CN205034333U - Pressure type driven multiaxis gyroplane - Google Patents
Pressure type driven multiaxis gyroplane Download PDFInfo
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- CN205034333U CN205034333U CN201520636281.XU CN201520636281U CN205034333U CN 205034333 U CN205034333 U CN 205034333U CN 201520636281 U CN201520636281 U CN 201520636281U CN 205034333 U CN205034333 U CN 205034333U
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Abstract
The utility model discloses a pressure type driven multiaxis gyroplane, include: the drive body frame is provided with engine, force pump and multiaxis gyroscope in the drive on the body frame, and the force pump is connected with this engine, the drive body frame be connected with the independent helix group spare of at least three groups all around, every group helix group spare includes and drives the support that the body frame is connected, is equipped with the pressure driven motor on the end of support, the pressure driven motor is connected with the screw, the pressure driven motor through the high -pressure pipe that is equipped with and low pressure back flow and the force pump is connected, is equipped with the pressure control valve door on high -pressure pipe, the pressure control valve door with the multiaxis gyroscope is connected. The utility model discloses drive the force pump by the engine and can adopt hydraulic pump and air pump as primary power source, this force pump, realize that the power take off of hydraulic pressure and atmospheric pressure replaces current electric power power take off, can greatly increase the utility model discloses a duration and lifting capacity are applicable to various large -scale or miniature unmanned aerial vehicle.
Description
Technical field
The utility model relates to the multiaxis cyclogyro that a kind of pressure type drives.
Background technology
At present, known Spaniard Xie Ba is autogyro utility model people.In generation nineteen twenty, the aircraft lifting and landing stall because of fault often, causes many people to die.So thank to bar trial-production self-rotary wings cyclogyro (hereinafter referred to as cyclogyro) to attempt to address this problem.Rotor rotates by evoking air-flow during airplane motion, and produce lift, make can not drop during aircraft stall, his this utility model was referred to as " windmill aircraft " by press at that time.
The maximum difference of cyclogyro and helicopter is that the rotor of cyclogyro is not connected with engine driving system, and driving engine is not drive rotor to provide lift for aircraft, but in the process of cyclogyro flight, blows rotor wing rotation produce lift by air-flow.Blowing the air-flow of rotor wing rotation, is produced when driving cyclogyro to advance by special power.Helicopter is different, and its rotor is connected with engine driving system, can produce lift, can provide again the power of flight.
Existing cyclogyro generally adopts electrodynamic type brake mode, there is following shortcoming, is limited to capacity of cell, the power that rotor provides limited thus cause overall load-carrying ability and flying power low, and too high in cost, be unfavorable for promoting.
Summary of the invention
The purpose of this utility model is the multiaxis cyclogyro providing a kind of pressure type to drive.
According to one side of the present utility model, provide the multiaxis cyclogyro that a kind of pressure type drives, comprise: drive body frame, described driving body frame is provided with driving engine, force lift and multiaxis gyroscope, described force lift is connected with this driving engine, the surrounding of described driving body frame is connected with at least three groups independently screw assembly, often organize screw assembly to comprise and the support driving body frame to be connected, the end of described support is provided with pressure-driven motor, described pressure-driven motor is connected with screw propeller, described pressure-driven motor is connected with described force lift by the high-pressure conduit that is provided with and low pressure return pipe, described high-pressure conduit is provided with pressure control valve, described pressure control valve is electrically connected with described multiaxis gyroscope.
Further, described force lift is Hydraulic Pump or air pump.
Further, described pressure-driven motor is oil motor or air motor.
Further, described multiaxis gyroscope is provided with servomechanism.
Principle of the present utility model is: by driven by engine force lift, the pressure-driven motor on each screw assembly is driven respectively by force lift, thus obtain pressure-driven motor driving screw blade, control the corresponding pressure control valve of each pressure-driven motor by multiaxis gyroscope, realize balance Control Scheme and the maneuvering and control of cyclogyro.
The beneficial effects of the utility model are: the utility model by driven by engine force lift as main power, this force lift can adopt Hydraulic Pump and air pump, the Power output realizing hydraulic pressure and air pressure replaces existing electric power and exports, can greatly increase flying power of the present utility model and load-carrying ability, be applicable to various large-scale or small-sized unmanned plane, adopt the one_to_one corresponding of multiple independently servomechanism and pressure control valve to control in addition, precisely can control the degree of balance on each direction and manipulative capability.
Accompanying drawing explanation
Fig. 1 is the structural representation of the multiaxis cyclogyro that a kind of pressure type drives.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Fig. 1 show schematically show the multiaxis cyclogyro driven according to a kind of pressure type of the present utility model.
The multiaxis cyclogyro that a kind of pressure type that the present embodiment provides drives, refer to Fig. 1, comprise: drive body frame 001, described driving body frame 001 is provided with driving engine 002, force lift 003 and multiaxis gyroscope 004, the embodiment force lift 003 same at this can adopt Hydraulic Pump or air pump, take the present embodiment as illustrative examples, in the present embodiment, force lift 003 is Hydraulic Pump, described force lift 003 is connected with this driving engine 002, the surrounding of described driving body frame 001 is connected with at least three groups independently screw assembly, such as in this enforcement, this screw assembly is provided with four groups, in other embodiment, three groups of screw assemblies etc. can also be set, the quantity of concrete screw assembly adjusts according to the actual requirements, four groups of screw assemblies of the present embodiment are only that a kind of signal is enumerated, often organize screw assembly to comprise and the support 011 driving body frame 001 to be connected, the end of described support 011 is provided with pressure-driven motor 005, in order to supporting with force lift 003, described pressure-driven motor 005 is oil motor or air motor, described pressure-driven motor 005 is connected with screw propeller 006, described pressure-driven motor 005 is connected with described force lift 003 by the high-pressure conduit 007 that is provided with and low pressure return pipe 008, described high-pressure conduit 007 is provided with pressure control valve 009, described pressure control valve 009 is electrically connected with described multiaxis gyroscope 004, described multiaxis gyroscope 004 is provided with servomechanism 010, this multiaxis gyroscope 004 controls the pressure control valve 009 in all directions by servomechanism 010.
Principle of the present utility model is: drive force lift 003 by driving engine 002, the pressure-driven motor 005 on each screw assembly is driven respectively by force lift 003, thus obtain pressure-driven motor 005 carrying screws 006 leaf, control the corresponding pressure control valve 009 of each pressure-driven motor 005 by multiaxis gyroscope 004, realize balance Control Scheme and the maneuvering and control of cyclogyro.
The beneficial effects of the utility model are: the utility model drives force lift 003 as main power by driving engine 002, this force lift 003 can adopt Hydraulic Pump and air pump, the Power output realizing hydraulic pressure and air pressure replaces existing electric power and exports, can greatly increase flying power of the present utility model and load-carrying ability, be applicable to various large-scale or small-sized unmanned plane, adopt the one_to_one corresponding of multiple independently servomechanism 010 and pressure control valve 009 to control in addition, precisely can control the degree of balance on each direction and manipulative capability.
Finally should be noted that; above embodiment is only in order to illustrate the technical solution of the utility model; but not the restriction to the utility model protection domain; although done to explain to the utility model with reference to preferred embodiment; those of ordinary skill in the art is to be understood that; can modify to the technical solution of the utility model or equivalent replacement, and not depart from essence and the scope of technical solutions of the utility model.
Claims (4)
1. the multiaxis cyclogyro of a pressure type driving, it is characterized in that, comprise: drive body frame, described driving body frame is provided with driving engine, force lift and multiaxis gyroscope, described force lift is connected with this driving engine, the surrounding of described driving body frame is connected with at least three groups independently screw assembly, often organize screw assembly to comprise and the support driving body frame to be connected, the end of described support is provided with pressure-driven motor, described pressure-driven motor is connected with screw propeller, described pressure-driven motor is connected with described force lift by the high-pressure conduit that is provided with and low pressure return pipe, described high-pressure conduit is provided with pressure control valve, described pressure control valve is electrically connected with described multiaxis gyroscope.
2. the multiaxis cyclogyro of pressure type driving according to claim 1, it is characterized in that, described force lift is Hydraulic Pump or air pump.
3. the multiaxis cyclogyro of pressure type driving according to claim 1, it is characterized in that, described pressure-driven motor is oil motor or air motor.
4. the multiaxis cyclogyro of pressure type driving according to claim 1, it is characterized in that, described multiaxis gyroscope is provided with servomechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520636281.XU CN205034333U (en) | 2015-08-21 | 2015-08-21 | Pressure type driven multiaxis gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520636281.XU CN205034333U (en) | 2015-08-21 | 2015-08-21 | Pressure type driven multiaxis gyroplane |
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| Publication Number | Publication Date |
|---|---|
| CN205034333U true CN205034333U (en) | 2016-02-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520636281.XU Active CN205034333U (en) | 2015-08-21 | 2015-08-21 | Pressure type driven multiaxis gyroplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151284A (en) * | 2015-08-21 | 2015-12-16 | 东莞市福莱特航空科技有限公司 | Pressure-driven multiaxial rotorcraft |
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2015
- 2015-08-21 CN CN201520636281.XU patent/CN205034333U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151284A (en) * | 2015-08-21 | 2015-12-16 | 东莞市福莱特航空科技有限公司 | Pressure-driven multiaxial rotorcraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191115 Address after: 255000 4 / F, building 17, Instrument Industrial Park, No. 9009, Qinglongshan Road, high tech Zone, Zibo City, Shandong Province Patentee after: Shandong fulet UAV Manufacturing Co., Ltd Address before: Changan Town, industrial zone, Fu Ning street lotus 523000 Guangdong city of Dongguan province No. 10 Patentee before: DONGGUAN FLIGHT AVIATION TECHNOLOGY CO., LTD. |