CN111572770A - Rescue unmanned aerial vehicle with generator and rescue mode thereof - Google Patents
Rescue unmanned aerial vehicle with generator and rescue mode thereof Download PDFInfo
- Publication number
- CN111572770A CN111572770A CN202010422149.4A CN202010422149A CN111572770A CN 111572770 A CN111572770 A CN 111572770A CN 202010422149 A CN202010422149 A CN 202010422149A CN 111572770 A CN111572770 A CN 111572770A
- Authority
- CN
- China
- Prior art keywords
- generator
- unmanned aerial
- aerial vehicle
- power
- management system
- 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.)
- Pending
Links
- 230000005540 biological transmission Effects 0.000 claims abstract description 31
- 230000007246 mechanism Effects 0.000 claims abstract description 16
- 230000000087 stabilizing effect Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 238000010248 power generation Methods 0.000 abstract description 3
- 238000001914 filtration Methods 0.000 description 5
- 239000003990 capacitor Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 206010033799 Paralysis Diseases 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
-
- 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
- B64D41/00—Power installations for auxiliary purposes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a rescue unmanned aerial vehicle with a generator and a rescue mode thereof, and the rescue unmanned aerial vehicle comprises an unmanned aerial vehicle, and an engine, a clutch and a generator which are arranged on a frame of the unmanned aerial vehicle, wherein a rotor wing of the unmanned aerial vehicle is connected with the clutch through a transmission mechanism, one end of the clutch is connected with the engine, and the other end of the clutch is connected with the generator through a coupler; the main control system of the unmanned aerial vehicle comprises a power management system and a power management system, wherein the power management system controls the power switcher, and the power management system is used for managing the power generator to supply power to the electric equipment. The invention is mainly used for providing temporary power guarantee in the emergency rescue and disaster relief processes, can convey a 30KW power generation device to a disaster area, can convert an engine of an airplane into a power device of a generator, thereby avoiding the technical problem of inconvenient conveying caused by conveying a storage battery, and meanwhile, does not need to excessively reform the original organic type of the unmanned aerial vehicle, and is convenient to use.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and relates to a rescue unmanned aerial vehicle with a generator and a rescue mode thereof, which can be used as a power supply in emergency rescue.
Background
In the case of a serious natural disaster such as an earthquake, the power system is in a paralyzed state, but many rescue devices and lighting devices need to be started by electric power, but the failure of power supply is not favorable for the development of disaster rescue activities, and the road is blocked, and it is not easy to send devices such as a generator to a disaster area, so that it is necessary to transport power generation devices or power storage devices to a designated place as a power supply, and further, the use of power utilization devices and the development of rescue activities are facilitated.
Disclosure of Invention
The invention aims to provide a rescue unmanned aerial vehicle with a generator and a rescue mode thereof, so that the generator can be conveniently transported and supplied with power.
The technical scheme adopted by the invention is as follows:
a rescue unmanned aerial vehicle with a generator comprises an unmanned aerial vehicle, and an engine, a clutch and a generator which are arranged on a frame of the unmanned aerial vehicle, wherein a rotor wing of the unmanned aerial vehicle is connected with the clutch through a transmission mechanism, one end of the clutch is connected with the engine, and the other end of the clutch is connected with the generator through a coupler; the main control system of the unmanned aerial vehicle comprises a power management system and a power management system, wherein the power management system controls the power switcher, and the power management system is used for managing the power generator to supply power to the electric equipment.
Preferably, the clutch includes a first mounting base connected to the engine, and a transmission toothed disc connected to the first mounting base, and the transmission toothed disc is connected to the transmission mechanism, and the transmission mechanism drives the rotary vane to rotate.
Further, the power management system is connected with an electromagnetic valve, and the electromagnetic valve is arranged at the current output end of the generator.
Further, the power management system comprises a rectifier, a filtering unit and a voltage stabilizing unit.
The utility model provides a rescue unmanned aerial vehicle's from area generator rescue mode utilizes foretell a rescue unmanned aerial vehicle from area generator to go on, specifically includes following two kinds of states:
in the first state, an electric signal is sent to a power switcher through a power management system in a master control system, so that an engine is ensured to drive a rotor wing to rotate, and further the unmanned aerial vehicle takes off and stably flies to a designated rescue place, wherein a power management system in the master control system controls an electromagnetic valve to be closed, so that a generator has no current output;
the second middle state is that the power management system in the main control system sends an electric signal to the power switcher, so that transmission between the engine and the rotor wing is cut off, the engine only drives the generator to operate, and meanwhile, the power management system of the main control system controls the generator to output stable direct current stably and act on the electric equipment.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the invention is mainly used for providing temporary power guarantee in the emergency rescue and disaster relief processes, can convey a 30KW power generation device to a disaster area, can convert an engine of an airplane into a power device of a generator, thereby avoiding the technical problem of inconvenient conveying caused by conveying a storage battery, and meanwhile, does not need to excessively reform the original organic type of the unmanned aerial vehicle, and is convenient to use.
Drawings
FIG. 1 is a schematic view of the internal structure of the unmanned aerial vehicle of the present invention;
the labels in the figure are: 1-fuselage, 2-frame, 3-rotor, 4-link, 5-undercarriage, 6-transmission mechanism, 7-power switcher, 8-engine, 9-clutch, 10-coupler, 11-generator, 12-electromagnetic valve, 13-rectifier;
FIG. 2 is a schematic diagram of a power switching process of the present invention;
FIG. 3 is a disassembled schematic view of the clutch structure of the present invention;
the labels in the figure are: 901-a first mounting seat, 902-a transmission fluted disc, 903-a clutch central shaft, 904-a throwing block seat, 905-a throwing block pad, 906-a throwing block, 907-a friction plate, 908-a clutch shell, 909-a second mounting seat and 910-a synchronous wheel;
fig. 4 is a schematic diagram of the external structure of the unmanned aerial vehicle of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in figures 1-3, a rescue unmanned aerial vehicle with a generator comprises a body 1, a frame 2, a rotor wing 3, a connecting frame 4, an undercarriage 5, an engine 8, a clutch 9 and a generator 11, wherein the engine, the clutch 9 and the generator are arranged on the frame.
The frame 2 is of a channel steel structure and is arranged in the machine body 1, the tops of two ends of the machine body 1 are respectively provided with a rotor wing 3, the rotor wings 3 are connected with a clutch 9 through a transmission mechanism 6, the clutch 9 is connected with an engine 8, and the other end of the clutch 9 is connected with a generator 11 through a coupler 10; the lower part of the frame 2 is also connected with a landing gear 5 through a connecting frame 4.
When the unmanned aerial vehicle is used, the unmanned aerial vehicle drives the generator to fly to a designated place, wherein the power of the unmanned aerial vehicle is provided by the engine 8, and after the unmanned aerial vehicle falls down, the power management system in the main control system of the unmanned aerial vehicle transmits a signal to the power switcher 7, so that the combination mode of the clutch 9 is changed, the engine 8 is connected with the generator 11, meanwhile, the power transmission between the engine 8 and the transmission mechanism 6 is disconnected, the generator 11 generates power under the driving of the power of the engine 8, the alternating current is converted into direct current through the rectifier 13, and the power supply management system in the main control system is used for power supply control, so that power is supplied to electric equipment.
For the implementation of the first state: the invention preferably adopts a double-rotor unmanned aerial vehicle, wherein the two rotors 3 are respectively arranged at the front end and the rear end of the top of the body 1, and the power of an engine is transmitted through a transmission mechanism 6 to further drive the rotors 3 to rotate, so that the unmanned aerial vehicle takes off.
The specific way in which the transmission mechanism 6 drives the rotor 3 to rotate can be implemented by using, but not limited to, a technical solution in a twin-rotor unmanned helicopter with application number CN 201810569523.6.
For the implementation of the second state:
as shown in fig. 3, the clutch 9 includes a first mounting base 901 connected to the engine 8, and a transmission gear 902 connected to the first mounting base 901, and the transmission gear 902 is connected to the transmission mechanism 6, and drives a transmission member in the transmission mechanism 6 through the transmission gear 902, so as to transmit power to the rotary vane.
The clutch 9 further comprises a clutch central shaft 903, a throwing block seat 904, a throwing block pad 905, a throwing block 906, a friction plate 907, a clutch shell 908, a second mounting seat 909 and a synchronizing wheel 910; wherein be equipped with three draw-in groove in throwing away piece 906, and throw a seat 904 and be hollow cylinder structure, throw a seat 904 outer wall and be equipped with three rectangle that corresponds with the draw-in groove and protruding, will throw a seat 904 joint in the draw-in groove through the rectangle is protruding, and then will throw a seat 904 and throw a connection of 906, throw a 906 and throw a seat 904 and slide relatively when the engine rotates at a high speed, make its surface and friction disc 907 combine to produce the slip frictional force, the frictional force is big when the rotational speed is big more.
In order to reduce the friction between the swinging block 906 and the clutch housing 908, prolong the service life of the equipment and ensure the smooth running of the equipment, a swinging block pad 905 is arranged between the swinging block 906 and the clutch housing 908, a friction plate 907 is arranged in the clutch housing 908, one end of a clutch central shaft 903 is fixed between the swinging block seat 904 and the transmission gear plate 902, the other end of the clutch central shaft passes through the swinging block seat 904, the swinging block pad 905 and the swinging block 906 in sequence and is sleeved in the clutch housing 908, a second mounting seat 909 is arranged outside the clutch housing 908, and finally a synchronous wheel 910 is arranged on the second mounting seat 909.
The synchronizing wheel 910 is connected with a connecting shaft of a generator through a coupler 10, and then drives the generator to generate electricity.
The power management system in the master control system can control the power switcher 7 to cut off the transmission between the transmission mechanism 6 and the rotor wing 3, so that the engine drives the generator to rotate, and the transmission between the transmission mechanism 6 and the rotor wing can be controlled to normally operate; the power switch 7 may be, but is not limited to, a power switch device of a hybrid vehicle having application No. CN 200510078096.4.
A power management system in the master control system performs power supply control, wherein the power management system comprises a rectifier 13, a filtering unit and a voltage stabilizing unit; the alternating current output by the generator outputs the required direct current through the rectifier 13, and then the direct current passes through the filtering unit and the voltage stabilizing unit, and the voltage stabilizing unit further stabilizes the voltage filtered by the filtering unit, so that the voltage with high stability is ensured to be output.
As a preferable filter unit, a capacitor filter circuit is specifically used, and an inductor filter circuit or a combined filter circuit composed of a capacitor and an inductor, for example, may be used, and a pi filter circuit, for example, may be used as the combined filter circuit.
The power management system is also connected with an electromagnetic valve 12, and can cut off or switch on the output current of the generator so as to control power supply.
In a first state, an electric signal is sent to a power switcher 7 through a power management system in a master control system, so that an engine 8 is ensured to drive a rotor 3 to rotate, the unmanned aerial vehicle takes off and stably flies to a designated rescue place, and in the process, a power management system in the master control system controls a solenoid valve 12 to be closed, so that no current is output from a generator; during the state in the second, send the signal of telecommunication for power switch 7 through the power management system among the major control system to cut off the transmission between engine 8 and the rotor 3, and then make the engine only drive the generator and operate, major control system power management system control solenoid valve 12 opens simultaneously, makes the generator output alternating current, and alternating current is through changing into the direct current through rectifier 13, rethread filtering wave unit and voltage stabilizing unit, makes the direct current stable and act on the consumer.
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 and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (5)
1. The rescue unmanned aerial vehicle with the generator is characterized by comprising an unmanned aerial vehicle, and an engine (8), a clutch (9) and a generator (11) which are arranged on a frame (2) of the unmanned aerial vehicle, wherein a rotor (3) of the unmanned aerial vehicle is connected with the clutch (9) through a transmission mechanism (6), one end of the clutch (9) is connected with the engine (8), and the other end of the clutch (9) is connected with the generator (11) through a coupler (10); the main control system of the unmanned aerial vehicle comprises a power management system and a power management system, wherein the power management system controls the power switcher (7), and the power management system is used for managing the power generator (11) to supply power to the electric equipment.
2. The unmanned rescue vehicle with generator as claimed in claim 1, wherein the clutch (9) comprises a first mounting seat (901) connected to the engine (8), a transmission gear plate (902) connected to the first mounting seat (901), and the transmission gear plate (902) is connected to the transmission mechanism (6), and the transmission mechanism (6) drives the rotary vane to rotate.
3. Rescue unmanned aerial vehicle with generator according to claim 1, characterized in that the power management system is connected with a solenoid valve (12), the solenoid valve (12) is arranged at the current output end of the generator (11).
4. The rescue unmanned aerial vehicle with generator as claimed in claim 3, wherein the power management system comprises a rectifier (13), a filter unit and a voltage stabilizing unit.
5. A rescue mode of a rescue unmanned aerial vehicle with a generator is characterized in that the rescue unmanned aerial vehicle with the generator is used according to claim 4, and the rescue unmanned aerial vehicle with the generator specifically comprises the following two states:
in the first state, an electric signal is sent to a power switcher (7) through a power management system in a master control system, so that an engine (8) is ensured to drive a rotor wing (3) to rotate, and further the unmanned aerial vehicle takes off and stably flies to a designated rescue place, wherein a power management system in the master control system controls a solenoid valve (12) to be closed, so that a generator (11) has no current output;
and in the second intermediate state, the power management system in the main control system sends an electric signal to the power switcher (7), so that the transmission between the engine (8) and the rotor wing (3) is cut off, the engine (8) only drives the generator (11) to operate, and meanwhile, the power management system of the main control system controls the generator (11) to output stable direct current stably and act on electric equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010422149.4A CN111572770A (en) | 2020-05-18 | 2020-05-18 | Rescue unmanned aerial vehicle with generator and rescue mode thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010422149.4A CN111572770A (en) | 2020-05-18 | 2020-05-18 | Rescue unmanned aerial vehicle with generator and rescue mode thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111572770A true CN111572770A (en) | 2020-08-25 |
Family
ID=72123172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010422149.4A Pending CN111572770A (en) | 2020-05-18 | 2020-05-18 | Rescue unmanned aerial vehicle with generator and rescue mode thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111572770A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1730330A (en) * | 2004-08-05 | 2006-02-08 | 本田技研工业株式会社 | Power switchover apparatus for a hybrid vehicle |
| CN105752344A (en) * | 2016-03-15 | 2016-07-13 | 电子科技大学 | Plug-in hybrid power driving device for tilt-rotor aircraft |
| CN105836141A (en) * | 2016-04-12 | 2016-08-10 | 电子科技大学 | Driving mechanism and driving method of hybrid power helicopter |
| CN108313305A (en) * | 2017-12-22 | 2018-07-24 | 成都才智圣有科技有限责任公司 | A kind of unmanned vehicle engine with generating function |
| CN207777446U (en) * | 2017-12-27 | 2018-08-28 | 四川珠峰金泉航空科技有限公司 | A kind of dynamic unmanned plane clutch system of oil |
| CN108639320A (en) * | 2018-06-05 | 2018-10-12 | 河南三和航空工业有限公司 | A kind of DCB Specimen unmanned helicopter |
| CN210027898U (en) * | 2019-04-24 | 2020-02-07 | 北京京东乾石科技有限公司 | Power system and unmanned aerial vehicle |
| CN210102007U (en) * | 2019-06-04 | 2020-02-21 | 南京灵龙旋翼无人机系统研究院有限公司 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
-
2020
- 2020-05-18 CN CN202010422149.4A patent/CN111572770A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1730330A (en) * | 2004-08-05 | 2006-02-08 | 本田技研工业株式会社 | Power switchover apparatus for a hybrid vehicle |
| CN105752344A (en) * | 2016-03-15 | 2016-07-13 | 电子科技大学 | Plug-in hybrid power driving device for tilt-rotor aircraft |
| CN105836141A (en) * | 2016-04-12 | 2016-08-10 | 电子科技大学 | Driving mechanism and driving method of hybrid power helicopter |
| CN108313305A (en) * | 2017-12-22 | 2018-07-24 | 成都才智圣有科技有限责任公司 | A kind of unmanned vehicle engine with generating function |
| CN207777446U (en) * | 2017-12-27 | 2018-08-28 | 四川珠峰金泉航空科技有限公司 | A kind of dynamic unmanned plane clutch system of oil |
| CN108639320A (en) * | 2018-06-05 | 2018-10-12 | 河南三和航空工业有限公司 | A kind of DCB Specimen unmanned helicopter |
| CN210027898U (en) * | 2019-04-24 | 2020-02-07 | 北京京东乾石科技有限公司 | Power system and unmanned aerial vehicle |
| CN210102007U (en) * | 2019-06-04 | 2020-02-21 | 南京灵龙旋翼无人机系统研究院有限公司 | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201544960U (en) | Hybrid power control system of rail hybrid power locomotive | |
| CN206068172U (en) | Fixed-wing formula hybrid power aeroplane | |
| CN205059313U (en) | Bi -motor multi -mode driving system of adjustable speed | |
| CN109094790B (en) | Power configuration scheme and control method for hybrid power system of helicopter | |
| CN103042945B (en) | Maglev train power system | |
| CN108082499A (en) | Planetary hybrid power helicopter dynamic coupling system and driving method | |
| CN109733621A (en) | A kind of hybrid power unmanned plane promoting mode more | |
| CN203543617U (en) | Dual-motor driving system for electric automobile | |
| CN105253028A (en) | Control method and device for hybrid power supply stroke-adding type electric vehicle | |
| CN103552477A (en) | Electromobile double-motor driving system | |
| CN106184779A (en) | A kind of hybrid power aeroplane coupled system | |
| CN108791905A (en) | A kind of aircraft hybrid power integrated unit | |
| CN210102007U (en) | Rotary wing vertical take-off and landing unmanned aerial vehicle combining oil-driven flight and electric take-off and landing | |
| CN205113038U (en) | Composite power source increases controlling means of form electric motor car | |
| CN111572770A (en) | Rescue unmanned aerial vehicle with generator and rescue mode thereof | |
| CN108545199A (en) | Parallel type hybrid dynamic aircraft power system | |
| CN206050087U (en) | Hybrid power aeroplane coupled system | |
| CN115489460B (en) | Power-on and power-off control method of all-in-one controller | |
| CN205034976U (en) | Support rubber -tired crane of two kinds of power supply modes | |
| CN216070500U (en) | Cruise hybrid power system of unmanned aerial vehicle | |
| CN109591528B (en) | Hybrid power highway-railway vehicle and control system thereof | |
| CN207644155U (en) | Transfer case, hybrid power system and vehicle | |
| CN207433818U (en) | A kind of aircraft hybrid power integrated unit | |
| CN207932878U (en) | Intelligent energy-saving device for escalator | |
| CN210455232U (en) | All-electric-driven rotary wing vertical take-off and landing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200825 |
|
| RJ01 | Rejection of invention patent application after publication |