CN204750561U - Four rotor crafts of area propulsion and steering control duct - Google Patents
Four rotor crafts of area propulsion and steering control duct Download PDFInfo
- Publication number
- CN204750561U CN204750561U CN201520264618.9U CN201520264618U CN204750561U CN 204750561 U CN204750561 U CN 204750561U CN 201520264618 U CN201520264618 U CN 201520264618U CN 204750561 U CN204750561 U CN 204750561U
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- rotor
- control panel
- flight control
- wires
- duct
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- 238000009434 installation Methods 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 4
- 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 22
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 10
- 229910052744 lithium Inorganic materials 0.000 claims description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses a four rotor crafts of area propulsion and steering control duct. It includes the organism: be in the plane and use the organism as the centre of a circle, evenly distributed at organism four rotors on every side: difference connect to engine body and four rotors and four rotor arms that correspond with four rotors, the direction of rotation of adjacent rotor is opposite. Two undercarriages that are connected with the organism downside are the retractable undercarriage, each distribute the 5th perpendicular rotor of installation and sextuple straight rotor (vice rotor system) on first rise and fall frame and the second undercarriage, two perpendicular rotor direction of rotation are opposite. The first frame that rises and falls pack up after this aircraft takes off with the second undercarriage, as the 5th perpendicular rotor and sextuple directly the rotor arm of rotor use. The utility model discloses a turning to and impeing of the rotational speed direct control aircraft of two perpendicular rotors, it is stable that flight in -process organism gesture can remain the level throughout, and remove rapidly, turns to the flexibility, and the structure is simplified, and the cost of manufacture is lower.
Description
Technical Field
The utility model relates to a four rotor crafts design and propulsion mode of area propulsion and steering control duct especially relate to the structural design of two vertical rotor.
Background
The four rotor crafts of tradition change the rotor rotational speed through adjusting four motor speed, realize the change of lift to control aircraft's flight gesture and position. Because the aircraft realizes lift change by changing the rotating speed of the rotor wing, the flying attitude is always in an unstable state which changes continuously when the aircraft flies forwards, turns and suspends in the wind, the stability of an aerial photography system carried by the aircraft is inevitably interfered, and the resistance is larger during flying.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a design scheme's purpose is in order to overcome the unstable shortcoming of flight gesture when traditional four rotors fly, has provided a four rotor craft design that advances and steering control duct in area, makes this aircraft under any flight gesture, and the organism can remain the horizontal stable state all the time, for the system of taking photo by plane provides a stable platform, has avoided causing the disturbance of the system of taking photo by plane because of the change of flight gesture. Meanwhile, the two ducts are fixed on the electric retractable landing gear, so that the whole weight of the aircraft is reduced, and meanwhile, a space is well reserved for full-angle shooting of the aerial photography system. Because the design scheme does not add other rotor arms to the auxiliary rotor system, the weight of the whole structure of the aircraft is increased to a limited extent, excessive load is not added, and the change of the flight attitude also reduces certain flight resistance of the aircraft.
The utility model discloses a realize through following technical scheme: a four-rotor aircraft with a propulsion and steering control duct mainly comprises a four-rotor frame, rotor arms, a shell, a brushless motor, propellers, electric retractable undercarriages, a duct, the propellers, the brushless motor, a receiver, an electronic speed regulator, a flight control panel, a lithium battery, a lead, a charger and a remote controller; the method is characterized in that: the four-rotor-wing aircraft comprises a four-rotor-wing rack, and is characterized in that two electric retractable undercarriages are symmetrically arranged at the bottom of the four-rotor-wing rack, an installation part with an upper surface and a lower surface which are in arc-shaped bulges is arranged in the middle of the four-rotor-wing rack, four rotor arms are uniformly and symmetrically arranged around the installation part, a flight control panel is fixedly arranged on the inner side of the middle of the four-rotor-wing rack; the upper end of the flight control panel is provided with a lithium battery, the receiver, the flight control panel and the lithium battery are all positioned in a shell, and the shell is arranged on the rack; the upper ends of the four rotor arms are fixedly connected with brushless motors, propellers are fixedly connected to the brushless motors, the brushless motors are connected with the electronic speed regulators through first wires, the first wires penetrate through the rotor arms and enter the installation parts, and the other ends of the first wires are connected to the flight control panel; the lower part of the rack is provided with an electric retractable landing gear group which is inserted into a landing gear channel of a receiver and is connected with the receiver through a second lead; the duct is fixed on the electric retractable landing gear set; brushless motor installs in the duct, brushless motor all has fixed screw, brushless motor is connected with electronic governor through No. three wires, No. three wires pass in the intraductal entering installation department of undercarriage, and the other end of No. three wires connects on the flight control panel.
The utility model discloses a impel and turn to device, including fifth vertical rotor, sixth vertical rotor, duct, brushless motor, electronic governor, first landing gear together. The vertical rotor is fixed with the landing gear through a duct, and the duct is not in contact with the ground. After the aircraft takes off perpendicularly, first landing gear and second undercarriage retract together for fifth vertical rotor, sixth vertical rotor and organism focus are on same water flat line, and the undercarriage uses as the rotor arm of fifth vertical rotor and sixth vertical rotor. When the aircraft flies in the horizontal direction, the flight control panel controls motors of the fifth vertical rotor and the sixth vertical rotor to rotate reversely at a constant speed, and power in the horizontal direction of the aircraft is provided for propelling; when the aircraft turns to and flies, the flight control panel forms the rotational speed difference through the motor rotational speed of control fifth vertical rotor and sixth vertical rotor, realizes the driftage of aircraft and turns to.
The utility model has the advantages that: the rotating speed of the two vertical rotors directly controls the turning and the propulsion of the aircraft, the attitude of the aircraft body can be always kept stable in the flying process, the aircraft moves quickly, the turning is flexible, the structure is simplified, and the manufacturing cost is lower.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a control schematic diagram of the present invention.
Figure 3 is a view of the landing gear stowed flight attitude of the present invention.
In the figure, 1, four-rotor frame, 2, rotor arm, 3, casing, 4, brushless motor (for horizontal rotor), 5, propeller (horizontal), 6, electric retractable landing gear, 7, duct, 8, propeller (vertical), 9, brushless motor (for vertical rotor), 10, receiver, 11, electronic governor, 12, flight control board, 13, lithium battery.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
Referring to the drawings, the present invention comprises a four-rotor frame 1, a rotor arm 2, a casing 3, a brushless motor (for a horizontal rotor) 4, a propeller (horizontal) 5, an electric retractable landing gear 6, a duct 7, a propeller (vertical) 8, a brushless motor (for a vertical rotor) 9, a receiver 10, an electronic governor 11, a flight control panel 12, a lithium battery 13, a wire, a charger, and a remote controller.
The four-rotor-wing aircraft comprises a four-rotor-wing rack 1, and is characterized in that two electric retractable landing gears 6 are symmetrically arranged at the bottom of the four-rotor-wing rack 1, an installation part with an upper surface and a lower surface which are in arc-shaped bulges is arranged in the middle of the four-rotor-wing rack 1, four rotor arms 2 are uniformly and symmetrically arranged around the installation part, a flight control panel 12 is fixedly arranged on the inner side of the middle of the four-rotor-wing rack 1, and; the upper end of the flight control panel 12 is provided with a lithium battery 13, the receiver 10, the flight control panel 12 and the lithium battery 13 are all positioned in the shell 3, and the shell 3 is arranged on the rack 1; the upper ends of the four rotor arms 2 are fixedly connected with brushless motors 4, the brushless motors (for horizontal propellers) 4 are fixedly connected with propellers (horizontal) 5, the brushless motors (for horizontal propellers) 4 are connected with electronic speed regulators 11 through first wires, the first wires penetrate through the rotor arms 2 and enter the installation part, and the other ends of the first wires are connected to a flight control panel 12; the lower part of the frame is provided with an electric retractable landing gear group 6 which is inserted into a landing gear channel of a receiver 10 and is connected with the receiver 10 through a second lead. The duct 7 is fixed on the electric retractable landing gear set 6; brushless motor (for perpendicular screw) 9 is installed in duct 7, brushless motor (for perpendicular screw) 9 is last all to have fixed screw (perpendicular) 8, brushless motor (for perpendicular screw) 9 is connected with electronic governor 11 through No. three wires, No. three wires pass in the intraductal entering installation department of undercarriage, and the other end of No. three wires connects on flight control panel 12.
A four-rotor aircraft device with a propulsion and steering control duct comprises four horizontal propellers (4) (main rotor systems), and is characterized in that a pair of ducts (7) are fixed on an electric retractable undercarriage (6) (the fixing mode is not limited); wherein,
the vertical propellers (8) are fixed in the duct (7), the vertical propellers (8) adopt a double-symmetrical wing type, and the rotating directions of the two vertical propellers (8) are opposite; the vertical propeller (8) is arranged on the brushless motor (9), the brushless motor (9) is arranged in the duct (7), and the rotating speed of the vertical propeller is controlled independently through the flight control panel (12) and the electronic speed regulator (11), so that any rotating speed difference can be formed by the vertical propeller (8); controlling horizontal forward flight propulsion and steering of the aircraft.
Claims (1)
1. A four-rotor aircraft with a propulsion and steering control duct mainly comprises a four-rotor frame, rotor arms, a shell, a brushless motor, propellers, electric retractable undercarriages, a duct, the propellers, the brushless motor, a receiver, an electronic speed regulator, a flight control panel, a lithium battery, a lead, a charger and a remote controller; the method is characterized in that: the four-rotor-wing aircraft comprises a four-rotor-wing rack, and is characterized in that two electric retractable undercarriages are symmetrically arranged at the bottom of the four-rotor-wing rack, an installation part with an upper surface and a lower surface which are in arc-shaped bulges is arranged in the middle of the four-rotor-wing rack, four rotor arms are uniformly and symmetrically arranged around the installation part, a flight control panel is fixedly arranged on the inner side of the middle of the four-rotor-wing rack; the upper end of the flight control panel is provided with a lithium battery, the receiver, the flight control panel and the lithium battery are all positioned in a shell, and the shell is arranged on the rack; the upper ends of the four rotor arms are fixedly connected with brushless motors, propellers are fixedly connected to the brushless motors, the brushless motors are connected with the electronic speed regulators through first wires, the first wires penetrate through the rotor arms and enter the installation parts, and the other ends of the first wires are connected to the flight control panel; the lower part of the rack is provided with an electric retractable landing gear group which is inserted into a landing gear channel of a receiver and is connected with the receiver through a second lead; the duct is fixed on the electric retractable landing gear set; brushless motor installs in the duct, brushless motor all has fixed screw, brushless motor is connected with electronic governor through No. three wires, No. three wires pass in the intraductal entering installation department of undercarriage, and the other end of No. three wires connects on the flight control panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520264618.9U CN204750561U (en) | 2015-04-29 | 2015-04-29 | Four rotor crafts of area propulsion and steering control duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520264618.9U CN204750561U (en) | 2015-04-29 | 2015-04-29 | Four rotor crafts of area propulsion and steering control duct |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204750561U true CN204750561U (en) | 2015-11-11 |
Family
ID=54465295
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520264618.9U Expired - Fee Related CN204750561U (en) | 2015-04-29 | 2015-04-29 | Four rotor crafts of area propulsion and steering control duct |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204750561U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775098A (en) * | 2016-04-14 | 2016-07-20 | 南昌航空大学 | Unmanned aerial vehicle with rotor and air bag hybrid power |
| CN106292680A (en) * | 2016-09-18 | 2017-01-04 | 上海交通大学 | Many rotor wing unmanned aerial vehicles and system thereof and flight control method |
| CN112731956A (en) * | 2020-12-28 | 2021-04-30 | 广东工业大学 | Omnibearing mobile detection detector, control system and control method |
-
2015
- 2015-04-29 CN CN201520264618.9U patent/CN204750561U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775098A (en) * | 2016-04-14 | 2016-07-20 | 南昌航空大学 | Unmanned aerial vehicle with rotor and air bag hybrid power |
| CN106292680A (en) * | 2016-09-18 | 2017-01-04 | 上海交通大学 | Many rotor wing unmanned aerial vehicles and system thereof and flight control method |
| CN112731956A (en) * | 2020-12-28 | 2021-04-30 | 广东工业大学 | Omnibearing mobile detection detector, control system and control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151111 Termination date: 20160429 |