CN109739142A - Embedded flight controller - Google Patents
Embedded flight controller Download PDFInfo
- Publication number
- CN109739142A CN109739142A CN201910041904.1A CN201910041904A CN109739142A CN 109739142 A CN109739142 A CN 109739142A CN 201910041904 A CN201910041904 A CN 201910041904A CN 109739142 A CN109739142 A CN 109739142A
- Authority
- CN
- China
- Prior art keywords
- unit
- pattern configurations
- interface
- plate
- flight controller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004891 communication Methods 0.000 claims abstract description 22
- 238000013500 data storage Methods 0.000 claims abstract description 5
- 238000012545 processing Methods 0.000 claims abstract description 5
- 238000005259 measurement Methods 0.000 claims description 20
- 238000006243 chemical reaction Methods 0.000 claims description 9
- 230000003750 conditioning effect Effects 0.000 claims description 8
- 238000012544 monitoring process Methods 0.000 claims description 7
- 238000001514 detection method Methods 0.000 claims description 4
- 239000000758 substrate Substances 0.000 claims description 2
- 230000003281 allosteric effect Effects 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 28
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 241001269238 Data Species 0.000 description 1
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 241001465382 Physalis alkekengi Species 0.000 description 1
- 210000004556 brain Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004377 microelectronic Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000013598 vector Substances 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Landscapes
- Navigation (AREA)
Abstract
The invention discloses a kind of embedded flight controllers, include core control panel, pattern configurations plate and internal bus；The core control panel carries out data processing and control, is provided with processor, data storage, remote-control-signal reception unit, control output driving unit and internal bus interface；The pattern configurations plate is used for linkage function module, and functional module is connected with core control panel, is provided with communication unit, control output interface, system power supply unit and internal bus interface；The internal bus is for connecting core control panel and pattern configurations plate.The present invention can easily realize that the automatic flight of various configuration (containing new configuration/allosteric type) aircraft controls, and controller has many advantages, such as that feature-rich, scalability is strong, simple for structure, cost savings, easy to control.
Description
Technical field
The present invention relates to a kind of flight controller, especially a kind of embedded flight controller.
Background technique
Aircraft is a kind of robot that can be flown in the sky, as controlled device its own stability by its structure spy
The influence for external disturbance of seeking peace.It is to be difficult stabilized flight to destination, especially rotor to fly when aircraft is not equipped with controller
Row device.Aircraft itself unstability will lead to fatal crass, therefore need to design a kind of control device that can play stabilization,
Realize that aircraft is completed the purpose of flight by mission requirements.Aircraft passes through VTOL, hovering, low-latitude flying, and high speed
The task-cycles such as cruise, are completed quickly and effectively aerial mission, make aircraft in troops' rapid deployment, landing operations and civilian
Specific effect is played in the disaster relief/equal fields of speedily carrying out rescue work, it is necessary to need to design a set of control device with automatic control ability,
The design invention achievement of the control device has broad application prospects.
In recent years, the research and development of unmanned vehicle has obtained the attention of people.With going out for all kinds of consumer level products
Existing, unmanned plane has come into the visual field of people gradually, enters in daily life.Unmanned vehicle has been widely used
In numerous areas, including video display industry, scientific research, accident relief, power-line patrolling etc..Brain as unmanned vehicle controls
Maincenter, embedded flight controller device are used to ensure the core apparatus of stability of aircraft and maneuverability, fly to aircraft
The raising of row quality and flight efficiency, the enhancing of aircraft safety, the burden mitigation of ground control personnel, entire aerial mission
It is fast and effective completion have the function of not replacing.
Embedded flight controller is for executing specified independent control function and there is complex way to handle data capability
Control system processing component.By a series of microelectronic components such as microprocessor chip, timer, sequencer or controller
The electronic equipment or device of composition complete the various automatic processing tasks such as monitoring, control together with external Aerial Electronic Equipment.With
Technology development, vehicle flight control system design increasingly tend to miniaturization, intelligence, it is desirable that the function of flight controller device
Consume it is low, small in size, light-weight, it is flexible and convenient with the interface mode of Aerial Electronic Equipment.And existing embedded flight controller exists
Function fix, connect defect inconvenient, that scalability is not strong with external equipment, it is difficult to adapt to engineer application and technology development
It needs to upgrade in time.
Summary of the invention
Goal of the invention: the technical problem to be solved in the present invention is to provide a kind of embedded flight controllers, solve tradition
The defect that embedded controller function is fixed, scalability is not strong can upgrade in time according to the needs that engineer application and technology develop
Flight controller device can conveniently be connect with equipment such as a variety of external sensors, control driving actuators, preferably full
The foot needs of all kinds of vehicle flight control system controller hardware device configurations.
Technical solution: embedded flight controller of the present invention includes core control panel, pattern configurations plate and interior
Portion's bus；
The core control panel carries out data processing and control, is provided with processor, data storage, remote signal and connects
Receive unit, control output driving unit and internal bus interface；
The pattern configurations plate is used for linkage function module, and functional module is connected with core control panel, is arranged
There are communication unit, control output interface, system power supply unit and internal bus interface；
The internal bus is for connecting core control panel and pattern configurations plate.
Further, the processor unit of the core control panel uses STM32F405ZGT6 microprocessor, the remote control
Device signal receiving unit includes the input of SBUS universal serial bus and multidiameter delay input channel, and the control output driving unit is simultaneously
Drive multiple executing agencies.
Further, the communication unit on the pattern configurations plate is serial data communication unit, includes asynchronous serial
Communication bus, spi bus, I2C bus and CAN bus it is one or more, the asynchronous serial communication bus has TTL electricity
Straight cut and RS232 electric level interface realize serial digital signal level conversion via MAX3232CSE chip.
Further, the pattern configurations plate is additionally provided with inertial navigation measuring unit, and inertial navigation measuring unit is
Built-in or external, built-in inertial navigation measuring unit is MPU9250 Inertial Measurement Unit, and external inertial navigation measures single
Member is connect by the communication unit with pattern configurations plate.
Further, the pattern configurations plate is additionally provided with GPS navigation measuring unit, and GPS navigation measuring unit is interior
It sets or external, built-in GPS navigation measuring unit uses OEM615GPS functional module, and external GPS navigation measuring unit is logical
The communication unit is crossed to connect with pattern configurations plate.
Further, the pattern configurations plate is additionally provided with rotation speed measurement unit, and the rotation speed measurement unit includes 4
A tachometric survey channel provides precise rotation measurement for speed closed loop control.
Further, the pattern configurations plate is additionally provided with voltage monitoring signal conditioning unit, voltage monitoring signal tune
Reason unit is 4 tunnels, is improved because detecting system power supply and electrical source of power, and believe external required measurement analog voltage
It number is improved.
Further, the system power supply unit includes 15V/5V power conversion module and the conversion of 5V/3.3V power supply
Module.
Further, the internal bus interface is plate and connector for substrate, and side is male connector, and the other side is can be with public affairs
The base of head make-up, connector is realized and is connected between plate and plate by 2 pair of 80 core row busbar needle, 1 pair of 60 core row's busbar needle, internal total
100 tunnel useful signal Shuo Wei of line.
Further, the interface of the communication unit is MicroUSB type interface, and the control output interface is 2.54 millis
The curved row's needle interface of rice.
The utility model has the advantages that the present invention uses core control panel and pattern configurations plate combination, difference can be easily realized
The automatic flight control of configuration (containing new configuration/allosteric type) aircraft, controller is with feature-rich, scalability is strong, structure is simple
Clean, cost savings, it is easy to control the advantages that, either be applied to small-sized unmanned aircraft, or be applied to other various configurations
Aircraft, only need to its pattern configurations plate carry out option and installment, can conveniently and efficiently from a variety of different external sensors, control
System driving actuator etc. equipment connection realizes that aircraft flies control automatically, can also facilitate and form multi-network multiprocessing
Device flight control system meets Large Scale Space Vehicle or the configuration of cluster vehicle flight control system hardware device using needs.
Detailed description of the invention
Fig. 1 is apparatus of the present invention configuration schematic diagram；
Fig. 2 is core control panel frontal design figure；
Fig. 3 is core control panel reverse side design drawing；
Fig. 4 is pattern configurations plate frontal design figure；
Fig. 5 is pattern configurations plate reverse side design drawing；
Fig. 6 is internal bus classification design figure.
Specific embodiment
As shown in Figure 1, this embedded flight controller device is by core control panel 1, pattern configurations plate 2, external function
Module and relevant interface are constituted.When device is applied to aircraft, core control panel 1 and pattern configurations plate 2 are combined together, mode
Configuration plate 2 can install built-in inertia functional module 62 and built-in GPS functional module 3, can also install external function module, than
Such as with external Aerial Electronic Equipment remote controler 100, external inertia functional module 200, external GPS functional module 201, external communication function
Module 202 is connected by the interface of the present apparatus.So application, which can facilitate, realizes that aircraft flies control automatically, solves currently
Market product flight controller function fixes, the problem that scalability is not strong, efficiently solves the control of various configuration aircraft flight
The dissimilarity problem of system control performance index request.
The frontal design block diagram of core control panel 1 is as shown in Fig. 2, designing on core control panel 1 has microprocessor 10, remote control
Receiver 11, control output driving unit 20, SD data storage 24, internal bus interface 21,22,23, program write-in interface
17,18, multiple groups status indicator lamp 12,13,19, buzzer 16, signal shaping conditioning circuit 14.Microprocessor 10 uses
STM32F405ZGT6 microprocessor, has the function of floating-point operation, can quickly handle a large amount of sensing datas, high-performance flight control
System rule operation, while there is Peripheral Interface abundant, interface is carried out with peripheral hardware input-output equipment by the way that internal bus is convenient.Shape
State indicator light is designed as 4 groups of tri coloured lanterns, 12,6 groups of monochromatic burner 13 and 1 group system heart-throb lamps 19.Writer design has two kinds of modes,
One is JTAG mode 17, another kind is serial ports mode 18.Remote controller signal receiving unit 11 is designed as SBUS bus and 1-9 is distant
Control device signal receiving channel, compatible remote control receiver nearly all on the market.
It is illustrated in figure 3 the reverse side design frame chart of core control panel 1, internal bus interface is laid out in this face, with 3 interfaces
21,22,23 100 internal signal wires are arranged, it is ensured that structure, signal transmission are reliable errorless.Output driving unit 20 is controlled to design
There are 16 tunnels to control output driving channel, output signal is improved with 74HC14 chip, it is ensured that control the reliability of output.SD
Data storage 24 is with most effective response speed and microprocessor minimum system interface.
As shown in Figure 4 and Figure 5, the design of pattern configurations plate 2 has built-in navigation attitude Inertial Measurement Unit, built-in GPS functional module
Unit, can external appearance Inertial Measurement Unit interface, can external GPS functional module elements interface, rotation speed measurement unit, voltage monitoring
Signal conditioning unit, system and power power supply unit, different types of serial data communication interface, control output driving interface.
Internal bus interface 31,32,33 designs 3 interfaces 21,22,23 in the front of pattern configurations plate, with core control panel reverse side
Make-up.
The built-in design of Inertial Measurement Unit 30,49 MPU9250 chip (the nine axis output containing three axis magnetic strength vectors),
MS5611 chip, external navigation attitude Inertial Measurement Unit 200 can match the avionics sensor for meeting pattern configurations plate interface requirement, and two
Sensor can obtain the higher aircraft inertia navigation information of measurement accuracy by data fusion, meet different aircraft to certainly
The high control performance requirement of dynamic flight control.Built-in GPS navigation measuring unit design 3 can use OEM615 or OEM618GPS etc.
Component, external GPS navigation measuring unit 201 can match the avionics sensor for meeting pattern configurations plate interface requirement, two sensors
The higher aircraft GPS navigation information of measurement accuracy can be obtained by data fusion, meet different aircraft to automatic flight control
The high control performance requirement of system.
The design of pattern configurations plate serial data communication unit has 6 universal asynchronous receiving-transmitting transmitters, connects via internal bus
Mouth enters the microprocessor minimum system of core control panel.Serial data communication signal on internal bus is Transistor-Transistor Logic level, each
Be designed as 2 kinds of signal level interfaces on serial data communication channel, a kind be Transistor-Transistor Logic level interface be positive connector 36 to
41,1 kinds are that the interface of RS232 level is the connector 52 to 57 of reverse side, realize that Transistor-Transistor Logic level is believed using MAX3232CSE chip 34
Conversion number between RS232 level signal, meets requirement of the different sensors to interface level.
The design of pattern configurations plate serial data communication unit has 1 road spi bus interface 42,1 road I2C bus interface 44,1 tunnel
CAN interface 47 meets requirement of the different Aerial Electronic Equipments to interface level.
Pattern configurations plate control output driving Interface design has 16 tunnels, wherein 6 tunnels layout is on 45,10 tunnel of left side of configuration plate
It is laid out on the right side 46 of configuration plate, power amplifier designs 20 on core control panel, is directly output to control by internal bus defeated
Driving interface out can meet requirement of a variety of various configuration aircraft to control output channel quantity.The design of reverser 61 meets
Different flight control systems control level demands.
The design of pattern configurations plate rotation speed measurement unit has 4 tunnel tachometric survey channels, the revolving speed to 4 motors can carry out simultaneously
Measurement, the interface 43,59 connecting with measurand design on pattern configurations plate, and signal shaping conditioning circuit 14 is designed in core
On control panel.Design has 4 tunnels to detect analog voltage conditioning circuit 35, and detection voltage external interface design, can be real in reverse side 58,60
Now to the detection of analog signal.The design of voltage monitoring signal conditioning unit has 4 tunnels, removes to system power supply and electrical source of power because of detection
Outside being improved, external required measurement analog voltage signal can also be improved.16 tunnels control output signal via defeated
Outgoing interface connector directly drives performing steering wheel.No. 5 reversers are for the requirement of flight control system difference output level.
System power supply and the design of electrical source of power power supply unit have 2 12V to 50,51 and 1 5V of 5V voltage transformation module extremely
3.3V voltage transformation module 15 meets actuator, related component to power requirement.The pattern configurations plate system power supply both may be used
It is loaded directly into 5V direct current, 12V DC electricity can also be loaded, 12V system power supply is mentioned via 12V/5V power conversion module for device
3.3V power supply is provided for working power, then via 5V/3.3V power conversion module for related device.Drive the rudder of aircraft flight
Machine/motor power power supply and system power supply are independently-powered, convert via voltage and provide power drive voltage.System power supply and power
Power supply can detect automatically.
As shown in fig. 6, designing the board to board connector 80 of 0.6 millimeter of spacing between core control panel and pattern configurations plate
For core 2 to, 60 cores 1 to being attached, 2 opposite cores transmit 1 road internal bus signal, it is ensured that plate to signal between plate transmit can
It leans on,.Connector between external equipment has a MicroUSB connector, respectively the 52 of plate positive 36 to 43 and reverse side to
60, curved row's needle 45 and 46 of 2.54 millimeters of spacing, 2.0 millimeters of spacing the interface forms such as curved row's needle 44 and 48.
Claims (10)
1. a kind of embedded flight controller, it is characterised in that: include core control panel, pattern configurations plate and internal bus；
The core control panel carries out data processing and control, is provided with processor, data storage, remote control signal receiver list
Member, control output driving unit and internal bus interface；
The pattern configurations plate is used for linkage function module, and functional module is connected with core control panel, is provided with logical
Believe unit, control output interface, system power supply unit and internal bus interface；
The internal bus is for connecting core control panel and pattern configurations plate.
2. embedded flight controller according to claim 1, it is characterised in that: the processor list of the core control panel
Member uses STM32F405ZGT6 microprocessor, and the remote controller signal receiving unit includes the input of SBUS universal serial bus and multichannel
Parallel input channels, the control output driving unit drive multiple executing agencies simultaneously.
3. embedded flight controller according to claim 1, it is characterised in that: the communication unit on the pattern configurations plate
Member be serial data communication unit, include asynchronous serial communication bus, spi bus, I2C bus and CAN bus one kind or
A variety of, the asynchronous serial communication bus has Transistor-Transistor Logic level interface and RS232 electric level interface, via MAX3232CSE chip
Realize serial digital signal level conversion.
4. embedded flight controller according to claim 1, it is characterised in that: the pattern configurations plate is additionally provided with
Inertial navigation measuring unit, to be built-in or external, built-in inertial navigation measuring unit is inertial navigation measuring unit
MPU9250 Inertial Measurement Unit, external inertial navigation measuring unit are connect by the communication unit with pattern configurations plate.
5. embedded flight controller according to claim 1, it is characterised in that: the pattern configurations plate is additionally provided with
GPS navigation measuring unit, GPS navigation measuring unit are that built-in or external, built-in GPS navigation measuring unit uses
OEM615GPS functional module, external GPS navigation measuring unit are connect by the communication unit with pattern configurations plate.
6. embedded flight controller according to claim 1, it is characterised in that: the pattern configurations plate is additionally provided with
Rotation speed measurement unit, the rotation speed measurement unit include 4 tachometric survey channels, provide precise rotation for speed closed loop control
Measurement.
7. embedded flight controller according to claim 1, it is characterised in that: the pattern configurations plate is additionally provided with
Voltage monitoring signal conditioning unit, voltage monitoring signal conditioning unit are 4 tunnels, to system power supply and electrical source of power because of detection needs
It is improved, and external required measurement analog voltage signal is improved.
8. embedded flight controller according to claim 1, it is characterised in that: the system power supply unit includes
15V/5V power conversion module and 5V/3.3V power conversion module.
9. embedded flight controller according to claim 1, it is characterised in that: the internal bus interface be plate with
Connector for substrate, side are male connector, and the other side is that can arrange busbar needle, 1 pair by 2 pair of 80 core with the base of male connector make-up, connector
60 cores row's busbar needle is realized to be connected between plate and plate, 100 tunnel useful signal Shuo Wei of internal bus.
10. embedded flight controller according to any one of claims 1 to 9, it is characterised in that: the communication unit
Interface is MicroUSB type interface, and the control output interface is 2.54 millimeters of curved row's needle interfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910041904.1A CN109739142A (en) | 2019-01-15 | 2019-01-15 | Embedded flight controller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910041904.1A CN109739142A (en) | 2019-01-15 | 2019-01-15 | Embedded flight controller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109739142A true CN109739142A (en) | 2019-05-10 |
Family
ID=66365128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910041904.1A Pending CN109739142A (en) | 2019-01-15 | 2019-01-15 | Embedded flight controller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109739142A (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN102033546A (en) * | 2010-11-09 | 2011-04-27 | 上海交通大学 | Low-altitude airship flight control system and flight control method thereof |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| CN102419586A (en) * | 2011-12-16 | 2012-04-18 | 新时代集团国防科技研究中心 | Method for monitoring condition of unmanned aerial vehicle based on serial bus |
| CN102520656A (en) * | 2011-12-16 | 2012-06-27 | 新时代集团国防科技研究中心 | Realization method for intelligent bus servo motor of unmanned aircraft |
| CN103034229A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Integrated type testing device for flying control |
| CN203084553U (en) * | 2013-01-17 | 2013-07-24 | 中国人民解放军武汉军械士官学校 | Integrated unmanned aerial vehicle avionics system device |
| CN204582551U (en) * | 2015-05-14 | 2015-08-26 | 康义 | The relay of aircraft remote control system |
| CN104977912A (en) * | 2015-07-02 | 2015-10-14 | 深圳市蜂鸟智航科技有限公司 | Ethernet-exchange-bus-based unmanned plane flight control system and method |
| CN205384514U (en) * | 2016-03-08 | 2016-07-13 | 王伟韵 | Survey many rotor unmanned aerial vehicle flight control |
| CN106054925A (en) * | 2016-07-13 | 2016-10-26 | 国网福建省电力有限公司 | Multi-matching unmanned plane autonomous obstacle avoiding system |
| CN108873792A (en) * | 2018-09-03 | 2018-11-23 | 中国科学院长春光学精密机械与物理研究所 | A kind of technical grade system for flight control computer based on ARM and DSP |
| US20180367211A1 (en) * | 2017-06-20 | 2018-12-20 | Honeywell International Inc. | Standalone flight management system interfacing devices, systems and methods |
| CN209327827U (en) * | 2019-01-15 | 2019-08-30 | 南京航空航天大学 | Embedded flight controller |
-
2019
- 2019-01-15 CN CN201910041904.1A patent/CN109739142A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN102033546A (en) * | 2010-11-09 | 2011-04-27 | 上海交通大学 | Low-altitude airship flight control system and flight control method thereof |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| CN102419586A (en) * | 2011-12-16 | 2012-04-18 | 新时代集团国防科技研究中心 | Method for monitoring condition of unmanned aerial vehicle based on serial bus |
| CN102520656A (en) * | 2011-12-16 | 2012-06-27 | 新时代集团国防科技研究中心 | Realization method for intelligent bus servo motor of unmanned aircraft |
| CN103034229A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Integrated type testing device for flying control |
| CN203084553U (en) * | 2013-01-17 | 2013-07-24 | 中国人民解放军武汉军械士官学校 | Integrated unmanned aerial vehicle avionics system device |
| CN204582551U (en) * | 2015-05-14 | 2015-08-26 | 康义 | The relay of aircraft remote control system |
| CN104977912A (en) * | 2015-07-02 | 2015-10-14 | 深圳市蜂鸟智航科技有限公司 | Ethernet-exchange-bus-based unmanned plane flight control system and method |
| CN205384514U (en) * | 2016-03-08 | 2016-07-13 | 王伟韵 | Survey many rotor unmanned aerial vehicle flight control |
| CN106054925A (en) * | 2016-07-13 | 2016-10-26 | 国网福建省电力有限公司 | Multi-matching unmanned plane autonomous obstacle avoiding system |
| US20180367211A1 (en) * | 2017-06-20 | 2018-12-20 | Honeywell International Inc. | Standalone flight management system interfacing devices, systems and methods |
| CN108873792A (en) * | 2018-09-03 | 2018-11-23 | 中国科学院长春光学精密机械与物理研究所 | A kind of technical grade system for flight control computer based on ARM and DSP |
| CN209327827U (en) * | 2019-01-15 | 2019-08-30 | 南京航空航天大学 | Embedded flight controller |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101515178B (en) | Master-slave burden type redundancy automatic unmanned aircraft pilot based on CAN bus | |
| CN205563189U (en) | Unmanned aerial vehicle flight controller | |
| CN102955456A (en) | Bus communication based small unmanned aerial vehicle control system | |
| CN202166892U (en) | Minitype unmanned aircraft control system based on bus communication | |
| CN105786755A (en) | High-integration satellite-borne computer system for nano-satellite | |
| CN108873792A (en) | A kind of technical grade system for flight control computer based on ARM and DSP | |
| CN113392064A (en) | Miniature integrated avionics core processor | |
| CN109634184A (en) | A kind of load sharing formula double-core flight-control computer | |
| CN209327827U (en) | Embedded flight controller | |
| CN118483947A (en) | Control module of mobile device and mobile device | |
| CN209230638U (en) | A kind of navigation control system based on multi-core processor | |
| CN109739142A (en) | Embedded flight controller | |
| CN202765287U (en) | Unmanned aerial vehicle onboard flight control system | |
| CN108313269A (en) | The landing gear mechanism and unmanned plane of unmanned plane | |
| CN207037474U (en) | A kind of system for flight control computer | |
| CN108594715A (en) | Unmanned plane master control borad | |
| CN215181985U (en) | Miniature integrated avionics core processor | |
| CN217384268U (en) | Aircraft attitude measuring device based on inertia measuring unit | |
| CN206541198U (en) | The combined navigation device of vision guided navigation and inertial navigation based on aircraft | |
| CN216748542U (en) | Unmanned aerial vehicle self-driving instrument system | |
| CN105573196B (en) | A kind of flight controller based on hard and soft integrated printed board | |
| CN108583888A (en) | A kind of large-scale unmanned plane device of inside small unmanned plane containing there are four | |
| CN114726672A (en) | High-speed aircraft ground station redundancy man-machine interaction system and method | |
| CN208110346U (en) | Unmanned plane master control borad | |
| CN207473827U (en) | Without aileron unmanned helicopter control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |