CN205229808U - Integration of many power flies accuse system for little small aircraft - Google Patents
Integration of many power flies accuse system for little small aircraft Download PDFInfo
- Publication number
- CN205229808U CN205229808U CN201521098235.5U CN201521098235U CN205229808U CN 205229808 U CN205229808 U CN 205229808U CN 201521098235 U CN201521098235 U CN 201521098235U CN 205229808 U CN205229808 U CN 205229808U
- Authority
- CN
- China
- Prior art keywords
- oar
- driftage
- attitude
- power system
- flight control
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model provides an integration of many power flies accuse system for little small aircraft, the system is including flying to control computer, flight parameter sensor, PID controller, driftage oar driving system, gesture oar driving system and main oar driving system, the output of flight parameter sensor is connected to the input that flies to control the computer, and the output that flies to control the computer is connected to driftage oar driving system, gesture oar driving system and main oar driving system respectively through the PID controller. The advantage does: (1 )Adopting the overall arrangement mode of main oar, gesture oar and driftage oar, can effectively reducing at flight in -process gesture oar load, effectual promotion aircraft driving system efficiency promotes aircraft time of endurance. (2 )Many sets of driving system fuse control to the aircraft, have solved the problem of this aircraft owner oar lift unstability and the reverse balance of main oar, finally realize the autonomic flight of the many rotor crafts of this new overall arrangement.
Description
Technical field
The utility model belongs to aircraft flight control system technical field, is specifically related to a kind of many power being applied to micro air vehicle and merges flight control system.
Background technology
Multi-rotor aerocraft is driven by many rotors can realize surely high spot hover, and under floating state, can change fuselage attitude rapidly, has good maneuverability, can carry load and complete aerial mission.
In prior art, conventional multi-rotor aerocraft mainly adopts multiple identical independent driving device to drive, and such as: for six rotorcraft, adopt the rotor driving that six identical, and six rotors is distributed on around aircraft body.The effect being arranged in the rotor around aircraft body comprises provides lift and gesture stability two aspect.
Due to many-side restriction, the multi-rotor aerocraft of above-mentioned normal arrangement has the lower deficiency of flight efficiency, cannot ensure the flight of multi-rotor aerocraft long-term stability.
Utility model content
For the defect that prior art exists, the utility model provides a kind of many power being applied to micro air vehicle to merge flight control system, multi-rotor aerocraft layout and flight control system are improved simultaneously, thus effectively improve aircraft flight efficiency, ensure the flight of aircraft long-term stability.
The technical solution adopted in the utility model is as follows:
The utility model provides a kind of many power being applied to micro air vehicle to merge flight control system, comprises flight control computer, flight parameter sensor, PID controller, driftage oar power system, attitude oar power system and main oar power system;
Wherein, described main oar power system is used for providing power for main oar, and described main oar refers to the screw propeller being laid in aircraft center; Described attitude oar power system is used for providing power for attitude oar, the unique corresponding described attitude oar power system of each attitude oar; The magnitude setting of described attitude oar is multiple, and its arrangement is: extend several horns from the outside divergent shape in aircraft center, arranges a described attitude oar at the end of each horn; Described driftage oar power system is used for for driftage oar provides power, the unique corresponding described driftage oar power system of each described driftage oar; The magnitude setting of described driftage oar is multiple, and its arrangement is: for being positioned at collinear two horns, be designated as the 1st horn and the 2nd horn respectively, installs a described driftage oar respectively in the symmetric position of described 1st horn and described 2nd horn;
The output terminal of described flight parameter sensor is connected to the input end of described flight control computer, and the output terminal of described flight control computer is connected respectively to described driftage oar power system, described attitude oar power system and described main oar power system by described PID controller.
Preferably, described flight parameter sensor comprises: gyroscope, accelerometer and barometric altimeter etc.
Preferably, described attitude oar is pitching/rolling screw propeller.
Preferably, described flight control computer is also connected with GPS locating device and storer; Described flight control computer is also connected with land station by data communication equipment (DCE).
Many power of what the utility model provided be applied to micro air vehicle merge flight control systems and have the following advantages:
(1) adopt the layout type of main oar, attitude oar and driftage oar, provide prevailing lift by main oar; Secondary lift is provided by attitude oar, owing to jointly providing lift needed for aircraft flight by main oar and attitude oar, therefore, attitude oar load in flight course can be effectively reduced in, thus effective promote Power System of Flight Vehicle efficiency, promote aircraft cruising time.
(2) fused controlling is carried out to aircraft many covers power system, solve the problem of this aircraft main oar lift instability and main oar reactive torque balance, finally realize the autonomous flight of this new layout multi-rotor aerocraft.
Accompanying drawing explanation
Fig. 1 merges the schematic layout pattern of the aircraft corresponding to flight control systems for many power that the utility model provides;
The hardware configuration schematic diagram of many power fusion flight control systems that Fig. 2 provides for the utility model.
Embodiment
The technical matters solved to make the utility model, technical scheme and beneficial effect are clearly understood, below in conjunction with drawings and Examples, are further elaborated to the utility model.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
The utility model discloses a kind of many power being applied to micro air vehicle and merge flight control system, many power merges flight control system and has three cover power systems, is respectively driftage oar power system, attitude oar power system and main oar power system; Wherein, main oar power system is connected with main oar, and main oar adopts large scale, the main oar of high-level efficiency, for generation of prevailing lift, improves full machine flight efficiency, makes it reach longer cruising time; Attitude oar power system is connected with oar state oar, maintains attitude of flight vehicle stablize for generation of the required secondary lift of flight, and it is motor-driven to coordinate main oar to carry out necessity; Driftage oar power system is connected with driftage oar, for offsetting the reactive torque of main oar, keeps vector to stablize.Many power designed by the utility model merge flight control system, carry out fused controlling, solve the technical matterss such as aircraft main oar lift instability and main oar opposing torque balance, achieve stability contorting, and can carry out autonomous flight three cover power systems; In addition, also effectively improve aircraft flight efficiency, ensure the flight of aircraft long-term stability.
Composition graphs 1 and Fig. 2, the utility model provides a kind of many power being applied to micro air vehicle to merge flight control system, comprises flight control computer, flight parameter sensor, PID controller, driftage oar power system, attitude oar power system and main oar power system;
Wherein, flight control computer adopts the STM32F427 processor of STMicw Electronics, and this processor is with Float Point Unit, and can carry out rapid computations to a large amount of sensing data, computational accuracy is high, can improve attitude algorithm level and control output accuracy.In addition, this processor is also integrated with abundant Peripheral Interface, facilitates the data transmission of sensor.
Flight parameter sensor comprises: gyroscope, accelerometer and barometric altimeter, for gathering aircraft real-time flight parameter comprehensively, all can adopt MEMS sensor, greatly reduces weight and the size of flight control system.Wherein, gyroscope uses MPU6050, can export in a digital manner 6 axles or 9 axis rotation matrixs, hypercomplex number, Eulerian angle form attitude merge calculation data.Barometric altimeter uses high-resolution MS5611, has temperature compensation function, makes resolution reach 10cm.
Main oar power system is used for providing power for main oar, and main oar refers to the screw propeller being laid in aircraft center;
Attitude oar power system is used for providing power for attitude oar, and attitude oar is pitching/rolling screw propeller, the unique corresponding attitude oar power system of each attitude oar; The magnitude setting of attitude oar is multiple, and its arrangement is: extend several horns from the outside divergent shape in aircraft center, arranges an attitude oar at the end of each horn;
Driftage oar power system is used for for driftage oar provides power, the unique corresponding driftage oar power system of each driftage oar; The magnitude setting of driftage oar is multiple, and its arrangement is: for being positioned at collinear two horns, being designated as the 1st horn and the 2nd horn respectively, installing a driftage oar respectively in the symmetric position of the 1st horn and the 2nd horn;
In FIG, main oar numeral 1 represents; Attitude oar numeral 2 represents; Driftage oar numeral 3 represents; In FIG, have 1 main oar, 4 attitude oars and 2 driftage oars.
By adopting the layout type of above-mentioned main oar, attitude oar and driftage oar, provide prevailing lift by main oar; Secondary lift is provided by attitude oar, owing to jointly providing lift needed for aircraft flight by main oar and attitude oar, therefore, attitude oar load in flight course can be effectively reduced in, thus effective promote Power System of Flight Vehicle efficiency, promote aircraft cruising time.In addition, by the setting of oar of going off course, offset the moment of torsion that main oar produces, ensure the operation of aircraft normal table.
The output terminal of flight parameter sensor is connected to the input end of flight control computer, and the output terminal of flight control computer is connected respectively to driftage oar power system, attitude oar power system and main oar power system by PID controller.
Visible, in the utility model, flight control computer, according to practical flight parameter, controls driftage oar, attitude oar and main oar respectively in real time, can ensure the operation of aircraft long-term stability, have high flight efficiency.
In addition, in practical application, flight control computer is also connected with GPS locating device and storer.Storer can adopt SD card, can carry out record to the Air Diary of aircraft, by the data in Air Diary, can carry out playback to the flight course of aircraft, can provide foundation for parameter adjustment simultaneously.
The employing of GPS locating device is low in energy consumption, precision is high, supports the locating device of multiple navigational system, uses I2C mode to communicate with flight control computer, provides aircraft current location information, for aircraft navigation provides reference.
Flight control computer is also connected with land station by data communication equipment (DCE).
Every data of aircraft are carried out wireless transmission by UART interface by data communication equipment (DCE), to be gone forward side by side row relax by ground station reception.
In practical application, flight parameter sensor, GPS locating device, storer and data communication interface are integrated on 1 piece of pcb board.
At present, the multiple identical power system drive of the many employings of conventional multi-rotor aerocraft, and each power system is distributed on around fuselage.And the multi-rotor aerocraft of the new topological design that the utility model provides, be provided with main oar in center and prevailing lift is provided, the reactive torque of the main oar of driftage paddle balance is set in horn side, adopt unsymmetric structure and have and overlap power system more.The utility model devises a kind of control algolithm of many power fusions for this new layout multi-rotor aerocraft, utilize flight control computer, fusion calculation is carried out to the data of each sensor and the telecommand of operator, obtain the output quantity of each power system, realize the stability contorting to aircraft.
As can be seen here, many power of what the utility model provided be applied to micro air vehicle merge flight control systems, have the following advantages:
(1) adopt the layout type of main oar, attitude oar and driftage oar, provide prevailing lift by main oar; Secondary lift is provided by attitude oar, owing to jointly providing lift needed for aircraft flight by main oar and attitude oar, therefore, attitude oar load in flight course can be effectively reduced in, thus effective promote Power System of Flight Vehicle efficiency, promote aircraft cruising time.
(2) fused controlling is carried out to aircraft many covers power system, solve the problem of this aircraft main oar lift instability and main oar reactive torque balance, finally realize the autonomous flight of this new layout multi-rotor aerocraft.
The above is only preferred implementation of the present utility model; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the utility model principle; can also make some improvements and modifications, these improvements and modifications also should look protection domain of the present utility model.
Claims (4)
1. the many power being applied to micro air vehicle merge a flight control system, it is characterized in that, comprise flight control computer, flight parameter sensor, PID controller, driftage oar power system, attitude oar power system and main oar power system;
Wherein, described main oar power system is used for providing power for main oar, and described main oar refers to the screw propeller being laid in aircraft center; Described attitude oar power system is used for providing power for attitude oar, the unique corresponding described attitude oar power system of each attitude oar; The magnitude setting of described attitude oar is multiple, and its arrangement is: extend several horns from the outside divergent shape in aircraft center, arranges a described attitude oar at the end of each horn; Described driftage oar power system is used for for driftage oar provides power, the unique corresponding described driftage oar power system of each described driftage oar; The magnitude setting of described driftage oar is multiple, and its arrangement is: for being positioned at collinear two horns, be designated as the 1st horn and the 2nd horn respectively, installs a described driftage oar respectively in the symmetric position of described 1st horn and described 2nd horn;
The output terminal of described flight parameter sensor is connected to the input end of described flight control computer, and the output terminal of described flight control computer is connected respectively to described driftage oar power system, described attitude oar power system and described main oar power system by described PID controller.
2. the many power being applied to micro air vehicle according to claim 1 merge flight control system, and it is characterized in that, described flight parameter sensor comprises: gyroscope, accelerometer and barometric altimeter.
3. the many power being applied to micro air vehicle according to claim 1 merge flight control system, and it is characterized in that, described attitude oar is pitching/rolling screw propeller.
4. the many power being applied to micro air vehicle according to claim 1 merge flight control system, and it is characterized in that, described flight control computer is also connected with GPS locating device and storer; Described flight control computer is also connected with land station by data communication equipment (DCE).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521098235.5U CN205229808U (en) | 2015-12-25 | 2015-12-25 | Integration of many power flies accuse system for little small aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521098235.5U CN205229808U (en) | 2015-12-25 | 2015-12-25 | Integration of many power flies accuse system for little small aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205229808U true CN205229808U (en) | 2016-05-11 |
Family
ID=55904858
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521098235.5U Expired - Fee Related CN205229808U (en) | 2015-12-25 | 2015-12-25 | Integration of many power flies accuse system for little small aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205229808U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| CN110217384A (en) * | 2018-03-01 | 2019-09-10 | 贝尔直升机德事隆公司 | Propulsion system for rotor craft |
| CN111061281A (en) * | 2018-10-16 | 2020-04-24 | 海鹰航空通用装备有限责任公司 | Aircraft flight scheme generation method and system and aircraft with aircraft flight scheme generation system |
-
2015
- 2015-12-25 CN CN201521098235.5U patent/CN205229808U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105468009A (en) * | 2015-12-25 | 2016-04-06 | 西北工业大学 | System and method for multi-power integrated flight control applied in micro air vehicle |
| CN110217384A (en) * | 2018-03-01 | 2019-09-10 | 贝尔直升机德事隆公司 | Propulsion system for rotor craft |
| CN110217384B (en) * | 2018-03-01 | 2023-04-07 | 德事隆创新公司 | Propulsion system for a rotorcraft |
| US11718390B2 (en) | 2018-03-01 | 2023-08-08 | Textron Innovations Inc. | Propulsion systems for rotorcraft |
| CN111061281A (en) * | 2018-10-16 | 2020-04-24 | 海鹰航空通用装备有限责任公司 | Aircraft flight scheme generation method and system and aircraft with aircraft flight scheme generation system |
| CN111061281B (en) * | 2018-10-16 | 2023-08-15 | 海鹰航空通用装备有限责任公司 | Aircraft flight scheme generation method and generation system and aircraft with same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105468009A (en) | System and method for multi-power integrated flight control applied in micro air vehicle | |
| CN105353762B (en) | The control method of six rotor wing unmanned aerial vehicles based on double remaining attitude transducers | |
| CN102424112B (en) | Three-layer airborne flight control device for micro four-rotor aerial vehicle | |
| CN106114854B (en) | A kind of push-button aircraft | |
| CN106114853B (en) | A kind of push-button aircraft | |
| US20170253333A1 (en) | Unmanned vehicle | |
| CN104597912A (en) | Tracking flying control system and method of six-rotor unmanned helicopter | |
| CN107264813A (en) | A kind of tailstock vertical takeoff and landing vehicle flight control system | |
| CN107132851A (en) | A kind of unmanned plane during flying navigation control system | |
| CN105607640B (en) | The Pose Control device of quadrotor | |
| CN205229808U (en) | Integration of many power flies accuse system for little small aircraft | |
| CN109606674A (en) | Tail sitting posture vertical take-off and landing drone and its control system and control method | |
| CN106828908A (en) | A kind of electronic single shaft shrouded propeller aircraft | |
| CN106325289A (en) | Renesas R5F100LEA master control-based four-rotor flight controller and control method thereof | |
| CN105974494A (en) | Radio-sondage system based on dual-redundancy fixed wing unmanned aerial vehicle | |
| CN106809383A (en) | A kind of electronic coaxial shrouded propeller aircraft | |
| CN104331086A (en) | Flight control system of small multi-rotor for power line patrol | |
| CN108706099A (en) | One kind is verted three axis composite wing unmanned planes and its control method | |
| CN105035299A (en) | Cruise and suspension aircraft and flight control method thereof | |
| CN105116933A (en) | Unmanned aircraft and method preventing unmanned aircraft from separation from control area | |
| CN203882149U (en) | Unmanned helicopter flight control system based on DSP and FPGA | |
| CN204314726U (en) | A kind of six rotor unmanned helicopters follow the tracks of flight control system | |
| CN107571990A (en) | A kind of highly sensitive three axles unmanned plane | |
| CN107757914A (en) | Double dynamical VTOL fixed-wing unmanned plane | |
| CN106199764A (en) | A kind of radio sounding system based on double remaining six rotor wing unmanned aerial vehicles |
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: 20160511 Termination date: 20201225 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |