of the embodiment of the utility model, there may be changes in the specific implementation and application scope, and in summary, the content of the present description should not be construed as a limitation to the utility model.
Claims (10)
1. A quad-rotor unmanned aerial vehicle, comprising:
a fuselage, a rotor, and a power source;
the fuselage includes: a first fuselage panel, a second fuselage panel, a third fuselage panel, and a wing arm;
the maximum surfaces of the fuselage panels are parallel to each other, the fuselage panels are aligned with each other, the first fuselage panel is connected with the second fuselage panel at intervals through a first connecting piece and is connected with the third fuselage panel at intervals through a second connecting piece, and the first end of the wing arm is connected to the periphery of the first fuselage panel;
the rotor comprises a propeller and a driving piece;
the propeller is connected with the second end of the wing arm through the driving piece;
the power supply is electrically connected with the driving piece.
2. A quad-rotor drone according to claim 1, characterized in that:
the fuselage panel is hollow out construction.
3. A quad-rotor drone according to claim 1, characterized in that:
the connecting piece is of a cylindrical structure;
one end of the first connecting piece is vertically connected with the first largest face of the first fuselage panel, and the other end of the first connecting piece is vertically connected with the opposite face of the second fuselage panel;
one end of the second connecting piece is vertically connected with the second largest surface of the first machine body plate, and the other end of the second connecting piece is vertically connected with the opposite surface of the third machine body plate;
the opposing face is a face opposing the first largest face or the second largest face.
4. A quad-rotor drone according to claim 1, further comprising:
a foot rest connected with the wing arm;
the foot rest is of a hollow structure.
5. A quad-rotor drone according to claim 4, characterized in that:
the foot rest is arranged on one side of the second end close to the third body plate;
the rotor is arranged on one side of the second end close to the second fuselage panel.
6. A quad-rotor drone according to claim 5, characterized in that:
the foot rest includes: the first vertical plate, the second vertical plate and the horizontal backing plate;
the first vertical plate and the second vertical plate are parallel to each other;
one end of the vertical plate is vertically connected with the second end, and the other ends of the vertical plate are connected with each other through the horizontal base plate;
the vertical plate is of a hollow structure.
7. A quad-rotor drone according to claim 1, characterized in that:
the propeller comprises a propeller hub and N blades, wherein N is an integer greater than or equal to 2;
the blades are uniformly connected to the periphery of the hub;
the driving piece is a rotating motor;
the propeller hub is sleeved on a rotating shaft of the rotating motor.
8. A quad-rotor drone according to claim 1, characterized in that:
the number of the wing arms is 4;
the wing arm is a square rod;
the 4 square rods are symmetrically distributed on two sides of the first machine body plate in a cross shape;
the first end is fixedly connected with the first machine body plate through a connecting plate.
9. A quad-rotor drone according to claim 1, further comprising:
the distribution board, the flight control, the electric regulation and the receiver are arranged on the first machine body board;
the input end of the distribution board is connected with the power supply, and the output end of the distribution board is respectively connected with the electric regulator and the flight control;
the electric controller is respectively connected with the driving piece and the flight control;
the flight control is connected with the receiver.
10. A quad-rotor drone according to claim 1, further comprising:
onboard computers and sensors;
the onboard computer is connected with the sensor;
the onboard computer is connected with the power supply.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123098437.8U CN216374971U (en) | 2021-12-10 | 2021-12-10 | Four rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123098437.8U CN216374971U (en) | 2021-12-10 | 2021-12-10 | Four rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216374971U true CN216374971U (en) | 2022-04-26 |
Family
ID=81223945
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123098437.8U Active CN216374971U (en) | 2021-12-10 | 2021-12-10 | Four rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216374971U (en) |
-
2021
- 2021-12-10 CN CN202123098437.8U patent/CN216374971U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20200277080A1 (en) | Systems and methods for in-flight operational assessment | |
| US11498677B2 (en) | Unmanned aerial vehicle | |
| CN105652886B (en) | A kind of internet unmanned plane persistently continued a journey | |
| CN111864891A (en) | UAV hybrid power system and method | |
| US12051923B2 (en) | Charger for an electric aircraft with failure monitoring and a method for its use | |
| US10538336B2 (en) | Unmanned aerial vehicle | |
| CN108423153A (en) | Modularized micro unmanned plane | |
| CN104267737B (en) | One kind can be to day solar battery quadrotor | |
| CN106672230A (en) | Ducted unmanned aerial vehicle | |
| CN206819162U (en) | A kind of unmanned plane based on CAN flies control hardware system | |
| CN216374971U (en) | Four rotor unmanned aerial vehicle | |
| CN104176249B (en) | A kind of non co axial anti-oar many rotors unmanned gyroplane | |
| CN210101983U (en) | Six rotor unmanned aerial vehicle | |
| CN206331305U (en) | Electricity tune, unmanned plane and its control system | |
| CN109250095A (en) | A kind of VTOL fixed wing aircraft | |
| CN210027898U (en) | Power system and unmanned aerial vehicle | |
| CN105048545B (en) | Photovoltaic quadrotor | |
| CN209795827U (en) | Double-engine full-vector multi-mode aircraft and flight system | |
| CN112849390A (en) | Dual-form unmanned aerial vehicle applying folding wings and coaxial double-propeller power module | |
| CN206579841U (en) | Array multi-rotor aerocraft | |
| CN108001678B (en) | A variable rotor connecting device for unmanned aerial vehicle | |
| CN207791154U (en) | VTOL flight instruments and fixed-wing unmanned plane | |
| CN219008149U (en) | Rotor unmanned aerial vehicle | |
| CN221938495U (en) | Coaxial aircraft based on storage type charging plate | |
| CN214267953U (en) | Unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |