CN202433775U - Flight control navigation system for miniature ornithopter - Google Patents
Flight control navigation system for miniature ornithopter Download PDFInfo
- Publication number
- CN202433775U CN202433775U CN2011204622354U CN201120462235U CN202433775U CN 202433775 U CN202433775 U CN 202433775U CN 2011204622354 U CN2011204622354 U CN 2011204622354U CN 201120462235 U CN201120462235 U CN 201120462235U CN 202433775 U CN202433775 U CN 202433775U
- Authority
- CN
- China
- Prior art keywords
- control
- communication interface
- data communication
- fly
- data
- 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
Images
Abstract
The utility model discloses a flight control navigation system for a miniature ornithopter. A signal output by a sensor unit is sent to a flight control navigation computer via a data communication interface after AD conversion. A GPS receiver sends the signal to the flight control navigation computer via the data communication interface for configuration. All programs of the flight control navigation computer and data are running in an SRAM memory. The flight control navigation computer outputs a control instruction to a steering engine and an electronic speed regulator via the data communication interface and is connected with a data link via the data communication interface for communication of remote measurement data and remote control commands. The flight control navigation system of the utility model helps to realize autonomous flight of a miniature ornithopter, and meets strict requirements about space, weight, electromagnetic compatibility and other aspects for the miniature ornithopter.
Description
Technical field
The present invention relates to aircraft control field, especially a kind of aircraft flies to control navigational system.
Background technology
The mini-sized flap wings aircraft is a kind of new ideas aircraft that imitates birds or insect flying; Its adopts and a pair of or several the wing of fluttering to be produced lift and thrust is flown simultaneously; Have that volume is little, in light weight, advantage such as good concealment, use are flexible, efficient height; If carry relevant data transmission and flight control system, just can form mini-sized flap wings unmanned vehicle platform, have wide dual-use prospect.At present international and domestic all in the research of carrying out mini-sized flap wings unmanned plane this respect, " Delfly " of wherein more influential " Microbat " that U.S. Aero Vironment company arranged, Dutch Delft university etc.; 2011 the beginning of the year Aero Vironment company showed up-to-date " Nano Hummingbird " mini-sized flap wings aircraft again, this aircraft can fly as hummingbird, has image investigation ability and stronger maneuverability.Though these mini-sized flap wings aircraft have possessed certain practical value, they all do not carry autonomous flight equipment, must fly control control through ground remote control, and the real practical UAS of distance also has certain gap.
Flying to control navigational system is difficult to use in the mini-sized flap wings aircraft following some reason is arranged: the first, and the complicacy that the flight control of mini-sized flap wings aircraft is intrinsic.On the one hand; The flapping flight process is with the pitching significantly and the cyclic fluctuation of drifting along; The mini-sized flap wings vehicle mass is light simultaneously, inertia is little; The external disturbance influence is remarkable, and these all can make the measured value generation random fluctuation that flies to control the navigational system sensor unit, and the attitude algorithm that causes classic method to be carried out is dispersed; On the other hand; Because the mini-sized flap wings vehicle mass is light, inertia is little, control response is responsive, and fault-tolerance is low; And its suffered external disturbance need control output offset; This control output that just requires to fly to control navigational system should have higher response speed to keep attitude, need avoid excessive output value or even reverse output again, and is just both fast and accurate.The second, as the airborne equipment of minute vehicle, the mini-sized flap wings aircraft flies to control navigational system must have enough little volume and weight, and aspects such as parts selection, circuit design, electromagnetic Compatibility Design have all been proposed harsh requirement.
Summary of the invention
Summary of the invention
Existing fly to control navigation system application and disperse, control the response speed of output and the deficiency that control accuracy deficiency, volume and weight can't satisfy installation requirement in order to overcome in the attitude algorithm that the mini-sized flap wings aircraft can occur; The present invention provide a kind of suitable minute vehicle particularly the mini-sized flap wings aircraft use fly to control navigational system; And make it to possess that volume is little, in light weight, attitude algorithm strong robustness, control output response speed be fast, the characteristics that control accuracy is high.
The technical solution adopted for the present invention to solve the technical problems comprises and flies to control navigational computer, sensor unit, storage unit, GPS receiver, gps antenna and data communication interface, all is integrated in 1 pcb board.
Saidly fly to control navigational computer and adopt Power PC processor.The integrated abundant peripheral interface of this type processor can reduce to fly to control the weight and the size of navigational system; Possess the floating-point operation ability, computational accuracy is high, can improve attitude algorithm level and control output accuracy.
Said sensor unit comprises three axis accelerometer, three-axis gyroscope, three axis magnetometer, static pressure transducer and dynamic pressure transducer, and wherein accelerometer, gyroscope, magnetometer adopt the MEMS sensor, have little, the lightweight characteristics of size; Each sensor signal of output is sent into by the SPI interface of data communication interface through AD conversion back and is flown to control navigational computer.
Said GPS receiver receives gps signal through gps antenna, gps signal is sent into through the UART interface of data communication interface to fly to control navigational computer and be configured again.
Said storage unit comprises SRAM storer and FLASH storer; High-speed bus through data communication interface with fly to control navigational computer and link to each other; All programs and the data that fly to control navigational computer are all moved in the SRAM storer, can guarantee arithmetic speed and access speed.
Saidly fly to control the PWM output interface of navigational computer through data communication interface, thereby accomplish the execution of controlling to topworkies such as steering wheel and electron speed regulator output steering order.
Saidly fly to control navigational computer and link to each other with data link, through this interface take remote measurement data and guidance command communication through UART interface special-purpose in the data communication interface.
Said data communication interface also comprises 1 serial ports, and the user is through this serial ports and saidly fly to control the navigational computer message exchange, and tradable information comprises air route, controlled variable and flying quality.
Said sensor unit uses independently high precision reference power source power supply, between the mimic channel of sensor unit and the digital circuit of flight control computer physical isolation is arranged, and prevents signal cross-talk, can obtain the measuring-signal of high precision, low noise.
The PCB design aspect of above-mentioned hardware is considered electromagnetic compatibility problem, on the multiple-plate basis of tradition, increases stratum and bus plane once more, and bus and clock line are distributed in separation layer inside, shortens the length of bus and clock line, improves Electro Magnetic Compatibility.
The inner function module that flies to control navigational computer comprises communication control module, remote control processing module, air route generation module; Position, speed, attitude control module; Inertial navigation and attitude algorithm module, manual mode module, sensor acquisition processing module and data recording, telemetry module.
Each sensor signal that said sensor processing module is sent into the SPI interface is carried out filtering; After removing useless noise; Send into said inertial navigation and attitude algorithm module; This module adopts the complete non-linear kalman filtering algorithm of total state to carry out attitude algorithm, obtains aircraft space position, air speed, ground velocity and 3 attitude angle, sends into position, speed, attitude control module.
Said communication control module obtains surface instruction through the special-purpose UART interface of data communication interface from data link, sends into said remote control processing module.The remote control processing module receives and resolves surface instruction, and the instruction after resolving is sent to said air route generation module according to command type, when offline mode is automatic mode, also instruction is sent to said position, speed, attitude control module; When offline mode is manual mode, also instruction is sent to said manual mode module.
Said air route generation module generates position, the speed that aircraft should fly in real time after receiving air route information, this information sends to said position, speed, attitude control module.
Said position, speed, attitude control module are divided into positioner, air speed controller, attitude controller and servo decoupling zero/mixture control.Positioner produces attitude control and air speed steering order according to the information of air route generation module, makes the flight path of the reality of aircraft meet predetermined air route.After the air speed controller receives the instruction of positioner; Go out instruction to the attitude controller sending and receiving; Attitude controller should instruction and the information of inertial navigation and attitude algorithm module relatively, form final steering order and send it to said servo decoupling zero/mixture control.Said servo decoupling zero/mixture control is assigned to corresponding topworks with the steering order that receives.
The gross energy control algolithm is adopted in vertical control of said position, speed, attitude control module; Its ultimate principle is the flutter lift of frequency shift generation and the size of thrust through the steering order control flapping wing aircraft that sends to electron speed regulator; Thereby the rate of change of control gross energy; Through sending to the steering order control elevating rudder drift angle change of flight device pitch attitude of elevating rudder steering wheel, the partition coefficient of control gross energy between kinetic energy and potential energy.This kind control algolithm is unified control with height and flying speed, has strengthened robustness, has realized fuzzy control.
Said data recordin module will fly to control the various parameters (data, locus, air speed, ground velocity, the attitude that comprise sensor unit) of navigational system and collect arrangement, store the FLASH storer of said storage unit then into.
Said data recordin module also sends to the data chainning link with above-mentioned parameter through communication controller, lets data link be sent to land station in real time, thereby lets the ground staff can monitor the aircraft flight state.
Said manual mode module is chosen as in flight control system accepts the Ground Control instruction that the remote control processing module is sent under the state of manual mode, issue said servo decoupling zero/mixture control after resolving.
The invention has the beneficial effects as follows:
The first, realized the flight control of mini-sized flap wings aircraft having realized autonomous flight.Adopting sensor and anti-tampering means such as digital circuit and mimic channel spatial separation to guarantee that measured value is accurate based on the MEMS technology.On the basis of traditional filtering method, use the complete Nonlinear Kalman filtering algorithm of total state to carry out attitude algorithm, improved the robustness of attitude algorithm.Aspect control algolithm, adopted the vertical control rate design based on gross energy, realized fuzzy control, can effectively resist the external disturbance in the flight course, kept flight stability, control effectively.
The second, satisfy of the strict demand of mini-sized flap wings aircraft for aspects such as space, weight, Electro Magnetic Compatibilities.Device selection aspect adopts the Power PC processor of integrated peripheral interface, avoids in the circuit PCB design peripheral interface and line specific placement thereof, and sensor unit is selected the original paper based on the MEMS technology as far as possible, helps to reduce the size and the weight of pcb board.The Electro Magnetic Compatibility aspect; On traditional multilayer board basis, increase stratum and bus plane again; Bus and clock line are distributed in separation layer inside, shorten the length of bus and clock line, improve Electro Magnetic Compatibility; Make fly to control navigational system can be under the complex electromagnetic environment of the inner finite space of mini-sized flap wings aircraft operate as normal, the operate as normal of other airborne equipments such as interfering data link, miniature image sensor not simultaneously.
Description of drawings
Accompanying drawing 1 is a hardware structure diagram of the present invention.
Accompanying drawing 2 is for flying to control the navigational computer theory diagram.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is done further explain.
The technical solution adopted for the present invention to solve the technical problems comprises and flies to control navigational computer, sensor unit, storage unit, GPS receiver and gps antenna, data communication interface, all is integrated in 1 pcb board.
The said MPC565 Power PC processor that flies to control navigational computer employing MOTOROLA company.The integrated abundant peripheral interface of this type processor can reduce to fly to control the weight and the size of navigational system; Possess the floating-point operation ability, computational accuracy is high, can improve attitude algorithm level and control output accuracy.
Said sensor unit comprises three axis accelerometer, three-axis gyroscope, three axis magnetometer, static pressure transducer and dynamic pressure transducer.Wherein accelerometer, gyroscope, magnetometer adopt the MEMS sensor, the gyro of ADI band temperature compensation sensor, and range ability is ± 150 °/s, weight is 2.1g only; ADI accelerometer, range ability are ± 5g that weight is 1.1g only, has little, the lightweight characteristics of size.All sensors can carry out adaptive calibration, has shortened use setup time, has improved usability.Each sensor signal is sent into by the SPI interface of data communication interface through AD conversion back and is flown to control navigational computer.
Said GPS receiver receives gps signal through said gps antenna, gps signal is sent into through the UART interface of data communication interface to fly to control navigational computer and be configured again.
Said storage unit comprises SRAM storer and FLASH storer; High-speed bus through data communication interface flies to control navigational computer and links to each other with said; All programs and the data that fly to control navigational computer are all moved in the SRAM storer, can guarantee arithmetic speed and access speed.
Saidly fly to control the PWM output interface of navigational computer through data communication interface, thereby accomplish the execution of control to topworkies such as steering wheel, electron speed regulator output steering order.
Saidly fly to control navigational computer and link to each other with data link, through this interface take remote measurement data and guidance command communication through UART interface special-purpose in the data communication interface.
Said data communication interface also comprises 1 serial ports, and the user is through this serial ports and saidly fly to control the navigational computer message exchange, and tradable information comprises air route, controlled variable and flying quality.
Said sensor unit uses independently high precision reference power source power supply, between the mimic channel of sensor unit and the digital circuit of flight control computer physical isolation is arranged, and prevents signal cross-talk, can obtain the measuring-signal of high precision, low noise.
The PCB design aspect of above-mentioned hardware is considered electromagnetic compatibility problem, on the multiple-plate basis of tradition, increases stratum and bus plane once more, and bus and clock line are distributed in separation layer inside, shortens the length of bus and clock line, improves Electro Magnetic Compatibility.
The inner function module that flies to control navigational computer comprises communication control module, remote control processing module, air route generation module; Position, speed, attitude control module; Inertial navigation and attitude algorithm module, manual mode module, sensor acquisition processing module and data recording, telemetry module.
Each sensor signal that said sensor processing module is sent into the SPI interface is carried out filtering; After removing useless noise; Send into said inertial navigation and attitude algorithm module; This module adopts the complete non-linear kalman filtering algorithm of total state to carry out attitude algorithm, obtains aircraft space position, air speed, ground velocity and 3 attitude angle, sends into position, speed, attitude control module.
Said communication control module obtains surface instruction through the special-purpose UART interface of data communication interface from data link, sends into said remote control processing module.The remote control processing module is responsible for telecommunication management and command analysis, is the external interface of total system.The remote control processing module receives and resolves surface instruction, and the instruction after resolving is sent to said air route generation module according to command type, when offline mode is automatic mode, also instruction is sent to said position, speed, attitude control module; When offline mode is manual mode, also instruction is sent to said manual mode module.
Said air route generation module generates position, the speed that aircraft should fly in real time after receiving air route information, this information sends to said position, speed, attitude control module.
The actual position information that the target position information that said position, speed, attitude control module provide air route generation module and remote control processing module and pressure altimeter, GPS receiver or inertial navigation computing module obtain compares, and produces position control instruction and speed command.Position, speed, attitude control module are divided into positioner, air speed controller, attitude controller and servo decoupling zero/mixture control.Positioner produces attitude control and air speed steering order according to the information of air route generation module, makes the flight path of the reality of aircraft meet predetermined air route.After the air speed controller receives the instruction of positioner; Go out instruction to the attitude controller sending and receiving; Attitude controller should instruction and the information of inertial navigation and attitude algorithm module relatively, form final steering order and send it to said servo decoupling zero/mixture control.Said servo decoupling zero/mixture control is assigned to corresponding topworks with the steering order that receives.
The gross energy control algolithm is adopted in vertical control of said position, speed, attitude control module; Its ultimate principle is the flutter lift of frequency shift generation and the size of thrust through the steering order control flapping wing aircraft that sends to electron speed regulator; Thereby the rate of change of control gross energy; Through sending to the steering order control elevating rudder drift angle change of flight device pitch attitude of elevating rudder steering wheel, the partition coefficient of control gross energy between kinetic energy and potential energy.For height and the speed of controlling aircraft, vertically control loop formation speed rate of change, vertical speed rate and normal acceleration instruction, these instructions finally influence power control loop and elevating rudder loop.
The aileron control loop of said position, speed, attitude control module is divided into outer shroud and interior ring.Outer shroud utilizes the instruction of pitch angle deviation calculation lift-over speed.In ring calculate the aileron instruction according to lift-over speed instruction and measured value thereof, comprise two of the time integrals of lift-over rate prediction, lift-over rate variance, final instruction is confirmed through two ailerons of suing for peace and carry out are spacing.
The elevating rudder control loop of said position, speed, attitude control module is used for controlling normal acceleration, also is divided into outer shroud and interior ring.Outer shroud adopts height and air speed loop to confirm the normal acceleration instruction.Interior ring comprises the prediction term according to the acceleration instruction, the integral of acceleration bias and the damping in pitch item of increase short period damping, and final steering order is the result of three summations.
The control law in the power control loop of said position, speed, attitude control module is made up of two parts, i.e. the feedback quantity of power premeasuring and deviation integration.The power predicted value is that instruction is tried to achieve according to speed, and feedback term then is based on the poor of demand power and real power.It should be noted that the integration saturation limit need deduct the prediction amount of power control, so that integral overcomes the prediction deviation of amount of power control.
Said data recordin module will fly to control the various parameters (data, locus, air speed, ground velocity, the attitude that comprise sensor unit) of navigational system and collect arrangement, store the FLASH storer of said storage unit then into.
Said data recordin module also sends to the data chainning link with above-mentioned parameter through communication controller, lets data link be sent to land station in real time, thereby lets the ground staff can monitor the aircraft flight state.
Said manual mode module is chosen as in flight control system accepts the Ground Control instruction that the remote control processing module is sent under the state of manual mode, issue said servo decoupling zero/mixture control after resolving.
Claims (6)
1. a mini-sized flap wings aircraft flies to control navigational system; Comprise and fly to control navigational computer, sensor unit, storage unit, GPS receiver, gps antenna and data communication interface; It is characterized in that: said sensor unit comprises three axis accelerometer, three-axis gyroscope, three axis magnetometer, static pressure transducer and dynamic pressure transducer, and each sensor signal of output is sent into by data communication interface through AD conversion back and flown to control navigational computer; Said GPS receiver receives gps signal through gps antenna, gps signal is sent into through data communication interface to fly to control navigational computer and be configured again; Said storage unit comprises SRAM storer and FLASH storer, through data communication interface with fly to control navigational computer and link to each other, all programs and the data that fly to control navigational computer are all moved in the SRAM storer; Saidly fly to control navigational computer and export steering order to steering wheel and electron speed regulator, link to each other the data that take remote measurement and guidance command communication through data communication interface with data link through data communication interface.
2. mini-sized flap wings aircraft according to claim 1 flies to control navigational system, it is characterized in that: describedly fly to control navigational computer, sensor unit, storage unit, GPS receiver, gps antenna and data communication interface and all be integrated in 1 pcb board.
3. mini-sized flap wings aircraft according to claim 2 flies to control navigational system, it is characterized in that: described pcb board increases stratum and bus plane on the multiple-plate basis of tradition, bus and clock line are distributed in separation layer inside.
4. mini-sized flap wings aircraft according to claim 1 flies to control navigational system, it is characterized in that: described accelerometer, gyroscope, magnetometer adopt the MEMS sensor.
5. mini-sized flap wings aircraft according to claim 1 flies to control navigational system; It is characterized in that: described data communication interface also comprises 1 serial ports; The user is through this serial ports and saidly fly to control the navigational computer exchange message, and exchange message comprises air route, controlled variable and flying quality.
6. mini-sized flap wings aircraft according to claim 1 flies to control navigational system, it is characterized in that: described sensor unit uses the independent current source power supply, between the mimic channel of sensor unit and the digital circuit of flight control computer physical isolation is arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011204622354U CN202433775U (en) | 2011-11-20 | 2011-11-20 | Flight control navigation system for miniature ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011204622354U CN202433775U (en) | 2011-11-20 | 2011-11-20 | Flight control navigation system for miniature ornithopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202433775U true CN202433775U (en) | 2012-09-12 |
Family
ID=46783211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011204622354U Expired - Fee Related CN202433775U (en) | 2011-11-20 | 2011-11-20 | Flight control navigation system for miniature ornithopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202433775U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102426457A (en) * | 2011-11-20 | 2012-04-25 | 西北工业大学 | Flight control navigation system of miniature flapping-wing flying vehicle |
| CN107203220A (en) * | 2017-05-27 | 2017-09-26 | 上海交通大学 | Flapping wing aircraft flight control method and system |
-
2011
- 2011-11-20 CN CN2011204622354U patent/CN202433775U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102426457A (en) * | 2011-11-20 | 2012-04-25 | 西北工业大学 | Flight control navigation system of miniature flapping-wing flying vehicle |
| CN107203220A (en) * | 2017-05-27 | 2017-09-26 | 上海交通大学 | Flapping wing aircraft flight control method and system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102426457B (en) | Flight control navigation system of miniature flapping-wing flying vehicle | |
| CN110262553B (en) | Fixed-wing unmanned aerial vehicle formation flying method based on position information | |
| CN102830622B (en) | Auto-disturbance-rejection automatic flight control method for four-rotor aircraft | |
| Iscold et al. | Development of a hand-launched small UAV for ground reconnaissance | |
| Santoso et al. | Hybrid PD-fuzzy and PD controllers for trajectory tracking of a quadrotor unmanned aerial vehicle: Autopilot designs and real-time flight tests | |
| CN204440169U (en) | The control system of the multi-modal autonomous flight of Miniature Unmanned Helicopter | |
| CN104656660A (en) | Control system for micro-unmanned helicopter multi-mode autonomous flight and method thereof | |
| CN104898429A (en) | Tri-rotor attitude control method based on auto-disturbance rejection controller | |
| TWI558617B (en) | Unmanned flight vehicle autonomous flight computer system and control method | |
| CN104765272A (en) | Four-rotor aircraft control method based on PID neural network (PIDNN) control | |
| CN102508493A (en) | Flight control method for small unmanned aerial vehicle | |
| CN101515178A (en) | Master-slave burden type redundancy automatic unmanned aircraft pilot based on CAN bus | |
| CN102968123A (en) | Automatic pilot of unmanned aerial vehicle | |
| Wenfu et al. | Flight control of a large-scale flapping-wing flying robotic bird: System development and flight experiment | |
| CN202939490U (en) | Autopilot for unmanned aerial vehicles | |
| CN105468010A (en) | Multi-degree of freedom inertial sensor four-axis unmanned aerial vehicle autonomous navigation flight controller | |
| CN107908194A (en) | A kind of hand-thrown type unmanned flight system | |
| Ramos et al. | Autonomous flight experiment with a robotic unmanned airship | |
| CN202433775U (en) | Flight control navigation system for miniature ornithopter | |
| Smit | Autonomous landing of a fixed-wing unmanned aerial vehicle using differential GPS | |
| Osborne | Transitions between hover and level flight for a tailsitter UAV | |
| Roos | Autonomous take-off and landing of a fixed wing unmanned aerial vehicle | |
| Zhou et al. | Control of a Tail-Sitter VTOL UAV Based on Recurrent Neural Networks | |
| Yin et al. | Research on Attitude Control System Design and Flight Experiments of Small-scale Unmanned Aerial Vehicle | |
| Verberne | Development of Robust Control Laws for Disturbance Rejection in Rotorcraft UAVs |
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: 20120912 Termination date: 20141120 |
|
| EXPY | Termination of patent right or utility model |