CN201698228U - Equipment supervisor in aircraft and health supervisor in equipment supervisor - Google Patents
Equipment supervisor in aircraft and health supervisor in equipment supervisor Download PDFInfo
- Publication number
- CN201698228U CN201698228U CN2010202329063U CN201020232906U CN201698228U CN 201698228 U CN201698228 U CN 201698228U CN 2010202329063 U CN2010202329063 U CN 2010202329063U CN 201020232906 U CN201020232906 U CN 201020232906U CN 201698228 U CN201698228 U CN 201698228U
- Authority
- CN
- China
- Prior art keywords
- unit
- failure
- spi bus
- health control
- integrated electronic
- 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 - Lifetime
Links
Images
Landscapes
- Testing And Monitoring For Control Systems (AREA)
Abstract
The utility model provides an equipment supervisor in aircraft and health supervisor in the equipment supervisor; wherein the health supervisor includes a failure diagnosis unit, a failure predication unit, a system reconfiguration unit as well as a failure detection and isolation unit connected with a series universal interface SPI bus; the failure diagnosis unit receives digital signals relevant to the respective running conditions of an aircraft subsystem and an integrated electronic system and emitted by the aircraft subsystem and the integrated electronic system through the SPI bus to implement failure diagnosis; the failure predication unit receives the digital signals emitted by the aircraft subsystem and the integrated electronic system through the SPI bus to implement failure predication; the system reconfiguration unit receives failure types emitted by the failure diagnosis unit and the failure predication unit to implement corresponding failure maintenance; and the failure detection and isolation unit receives a maintenance failure instruction emitted by the system reconfiguration unit to isolate the failures which are failed to be maintained. The scheme provided by the utility model can realize the aircraft to automatically implement health supervision.
Description
Technical field
The utility model relates to communication technical field, relates in particular to equipment manager in the aircraft and the health control device in this equipment manager.
Background technology
Referring to Fig. 1, be the structural representation of equipment manager in the prior art aircraft, described aircraft refers to dirigible, satellite, aircraft, airship, rocket, guided missile etc.This equipment manager comprises serial general-purpose interface (SPI, Serial Peripheral Interface) bus, and Integrated Electronic System that is connected with spi bus and aircraft subsystem.
Integrated Electronic System is used for aircraft is carried out integral body control, specifically comprises each aircraft subsystem is controlled.
The aircraft subsystem refers to propelling subsystem, rail control subsystem and the structure subsystem etc. among the figure.At different aircraft, different aircraft subsystem combinations is arranged; For example:, comprise structure subsystem for dirigible; For satellite, comprise advancing subsystem, rail control subsystem and structure subsystem.Be example with the satellite among Fig. 1, show the aircraft subsystem that satellite comprises.Below part aircraft subsystem is described:
Advance subsystem, be used to change the direction and the attitude of spacecraft.Can place on rocket, the satellite.
The rail control subsystem is used to control the attitude and the track of satellite.Can place on satellite, the airship.
Structure subsystem is used to gather and the physical construction of controlling aircraft and the physical signalling of heat structure.Can place on dirigible, satellite, the aircraft.
For aircraft is carried out health control, be provided with four equipment respectively on ground, be respectively: failure diagnosis apparatus, failure prediction equipment, system reconfiguration equipment and fault detect and xegregating unit.
All comprise sensor node in Integrated Electronic System and each aircraft subsystem, when carrying out health control, ground equipment sends the health control instruction by wireless mode to Integrated Electronic System, after sensor node in the Integrated Electronic System receives the health control instruction, send the health control instruction to each aircraft subsystem by spi bus; The sensor node of Integrated Electronic System and each aircraft subsystem is gathered the simulating signal of the operation conditions of this sensor node place aircraft subsystem or Integrated Electronic System then, is to feed back to ground relevant device after the digital signal with analog signal conversion; Relevant device is handled to obtain the relevant information about health control after receiving the digital signal that sensor node sends.Following mask body describes.
In the time of need carrying out fault diagnosis to aircraft, failure diagnosis apparatus sends the Gernral Check-up instruction by wireless mode to aircraft, after the sensor node of the Integrated Electronic System of aircraft receives the Gernral Check-up instruction, send the Gernral Check-up instruction to each aircraft subsystem; The sensor node that comprises in Integrated Electronic System and each aircraft subsystem is gathered the simulating signal of the operation conditions of this sensor node place aircraft subsystem or Integrated Electronic System respectively, is to feed back to ground failure diagnosis apparatus after the digital signal with analog signal conversion; Failure diagnosis apparatus carries out algorithm process to digital signal, carries out fault diagnosis according to the final data after handling, and draws fault type; Described algorithm process specifically can comprise: processing such as filtering, denoising, feature extraction, data mining.After drawing fault type, failure diagnosis apparatus can also send to system reconfiguration equipment with fault type according to the request of system reconfiguration equipment.
In the time of need carrying out failure prediction to aircraft, failure prediction equipment sends the health forecast instruction by wireless mode to aircraft, after the sensor node of the Integrated Electronic System of aircraft receives the health forecast instruction, send the health forecast instruction to each aircraft subsystem; The sensor node that comprises in Integrated Electronic System and each aircraft subsystem is gathered the simulating signal of the operation conditions of this sensor node place aircraft subsystem or Integrated Electronic System respectively, is to feed back to ground failure prediction equipment after the digital signal with analog signal conversion; Failure prediction equipment carries out algorithm process to digital signal, carries out failure prediction, the type of the fault that acquisition will take place according to the digital signal after handling; Described algorithm process specifically can comprise: processing such as filtering, denoising, feature extraction, data mining.After drawing fault type, failure prediction equipment can also send to system reconfiguration equipment with fault type according to the request of system reconfiguration equipment.
In the time of need being reconstructed the fault that failure diagnosis apparatus is diagnosed out, system reconfiguration equipment obtains fault type from failure diagnosis apparatus, makes up maintenance instruction, sends to Integrated Electronic System, Integrated Electronic System is safeguarded after receiving maintenance instruction by sensor node accordingly; If safeguard successfully, then Integrated Electronic System sends to system reconfiguration equipment by sensor node and safeguards successful feedback information, if safeguard failure, then Integrated Electronic System sends the feedback information of safeguarding failure by sensor node to system reconfiguration equipment.System reconfiguration equipment can also send to fault detect and xegregating unit with fault type according to the request of fault detect and xegregating unit after receiving the feedback information of safeguarding failure.
In the time of need being reconstructed the device predicted fault that has of failure prediction, system reconfiguration equipment obtains fault type from failure prediction equipment, makes up maintenance instruction, sends to Integrated Electronic System, Integrated Electronic System is safeguarded after receiving maintenance instruction by sensor node accordingly; If safeguard successfully, then Integrated Electronic System sends to system reconfiguration equipment by sensor node and safeguards successful feedback information, if safeguard failure, then Integrated Electronic System sends the feedback information of safeguarding failure by sensor node to system reconfiguration equipment.System reconfiguration equipment can also send to fault detect and xegregating unit with fault type according to the request of fault detect and xegregating unit after receiving the feedback information of safeguarding failure.
In the time of need carrying out fault isolation, fault detect and xegregating unit obtain fault type from system reconfiguration equipment, make up isolated instructions, send to Integrated Electronic System, and Integrated Electronic System is isolated after receiving isolated instructions by sensor node accordingly; If isolate successfully, then Integrated Electronic System sends the successful feedback information of isolation by sensor node to fault detect and xegregating unit, if isolate failure, then Integrated Electronic System sends the feedback information of isolating failure by sensor node to fault detect and xegregating unit.
Certainly, the structure of equipment manager is not limited in shown in Figure 1ly in the aircraft, for example, can also comprise the task manager that is connected with spi bus in the equipment manager, is used to carry out task ability and recovers, and carry out the flight operation management; And, can also comprise the Action Manager that is connected with spi bus, be used to carry out the space instruction manipulation, carry out aircraft beamhouse operation and space maintenance.
To sum up, when aircraft is carried out health control, need ground four equipment to assist to finish, aircraft can not independently be finished health control, lacks independence.
Summary of the invention
The utility model provides the equipment manager in a kind of aircraft, and this equipment manager can independently carry out health control.
The utility model also provides a kind of health control device, and this health control device can independently carry out health control.
Equipment manager in a kind of aircraft, this equipment manager comprises spi bus, and the health control device that is connected with spi bus, Integrated Electronic System and aircraft subsystem; Described health control device comprises failure diagnosis unit, failure prediction unit, system reconfiguration unit and fault detect and isolated location;
Described Integrated Electronic System receives the health control instruction that ground sends, and sends the health control instruction by spi bus to each aircraft subsystem; The aircraft subsystem receives the health control instruction, gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus; And, after Integrated Electronic System receives the health control instruction of ground transmission, also gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carry out algorithm process, send the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus;
Described failure diagnosis unit is carried out fault diagnosis by the digital signal that spi bus reception aircraft subsystem and Integrated Electronic System send, and after diagnosis is out of order fault type is sent to the system reconfiguration unit; Described failure prediction unit receives the digital signal that the aircraft subsystem sends by spi bus, carries out failure prediction, doping will break down the time, fault type is sent to the system reconfiguration unit; Described system reconfiguration unit receives the fault type of failure diagnosis unit and the transmission of failure prediction unit, carry out corresponding Breakdown Maintenance, when safeguarding successfully, send the successful feedback information of maintenance to Integrated Electronic System, when safeguarding failure, safeguard the indication of failing to fault detect and isolated location transmission by spi bus; Described fault detect and isolated location receive the maintenance failure indication that described system reconfiguration unit sends, and the fault of safeguarding failure is isolated, and send the feedback information of successful isolated fault again to Integrated Electronic System by spi bus.
A kind of health control device, this health control device comprises spi bus, the failure diagnosis unit that is connected with spi bus, failure prediction unit, system reconfiguration unit and fault detect and isolated location;
Described failure diagnosis unit by spi bus receive that aircraft subsystem and Integrated Electronic System send about the digital signal of operation conditions separately, carry out fault diagnosis, after diagnosis is out of order fault type is sent to the system reconfiguration unit; Described failure prediction unit receives the digital signal that aircraft subsystem and Integrated Electronic System send by spi bus, carries out failure prediction, doping will break down the time, fault type is sent to the system reconfiguration unit; Described system reconfiguration unit receives the fault type of failure diagnosis unit and the transmission of failure prediction unit, carry out corresponding Breakdown Maintenance, when safeguarding successfully, send the successful feedback information of maintenance to Integrated Electronic System, when safeguarding failure, safeguard the indication of failing to fault detect and isolated location transmission by spi bus; Described fault detect and isolated location receive the maintenance failure indication that described system reconfiguration unit sends, and the fault of safeguarding failure is isolated, and send the feedback information of successful isolated fault again to Integrated Electronic System by spi bus.
From such scheme as can be seen, the utility model is provided with the health control device that is connected with spi bus in the equipment manager of aircraft, by failure diagnosis unit, failure prediction unit, system reconfiguration unit and fault detect and the isolated location that comprises in the health control device, realized aircraft is independently carried out health control.
Description of drawings
The structural representation of equipment manager in Fig. 1 prior art aircraft;
Fig. 2 is the structural representation of equipment manager in the utility model aircraft.
Embodiment
For making the purpose of this utility model, technical scheme and advantage clearer,, the utility model is further described below in conjunction with embodiment and accompanying drawing.
The utility model is provided with the health control device that is connected with spi bus in the equipment manager of aircraft, by the autonomous health control of health control device realization to aircraft.Referring to Fig. 2, equipment manager structural representation in the aircraft that provides for the utility model, described aircraft refers to dirigible, satellite, aircraft, airship, rocket, guided missile etc.This equipment manager comprises spi bus, and the health control device that is connected with spi bus, Integrated Electronic System and aircraft subsystem; Described health control device comprises failure diagnosis unit, failure prediction unit, system reconfiguration unit and fault detect and isolated location.
Integrated Electronic System is used for aircraft is carried out integral body control, specifically comprises each aircraft subsystem, health control device etc. are controlled.
The aircraft subsystem refers to propelling subsystem, rail control subsystem and the structure subsystem etc. among the figure.At different aircraft, different aircraft subsystem combinations is arranged; For example:, comprise structure subsystem for dirigible; For satellite, comprise advancing subsystem, rail control subsystem and structure subsystem.Be example with the satellite among Fig. 2, show the aircraft subsystem that satellite comprises.Below part aircraft subsystem is described:
Advance subsystem, be used to change the direction and the attitude of spacecraft.Can place on rocket, the satellite.
The rail control subsystem is used to control the attitude and the track of satellite.Can place on satellite, the airship.
Structure subsystem is used to gather and the physical construction of controlling aircraft and the physical signalling of heat structure.Can place on dirigible, satellite, the aircraft.
Spi bus has extensive interface, according to the needs of each aircraft, can connect the each several part parts of these aircraft needs at extensive interface: for example, for dirigible, insert health control device, Integrated Electronic System and structure subsystem etc. on spi bus; For satellite, on spi bus, connect the health control device, advance subsystem, rail control subsystem, Integrated Electronic System and structure subsystem etc.
In carrying out the health control process, described Integrated Electronic System receives the health control instruction that ground sends by wireless mode, sends the health control instruction by spi bus to each aircraft subsystem; The aircraft subsystem receives the health control instruction, gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus; And, after Integrated Electronic System receives the health control instruction of ground transmission by wireless mode, also gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carry out algorithm process, send the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus.Described algorithm process refers to specifically can comprise: processing such as filtering, denoising, feature extraction, data mining the optimization process carried out of digital signal after the conversion.
Described failure diagnosis unit is carried out fault diagnosis by the digital signal that spi bus reception aircraft subsystem and Integrated Electronic System send, and after diagnosis is out of order fault type is sent to the system reconfiguration unit; Described failure prediction unit receives the digital signal that the aircraft subsystem sends by spi bus, carries out failure prediction, doping will break down the time, fault type is sent to the system reconfiguration unit; Described system reconfiguration unit receives the fault type of failure diagnosis unit and the transmission of failure prediction unit, carry out corresponding Breakdown Maintenance, when safeguarding successfully, send the successful feedback information of maintenance to Integrated Electronic System, when safeguarding failure, safeguard the indication of failing to fault detect and isolated location transmission by spi bus; Described fault detect and isolated location receive the maintenance failure indication that described system reconfiguration unit sends, and the fault of safeguarding failure is isolated, and send the feedback information of successful isolated fault again to Integrated Electronic System by spi bus.
Above-mentioned failure diagnosis unit is carried out fault diagnosis according to the digital signal about a certain aircraft subsystem or Integrated Electronic System that receives, particularly, can be receiving digital signals, the healthy degenerate case about the healthy historical information of aircraft subsystem or Integrated Electronic System according to digital signal comprises generates the fault diagnosis conclusion that has degree of confidence; In this process, but exploit information fusion and intelligent diagnosis technique, to improve the accuracy of diagnosis.The scheme of carrying out fault diagnosis can adopt existing techniques in realizing, does not give unnecessary details here.
The digital signal about a certain aircraft subsystem or Integrated Electronic System that above-mentioned failure prediction unit basis receives is carried out the scheme of failure prediction, can adopt existing techniques in realizing.
The said system reconfiguration unit is safeguarded Integrated Electronic System or aircraft subsystem, can be adopted existing techniques in realizing; For example, can repair, make the aircraft subsystem recover normal operation by means such as redundancy backups.
The scheme that above-mentioned fault detect and isolated location carry out fault isolation also can adopt existing techniques in realizing, does not give unnecessary details here.
Alternatively, described aircraft subsystem comprises sensor node and health monitoring unit, described sensor node receives the health control instruction that Integrated Electronic System sends by spi bus, gather the simulating signal of this sensor node place aircraft subsystem operation conditions, send the health monitoring unit to; Described health monitoring unit is a digital signal with the analog signal conversion that receives, and carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus.
Alternatively, described Integrated Electronic System comprises sensor node and health monitoring unit; Described sensor node receives the health control instruction that ground sends by wireless mode, send the health control instruction by spi bus to each aircraft subsystem, and, after described sensor node receives the health control instruction of ground by the wireless mode transmission, also gather the simulating signal of Integrated Electronic System operation conditions, send the health monitoring unit to; Described health monitoring unit receives the simulating signal that described sensor node transmits, be converted to digital signal after, carry out algorithm process, the digital signal after handling is sent to the failure diagnosis unit and the failure prediction unit of health control device by spi bus.
In the equipment manager that the utility model provides, a health control device can be set link to each other, two health control devices also can be set link to each other with spi bus with spi bus; When two health control devices being set linking to each other with SPI, one of them is made as main health control device, another is made as health control device fully.
After described Integrated Electronic System receives the health control instruction of ground transmission, if it is normal to detect main health control device by spi bus, then send enabled instruction to start main health control device to main health control device by spi bus, break down if detect main health control device, then send enabled instruction to start health control device fully to being equipped with the health control device by spi bus by spi bus.Correspondingly, the digital signal after described Integrated Electronic System and described aircraft subsystem will be handled sends to the health control device that has started.
Certainly, the structure of equipment manager is not limited in shown in Figure 2ly in the aircraft, for example, can also comprise the task manager that is connected with spi bus in the equipment manager, is used to carry out task ability and recovers, and carry out the flight operation management; Simultaneously can also comprise the Action Manager that is connected with spi bus, be used to carry out the space instruction manipulation, carry out aircraft beamhouse operation and space maintenance.
Further, in design of the present utility model, the health control device can also be designed to apply on the uniform platform.Particularly, in the bottom frame of each unit of health control device is realized, can use for reference the mentality of designing of European Space Agency, realize by Design Mode and small frame; Bottom-layer design by the task layering, is divided into four layers of hardware resource layer, device interface layer, system services layer and application layers; Real-time oss in the bottom-layer design framework of unifying all belongs to service layer, function is encapsulated, with each aircraft subsystem different health control modules is set respectively at Integrated Electronic System, each health control module is mutually independent, and each health control module provides interface to application layer.
In four layers of bottom-layer design, hardware resource layer, device interface layer and system services layer can adopt existing scheme to realize, mainly the upper layer application layer are described below.For the upper layer application layer, reserve interface, for different aircraft, develop health control module separately respectively, different health control modules are registered to system services layer with the form of member.At the upper layer application layer, except comprising the fault-tolerant module in having now, can also increase health evaluating module and the wrong module of recovering; When the upper layer application layer detects fault, send failure message to the health evaluating module with the form of incident, simultaneously failure message is saved in the health control event base of system services layer; The health evaluating module is assessed failure message, carry out fault recovery if desired, send enabled instruction to fault-tolerant module, fault-tolerant module inquires about whether preserve corresponding recovery incident in the health control event base, if having, then extract this recovery incident, send to the wrong module of recovering, mistake is recovered module and is carried out this rejuvenation according to this recovery incident, finishes the processing to fault, and this processing specifically comprises system reconfiguration, isolation; If inquiring, fault-tolerant module do not preserve corresponding rejuvenation in the health control event base, then recover module and send the recovery instruction to mistake, after mistake recovery module receives this recovery instruction, generate the recovery incident, carry out rejuvenation, this recovery incident that also will generate simultaneously, is stored in the health control event base in the system services layer.
The utility model is provided with the health control device in aircraft, realize the health control to aircraft, by the health control device, just can monitor aircraft oneself state health status, can independently repair, isolate the fault that occurs; Like this, aircraft is independently determined the health status of self according to operating various state parameters, and then independently formulates suitable instruction sequence and handle corresponding fault.And need not be as prior art, other equipment of four branches need be set on ground assist to finish, thereby, the independence of aircraft improved.
And in the existing scheme, at different aircraft, ground need be provided with four equipment respectively, has defectives such as dispersion, cost height.And employing the utility model can be provided with general health control device to realize health control in various aircraft, has reached effect such as to concentrate, cost is low.
The above only is preferred embodiment of the present utility model; not in order to restriction the utility model; all within spirit of the present utility model and principle, any modification of being made, be equal to replacement, improvement etc., all should be included within the scope of the utility model protection.
Claims (5)
1. a health control device is characterized in that, this health control device comprises serial general-purpose interface spi bus, the failure diagnosis unit that is connected with spi bus, failure prediction unit, system reconfiguration unit and fault detect and isolated location;
Described failure diagnosis unit by spi bus receive that aircraft subsystem and Integrated Electronic System send about the digital signal of operation conditions separately, carry out fault diagnosis, after diagnosis is out of order fault type is sent to the system reconfiguration unit; Described failure prediction unit receives the digital signal that aircraft subsystem and Integrated Electronic System send by spi bus, carries out failure prediction, doping will break down the time, fault type is sent to the system reconfiguration unit; Described system reconfiguration unit receives the fault type of failure diagnosis unit and the transmission of failure prediction unit, carry out corresponding Breakdown Maintenance, when safeguarding successfully, send the successful feedback information of maintenance to Integrated Electronic System, when safeguarding failure, safeguard the indication of failing to fault detect and isolated location transmission by spi bus; Described fault detect and isolated location receive the maintenance failure indication that described system reconfiguration unit sends, and the fault of safeguarding failure is isolated, and send the feedback information of successful isolated fault again to Integrated Electronic System by spi bus.
2. the equipment manager in the aircraft is characterized in that this equipment manager comprises spi bus, and the health control device that is connected with spi bus, Integrated Electronic System and aircraft subsystem; Described health control device comprises failure diagnosis unit, failure prediction unit, system reconfiguration unit and fault detect and isolated location;
Described Integrated Electronic System receives the health control instruction that ground sends, and sends the health control instruction by spi bus to each aircraft subsystem; The aircraft subsystem receives the health control instruction, gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus; And, after Integrated Electronic System receives the health control instruction of ground transmission, also gather the simulating signal of self-operating situation, with analog signal conversion is digital signal, carry out algorithm process, send the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus;
Described failure diagnosis unit is carried out fault diagnosis by the digital signal that spi bus reception aircraft subsystem and Integrated Electronic System send, and after diagnosis is out of order fault type is sent to the system reconfiguration unit; Described failure prediction unit receives the digital signal that the aircraft subsystem sends by spi bus, carries out failure prediction, doping will break down the time, fault type is sent to the system reconfiguration unit; Described system reconfiguration unit receives the fault type of failure diagnosis unit and the transmission of failure prediction unit, carry out corresponding Breakdown Maintenance, when safeguarding successfully, send the successful feedback information of maintenance to Integrated Electronic System, when safeguarding failure, safeguard the indication of failing to fault detect and isolated location transmission by spi bus; Described fault detect and isolated location receive the maintenance failure indication that described system reconfiguration unit sends, and the fault of safeguarding failure is isolated, and send the feedback information of successful isolated fault again to Integrated Electronic System by spi bus.
3. equipment manager as claimed in claim 2, it is characterized in that, described aircraft subsystem comprises sensor node and health monitoring unit, described sensor node receives the health control instruction that Integrated Electronic System sends by spi bus, gather the simulating signal of this sensor node place aircraft subsystem operation conditions, send the health monitoring unit to; Described health monitoring unit is a digital signal with the analog signal conversion that receives, and carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus.
4. equipment manager as claimed in claim 2 is characterized in that, described Integrated Electronic System comprises sensor node and health monitoring unit;
Described sensor node receives ground by the health control instruction that wireless mode sends, and sends the health control instruction by spi bus to each aircraft subsystem; And, after described sensor node receives the health control instruction of ground by the wireless mode transmission, also gather the simulating signal of Integrated Electronic System operation conditions, send the health monitoring unit to; Described health monitoring unit is a digital signal with the analog signal conversion that receives, and carries out algorithm process, sends the digital signal after handling to described failure diagnosis unit and described failure prediction unit by spi bus.
5. equipment manager as claimed in claim 2 is characterized in that, the health control device that is connected with spi bus is two, and one of them is main health control device, and another is for being equipped with the health control device;
Described Integrated Electronic System breaks down if detect main health control device by spi bus after receiving the health control instruction of ground transmission, then sends enabled instruction to start health control device fully by spi bus to being equipped with the health control device; Digital signal after described Integrated Electronic System and described aircraft subsystem will be handled sends to the health control device fully that has started.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202329063U CN201698228U (en) | 2010-06-12 | 2010-06-12 | Equipment supervisor in aircraft and health supervisor in equipment supervisor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202329063U CN201698228U (en) | 2010-06-12 | 2010-06-12 | Equipment supervisor in aircraft and health supervisor in equipment supervisor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201698228U true CN201698228U (en) | 2011-01-05 |
Family
ID=43399476
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202329063U Expired - Lifetime CN201698228U (en) | 2010-06-12 | 2010-06-12 | Equipment supervisor in aircraft and health supervisor in equipment supervisor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201698228U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103217974A (en) * | 2013-04-22 | 2013-07-24 | 北京空间飞行器总体设计部 | Spacecraft autonomous health management architecture based on comprehensive electronic platform |
| CN104408230A (en) * | 2014-10-31 | 2015-03-11 | 哈尔滨工业大学 | Spacecraft integral performance health management method based on improved directed graph |
| CN104803009A (en) * | 2015-04-27 | 2015-07-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle (UAV) ground comprehensive detection system and UAV ground comprehensive detection method |
| CN104898645A (en) * | 2015-04-30 | 2015-09-09 | 北京控制工程研究所 | Satellite fault detection isolation recovery strategy and strategy dynamic adjustment method |
| CN105867281A (en) * | 2016-06-12 | 2016-08-17 | 哈尔滨工业大学 | Wireless monitoring system for aircraft running state |
| CN106056269A (en) * | 2016-05-18 | 2016-10-26 | 王洋 | NanoSat satellite house-keeping health management system based on Bayes network model |
| CN106610345A (en) * | 2015-10-27 | 2017-05-03 | 北京卫星环境工程研究所 | Health state monitoring system for spatial environment simulation test equipment |
| CN108563166A (en) * | 2018-03-23 | 2018-09-21 | 哈尔滨工程大学 | The in-orbit healthy integrated management terminal of moonlet based on FPGA and management method |
| CN109358607A (en) * | 2018-11-09 | 2019-02-19 | 北京空间技术研制试验中心 | The autonomous health control method of spacecraft based on feedback control |
| CN109649668A (en) * | 2018-11-12 | 2019-04-19 | 湖北三江航天红峰控制有限公司 | A kind of aircraft health status managing device and method |
| CN111781946A (en) * | 2020-06-11 | 2020-10-16 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle control and control system based on link |
| CN115017016A (en) * | 2022-08-09 | 2022-09-06 | 中国电子科技集团公司第十研究所 | Design method of airborne health management domain with multi-level model fusion |
-
2010
- 2010-06-12 CN CN2010202329063U patent/CN201698228U/en not_active Expired - Lifetime
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN103217974A (en) * | 2013-04-22 | 2013-07-24 | 北京空间飞行器总体设计部 | Spacecraft autonomous health management architecture based on comprehensive electronic platform |
| CN103217974B (en) * | 2013-04-22 | 2015-02-11 | 北京空间飞行器总体设计部 | Spacecraft autonomous health management architecture based on comprehensive electronic platform |
| CN104408230B (en) * | 2014-10-31 | 2017-06-13 | 哈尔滨工业大学 | A kind of comprehensive health control method of spacecraft based on improvement digraph |
| CN104408230A (en) * | 2014-10-31 | 2015-03-11 | 哈尔滨工业大学 | Spacecraft integral performance health management method based on improved directed graph |
| CN104803009A (en) * | 2015-04-27 | 2015-07-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle (UAV) ground comprehensive detection system and UAV ground comprehensive detection method |
| CN104898645A (en) * | 2015-04-30 | 2015-09-09 | 北京控制工程研究所 | Satellite fault detection isolation recovery strategy and strategy dynamic adjustment method |
| CN104898645B (en) * | 2015-04-30 | 2018-02-09 | 北京控制工程研究所 | A kind of satellite fault detection isolation recovery policy and tactful dynamic adjusting method |
| CN106610345B (en) * | 2015-10-27 | 2019-10-25 | 北京卫星环境工程研究所 | A set of health status monitoring system for space-environment facility |
| CN106610345A (en) * | 2015-10-27 | 2017-05-03 | 北京卫星环境工程研究所 | Health state monitoring system for spatial environment simulation test equipment |
| CN106056269A (en) * | 2016-05-18 | 2016-10-26 | 王洋 | NanoSat satellite house-keeping health management system based on Bayes network model |
| CN105867281A (en) * | 2016-06-12 | 2016-08-17 | 哈尔滨工业大学 | Wireless monitoring system for aircraft running state |
| CN108563166A (en) * | 2018-03-23 | 2018-09-21 | 哈尔滨工程大学 | The in-orbit healthy integrated management terminal of moonlet based on FPGA and management method |
| CN108563166B (en) * | 2018-03-23 | 2020-11-20 | 哈尔滨工程大学 | FPGA-based small satellite on-orbit health comprehensive management terminal and management method |
| CN109358607A (en) * | 2018-11-09 | 2019-02-19 | 北京空间技术研制试验中心 | The autonomous health control method of spacecraft based on feedback control |
| CN109649668A (en) * | 2018-11-12 | 2019-04-19 | 湖北三江航天红峰控制有限公司 | A kind of aircraft health status managing device and method |
| CN111781946A (en) * | 2020-06-11 | 2020-10-16 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle control and control system based on link |
| CN111781946B (en) * | 2020-06-11 | 2024-03-19 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle monitoring and control system based on link |
| CN115017016A (en) * | 2022-08-09 | 2022-09-06 | 中国电子科技集团公司第十研究所 | Design method of airborne health management domain with multi-level model fusion |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201698228U (en) | Equipment supervisor in aircraft and health supervisor in equipment supervisor | |
| CN103217974B (en) | Spacecraft autonomous health management architecture based on comprehensive electronic platform | |
| CN104821894B (en) | A kind of in-orbit autonomous management system of satellite and autonomous management method | |
| CN102932049B (en) | Information transmission method of spacecraft | |
| CN104461752B (en) | A kind of multimedia distributed task processing method of two-stage failure tolerant | |
| CN106887161B (en) | Unmanned aerial vehicle automatic take-off and landing management station, unmanned aerial vehicle automatic take-off and landing management system and method | |
| CN102483865B (en) | There is automated aircraft flight data transmission and the management system of demand model | |
| CN103869781B (en) | A kind of non-similar triplex redundance machine on-board electrical Electrical Load Management Center | |
| CN104360868A (en) | Multi-stage failure management method for use in large-sized plane comprehensive processing platform | |
| CN103955188A (en) | Control system and method supporting redundancy switching function | |
| CN103544092A (en) | Health monitoring system of avionic electronic equipment based on ARINC653 standard | |
| CN110071754A (en) | UAV TTC channel outage emergency processing method | |
| CN103605581B (en) | A kind of Distributed Computer System troubleshooting process | |
| US20160052640A1 (en) | Health management unit and method for monitoring health information and method of reporting critical failure information | |
| TW201939187A (en) | Managing limited safe mode operations of a robotic vehicle | |
| SalarKaleji et al. | A survey on fault detection, isolation and recovery (FDIR) module in satellite onboard software | |
| CN106292589B (en) | A kind of redundancy management method of the manual intervention applied to unmanned plane | |
| CN108375899B (en) | High-reliability wave glider control system | |
| CN109189042A (en) | A kind of in-orbit Autonomous fault processing scheme of satellite | |
| WO2020195122A1 (en) | Communication management device, communication management system, communication management method, and communication management program | |
| US9280403B2 (en) | Node including a CPU which is connected to other nodes constituting a computer system | |
| CN108563166A (en) | The in-orbit healthy integrated management terminal of moonlet based on FPGA and management method | |
| CN208173251U (en) | A kind of radiation monitoring system and nuclear power station | |
| CN114138007A (en) | Cloud backup-based flight management system and method | |
| CN113119994B (en) | Method and device for operating an autonomous vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 16th Floor of No.63 Satellite Building, Zhichun Road, Haidian District, Beijing, 100190 Patentee after: Beijing Guoke Huanyu Science and Technology Co., Ltd. Address before: 16th Floor of No.63 Satellite Building, Zhichun Road, Haidian District, Beijing, 100190 Patentee before: Beijing Guokehuanyu Space Technology Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110105 |