CN100458624C - Semi-independent flight control system of unmanned airship and control method thereof - Google Patents
Semi-independent flight control system of unmanned airship and control method thereof Download PDFInfo
- Publication number
- CN100458624C CN100458624C CNB2004100157930A CN200410015793A CN100458624C CN 100458624 C CN100458624 C CN 100458624C CN B2004100157930 A CNB2004100157930 A CN B2004100157930A CN 200410015793 A CN200410015793 A CN 200410015793A CN 100458624 C CN100458624 C CN 100458624C
- Authority
- CN
- China
- Prior art keywords
- chip microcomputer
- remote control
- flight
- ground
- transmission module
- 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 present invention is the flying control system and method for semi-autonomous flying of unattended aeroboat. The control system includes aeroboat borne system and ground system, the aeroboat borne system has structure comprising sensors, A/D converter, monolithic computer, analog multiplexer, executor, aeroboat borne data transmission module, remote controlled signal receiver, etc. connected together; and the ground system has PC, ground data transmission module and remote signal emitter. The aeroboat borne data transmission module and the remote controlled signal receiver in the aeroboat borne system associate with the ground data transmission module and the remote signal emitter of the ground system via RF signal. The control system can identify the mode channel signal and realize the mode switching among remote control, local remote control and autonomous flying.
Description
Technical field
The present invention relates to half independent flight control system and the control method thereof of a kind of flight control and control method thereof, particularly a kind of unmanned airship.
Background technology
Dirigible is a kind ofly to be lighter than air (Lighter Than Air, aircraft LTA), its chief component have the air bag that is full of light gas, one or several engine, gondola, empennage and the control systems etc. that produce thrust.Be with the main difference of the aircraft that overweights air: dirigible relies on the gas that is lighter than air (as hydrogen, helium or hot-air etc.) that is sealed in the air bag that whole or most lift are provided, dirigible and load thereof are supported in the air, and this lift and flying speed are irrelevant.The main difference that dirigible and other are lighter than the air aircraft is: dirigible be dynamic, can control, engine provides power for it, by handling the elevating rudder on the empennage and the pitching and the direction motion of yaw rudder control dirigible.The characteristic dimension of unmanned airship is about below the 20m, can carry certain task load, and cruising time is generally in 2h.
Compare with unmanned rotary wing aircraft with unmanned fixed-wing aircraft, unmanned airship have make that maintenance cost is low, commercial transport-big from anharmonic ratio, cruising time is long, maneuverability is strong, control is simple and safe, can realize advantage such as low-altitude low-speed flight.From the eighties in 20th century; many countries have carried out the research of unmanned airship; fundamental purpose is to be platform with it, carries out traffic monitoring, city planning, electric wire and pipeline construction and detection, mining site or archaeology place exploration and protection, enforcement, communication relaying and environment, bio-diversity, climate monitoring and research etc.In recent years, the microminiature unmanned airship has obtained increasing application, is just becoming an international research focus.
The overwhelming majority of unmanned airship adopts remote control mode, and remote control distance is generally in the horizon range.Obviously, remote control mode exists not enough, and is limited as remote control distance, and when objective was in the place (as fully stocked wood, marsh) that the beeper is difficult to arrive, unmanned airship can't fly; Beeper's labour intensity is big, and the beeper faces upward always and sees dirigible limit operation in front, especially fatigue etc. easily under some long-time flight situations.
The purpose of half autonomous/autonomous unmanned airship flight control system is partly to replace hand control, makes dirigible have certain independence.In this respect, a large amount of work has been done by the research institutions such as AURORA planning item, Centre National de la Recherche Scientifique system architecture and assay laboratory of Brazil, but its research is based on expensive sensor groups, is unfavorable for realizing commercialization.
Summary of the invention
The object of the present invention is to provide a kind of half independent flight control system and control method thereof of unmanned airship, improve the autonomous performance of unmanned airship flight, alleviate the labour intensity of teleoperator, widen the range of application of unmanned airship.
For achieving the above object, design of the present invention is: half independent flight control system of this unmanned airship comprises mobile system and ground system two parts, and wherein mobile system is made up of sensor groups (comprising position transducer and attitude sensor), single-chip microcomputer, remote control signal receiver, analog multichannel switch, actuator, airborne digital transmission module.The single-chip microcomputer signal links to each other with the actuator signal line through analog multichannel switch with the remote control signal receiver signal, and the single-chip microcomputer pin links to each other with the control end of analog multichannel switch; Single-chip microcomputer by serial communication interface and (or) mould/number conversion interface obtains the sensor groups signal; The general purpose I of single-chip microcomputer/O pin links to each other with the signal wire of the relevant control channel of remote control signal receiver; Single-chip microcomputer links to each other with digital transmission module by serial ports.Ground system comprises remote control signal transmitter, PC, ground digital transmission module; Remote control signal transmitter is operated by the beeper; The ground digital transmission module links to each other with PC by serial ports.
In order to make this control system can satisfy multiple user's request, by following some designed the control method of this system.
1. single-chip microcomputer is by discerning the receiver mode channel signal, control end by the control analog multichannel switch, control system is switched in these three kinds of patterns of manual remote control, local manual remote control and autonomous flight, thereby can realize the autonomous flight of unmanned airship, can in time switch under the remote control mode under special circumstances again, improve the security of unmanned airship.
2. single-chip microcomputer is gathered the transducing signals such as attitude, position, speed, direction of unmanned airship by interrupt routine, calculate the following controlled quentity controlled variable that requires each passage of control of current flight control model according to control algolithm after treatment, send, control the relevant rudder face of unmanned airship by the I/O mouth, thereby control the flight of dirigible through analog multichannel switch to actuator.
3. by setting in advance or in flight course, setting way point in real time, make independently by the path flight of setting.
4, make mistakes according to module data and the adverse effect brought for fear of factor, to the form of the data setting strictness that digital transmission module transmitted and verification is set, whether correctly mobile system and ground system can be distinguished easily transmit data.
According to above-mentioned design, the present invention adopts following technical proposals:
A kind of half independent flight control system of unmanned airship, comprise mobile system and ground system, the system architecture that it is characterized in that mobile system is: the output of sensor groups is connected the input port of single-chip microcomputer by serial communication interface and/or mould/number conversion interface, the output of single-chip microcomputer is connected with the analog multichannel switch input end by the I/O pin, the output terminal of analog multichannel switch connects the input end of actuator group, single-chip microcomputer links to each other with airborne digital transmission module by serial ports, and by module channels connection remote control signal receiver, the delivery outlet of remote control signal receiver connects analog switch; Ground system has PC to connect a ground digital transmission module by serial ports, and a remote control signal transmitter is arranged; The airborne digital transmission module of mobile system and remote control signal receiver are got in touch by the ground digital transmission module and the remote signal machine of radiofrequency signal and ground system respectively;
Above-mentioned single chip circuit is made of a C8051F020 type single-chip microcomputer, double 5 * 2 standard socket, a 24M type crystal oscillator, 11 electric capacity and a resistance.
Above-mentioned sensor groups is made of a MAX3232 type serial communication interface chip, four electric capacity, a HMR3000 type digital compass and a RGM3000 type GPS receiver module.
Above-mentioned sensor groups, single-chip microcomputer and analog multichannel switch are made on the printed circuit board, be connected airborne digital transmission module by cable respectively by the data radio station connector lug on the printed circuit board (PCB), remote control signal receiver connector lug and actuator group connector lug, remote control signal receiver and actuator group.
Above-mentioned analog multichannel switch is a MAX333 cake core.
Above-mentioned data radio station connector lug adopts the accurate socket of single four pin marks, remote control signal receiver connector lug to adopt the accurate socket of single three pin marks, and the actuator group connector lug adopts the accurate socket of single three pin marks.
Above-mentioned sensor groups includes position transducer and attitude sensor, and actuator group is a steering wheel.
A kind of control method that is used for half independent flight control system of the described unmanned airship of claim 1 is characterized in that controlled step is:
A. in mobile system, the attitude of sensor groups perception unmanned airship and the signal of position are sent to the single-chip microcomputer processing;
B. in ground system, there is the beeper to handle remote control signal transmitter and sends remote signal, comprise the offline mode switching signal;
C. single-chip microcomputer is passed to the radiofrequency signal that the data-switching of airborne digital transmission module becomes in the ground digital transmission module receiver loading system, delivers to the ground PC and handles;
D. the ground digital transmission module receives the flight control instruction of PC, and is converted into radiofrequency signal and sends;
E. airborne digital transmission module receives the flight control instruction and is sent to the single-chip microcomputer processing, comprises the switching offline mode;
F. the single-chip microcomputer in the mobile system is by controlling the I/O pin level that is connected with the control end of analog multichannel switch, select one between the two in the remote signal of remote control signal receiver reception ground remote control signal transmitter and the flight control signal of single-chip microcomputer transmission, the actuator group steering wheel is controlled, realized attitude control and navigation.
In above-mentioned control method, by of the state recognition of airborne single-chip microcomputer to remote control signal receiver pattern passage, change the control end level of analog multichannel switch related channel program, make corresponding actuator group signal in remote control signal receiver signal or single-chip microcomputer signal, select one, thereby flight control system is switched between manual remote control flight, the flight of local manual remote control and three kinds of patterns of automatic remote control flight.
In above-mentioned autonomous flight pattern, by in single-chip microcomputer, setting in advance the flight way point, or in flight course, set the flight way point in real time, unmanned airship is flown by way point.
The present invention compared with prior art, have following conspicuous outstanding feature and remarkable special advantage: in the control system of the present invention's design, single-chip microcomputer is discerned remote-control receiver pattern channel signal, and telechirics can be switched in manual remote control, local manual remote control and three kinds of patterns of autonomous flight; Can make independently and fly by setting in advance or in flight course, setting way point in real time, carry out default task by setting path; Ground can send the instruction unmanned airship by remote control signal transmitter, and behaviour's short side just; Can obtain the various flying qualities of unmanned airship by the ground digital transmission module, be convenient to real time remote control.The present invention has improved the autonomous performance of dirigible, has alleviated beeper's labour intensity, can widen the range of application of unmanned airship simultaneously.
Description of drawings
Fig. 1 is the system architecture diagram of one embodiment of the invention
Fig. 2 is Fig. 1 example system structural representation
Fig. 3 is the circuit theory diagrams of printed circuit board (PCB) among Fig. 2
Fig. 4 is the principle schematic of single-pole double-throw (SPDT) analog switch
Fig. 5 is the program flow diagram of single-chip microcomputer in Fig. 1 example
Fig. 6 is an offline mode changeover program process flow diagram in Fig. 1 example
Fig. 7 is the control block diagram in Fig. 1 example
Fig. 8 is the format chart that digital transmission module transmits data in Fig. 1 example
Embodiment
A preferred embodiment of the present invention is as detailed below:
Referring to Fig. 1 and Fig. 2, half independent flight control system of this unmanned airship, comprise mobile system 2 and ground system 1, the system architecture of mobile system 2 is: the output of sensor groups 3 is connected the input port of single-chip microcomputer 4 by serial communication interface and/or mould/number conversion interface, the output of single-chip microcomputer 4 is connected with analog multichannel switch 5 input ends by the I/O pin, the output terminal of analog multichannel switch 5 connects the input end of actuator group 6, single-chip microcomputer 4 links to each other with airborne digital transmission module 7 by serial ports, and by module channels connection remote control signal receiver 8, the delivery outlet of remote control signal receiver 8 connects analog switch 5; Ground system 1 has PC 11 to connect a ground digital transmission module 9 by serial ports, and a remote control signal transmitter 10 is arranged; The airborne digital transmission module 7 of mobile system 2 and remote control signal receiver 8 are got in touch by the ground digital transmission module 9 and the remote signal machine 10 of radiofrequency signal and ground system 1 respectively.Above-mentioned sensor groups 3, single-chip microcomputer 4 and analog multichannel switch 5 are made on the printed circuit board 12, be connected airborne digital transmission module 7 by cable respectively by the data radio station connector lug 14 on the printed circuit board (PCB) 12, remote control signal receiver connector lug 15 and actuator group connector lug 13, remote control signal receiver 8 and actuator group 6.Sensor groups 3 includes position transducer and attitude sensor, position transducer adopts the RGM3000 type GPS receiver of RoyalTek company, attitude sensor is the HMR3000 digital compass of HoneyWell company, these two sensors are all communicated by letter with single-chip microcomputer 4 by serial ports, in addition, because the serial ports of data radio station and digital compass is the RS232 level, so need utilize the serial interface chip to be converted into single-chip microcomputer 4 acceptable Transistor-Transistor Logic levels, adopted in this example MAX3232 as under the interface core of sensor to realize this function; The C8051F020 type single-chip microcomputer that single-chip microcomputer 4 is produced for Cygnal company; The Max333 type element that analog multichannel switch 5 is made for MAXIUM company; The R149DP type 9 passage receivers that remote control signal receiver 8 is produced for Futaba company; The Futaba S9204 type steering wheel that actuator 6 is produced for Futaba company.The T9CAP type transmitter that remote control signal transmitter 10 is produced for Futaba company in the ground system 1, ground PC 11 can be general portable laptop. Digital transmission module 7,9 in ground system 1 and the mobile system 2 is the TDX-230 type duplex data radio station that prosperous company of Taida produces, and all links to each other with single-chip microcomputer 4 or PC 11 by serial ports.In order to improve the integrated level of system, in this example sensor groups and interface 3 circuit thereof, one-chip computer module 4, analog multichannel switch 5 etc. are integrated in the printed circuit board (PCB) 12, and on this circuit board, reserved connector lug 14 with the serial ports of airborne data radio station, reserved with remote control signal receiver 8 second and third, the connector lug 15 of four, six, eight channel signal interfaces, reserved interface 13 with four steering wheels 6.
Referring to Fig. 4, the each several part of above-mentioned printed circuit board (PCB) 12 circuit is respectively:
One-chip computer module 4 contains: the C8051F020 type single-chip microcomputer that U2-Cygnal company produces; The Y1-24M crystal oscillator; C14 and C15-27pF electric capacity; C1 ~ C9-0.1uF electric capacity; Double 5 * 2 standard socket of HDR1-, Single Chip Microcomputer (SCM) program programming JTAG socket.
Remote control signal receiver joint 8 contains: the accurate socket of single three pin marks of CON1 ~ CON5-, be connected to passage 2, passage 3, passage 4, passage 6, the passage 8 of receiver respectively, and CON5 is connected with single-chip microcomputer P3.4 pin.
Steering wheel connector lug 13 contains: the accurate socket of single three pin marks of CON7 ~ CON10-is connected to unmanned airship elevating rudder steering wheel, Left Hand Engine air door steering wheel, yaw rudder steering wheel, right engine air door steering wheel respectively.
Sensor groups and interface circuit 3 thereof contain: U3-serial communication interface chip MAX3232; U4-GPS receiver module RGM3000; U5-digital compass HMR3000; C10 ~ C13-1.0uF tantalum electric capacity.
Data radio station connector lug 14 contains: the accurate socket of single four pin marks of CON6-.
Fig. 2 is the synoptic diagram that the single-pole double-throw (SPDT) pattern is intended switch.When control end is low level, common port with often close the end conducting; Otherwise when control end is high level, common port with often close the end conducting.The Max333 type element of the MAXIUM company manufacturing of adopting in the present embodiment has four road so independently analog switches, remote control signal receiver second and third, four, six passages elevating rudder, Left Hand Engine air door rudder, yaw rudder, the right engine air door rudder of corresponding dirigible (respectively) are connected with the Chang Heduan of Max333 respectively, its Chang Kaiduan, control end are communicated with the pin of corresponding single-chip microcomputer respectively, and common port is communicated with the actuator signal line.So by changing the level of control end, single-chip microcomputer can be controlled the source of actuator signal.
Each road of table 1 analog switch connects situation
| Multi-way switch | The 1 the tunnel | The 2 the tunnel | The 3 the tunnel | The 4 the tunnel |
| Chang Heduan | Remote control |
Remote control |
Remote control |
Remote control |
| Chang Kaiduan | Single-chip microcomputer P0.5 | Single-chip microcomputer P0.6 | Single-chip microcomputer P0.7 | Single-chip microcomputer P1.0 |
| Control end | Single-chip microcomputer P2.0 | Single-chip microcomputer P2.1 | Single-chip microcomputer P2.2 | Single-chip microcomputer P2.3 |
| Common port | Unmanned airship elevating rudder steering wheel | Unmanned airship Left Hand Engine air door steering wheel | Unmanned airship yaw rudder steering wheel | The right engine air door of unmanned airship steering wheel |
The control method of half independent flight control system of this unmanned airship is as described below: the controlled step of this control method is:
A. in mobile system 2, the attitude of sensor groups 3 perception unmanned airships and the signal of position are sent to the single-chip microcomputer processing;
B. in ground system, there is the beeper to handle remote control signal transmitter 10 and sends remote signal, comprise the offline mode switching signal;
C. single-chip microcomputer 4 is passed to the radiofrequency signal that the data-switching of airborne digital transmission module 7 becomes in the ground digital transmission module 9 receiver loading systems, delivers to ground PC 11 and handles;
D. ground digital transmission module 9 is accepted the flight control instruction of PC 11, and is converted into radiofrequency signal and sends;
E. airborne digital transmission module 7 is accepted the flight control instruction and is sent to single-chip microcomputer 4 processing, comprises the switching offline mode;
F. the analog multichannel switch 5 in the mobile system 2 is accepted the remote signal of ground remote control signal transmitter 10 and single-chip microcomputer 4 sends the flight control signals at remote control signal receiver 8, and actuator group steering wheel 6 is controlled, and realizes attitude control and navigation.
In the above-mentioned control method, state recognition by 4 pairs of remote control signal receiver 8 pattern passages of airborne single-chip microcomputer, the control end level of improvement analog multichannel switch 5 related channel programs, make corresponding actuator group 6 signals in remote control signal receiver 8 signals or single-chip microcomputer 4 signals, select one, thereby flight control system is switched between manual remote control flight, the flight of local manual remote control and three kinds of patterns of automatic remote control flight.
In the above-mentioned autonomous flight pattern, by in single-chip microcomputer, setting in advance the flight way point, or in flight course, set the flight way point in real time, unmanned airship is flown by way point.
Fig. 5 provides the program flow diagram of the airborne single-chip microcomputer of this unmanned airship flight control system.After the program initialization,, carry out in the cycle control then by the flight way point of unmanned airship being set with man-machine interactively.In cycle control, utilize the interrupt routine of single-chip microcomputer 4 to handle GPS and the signal statement of digital compass 3 and the steering order of importing into through serial ports that ground PC 11 is uploaded, if statement receives and disposes, then write corresponding identification.In a circulation, at first judge the offline mode of unmanned airship; Inquire about the sign whether Interrupt Process is finished then, be designated 1, then this sensing data is sent to ground by certain form, then with corresponding identification clear 0 if certain sensor signal disposes; PC 11 steering orders in ground are used in the control algolithm with sensing data after receiving and handling, and control algolithm is by current flight state and dbjective state, calculate the required controlled quentity controlled variable of each steering wheel 6, send to multi-way switch 5.
It in the frame of broken lines of Fig. 6 offline mode changeover program process flow diagram.The P3.4 pin is communicated with the passage 8 of remote control signal receiver 8 in the present embodiment, because the signal of all passages all is width modulation (PWM) signals, therefore single-chip microcomputer 4 can be known the offline mode that the beeper sets by the high level time t of PWM ripple in the timer/counter calculating one-period.In an embodiment, set when 700＜t≤1200, show that the operator wishes that unmanned airship is in the remote control distributor pattern, at this moment, single-chip microcomputer 4 control P2.0, P2.1, P2.2, P2.3 are that the level of control end of four passages of analog switch 5 is low, make each road often close end and common port conducting, promptly the input signal of all actuators 6 is the signal of receiver 8, thus remote-controlled all passages that are lighter than the air aircraft of beeper.When 1200＜t≤1800, show that the operator wishes that unmanned airship is in local manual remote control offline mode, at this moment, Single-chip Controlling P2.0, P2.1, P2.3 are changed to high level, P2.2 is changed to low level, thereby the yaw rudder that the beeper can the remotely pilotless dirigible, other passage are then by single-chip microcomputer 4 controls.When 1800＜t or t≤700, show that the operator wishes that unmanned airship is in the autonomous flight pattern, at this moment, single-chip microcomputer 4 control P2.0, P2.1, P2.2, P2.3 are that the level of control end of four passages of analog switch 5 is height, make normal beginning of each road and common port conducting, promptly all steering wheels 6 are by single-chip microcomputer 4 controls.Like this, the beeper, generally speaking, is provided with passage 8 and is third gear switch to realize the switching between the offline mode by operating walk way 8.
Fig. 7 is the control block diagram of each passage.The control basic process of each passage is: the desired value of controlled quentity controlled variable is set, and this desired value and sensor 3 measured values compare and obtain error e, by algorithm calculate controlled quentity controlled variable to steering wheel 6, thereby the motion of control unmanned airship, so circulation.In unmanned airship the amount of required control have speed, highly, three kinds in course, respectively by engine air door steering wheel, elevating rudder steering wheel, yaw rudder steering wheel are controlled.Because the characteristic of dirigible, the gondola that quality is bigger generally are located at the utricule bottom, so needn't control the roll passage; Its lift of dirigible mainly is aerostatic buoyancy, and is irrelevant with speed, so there is not the problem of stall in dirigible, therefore needn't consider the coupled relation between each passage in control, thus speed, highly, the three kinds of amounts in course can control separately, thereby the simplification control algolithm; Adopt and realize conveniently, control reliable pid control algorithm.Particularly, speed is controlled by adjusting engine air door steering wheel, and the ground velocity that is provided by GPS is represented the speed of dirigible, if ground velocity has gap with the setting flying speed, then, calculate the adjustment amount of air door steering wheel, realize speed control thereby constantly revise air door by control algolithm.Height is controlled by adjusting the lifting steering wheel, and the height that is provided by GPS compares with the flying height of setting, calculates the adjustment amount of elevating rudder steering wheel by control algolithm, realizes highly controlling thereby constantly adjust.The course is controlled by adjusting the yaw rudder steering wheel, and the first deflection of ship and the direction desired value that are provided by compass compare, and calculate the adjustment amount of yaw rudder steering wheel by control algolithm, realize direction control thereby constantly adjust; Wherein the direction desired value draws by Current GPS position and next way point GPS position calculation.
Fig. 8 transmits the form of data for digital transmission module.Wherein numerical value of Chuan Songing and title thereof are variable parts, and check code HH is the XOR result of each character of these two parts and 0.In this way, can guarantee that mobile system and ground system can discern correct or wrong data, the adverse effect that causes to avoid digital transmission module to be interfered easily.
This control system and control method are used for 12 meters half Autonomous Control of filling the helium dirigible of length of Shanghai arrow micro-electromechanical technology company limited development, and be respond well.
Claims (8)
1. half independent flight control system of a unmanned airship, comprise mobile system (2) and ground system (1), the system architecture that it is characterized in that mobile system (2) is: the output of sensor groups (3) is connected the input port of single-chip microcomputer (4) by serial communication interface and/or mould/number conversion interface, the output of single-chip microcomputer (4) is connected with analog multichannel switch (5) input end by the I/O pin, the output terminal of analog multichannel switch (5) connects the input end of actuator group (6), single-chip microcomputer (4) links to each other with airborne digital transmission module (7) by serial ports, and by module channels connection remote control signal receiver (8), the delivery outlet of remote control signal receiver (8) connects analog switch (5); Ground system (1) has PC (11) to connect a ground digital transmission module (9) by serial ports, and a remote control signal transmitter (10) is arranged; The airborne digital transmission module (7) of mobile system (2) and remote control signal receiver (8) are got in touch by the ground digital transmission module (9) and the remote signal machine (10) of radiofrequency signal and ground system (1) respectively; Described single-chip microcomputer (4) circuit is made of a C8051F020 type single-chip microcomputer (U2), double 5 * 2 standard socket (HDR1), a 24M type crystal oscillator (Y1), 11 electric capacity (C14, C15, C1-C9) and a resistance (R1); Sensor groups (3) is made of a MAX3232 type serial communication interface chip (U3), four electric capacity (C10-C13), a HMR3000 type digital compass (U5) and a RGM3000 type GPS receiver module (U4).
2. half independent flight control system of unmanned airship according to claim 1, it is characterized in that sensor groups (3), single-chip microcomputer (4) and analog multichannel switch (5) are made on the printed circuit board (12), be connected airborne digital transmission module (7) by cable respectively by the data radio station connector lug (14) on the printed circuit board (PCB) (12), remote control signal receiver connector lug (15) and actuator group connector lug (13), remote control signal receiver (8) and actuator group (6).
3. half independent flight control system of unmanned airship according to claim 1 and 2 is characterized in that analog multichannel switch (5) is a MAX333 cake core (U1).
4. half independent flight control system of unmanned airship according to claim 2, it is characterized in that data radio station connector lug (14) adopts the accurate sockets of single four pin marks (CON6), remote control signal receiver connector lug (15) to adopt the accurate sockets of single three pin marks (CON1-CON5), actuator group connector lug (13) adopts the accurate sockets of single three pin marks (CON7-CON10).
5. half independent flight control system of unmanned airship according to claim 1 is characterized in that sensor groups (3) includes position transducer and attitude sensor, and actuator group (6) is a steering wheel.
6. control method that is used for half independent flight control system of the described unmanned airship of claim 1 is characterized in that controlled step is:
A. in mobile system (2), the attitude of sensor groups (3) perception unmanned airship and the signal of position are sent to the single-chip microcomputer processing;
B. in ground system, handle remote control signal transmitter (10) by the beeper and send remote signal, comprise the offline mode switching signal;
C. single-chip microcomputer (4) is passed to the radiofrequency signal that the data-switching of airborne digital transmission module (7) becomes in ground digital transmission module (9) the receiver loading system, delivers to ground PC (11) and handles;
D. ground digital transmission module (9) receives the flight control instruction of PC (11), and is converted into radiofrequency signal and sends;
E. airborne digital transmission module (7) receives the flight control instruction and is sent to single-chip microcomputer (4) processing, comprises the switching offline mode;
F. the single-chip microcomputer (4) in the mobile system (2) is by controlling the I/O pin level that is connected with the control end of analog multichannel switch (5), select one between the two in the remote signal of remote control signal receiver (8) reception ground remote control signal transmitter (10) and the flight control signal of single-chip microcomputer (4) transmission, actuator group steering wheel (6) is controlled, realized attitude control and navigation.
7. the control method of half independent flight control system of unmanned airship according to claim 6, it is characterized in that by the state recognition of airborne single-chip microcomputer (4) remote control signal receiver (8) pattern passage, change the control end level of analog multichannel switch (5) related channel program, make corresponding actuator group (6) signal in remote control signal receiver (8) signal or single-chip microcomputer (4) signal, select one, thereby flight control system is switched between manual remote control flight, the flight of local manual remote control and three kinds of patterns of automatic remote control flight.
8. the control method of half independent flight control system of unmanned airship according to claim 6, it is characterized in that in the autonomous flight pattern, by in single-chip microcomputer, setting in advance the flight way point, or in flight course, set the flight way point in real time, unmanned airship is flown by way point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100157930A CN100458624C (en) | 2004-01-13 | 2004-01-13 | Semi-independent flight control system of unmanned airship and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100157930A CN100458624C (en) | 2004-01-13 | 2004-01-13 | Semi-independent flight control system of unmanned airship and control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1557676A CN1557676A (en) | 2004-12-29 |
| CN100458624C true CN100458624C (en) | 2009-02-04 |
Family
ID=34351519
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100157930A Expired - Fee Related CN100458624C (en) | 2004-01-13 | 2004-01-13 | Semi-independent flight control system of unmanned airship and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100458624C (en) |
Families Citing this family (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100495275C (en) * | 2006-11-24 | 2009-06-03 | 中国科学院沈阳自动化研究所 | Small-sized depopulated helicopter independent flight control system |
| CN102190081B (en) * | 2010-03-04 | 2013-09-04 | 南京航空航天大学 | Vision-based fixed point robust control method for airship |
| CN102033546B (en) * | 2010-11-09 | 2013-03-27 | 上海交通大学 | Low-altitude airship flight control system and flight control method thereof |
| CN102249002B (en) * | 2011-03-30 | 2013-07-03 | 杨当立 | Air sampling aircraft and air sampling method |
| CN102183941B (en) * | 2011-05-31 | 2013-11-13 | 河北科技大学 | Civil-mobile-phone-network-based ultra-long-range unmanned aerial vehicle control system |
| CN102553258B (en) * | 2012-03-02 | 2013-12-11 | 北京航空航天大学 | Switcher of model airplane remote controller |
| CN102737416A (en) * | 2012-06-08 | 2012-10-17 | 清华大学 | Data recorder of unmanned aircraft |
| CN102874399A (en) * | 2012-10-13 | 2013-01-16 | 广西电网公司南宁供电局 | Unmanned automatic-driving airship for inspecting power transmission lines |
| CN103231794B (en) * | 2013-04-17 | 2016-12-28 | 华南农业大学 | A kind of many air bags aerial work platform |
| CN104155992B (en) * | 2013-05-14 | 2017-06-27 | 中国电信股份有限公司 | Realize system on method, system and the unmanned plane machine of Navigation of Pilotless Aircraft |
| CN103838152B (en) * | 2014-02-28 | 2016-08-17 | 北京航空航天大学 | A kind of ground test device for flight control system and control method |
| CN104118555B (en) * | 2014-07-14 | 2016-08-24 | 北京大学 | A kind of unmanned control and the method for building up of flight control system thereof |
| CN104608906B (en) * | 2014-12-05 | 2017-01-18 | 中国航空工业集团公司第六三一研究所 | Stratospheric airship task control subsystem |
| CN106292695A (en) * | 2015-12-11 | 2017-01-04 | 中国特种飞行器研究所 | A kind of automatic flight control system for miniature self-service dirigible |
| CN105717919B (en) * | 2016-01-16 | 2018-09-28 | 深圳先进技术研究院 | A kind of scenic spot tour guide's salvage system based on dirigible |
| CN105607644A (en) * | 2016-01-16 | 2016-05-25 | 深圳先进技术研究院 | Non-obstacle flight system |
| CN105573339B (en) * | 2016-01-16 | 2019-01-11 | 深圳先进技术研究院 | A kind of navigation flight system based on rotor dirigible |
| CN106647801A (en) * | 2016-10-21 | 2017-05-10 | 广东容祺智能科技有限公司 | Planning system for unmanned aerial vehicle's back trip course |
| CN106828860B (en) * | 2017-03-01 | 2019-11-05 | 北京天恒长鹰科技股份有限公司 | A kind of remote control system and its control method of stratospheric airship |
| CN107450396B (en) * | 2017-08-16 | 2019-10-11 | 大连海事大学 | A kind of autonomous navigation of unmanned boat and remote control navigation switching control module |
| CN108032985A (en) * | 2017-12-05 | 2018-05-15 | 哈尔滨工程大学 | Kite balloon airship system based on the comprehensive monitoring of marine desired target area |
| CN109144075A (en) * | 2018-10-29 | 2019-01-04 | 长沙理工大学 | A kind of control system and control method of unmanned boat |
| CN110653832A (en) * | 2019-09-29 | 2020-01-07 | 河海大学常州校区 | Man-machine cooperation football robot decision-making subsystem and working method thereof |
| CN111198575A (en) * | 2020-02-27 | 2020-05-26 | 西北工业大学 | Unmanned aerial vehicle flight controller |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5716032A (en) * | 1996-04-22 | 1998-02-10 | United States Of America As Represented By The Secretary Of The Army | Unmanned aerial vehicle automatic landing system |
| CN2274602Y (en) * | 1995-10-05 | 1998-02-18 | 王嘉謇 | Remote controlling hot air airship |
| US5904724A (en) * | 1996-01-19 | 1999-05-18 | Margolin; Jed | Method and apparatus for remotely piloting an aircraft |
| CN1358650A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Remote control system for axle-shared double-rotary wing pilotless helicopter |
| CN2532511Y (en) * | 2001-07-26 | 2003-01-22 | 北京超翼技术研究所有限公司 | Real-time natural-imitated monitor system |
| US20030025034A1 (en) * | 2001-07-06 | 2003-02-06 | Yutaka Akahori | Airship system |
-
2004
- 2004-01-13 CN CNB2004100157930A patent/CN100458624C/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2274602Y (en) * | 1995-10-05 | 1998-02-18 | 王嘉謇 | Remote controlling hot air airship |
| US5904724A (en) * | 1996-01-19 | 1999-05-18 | Margolin; Jed | Method and apparatus for remotely piloting an aircraft |
| US5716032A (en) * | 1996-04-22 | 1998-02-10 | United States Of America As Represented By The Secretary Of The Army | Unmanned aerial vehicle automatic landing system |
| US20030025034A1 (en) * | 2001-07-06 | 2003-02-06 | Yutaka Akahori | Airship system |
| CN2532511Y (en) * | 2001-07-26 | 2003-01-22 | 北京超翼技术研究所有限公司 | Real-time natural-imitated monitor system |
| CN1358650A (en) * | 2002-01-29 | 2002-07-17 | 北京航空航天大学 | Remote control system for axle-shared double-rotary wing pilotless helicopter |
Non-Patent Citations (6)
| Title |
|---|
| 基于C8051F020单片机的某无人机飞控系统硬件平台的设计与开发. 潘慕绚，张天宏，黄金泉.测控技术，第22卷第1期. 2003 |
| 基于C8051F020单片机的某无人机飞控系统硬件平台的设计与开发. 潘慕绚，张天宏，黄金泉.测控技术，第22卷第1期. 2003 * |
| 小型无人机飞行控制器的硬件设计. 刘歌群.计算机测量与控制，第11卷第2期. 2003 |
| 小型无人机飞行控制器的硬件设计. 刘歌群.计算机测量与控制，第11卷第2期. 2003 * |
| 平流层通讯平台及其运行过程中的控制. 方存光，王伟.控制工程，第10卷第增刊期. 2003 |
| 平流层通讯平台及其运行过程中的控制. 方存光，王伟.控制工程，第10卷第增刊期. 2003 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1557676A (en) | 2004-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100458624C (en) | Semi-independent flight control system of unmanned airship and control method thereof | |
| CN203433367U (en) | Over-the-horizon wireless remote control system of small unmanned aerial vehicle | |
| CN100587640C (en) | Double-mode ground control system for coaxial dual-rotor unmanned helicopter | |
| CN202230330U (en) | Physical simulation experimental platform for civil fixed-wing unmanned aerial vehicle | |
| CN104808675B (en) | Body-sensing flight control system and terminal device based on intelligent terminal | |
| CN101515178B (en) | Master-slave burden type redundancy automatic unmanned aircraft pilot based on CAN bus | |
| CN105353762B (en) | The control method of six rotor wing unmanned aerial vehicles based on double remaining attitude transducers | |
| CN104656664B (en) | Vehicle-mounted many rotor unmanned helicopter approaching and landing system control systems and guiding control method | |
| CN202533754U (en) | Ground monitoring system for unmanned vehicle physical simulated test platform | |
| CN204440169U (en) | The control system of the multi-modal autonomous flight of Miniature Unmanned Helicopter | |
| CN102331783A (en) | Autopilot for indoor airship | |
| CN101561681B (en) | Anti-jamming real-time data sampling system of unmanned aerial vehicle | |
| CN103294064A (en) | Autopilot flight control system | |
| CN103019112A (en) | Control communication apparatus, controlled communication apparatus and control communication system | |
| CN108958260A (en) | A kind of agricultural machinery automated driving system based on farm implements position | |
| CN105068444B (en) | A kind of universal Unmanned Aerial Vehicle Data Link analogue system | |
| CN107145159A (en) | One kind is vehicle-mounted to be tethered at many rotor control system frameworks and control method | |
| CN101813944A (en) | Height control stabilizing system of coaxial unmanned helicopter and operation method | |
| CN102814047A (en) | Autonomous return system and control method of dual-rotor remote-controlled model helicopter | |
| CN102968123A (en) | Automatic pilot of unmanned aerial vehicle | |
| CN104062933A (en) | Unmanned helicopter flight control system and method based on DSP and FPGA | |
| CN107505949A (en) | A kind of UAV Flight Control method and system | |
| CN202939490U (en) | Autopilot for unmanned aerial vehicles | |
| CN112327668A (en) | Modeling and semi-physical simulation method and system for medium and large unmanned aerial vehicle | |
| CN107153392A (en) | One kind is vehicle-mounted to be tethered at many rotor control system frameworks and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090204 Termination date: 20120113 |