CN114132515A - Aircraft monitoring, control and management system - Google Patents
Aircraft monitoring, control and management system Download PDFInfo
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- CN114132515A CN114132515A CN202111622174.8A CN202111622174A CN114132515A CN 114132515 A CN114132515 A CN 114132515A CN 202111622174 A CN202111622174 A CN 202111622174A CN 114132515 A CN114132515 A CN 114132515A
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- engine data
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 22
- 230000005540 biological transmission Effects 0.000 claims abstract description 56
- 238000012545 processing Methods 0.000 claims description 27
- 238000004364 calculation method Methods 0.000 claims description 21
- 238000000034 method Methods 0.000 claims description 9
- 238000004132 cross linking Methods 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 238000003860 storage Methods 0.000 claims description 6
- 238000013480 data collection Methods 0.000 claims 5
- 238000012937 correction Methods 0.000 claims 1
- 230000002452 interceptive effect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 abstract 2
- 230000009471 action Effects 0.000 description 3
- 241000282414 Homo sapiens Species 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 241001465754 Metazoa Species 0.000 description 1
- 230000005856 abnormality Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
Abstract
The invention discloses an aircraft monitoring and control management system which comprises an aircraft engine load end module and an aircraft engine land end monitoring and control management module, wherein the aircraft engine load end module comprises an aircraft engine data acquisition unit, a first aircraft engine data wireless transmission unit and an aircraft engine body control unit. The instruction signal of artifical regulation control is generated in order to transmit to first aircraft engine data wireless transmission unit through second aircraft engine data wireless transmission unit wireless, thereby detect engine data in real time, reach the effect of being convenient for monitor engine anomaly immediately, the effect of being convenient for immediately react in order to manage has been realized, interactive efficiency has greatly been improved, the data limitation of transmission has been reduced, the security of using has been ensured, and the flexibility has been improved.
Description
Technical Field
The invention relates to the technical field of aircraft management systems, in particular to an aircraft monitoring and control management system.
Background
The aircraft is an apparatus flying in the atmosphere or the space (space) outside the atmosphere, and the aircraft is divided into 3 types: aircraft, spacecraft, rockets and missiles, which fly in the atmosphere and are called aircrafts such as balloons, airships, airplanes and the like, fly by the static buoyancy of air or the aerodynamic force generated by the relative motion of air, and which fly in space and are called spacecrafts such as artificial earth satellites, manned spacecrafts, space detectors, space planes and the like, which get the necessary velocity into space under the driving of a carrier rocket and then make orbital motion similar to celestial bodies by means of inertia, wherein the aircrafts are instrument flyers which are manufactured by human beings, can fly off the ground, fly in space and are controlled by human beings and fly in the atmosphere or in the space (space) outside the atmosphere, and the aircrafts which fly in the atmosphere and are called spacecrafts.
In the civil field, the most common aircrafts and those with application spaces are unmanned aerial vehicles, which are unmanned aerial vehicles operated by radio remote control devices and self-contained program control devices, or operated autonomously by an on-board computer, either completely or intermittently, and which are often better suited to tasks that are too "foolproof, dirty or dangerous" than piloted aircraft, civil unmanned aerial vehicles + industrial applications, which are really just needed by unmanned aerial vehicles; the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand the industrial application and develop the unmanned aerial vehicle technology. The engine of the unmanned aerial vehicle is the core driven by the unmanned aerial vehicle, and the engine management of the unmanned aerial vehicle needs to be adapted to an electric control system so as to adapt to complex service environments and various service requirements
Aircraft unmanned aerial vehicle's engine is at the in-process that puts into operation, and the system of current control and management is difficult to detect engine data in real time to be difficult to the instant monitoring engine unusual, thereby be difficult to respond to in order to manage immediately, interactive efficiency is lower moreover, and the data limitation of transmission is great, and it is relatively poor not only to use the security, but also very inflexible.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an aircraft monitoring and control management system, which solves the problems that the abnormality of an engine is difficult to monitor in real time, so that the engine is difficult to respond in real time for management, the interaction efficiency is low, the transmitted data is large in limitation, and the safety is poor and the application is not flexible.
In order to achieve the purpose, the invention adopts the following technical scheme:
the aircraft engine load end module comprises an aircraft engine data acquisition unit, a first aircraft engine data wireless transmission unit and an aircraft engine body control unit, and the aircraft engine land end monitoring and control management module comprises a second aircraft engine data wireless transmission unit, an aircraft engine data processing unit, an aircraft engine data display unit, an aircraft engine data calculation unit, an aircraft engine instruction generation unit and an aircraft engine control management and control unit;
the aircraft engine data wireless transmission unit is connected with the aircraft engine body control unit and receives instruction information and control management information to provide the aircraft engine body control unit for controlling the aircraft;
the second aircraft engine data wireless transmission unit is connected with the aircraft engine data processing unit, the aircraft engine data processing unit is respectively connected with the aircraft engine data display unit and the aircraft engine data calculation unit, the aircraft engine data calculation unit is respectively connected with the aircraft engine instruction generation unit and the aircraft engine control management and control unit, the second aircraft engine data wireless transmission unit receives aircraft engine data output by the first aircraft engine data wireless transmission unit and processes the aircraft engine data to the aircraft engine data processing unit, the aircraft engine data processing unit displays processed data information through the aircraft engine data display unit after processing, and the aircraft engine data processing unit calculates the processed data information through the aircraft engine data calculation unit after processing, the aircraft engine data calculation unit calculates the data and then generates instruction information through the aircraft engine instruction generation unit, the aircraft engine data calculation unit calculates the data and then performs manual regulation control through the aircraft engine control management and control unit, and instruction signals of the manual regulation control are generated to be wirelessly transmitted to the first aircraft engine data wireless transmission unit through the second aircraft engine data wireless transmission unit.
Preferably, the aircraft engine data acquisition unit is used for acquiring the data of the crosslinking system received by the input channel of the aircraft engine crosslinking system in real time.
Preferably, after the data of the aircraft engine data acquisition unit are acquired, the parameter information and the air running time data of the aircraft engine are output to a recording storage space of the aircraft engine through the first aircraft engine data wireless transmission unit.
Preferably, the first aircraft engine data wireless transmission unit outputs the generated parameter information of the aircraft engine and the air operating time data to the second aircraft engine data wireless transmission unit.
Preferably, the aircraft engine data acquisition unit is used for backing up the acquired data and storing the data into an own storage space.
Preferably, if the first aircraft engine data wireless transmission unit and the second aircraft engine data wireless transmission unit are connected with the data stored in the aircraft engine data acquisition unit in a backup mode, the aircraft engine control management and control unit manages, queries and corrects the data through the aircraft engine control management and control unit.
Preferably, the aircraft engine data acquisition unit acquires the aircraft engine data in real time according to digital signals and analog signals.
Preferably, the aircraft engine data acquisition unit performs data acquisition according to the digital signals and the analog signals, performs comprehensive comparison, and transmits the data together with the original data and the comparison data which are not compared when performing wireless output through the first aircraft engine data wireless transmission unit.
Compared with the prior art, the invention has the beneficial effects that: the aircraft monitoring and control management system comprises an aircraft engine data acquisition unit, a first aircraft engine data wireless transmission unit, an aircraft engine body control unit, an aircraft engine data calculation unit, an aircraft engine control management and control unit, a second aircraft engine data wireless transmission unit, a first aircraft engine data wireless transmission unit, a second aircraft engine data wireless transmission unit, a third aircraft engine data wireless transmission unit, a fourth aircraft control unit, a, interaction efficiency is greatly improved, limitation of transmitted data is reduced, application safety is guaranteed, and flexibility is improved.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example (b): referring to fig. 1, the aircraft monitoring and control management system is characterized by comprising an aircraft engine load end module and an aircraft engine land end monitoring and control management module, wherein the aircraft engine load end module comprises an aircraft engine data acquisition unit, a first aircraft engine data wireless transmission unit and an aircraft engine body control unit, and the aircraft engine land end monitoring and control management module comprises a second aircraft engine data wireless transmission unit, an aircraft engine data processing unit, an aircraft engine data display unit, an aircraft engine data calculation unit, an aircraft engine instruction generation unit and an aircraft engine control unit;
the aircraft engine data wireless transmission unit is connected with the aircraft engine body control unit and used for receiving instruction information and control management information to provide the aircraft engine body control unit for controlling the aircraft;
the second aircraft engine data wireless transmission unit is connected with the aircraft engine data processing unit, the aircraft engine data processing unit is respectively connected with the aircraft engine data display unit and the aircraft engine data calculation unit, the aircraft engine data calculation unit is respectively connected with the aircraft engine instruction generation unit and the aircraft engine control management and control unit, the second aircraft engine data wireless transmission unit receives the aircraft engine data output by the first aircraft engine data wireless transmission unit and processes the aircraft engine data to the aircraft engine data processing unit, the aircraft engine data processing unit displays the processed data information through the aircraft engine data display unit after processing, the aircraft engine data processing unit calculates the processed data information through the aircraft engine data calculation unit after processing, the aircraft engine data calculation unit calculates the data and then generates instruction information through the aircraft engine instruction generation unit, the aircraft engine data calculation unit calculates the data and then performs manual regulation control through the aircraft engine control management and control unit, and an instruction signal of the manual regulation control is generated and is transmitted to the first aircraft engine data wireless transmission unit through the second aircraft engine data wireless transmission unit in a wireless mode.
In the invention, the aircraft engine data acquisition unit is used for acquiring the data of the crosslinking system received by the input channel of the aircraft engine crosslinking system in real time.
According to the invention, after the data of the aircraft engine data acquisition unit are acquired, the parameter information and the air running time data of the aircraft engine are output to the recording storage space of the aircraft engine through the first aircraft engine data wireless transmission unit.
In the invention, the first aircraft engine data wireless transmission unit outputs the generated parameter information and the air running time data of the aircraft engine to the second aircraft engine data wireless transmission unit.
In the invention, the aircraft engine data acquisition unit is used for backing up the acquired data and storing the data into a self-contained storage space.
In the invention, if the first aircraft engine data wireless transmission unit and the second aircraft engine data wireless transmission unit are connected with the data stored in the aircraft engine data acquisition unit in a backup mode, the aircraft engine control management and control unit manages, inquires and corrects the data through the aircraft engine control management and control unit.
In the invention, the data acquisition unit of the aircraft engine acquires the data of the aircraft engine in real time according to the digital signal and the analog signal.
In the invention, the aircraft engine data acquisition unit acquires data according to the digital signal and the analog signal, then performs comprehensive comparison, and transmits the acquired data together with the original data and the comparison data which are not compared when performing wireless output through the first aircraft engine data wireless transmission unit.
The working principle is as follows: the aircraft engine data acquisition unit outputs acquired aircraft engine data through the first aircraft engine data wireless transmission unit, the first aircraft engine data wireless transmission unit receives instruction information and control management information to provide an aircraft engine body control unit to control an aircraft, the second aircraft engine data wireless transmission unit receives aircraft engine data output by the first aircraft engine data wireless transmission unit and processes the aircraft engine data to the aircraft engine data processing unit, the aircraft engine data processing unit displays the processed data information through the aircraft engine data display unit after processing, the aircraft engine data processing unit calculates the processed data information through the aircraft engine data calculation unit, the aircraft engine data calculation unit calculates the data and then generates the instruction information through the aircraft engine instruction generation unit, the aircraft engine data calculation unit calculates the data, then the aircraft engine control management and control unit performs manual regulation control, and instruction signals of the manual regulation control are generated to be wirelessly transmitted to the first aircraft engine data wireless transmission unit through the second aircraft engine data wireless transmission unit.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The aircraft monitoring and control management system is characterized by comprising an aircraft engine load end module and an aircraft engine land end monitoring and control management module, wherein the aircraft engine load end module comprises an aircraft engine data acquisition unit, a first aircraft engine data wireless transmission unit and an aircraft engine body control unit;
the aircraft engine data wireless transmission unit is connected with the aircraft engine body control unit and receives instruction information and control management information to provide the aircraft engine body control unit for controlling the aircraft;
the second aircraft engine data wireless transmission unit is connected with the aircraft engine data processing unit, the aircraft engine data processing unit is respectively connected with the aircraft engine data display unit and the aircraft engine data calculation unit, the aircraft engine data calculation unit is respectively connected with the aircraft engine instruction generation unit and the aircraft engine control management and control unit, the second aircraft engine data wireless transmission unit receives aircraft engine data output by the first aircraft engine data wireless transmission unit and processes the aircraft engine data to the aircraft engine data processing unit, the aircraft engine data processing unit displays processed data information through the aircraft engine data display unit after processing, and the aircraft engine data processing unit calculates the processed data information through the aircraft engine data calculation unit after processing, the aircraft engine data calculation unit calculates the data and then generates instruction information through the aircraft engine instruction generation unit, the aircraft engine data calculation unit calculates the data and then performs manual regulation control through the aircraft engine control management and control unit, and instruction signals of the manual regulation control are generated to be wirelessly transmitted to the first aircraft engine data wireless transmission unit through the second aircraft engine data wireless transmission unit.
2. The aircraft monitoring, control and management system of claim 1 wherein the aircraft engine data collection unit is configured to collect cross-linking system data received by the aircraft engine cross-linking system input channel in real-time.
3. The aircraft monitoring, control and management system according to claim 3, wherein the aircraft engine data acquisition unit outputs the aircraft engine parameter information and the air operating time data to the recording storage space of the aircraft engine through the first aircraft engine data wireless transmission unit after acquiring the data.
4. The aircraft monitoring, control and management system of claim 3 wherein the first wireless aircraft engine data transmission unit outputs the generated aircraft engine parameter information and air operating time data to the first wireless aircraft engine data transmission unit.
5. The aircraft monitoring, control and management system of claim 1 wherein the aircraft engine data collection unit is configured to backup collected data and store the backed up data in an on-board storage space.
6. The aircraft monitoring, control and management system according to claim 6, wherein the aircraft engine control management and control unit performs management and query and correction through the aircraft engine control management and control unit if the first and second wireless transmission units of aircraft engine data are connected with the data backed up and stored by the aircraft engine data collection unit.
7. The aircraft monitoring, control and management system of claim 1 wherein the real-time collection of aircraft engine data by the aircraft engine data collection unit is data collection in digital and analog signals.
8. The aircraft monitoring, control and management system according to claim 7 wherein the aircraft engine data acquisition unit performs data acquisition according to digital signals and analog signals, performs comprehensive comparison, and transmits the data together with the raw data and the comparison data that are not compared when wirelessly outputting through the first aircraft engine data wireless transmission unit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111622174.8A CN114132515A (en) | 2021-12-28 | 2021-12-28 | Aircraft monitoring, control and management system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111622174.8A CN114132515A (en) | 2021-12-28 | 2021-12-28 | Aircraft monitoring, control and management system |
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| CN114132515A true CN114132515A (en) | 2022-03-04 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1288644A2 (en) * | 2001-08-31 | 2003-03-05 | General Electric Company | Diagnostic method and system for turbine engines |
| CN106197559A (en) * | 2016-08-26 | 2016-12-07 | 西安航空电子科技有限公司 | A kind of general aircraft engine parameter collecting method and device |
| US20170180962A1 (en) * | 2015-12-21 | 2017-06-22 | Ge Aviation Systems Llc | Aircraft Data Handoff |
| CN107539484A (en) * | 2016-06-23 | 2018-01-05 | 通用电气公司 | Wireless aircraft engine monitoring system |
| CN109703766A (en) * | 2018-12-14 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of remote starting system of piston engine unmanned plane |
| CN113075879A (en) * | 2020-01-03 | 2021-07-06 | 中国科学院沈阳自动化研究所 | Engine control system of tilt rotor unmanned aerial vehicle |
-
2021
- 2021-12-28 CN CN202111622174.8A patent/CN114132515A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1288644A2 (en) * | 2001-08-31 | 2003-03-05 | General Electric Company | Diagnostic method and system for turbine engines |
| US20170180962A1 (en) * | 2015-12-21 | 2017-06-22 | Ge Aviation Systems Llc | Aircraft Data Handoff |
| CN107539484A (en) * | 2016-06-23 | 2018-01-05 | 通用电气公司 | Wireless aircraft engine monitoring system |
| CN106197559A (en) * | 2016-08-26 | 2016-12-07 | 西安航空电子科技有限公司 | A kind of general aircraft engine parameter collecting method and device |
| CN109703766A (en) * | 2018-12-14 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of remote starting system of piston engine unmanned plane |
| CN113075879A (en) * | 2020-01-03 | 2021-07-06 | 中国科学院沈阳自动化研究所 | Engine control system of tilt rotor unmanned aerial vehicle |
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