CN105373136A - Integrated electronic system based on VPX architecture - Google Patents
Integrated electronic system based on VPX architecture Download PDFInfo
- Publication number
- CN105373136A CN105373136A CN201410571248.3A CN201410571248A CN105373136A CN 105373136 A CN105373136 A CN 105373136A CN 201410571248 A CN201410571248 A CN 201410571248A CN 105373136 A CN105373136 A CN 105373136A
- Authority
- CN
- China
- Prior art keywords
- data
- unit
- electronic system
- integrated electronic
- interface
- 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
Landscapes
- Radio Relay Systems (AREA)
Abstract
The invention discloses an integrated electronic system based on a VPX architecture. The system comprises an interface unit, an integration data unit, a master control unit, a flight control unit and a power supply unit, wherein the interface unit is used to send a received control instruction to the master control unit, carry out format conversion on received inertial navigation data and satellite data and send the converted data to the integration data unit; the integration data unit is used to classify and store the received data after the format conversion and send the data to other units of the integrated electronic system; the master control unit is used to control a corresponding unit of the integrated electronic system according to the received control instruction; the flight control unit is used to control flight of an aircraft based on the inertial navigation data and satellite data; the power supply unit is used to provide power for the integrated electronic system. The integrated electronic system provided in the invention possesses a high system bandwidth, a serial bus rate is high, there are many kinds of external interfaces of the interface unit and a high automation degree is possessed.
Description
Technical field
The present invention relates to technical field of aerospace, be specifically related to the Integrated Electronic System based on VPX framework that a kind of flight for the aircraft such as aircraft, guided missile controls.
Background technology
Composite elctronics technical is that the functions such as integrated data chain, flight control, satellite navigation, remote sensing, communication, electronic countermeasure and enemy and we's identification are in the integrated technology of one.Composite elctronics technical is based on the communication technology and electronic technology, adopt the method for systems engineering, to detect in platform physical structure space, communicate, navigate, identify, electronic warfare, task management, function and the corresponding electronic equipment such as flight and firepower control, an organic whole is synthesized by the technology groups such as bus and software, i.e. Integrated Electronic System, to realize the shared resources of system resource, the raising of overall efficiency, expects the maximization realizing system operational performance, availability and life cycle simultaneously.
In above-mentioned Integrated Electronic System, in the occasion needing the board of different control functions interconnected, due to the reason such as incompatible, there will be system bus resource lacks, and communication speed reduces, the interconnected problem such as too complicated.
Summary of the invention
In view of this, for overcoming at least one shortcoming above-mentioned, and providing following at least one advantage, the invention discloses a kind of Integrated Electronic System based on VPX framework.
For solving the problems of the technologies described above, the present invention by the following technical solutions: a kind of Integrated Electronic System based on VPX framework, comprises and is arranged in VPX back panel respectively by bus:
Interface unit, for the steering order received is sent to main control unit, carries out format conversion by the inertial guidance data received, satellite data, and the data after conversion are sent to integrated data unit;
Described integrated data unit, stores for carrying out classification to the data after the format conversion received, and described data is sent to other unit of described Integrated Electronic System;
Described main control unit, for controlling according to the unit of received steering order to the correspondence of described Integrated Electronic System;
Flight control units, for based on described inertial guidance data and described satellite data, controls the flight of aircraft; And
Power supply unit, for providing electric power for described Integrated Electronic System.
In the Integrated Electronic System based on VPX framework as above, described interface unit comprises:
Control interface, for receiving the steering order from airborne equipment, ground control station or repeater satellite, and is sent to described main control unit by described steering order; And
Data-interface, for receiving satellite data from airborne equipment, ground control station or repeater satellite and inertial guidance data, carries out format conversion to the data received, and the described data after conversion are sent to described integrated data unit,
Wherein, described satellite data comprise in the velocity information of described aircraft, positional information and image information one or more, described inertial guidance data comprises the angle of pitch of described aircraft, roll angle, course angle, three axis angular rates, one or more highly, in speed and acceleration.
In the Integrated Electronic System based on VPX framework as above, described data-interface comprise in RS-422, RS-485, Ethernet interface, digital format images interface, ARINC429, MIL-STD-1553B, AMBA one or more, and analog image interface, one or more in audio interface.
In the Integrated Electronic System based on VPX framework as above, described flight control units comprises:
Satellite navigation unit, for based on the described velocity information in described satellite data and described positional information, calculates the first navigational parameter of the flight for controlling described aircraft;
Inertial navigation unit, for based on described inertial guidance data, calculates the second navigational parameter of the flight for controlling described aircraft; And
Assembled unit, for based on described first navigational parameter and the second navigational parameter, draws the final navigational parameter of the flight for controlling described aircraft.
In the Integrated Electronic System based on VPX framework as above, described flight control units also for based on described final navigational parameter, controls the flight attitude of described aircraft, course, height and course line.
In the Integrated Electronic System based on VPX framework as above, also comprise: remote control remote sensing unit, remotely-sensed data for being obtained by remote sensing satellite is sent to described ground control station, and the telecommand from described ground control station is sent to described main control unit.
In the Integrated Electronic System based on VPX framework as above, described remote control remote sensing unit comprises:
Remote sensing module, for by remote sensing to remotely-sensed data carry out coded modulation process, and by process after remotely-sensed data be sent to ground control station by described repeater satellite; And
Remote control module, for receiving the telecommand that ground control station generates based on described remotely-sensed data, and is sent to described main control unit by described telecommand by described repeater satellite.
In the Integrated Electronic System based on VPX framework as above, the information monitored also for monitoring temperature and the information of voltage of the unit of described Integrated Electronic System, and is sent to airborne equipment or ground control station by described main control unit.
By adopting technique scheme, of the present invention reached beneficial effect is: because Integrated Electronic System provided by the invention adopts VPX system architecture, thus have higher system bandwidth, multiple bus can be adopted to carry out interconnected between module, universal serial bus speed is high; And the external interface kind of interface unit is more, and compatible military aviation bus and civil aviation bus, possess higher automaticity.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, below the accompanying drawing used required in describing the embodiment of the present invention is briefly described, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to the content of the embodiment of the present invention and these accompanying drawings.
The structural representation of the Integrated Electronic System based on VPX framework that Fig. 1 provides for one embodiment of the invention;
The structural representation of the Integrated Electronic System based on VPX framework that Fig. 2 provides for another embodiment of the present invention;
The structural representation of the remote control remote sensing unit that Fig. 3 provides for one embodiment of the invention.
Embodiment
The technical matters solved for making the present invention, the technical scheme of employing and the technique effect that reaches are clearly, be described in further detail below in conjunction with the technical scheme of accompanying drawing to the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those skilled in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
Technical scheme of the present invention is further illustrated by embodiment below in conjunction with accompanying drawing.
VPX is a kind of system architecture improved based on VME (VersaModuleEurocard), and its total bandwidth can reach 100GB/s.VPX bus, while some characteristic of reservation VME bus, also introduces high-speed serial bus and carrys out alternative parallel bus.Interconnected between VPX module can be realized, as its travelling speed of RapidIO can reach 3.125Gb/s by high-speed serial bus such as SerialRapidIO, PCIExpressFibreChannel, InfiniBand, Hypertransport, 10GB Ethernets.Adopt serial interconnection framework, while significantly increasing bandwidth, its total bandwidth can reach 100GB/s, and under the harsh environment such as vibrations, high temperature and humidity can be applied to.The present inventor improve Integrated Electronic System process in, innovatively by VPX framework applications to Integrated Electronic System, propose a kind of Integrated Electronic System based on VPX framework.
embodiment 1
As shown in Figure 1, the structural representation of the Integrated Electronic System based on VPX framework provided for one embodiment of the invention; This Integrated Electronic System 100 comprises: interface unit 11, integrated data unit 12, main control unit 13, flight control units and power supply unit 16, and said units is all connected with VPX back panel 17 by data bus or control bus.
Wherein, interface unit 11 is for being sent to main control unit 13 by the steering order received, also for the inertial guidance data received and satellite data being converted to the standard data format meeting Integrated Electronic System 100 internal agreement, the digitizing of such as simulating signal, and the data after conversion are sent to integrated data unit 12 by VPX back panel 17.
Specifically, interface unit 11 comprises control interface 111 and data-interface 112, wherein control interface 111 is for receiving the steering order (such as, the course angle steering order of aircraft) from airborne equipment or ground control station or repeater satellite etc., and is transferred to main control unit 14.In the present embodiment, control interface 111 is mainly numeric class interface.Data-interface 112, for receiving inertial guidance data and satellite data, carries out Data Format Transform to the data received, and the data after conversion are sent to integrated data unit 12.In the present embodiment, data-interface 112 comprises digital data interface and simulated data interface two class, and digital data interface mainly comprises the bus interface such as RS-422, RS-485, Ethernet, digital format images interface and ARINC429, MIL-STD-1553B, AMBA; Simulated data interface mainly comprises analog image interface, audio interface etc.Wherein ARINC429 bus interface is civil aviation bus interface, MIL-STD-1553B and AMBA bus interface is military aviation bus interface.Above-mentioned satellite data comprise in the velocity information of aircraft, positional information and image information one or more, above-mentioned inertial guidance data comprises the angle of pitch of aircraft, roll angle, course angle, three axis angular rates, one or more highly, in speed and acceleration.
Further, interface unit 11 also for realizing the functions such as EMI (ElectricMagneticInterference, the electromagnetic interference (EMI)) filtering of power interface, and exports filtered electric power to power supply unit 17 by VPX back panel 18.
Integrated data unit 12, for the data received from interface unit 11 being stored, if the data received are the data of encryption, stores after to decrypt data again.And preferably, integrated data unit 12 also stores for carrying out classification to data under the control of main control unit 14, then the data of storage is sent to unit respectively according to the actual needs of unit.Further, the data that integrated data unit 12 stores also comprise the shared data of data that system cannot process in time and system.Wherein, the classification storage mode of data has multiple, such as, can store according to the difference of agreement, also can store according to the difference of purposes.
Main control unit 13 for controlling the configuration of the aggregate resource of Integrated Electronic System 100 according to the steering order received, and controls the operation of each unit.Preferably, main control unit 13 is also monitored for the information such as temperature, voltage of each unit to Integrated Electronic System 100, and by interface unit 11 by the information reporting that monitors to the aircraft such as ground control station or airborne equipment control gear.
Flight control units is used for the inertial guidance data that receives based on interface unit 11 and satellite data, controls the flight of aircraft.In the present embodiment, flight control units can comprise satellite navigation unit 14 and inertial navigation unit 15.
Specifically, satellite navigation unit 14 for being received velocity information and the positional information of satellite by interface unit 11, and goes out the first navigational parameter of the flight for controlling the aircrafts such as aircraft based on this velocity information and positional information calculation.Inertial navigation unit 15 for receiving inertial guidance data by interface unit 11, and calculates the second navigational parameter of the flight for controlling the aircrafts such as aircraft based on inertial guidance data.Bad due to gps signal under many circumstances, only the first navigational parameter of going out of satellite-based velocity information and positional information calculation is accurate not, and the second navigational parameter only drawn based on inertial guidance data is also accurate not.Therefore, preferably, in satellite navigation unit 14 or inertial navigation unit 15, also assembled unit is provided with, for the first navigational parameter and the second navigational parameter are carried out the navigational parameter combining the flight being finally used for controlling aircraft.
Particularly, the angle of pitch that the gyropanel that inertial guidance data comprises aircraft exports and roll angle, the information such as the course angle that heading sensor exports and the tri-axis angular rate that angular rate gyroscope exports, also comprise elevation information and the velocity information of air data sensor instrument's output; The speed of satellite and positional information comprise longitude, latitude, the information such as height and flight-path angle of GPS inertial navigation array output.The final navigational parameter that flight control units calculates based on assembled unit, flies by aircraft the relevant rudder face controlling inner looping operating aircraft, realizes the control in the increasing of aircraft steady and flight attitude and course; By highly stable loop operate lifting rudder, realize the stable of flying height and handle; Autonomous flight control is carried out in the air route arranged based on routeing, realizes the stable and manipulation of flight attitude and flying height in flight profile, mission profile.In a kind of possible implementation, satellite navigation unit 14 can adopt modular design proposal, such as, can comprise the hardware expanding resources such as processor module, memory module, signal acquisition module, drive control module, multi-channel serial communication module and wireless communication module.
Power supply unit 16 is interconnected by the reception power rail of VPX back panel 17 and interface unit 11, and is realized the isolation of external power source and internal electric source by insulating power supply module, provides+5V and+3.3V power rail to whole Integrated Electronic System 100.In addition, the power panel of power supply unit 16 can be provided with system management circuit in addition, for information such as monitoring voltage, electric current and temperature, run to ensure that the safety of system is normal.
embodiment 2
As shown in Figure 2, the structural representation of the Integrated Electronic System based on VPX framework provided for another embodiment of the present invention; This Integrated Electronic System 200 is with the key distinction of the Integrated Electronic System 100 in embodiment 1: when needing to control aircraft on the ground, this Integrated Electronic System 200 also comprises remote control remote sensing unit 18, for by remote sensing to satellite data be sent to ground control station, receive the telecommand that ground control station sends, and this telecommand is sent to main control unit 13.
As shown in Figure 3, remote control remote sensing unit 18 specifically comprises remote sensing module 181 and remote control module 182.Remote sensing module 181 by external communication link by remote sensing to satellite data carry out coded modulation process, and the data after process are sent to repeater satellite through main control unit 11, integrated data 12 and interface unit 11, the remotely-sensed data received is sent to ground control station by repeater satellite.Aerial mission packing is generated telecommand according to remotely-sensed data by ground control station, by repeater satellite, telecommand is forwarded to aircraft or guided missile, and be down-converted to intermediate-freuqncy signal by receiving antenna, send to the interface unit 11 of Integrated Electronic System 200, finally remote control module 182 is arrived through integrated data unit 12, remote control module 182 parses telecommand, and is sent to main control unit 14 and performs.Main control unit 13 receives the telecommand of remote control remote sensing unit 16, according to the object controlled, this telecommand is sent to corresponding unit.
All or part of content in the technical scheme that above embodiment provides can be realized by software programming, and its software program is stored in the storage medium that can read, storage medium such as: the hard disk in computing machine, CD or floppy disk.
Note, above are only preferred embodiment of the present invention and institute's application technology principle.Skilled person in the art will appreciate that and the invention is not restricted to specific embodiment described here, various obvious change can be carried out for a person skilled in the art, readjust and substitute and can not protection scope of the present invention be departed from.Therefore, although be described in further detail invention has been by above embodiment, the present invention is not limited only to above embodiment, when not departing from the present invention's design, can also comprise other Equivalent embodiments more, and scope of the present invention is determined by appended right.
Claims (8)
1. based on an Integrated Electronic System for VPX framework, it is characterized in that, comprise and be arranged in VPX back panel respectively by bus:
Interface unit, for the steering order received is sent to main control unit, carries out format conversion by the inertial guidance data received, satellite data, and the data after conversion are sent to integrated data unit;
Described integrated data unit, stores for carrying out classification to the data after the format conversion received, and described data is sent to other unit of described Integrated Electronic System;
Described main control unit, for controlling according to the unit of received steering order to the correspondence of described Integrated Electronic System;
Flight control units, for based on described inertial guidance data and described satellite data, controls the flight of aircraft; And
Power supply unit, for providing electric power for described Integrated Electronic System.
2., as claimed in claim 1 based on the Integrated Electronic System of VPX framework, it is characterized in that, described interface unit comprises:
Control interface, for receiving the steering order from airborne equipment, ground control station or repeater satellite, and is sent to described main control unit by described steering order; And
Data-interface, for receiving satellite data from airborne equipment, ground control station or repeater satellite and inertial guidance data, carries out format conversion to the data received, and the described data after conversion are sent to described integrated data unit,
Wherein, described satellite data comprise in the velocity information of described aircraft, positional information and image information one or more, described inertial guidance data comprises the angle of pitch of described aircraft, roll angle, course angle, three axis angular rates, one or more highly, in speed and acceleration.
3. as claimed in claim 2 based on the Integrated Electronic System of VPX framework, it is characterized in that, described data-interface comprise in RS-422, RS-485, Ethernet interface, digital format images interface, ARINC429, MIL-STD-1553B, AMBA one or more, and analog image interface, one or more in audio interface.
4., as claimed in claim 2 based on the Integrated Electronic System of VPX framework, it is characterized in that, described flight control units comprises:
Satellite navigation unit, for based on the described velocity information in described satellite data and described positional information, calculates the first navigational parameter of the flight for controlling described aircraft;
Inertial navigation unit, for based on described inertial guidance data, calculates the second navigational parameter of the flight for controlling described aircraft; And
Assembled unit, for based on described first navigational parameter and the second navigational parameter, draws the final navigational parameter of the flight for controlling described aircraft.
5., as claimed in claim 4 based on the Integrated Electronic System of VPX framework, it is characterized in that, described flight control units also for based on described final navigational parameter, controls the flight attitude of described aircraft, course, height and course line.
6., as claimed in claim 1 based on the Integrated Electronic System of VPX framework, it is characterized in that, also comprise:
Remote control remote sensing unit, the remotely-sensed data for being obtained by remote sensing satellite is sent to described ground control station, and the telecommand from described ground control station is sent to described main control unit.
7., as claimed in claim 6 based on the Integrated Electronic System of VPX framework, it is characterized in that, described remote control remote sensing unit comprises:
Remote sensing module, for by remote sensing to data carry out coded modulation process, and by process after remotely-sensed data be sent to ground control station by described repeater satellite; And
Remote control module, for receiving the telecommand that ground control station generates based on described remotely-sensed data, and is sent to described main control unit by described telecommand by described repeater satellite.
8. as claimed in claim 1 based on the Integrated Electronic System of VPX framework, it is characterized in that, the information monitored also for monitoring temperature and the information of voltage of the unit of described Integrated Electronic System, and is sent to airborne equipment or ground control station by described main control unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410571248.3A CN105373136A (en) | 2014-10-22 | 2014-10-22 | Integrated electronic system based on VPX architecture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410571248.3A CN105373136A (en) | 2014-10-22 | 2014-10-22 | Integrated electronic system based on VPX architecture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105373136A true CN105373136A (en) | 2016-03-02 |
Family
ID=55375416
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410571248.3A Pending CN105373136A (en) | 2014-10-22 | 2014-10-22 | Integrated electronic system based on VPX architecture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105373136A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031867A (en) * | 2016-10-18 | 2017-08-11 | 中国运载火箭技术研究院 | A kind of configurable Integrated Electronic System for implementing space tasks contexture by self |
| CN107919903A (en) * | 2017-11-21 | 2018-04-17 | 中国电子科技集团公司第五十四研究所 | A kind of multi-mode satellite communication apparatus based on VPX frameworks |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
| CN109407573A (en) * | 2018-09-17 | 2019-03-01 | 西北工业大学 | A kind of CAN bus based moonlet Integrated Electronic System and method for allocating tasks |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2627492A1 (en) * | 2005-11-18 | 2007-05-24 | Airbus Deutschland Gmbh | Modular avionics system of an aircraft |
| US20080027592A1 (en) * | 2006-07-07 | 2008-01-31 | Airbus France | Avionic system and architecture with integrated power management |
| CN101604162A (en) * | 2009-07-02 | 2009-12-16 | 北京航空航天大学 | A kind of comprehensively modularized core processing system for civil avionics |
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN102201027A (en) * | 2010-03-26 | 2011-09-28 | 国营东方仪器厂 | Navigation/flight control computer for unmanned aerial vehicle |
| CN202414169U (en) * | 2011-12-08 | 2012-09-05 | 西安航空电子科技有限公司 | Configurable universal comprehensive avionics system |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
| CN102495635B (en) * | 2011-12-08 | 2013-06-05 | 西安航空电子科技有限公司 | Comprehensive avionics system for small-sized general aircraft |
-
2014
- 2014-10-22 CN CN201410571248.3A patent/CN105373136A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2627492A1 (en) * | 2005-11-18 | 2007-05-24 | Airbus Deutschland Gmbh | Modular avionics system of an aircraft |
| US20080027592A1 (en) * | 2006-07-07 | 2008-01-31 | Airbus France | Avionic system and architecture with integrated power management |
| CN101604162A (en) * | 2009-07-02 | 2009-12-16 | 北京航空航天大学 | A kind of comprehensively modularized core processing system for civil avionics |
| CN102201027A (en) * | 2010-03-26 | 2011-09-28 | 国营东方仪器厂 | Navigation/flight control computer for unmanned aerial vehicle |
| CN101913427A (en) * | 2010-08-04 | 2010-12-15 | 北京航空航天大学 | Avionics system suitable for multi-purpose unmanned aircraft |
| CN202414169U (en) * | 2011-12-08 | 2012-09-05 | 西安航空电子科技有限公司 | Configurable universal comprehensive avionics system |
| CN102495635B (en) * | 2011-12-08 | 2013-06-05 | 西安航空电子科技有限公司 | Comprehensive avionics system for small-sized general aircraft |
| CN103064392A (en) * | 2012-12-28 | 2013-04-24 | 中国人民解放军国防科学技术大学 | Satellite borne integrated electronic system |
Non-Patent Citations (1)
| Title |
|---|
| R ADIGA: "Performance analysis of VPX backplane in integrated modular avionics system", 《EE TIMES》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031867A (en) * | 2016-10-18 | 2017-08-11 | 中国运载火箭技术研究院 | A kind of configurable Integrated Electronic System for implementing space tasks contexture by self |
| CN107031867B (en) * | 2016-10-18 | 2019-08-09 | 中国运载火箭技术研究院 | A kind of configurable Integrated Electronic System for implementing space tasks contexture by self |
| CN107919903A (en) * | 2017-11-21 | 2018-04-17 | 中国电子科技集团公司第五十四研究所 | A kind of multi-mode satellite communication apparatus based on VPX frameworks |
| CN109240959A (en) * | 2018-09-13 | 2019-01-18 | 垣纬多媒体卫星通信（上海）有限公司 | A kind of spaceborne Integrated Electronic System |
| CN109407573A (en) * | 2018-09-17 | 2019-03-01 | 西北工业大学 | A kind of CAN bus based moonlet Integrated Electronic System and method for allocating tasks |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Ebeid et al. | A survey on open-source flight control platforms of unmanned aerial vehicle | |
| US11340608B2 (en) | Unmanned aircraft with a modular swarm control unit | |
| EP3674657A1 (en) | Construction and update of elevation maps | |
| CN104820431A (en) | Multi-unmanned-aerial-vehicle cluster to-the-ground observation system and formation control method | |
| CN108153327B (en) | Four-rotor aircraft outdoor formation light performance system and control method | |
| CN104808675A (en) | Intelligent terminal-based somatosensory flight operation and control system and terminal equipment | |
| Dittrich et al. | Multi-sensor navigation system for an autonomous helicopter | |
| CN104115081A (en) | Wind calculation system using constant bank angle turn | |
| CN104180803A (en) | Non-similar dual-redundancy integrated navigation device applied to unmanned plane | |
| CN102955456A (en) | Bus communication based small unmanned aerial vehicle control system | |
| CN105373136A (en) | Integrated electronic system based on VPX architecture | |
| Kortunov et al. | Review and comparative analysis of mini-and micro-UAV autopilots | |
| CN104808558A (en) | Multi-task loading system applicable to special and general airplanes | |
| CN106054923A (en) | Asymmetric unmanned aerial vehicle clustering system | |
| CN105468010A (en) | Multi-degree of freedom inertial sensor four-axis unmanned aerial vehicle autonomous navigation flight controller | |
| CN106547275A (en) | A kind of new rotor class unmanned plane is automatically positioned control method | |
| Bingler et al. | Dual radio autopilot system for lightweight, swarming micro/miniature aerial vehicles | |
| Li et al. | Beyond visual line of sight UAV control for remote monitoring using directional antennas | |
| Ramos et al. | Autonomous flight experiment with a robotic unmanned airship | |
| US20240171416A1 (en) | Systems And Methods For Acquisition Of Data From Sensors | |
| Krings et al. | ULTRA-unmanned low-cost testing research aircraft | |
| Tang et al. | Platform and State Estimation Design of a Small‐Scale UAV Helicopter System | |
| US20220264007A1 (en) | Intelligent gimbal assembly and method for unmanned vehicle | |
| EP4027579B1 (en) | Spatial web of trust key initialization method for sensor platform array using directed close-field communication | |
| Grassi et al. | Application of an inspection robot composed by collaborative terrestrial and aerial modules for an operation in agriculture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160302 |