CN114148502A - Four-rotor aircraft based on floating platform - Google Patents
Four-rotor aircraft based on floating platform Download PDFInfo
- Publication number
- CN114148502A CN114148502A CN202111472296.3A CN202111472296A CN114148502A CN 114148502 A CN114148502 A CN 114148502A CN 202111472296 A CN202111472296 A CN 202111472296A CN 114148502 A CN114148502 A CN 114148502A
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- rotor
- floating platform
- equipment
- quad
- spherical structure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/24—Arrangement of propulsion plant
- B64B1/30—Arrangement of propellers
- B64B1/34—Arrangement of propellers of lifting propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/58—Arrangements or construction of gas-bags; Filling arrangements
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radio Relay Systems (AREA)
Abstract
The application provides a four rotor crafts based on platform floats, four rotor crafts include: the floating platform is provided with a spherical structure; wherein the floating platform is used for providing main lift; the rotor wing mechanisms are symmetrically arranged in the spherical structure and are used for providing auxiliary lifting force and air maneuvering capacity; the task load equipment is arranged on the spherical structure and used for carrying out communication relay, reconnaissance monitoring and live video recording; the application provides a four rotor crafts based on floating platform has had the advantage of the time of endurance and flexible concurrently.
Description
Technical Field
The application belongs to the technical field of aerostatics, especially relates to a four rotor crafts based on platform floats.
Background
The four-rotor aircraft based on the floating platform is a long-endurance and large-load new concept aircraft which utilizes net buoyancy to realize height control and four rotors to execute anti-wind maneuver flight, and provides a brand-new technical means for the application fields of battlefield reconnaissance and monitoring, live competition, earthquake relief, infrastructure monitoring, environment monitoring, high-speed communication, agriculture and forestry plant protection and the like by carrying optical, microwave and other remote sensing loads and wireless communication loads.
At present, four rotor crafts are generally short when navigating, and adopt the problem of battery continuation of the journey that four rotor unmanned aerial vehicle of mooring mode have solved, but it can only remove at fixed mooring position, and mobility is relatively poor, can't change in real time as required and observe the position.
Therefore, in order to solve the above technical problems, the present application proposes a four-rotor aerostat having both advantages of long endurance and maneuverability.
Disclosure of Invention
To the above technical problem, the application provides a four rotor crafts based on floating platform, four rotor crafts include:
the floating platform is provided with a spherical structure; wherein the floating platform is used for providing main lift;
the rotor wing mechanisms are symmetrically arranged in the spherical structure and are used for providing auxiliary lifting force and air maneuvering capacity;
and the task load equipment is arranged on the spherical structure and is used for carrying out communication relay, reconnaissance monitoring and live video recording.
Preferably, the sphere structure comprises a capsule filled with helium; wherein the helium gas is used to provide a primary lift.
Preferably, the floating platform further comprises:
a pressure regulating device for controlling the pneumatic profile and stiffness of the spherical structure;
a measurement and control device having a sensor; the sensor is used for detecting flight parameters of the four-rotor aircraft and sending the flight parameters to a control center;
the power supply equipment is electrically connected with the pressure regulating equipment and the measurement and control equipment respectively; the power supply equipment is used for supplying power to the pressure regulating equipment and the measurement and control equipment.
Preferably, said power supply apparatus is also electrically connected to said rotor mechanism and said mission load apparatus, respectively; wherein the power supply device is configured to supply power to the rotor mechanism and the mission load device.
Preferably, the rotor mechanism comprises:
the rotor wings are symmetrically arranged in four directions outside the floating platform;
the motor, with the rotor is connected, is used for doing the rotor provides power.
Preferably, the rotor mechanism further comprises:
electrically adjusting;
the flight control computer is connected with the electric tuning; wherein the flight control computer and the electric controller are used for controlling the rotating speed and the deflection angle of the rotor wing
Preferably, the task load device comprises a video and audio acquisition device, an atmospheric environment monitoring device and a data acquisition system.
Preferably, the mission load device further comprises an air data communication and network system, an optical-electric load and a wireless communication device.
The beneficial technical effect of this application:
the application provides a four rotor crafts based on floating platform has had the advantage of the time of endurance and flexible concurrently.
Drawings
FIG. 1 is a schematic structural diagram of a four-rotor aircraft based on a floating platform according to an embodiment of the present application;
fig. 2 is a top view of a quad-rotor aircraft based on a floating platform according to an embodiment of the present application.
Detailed Description
Referring to fig. 1-2, the present application belongs to the field of aerostat, and the aircraft provided by the present application has wide application prospect in military and civil fields.
It should be noted that this aircraft has aerostatics and four rotor unmanned aerial vehicle's characteristics concurrently. Compared with an aerostat, the four-rotor aerostat adopts a layout mode of fusion of four rotors and an air bag, is more beneficial to balance of an aircraft, reduces flight resistance, has the characteristics of strong maneuverability, high wind resistance, flexible use and the like, and can continuously hover to execute flight tasks.
Compared with an unmanned aerial vehicle, the endurance time of the four-rotor aerostat is far longer than the average endurance time (30min) of the multi-rotor aircraft, the load capacity of the floating platform is remarkably improved, the four-rotor aerostat can be rapidly deployed in a medium and low altitude environment area, and cooperation operation among the aircrafts can be realized through multi-machine formation flying in the future.
In this application embodiment, the aircraft of this application mainly is used for realizing communication to ground, monitoring and function of making a video recording: the camera/photoelectric pod and other loads shoot target images in real time, position and time signals of the aircraft are collected and recorded through a controller (such as a single chip microcomputer and a PLC), and meanwhile, the data transmission/image transmission platform transmits images and flight parameters to the ground.
And after the four-rotor aerostat is lifted off, the height is kept by virtue of helium buoyancy and lift force generated by the rotor, and the anti-wind hovering effect can be realized by virtue of the vector rotation of the motor, so that the purpose of fixed-point observation in long-endurance flight is achieved.
In a feasible realization mode, the four-rotor aerostat mainly comprises a rotor wing mechanism, an aerostat and a task load.
The floating platform provides main lift, the rotor wing mechanism provides auxiliary lift and air maneuvering capability, and the task load can carry different devices according to task requirements to complete tasks such as communication relay, reconnaissance monitoring and live broadcast video recording, as shown in fig. 2.
In a feasible implementation manner, as shown in fig. 1, the rotor mechanism mainly comprises a rotor, a motor, an electric speed regulator, a flight control computer and the like, the rotor is symmetrically arranged in four directions outside the aerostat, and the flight control computer controls the rotation speed and the deflection angle of the rotor so as to provide continuous space-parking and maneuvering flight capabilities for the aerostat.
Wherein, be in heavy buoyancy balanced state at suitable high department aerostatics, rotor mechanism only needs carry out the gesture to the aerostatics this moment and adjusts in order to stabilize aerial state, greatly reduced rotor mechanism electric quantity demand, promote its aerial long endurance working ability.
In a feasible implementation mode, the floating platform is composed of a sphere structure, pressure adjusting equipment, power supply equipment, measurement and control equipment and the like. The spheroid structure main part is the utricule, and inside is filled the helium and provides lift for four rotor aerostatics.
The pressure adjusting equipment can ensure that the floating platform can keep good pneumatic appearance at different heights and has enough rigidity; the power supply equipment mainly provides electric energy required by the operation of the rotor wing mechanism, the task load equipment, the pressure regulating equipment and the measurement and control equipment under normal and emergency conditions; the measurement and control equipment monitors various parameters of the four-rotor floating system through the sensor and provides data processing for the control center.
In a feasible implementation mode, the task load equipment mainly comprises an atmospheric environment monitoring and data acquisition system, an air data communication and network system, a photoelectric load, wireless communication equipment and the like, and is reasonably matched according to different task requirements; other devices are also possible and are not limited herein.
This application belongs to four rotor crafts based on floating platform, and the long voyage of full play aerostatics flies and four rotors can hover or maneuver flight's advantage, makes this aircraft have characteristics such as development cost is low, fail safe nature is high, long voyage heavy load.
The aircraft provided by the application can integrate multiple functions and interfaces, is high in expansibility, and can carry out various flight tasks through loads (remote sensing loads, photoelectric loads and wireless communication loads) carrying different types, so that special requirements of users are met.
Claims (8)
1. A quad-rotor aircraft based on a floating platform, comprising:
the floating platform is provided with a spherical structure; wherein the floating platform is used for providing main lift;
the rotor wing mechanisms are symmetrically arranged in the spherical structure and are used for providing auxiliary lifting force and air maneuvering capacity;
and the task load equipment is arranged on the spherical structure and is used for carrying out communication relay, reconnaissance monitoring and live video recording.
2. The floating platform based quadrotor aircraft according to claim 1, wherein the sphere structure comprises a capsule filled with helium; wherein the helium gas is used to provide a primary lift.
3. A quad-rotor aerial vehicle based on a floating platform according to claim 1, wherein the floating platform further comprises:
a pressure regulating device for controlling the pneumatic profile and stiffness of the spherical structure;
a measurement and control device having a sensor; the sensor is used for detecting flight parameters of the four-rotor aircraft and sending the flight parameters to a control center;
the power supply equipment is electrically connected with the pressure regulating equipment and the measurement and control equipment respectively; the power supply equipment is used for supplying power to the pressure regulating equipment and the measurement and control equipment.
4. A quad-rotor craft based on a floating platform according to claim 3,
the power supply equipment is also electrically connected with the rotor wing mechanism and the task load equipment respectively; wherein the power supply device is configured to supply power to the rotor mechanism and the mission load device.
5. A quad-rotor aerial vehicle based on a floating platform according to claim 4, wherein the rotor mechanism comprises:
the rotor wings are symmetrically arranged in four directions outside the floating platform;
the motor, with the rotor is connected, is used for doing the rotor provides power.
6. A quad-rotor aerial vehicle based on a floating platform according to claim 5, wherein the rotor mechanism further comprises:
electrically adjusting;
the flight control computer is connected with the electric tuning; the flight control computer and the electric controller are used for controlling the rotating speed and the deflection angle of the rotor wing.
7. A quad-rotor aerial vehicle based on a floating platform according to claim 4, wherein the mission load equipment comprises video and audio acquisition equipment, atmospheric monitoring equipment and a data acquisition system.
8. The floating platform based quad-rotor aircraft according to claim 7, wherein the mission load device further comprises an airborne data communication and networking system, a photovoltaic load, and a wireless communication device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111472296.3A CN114148502A (en) | 2021-12-03 | 2021-12-03 | Four-rotor aircraft based on floating platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111472296.3A CN114148502A (en) | 2021-12-03 | 2021-12-03 | Four-rotor aircraft based on floating platform |
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| Publication Number | Publication Date |
|---|---|
| CN114148502A true CN114148502A (en) | 2022-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111472296.3A Pending CN114148502A (en) | 2021-12-03 | 2021-12-03 | Four-rotor aircraft based on floating platform |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102424104A (en) * | 2011-12-31 | 2012-04-25 | 沈阳航空航天大学 | Four-rotor-wing indoor airship |
| CN206278253U (en) * | 2016-12-16 | 2017-06-27 | 中国电子科技集团公司第三十八研究所 | One kind is used for captive balloon emergency pressure control device |
| CN106892081A (en) * | 2015-12-21 | 2017-06-27 | 深圳光启空间技术有限公司 | Multi-rotor aerocraft |
| CN206544591U (en) * | 2017-02-28 | 2017-10-10 | 南昌航空大学 | A kind of rotor dirigible of new culvert type four |
| US20180022461A1 (en) * | 2016-02-05 | 2018-01-25 | Brendon G. Nunes | Hybrid airship |
| CN108146608A (en) * | 2017-12-19 | 2018-06-12 | 北京航空航天大学 | A kind of rotor with vectored thrust and air bag combined type lighter-than-air flight device |
| CN108238228A (en) * | 2017-12-13 | 2018-07-03 | 中国特种飞行器研究所 | A kind of buoyance lift integrated flight device |
| CN109436283A (en) * | 2018-09-30 | 2019-03-08 | 中国特种飞行器研究所 | A kind of flying wing type variant dirigible |
| CN111216867A (en) * | 2018-11-27 | 2020-06-02 | 童恬 | Aircraft |
-
2021
- 2021-12-03 CN CN202111472296.3A patent/CN114148502A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102424104A (en) * | 2011-12-31 | 2012-04-25 | 沈阳航空航天大学 | Four-rotor-wing indoor airship |
| CN106892081A (en) * | 2015-12-21 | 2017-06-27 | 深圳光启空间技术有限公司 | Multi-rotor aerocraft |
| US20180022461A1 (en) * | 2016-02-05 | 2018-01-25 | Brendon G. Nunes | Hybrid airship |
| CN206278253U (en) * | 2016-12-16 | 2017-06-27 | 中国电子科技集团公司第三十八研究所 | One kind is used for captive balloon emergency pressure control device |
| CN206544591U (en) * | 2017-02-28 | 2017-10-10 | 南昌航空大学 | A kind of rotor dirigible of new culvert type four |
| CN108238228A (en) * | 2017-12-13 | 2018-07-03 | 中国特种飞行器研究所 | A kind of buoyance lift integrated flight device |
| CN108146608A (en) * | 2017-12-19 | 2018-06-12 | 北京航空航天大学 | A kind of rotor with vectored thrust and air bag combined type lighter-than-air flight device |
| CN109436283A (en) * | 2018-09-30 | 2019-03-08 | 中国特种飞行器研究所 | A kind of flying wing type variant dirigible |
| CN111216867A (en) * | 2018-11-27 | 2020-06-02 | 童恬 | Aircraft |
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