CN111295013B - Attack angle indication dimming and landing indication dimming system based on data bus control - Google Patents
Attack angle indication dimming and landing indication dimming system based on data bus control Download PDFInfo
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- CN111295013B CN111295013B CN201811494112.1A CN201811494112A CN111295013B CN 111295013 B CN111295013 B CN 111295013B CN 201811494112 A CN201811494112 A CN 201811494112A CN 111295013 B CN111295013 B CN 111295013B
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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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/18—Visual or acoustic landing aids
- B64F1/20—Arrangement of optical beacons
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B20/00—Energy efficient lighting technologies, e.g. halogen lamps or gas discharge lamps
- Y02B20/40—Control techniques providing energy savings, e.g. smart controller or presence detection
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Circuit Arrangement For Electric Light Sources In General (AREA)
Abstract
The invention discloses an attack angle indication dimming and landing indication dimming system based on data bus control, which comprises a left attack angle indicator; a right angle of attack indicator; landing indicating device; the central processing unit is provided with a first CPU and a second CPU, wherein the first CPU and the second CPU respectively receive limit information of the aircraft through two paths of bus paths, and the first CPU and the second CPU share information and compare information through a CAN bus; a dimming driving unit having a first dimming circuit and a second dimming circuit; a state control driving unit having a first driving circuit and a second driving circuit; and a landing indication power supply driving circuit. The invention has the advantages that: and the dual-redundancy bus control attack angle indication and landing indication are realized.
Description
Technical Field
The invention relates to the field of dimming systems, in particular to an attack angle indication dimming and landing indication dimming system based on data bus control.
Background
The approach attack angle indication and the landing indication are important indication tools for landing an aircraft, and the data bus is an important means for realizing information transmission on the aircraft. In order to safely and reliably realize attack angle indication and landing indication through bus control and simultaneously realize stepless brightness adjustment of attack angle indication and day and night brightness control of landing indication, a attack angle indication and landing indication system based on a data bus and having a dimming function is designed. When the aircraft is on a ship, a landing commander obtains accurate information of the attack angle of the aircraft and whether a landing hook is put down or not according to state information of a landing indication. The brightness of the signal lamp indicated by the landing ship provides day brightness and night brightness according to different environments. Meanwhile, the driver obtains accurate information of the aircraft attack angle according to the independent left attack angle and right attack angle. The brightness of the signal lamp indicated by the attack angle can be manually or automatically adjusted according to different ambient lights so as to meet the visual needs of pilots.
Whether the system can work normally and directly in a severe environment relates to landing safety of the carrier-based aircraft, the traditional attack angle indication and carrier landing indication system cannot meet the requirements of novel carrier-based aircraft, and along with the increasing requirements of the aircraft on man-machine efficiency, the design of a data bus control attack angle indication and light modulation and carrier landing indication and light modulation system is needed.
Disclosure of Invention
The invention aims to overcome the problems in the prior art and provides a novel attack angle indication dimming and landing indication dimming system based on data bus control.
In order to achieve the purpose, the technical scheme of the invention is as follows: an attack angle indication dimming and landing indication dimming system based on data bus control comprises,
a left angle of attack indicator;
a right angle of attack indicator;
landing indicating device;
the central processing unit is provided with a first CPU and a second CPU, the first CPU and the second CPU respectively receive limit information of the aircraft through two paths of bus paths, the first CPU and the second CPU share information and compare information through a CAN bus, and if the information is consistent, the first CPU and the second CPU respectively control respective ports to carry out control logic output; if the information is inconsistent, respectively generating and reporting alarm signals; the central processing unit outputs dimming information through two paths of D/A converters respectively;
the dimming driving unit is provided with a first dimming circuit and a second dimming circuit, the first dimming circuit adjusts the brightness of the left angle-of-attack indicator according to a brightness adjusting signal provided by the first CPU, and the second dimming circuit adjusts the brightness of the right angle-of-attack indicator according to a brightness adjusting signal provided by the second CPU; the method comprises the steps of,
the state control driving unit is provided with a first driving circuit and a second driving circuit, the first driving circuit controls the left angle-of-attack indicator and the corresponding signal lamp of the landing indicating device to be synchronously lighted according to the driving signal of the first CPU, and the second driving circuit controls the right angle-of-attack indicator to be correspondingly lighted according to the driving signal of the second CPU.
Compared with the prior art, the invention has the beneficial effects that: 1. and realizing attack angle indication and landing indication based on the aviation data bus. 2. And the reliability of aviation data communication is ensured by double redundancy data bus communication. 3. The two CPUs share and compare the limit information, so that the attack angle indication information is more accurate and reliable, and the aircraft landing is safer. 4. The stepless dimming of the angle of attack indication signal lamp is realized, and the man-machine effect of the cockpit is improved. 5. The synchronous automatic and manual dimming of the attack angle indication signal lamp and the cockpit signal lamp is realized. 6. Automatic and manual switching of the day/night brightness of the landing indication signal lamp is realized. 7. The left attack angle indication state control driving function module and the right attack angle indication state control driving function module are mutually independent, so that the reliability of the pilot for obtaining attack angle information is improved.
In addition to the technical problems, features constituting the technical solutions and advantageous effects caused by the technical features of the technical solutions described above, other technical problems that the present invention can solve, other technical features included in the technical solutions and advantageous effects caused by the technical features will be described in further detail with reference to the accompanying drawings.
Drawings
Fig. 1 is a schematic structural diagram of an embodiment of the present invention.
FIG. 2 is a schematic block diagram of a CPU of an embodiment of a bus 1553B according to an embodiment of the invention.
Detailed Description
The invention will be described in further detail below with reference to the drawings by means of specific embodiments. The description of these embodiments is provided to assist understanding of the present invention, but is not to be construed as limiting the present invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
Referring to fig. 1, the system for controlling the attack angle indication dimming and landing indication dimming by using the data bus is composed of a central processing unit, a state control driving unit, a dimming driving unit and a landing indication power driving unit.
The central processing unit receives limit information of the aircraft through two paths of bus paths by two CPUs respectively, and performs information sharing and information comparison through a CAN bus. The central processing unit of this example is seen in fig. 2. And the CPU and the 1553B processing unit are used for carrying out information interaction through an SPI interface. The CPU1 receives the limit information of the airplane through the 1553B processing unit 1, the CPU2 receives the limit information of the airplane through the 1553B processing unit 2, and information sharing is carried out between the CPU1 and the CPU through the CAN bus. CPU1 receives limit information shared by CPU2 and then carries out correction processing with limit information received by CPU2 through 1553B bus, CPU2 receives limit information shared by CPU1 and then carries out correction processing with limit information received by CPU through 1553B bus, if the information is consistent, CPU1 and CPU2 respectively control respective ports to carry out control logic output; if the information is inconsistent, alarm signals are respectively generated and reported. The central processing unit outputs dimming information through two paths of D/A converters respectively.
The state control driving units are mutually independent driving circuits and perform corresponding driving output according to control logic signals. Three paths of independent control signals are respectively output through three paths of GPIO ports of the CPU1, the control attack angle indication green, yellow and red lamp state control driving circuits output three paths of ground/open-circuit signals, and the corresponding signal lamps of the left attack angle indicator are controlled to be lighted; the three paths of independent control signals synchronously and respectively control the landing indication green, yellow and red light state control driving circuits to output three paths of high/open-circuit signals, and the landing indication green, yellow and red light power supply driving circuits control the corresponding signal lamps of the landing indication device to be lighted. Three paths of independent control signals are respectively output through three paths of GPIO ports of the CPU2, the control attack angle indication green, yellow and red light state control driving circuit outputs three paths of ground/open-circuit signals, and the corresponding signal lamp of the right attack angle indicator is controlled to be lighted.
The dimming driving unit is powered by 28VDC, outputs 0-5V adjusting voltage through the D/A converting circuit, performs error amplification with the sampling voltage obtained by the sampling feedback circuit, drives the corresponding voltage adjusting circuit, outputs a stable variable angle indicator voltage source, supplies power to the angle indicator, and realizes brightness adjustment of the angle indicator signal lamp. The output voltage range of the voltage source is 3.0 VDC-26.0 VDC.
The landing indication power supply driving circuit outputs three paths of signal lamp power supplies respectively, and the day/night control is controlled by the IO port of the CPU1 through the control driving circuit.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof herein may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. Accordingly, the scope of protection of the present invention is to be determined by the appended claims.
Claims (1)
1. The attack angle indication dimming and landing indication dimming system based on the data bus control is characterized by comprising,
a left angle of attack indicator;
a right angle of attack indicator;
landing indicating device;
the central processing unit is provided with a first CPU and a second CPU, the first CPU and the second CPU respectively receive limit information of the aircraft through two paths of bus paths, the first CPU and the second CPU share information and compare information through a CAN bus, and if the information is consistent, the first CPU and the second CPU respectively control respective ports to carry out control logic output; if the information is inconsistent, respectively generating and reporting alarm signals; the central processing unit outputs dimming information through two paths of D/A converters respectively;
the dimming driving unit is provided with a first dimming circuit and a second dimming circuit, the first dimming circuit adjusts the brightness of the left angle-of-attack indicator according to a brightness adjusting signal provided by the first CPU, and the second dimming circuit adjusts the brightness of the right angle-of-attack indicator according to a brightness adjusting signal provided by the second CPU; the method comprises the steps of,
a state control driving unit having a first driving circuit and a second driving circuit;
the first driving circuit is provided with a green, yellow and red light state control driving circuit for attack angle indication and a green, yellow and red light state control driving circuit for landing indication; three paths of independent control signals are respectively output through three paths of GPIO ports of the first CPU, and the control attack angle indication green, yellow and red lamp state control driving circuit outputs three paths of ground/open circuit signals so as to control the corresponding signal lamp of the left attack angle indicator to be lighted; the three paths of independent control signals synchronously and respectively control the landing indication green, yellow and red lamp state control driving circuits to output three paths of high/open-circuit signals, and the landing indication green, yellow and red lamp power supply driving circuits control the corresponding signal lamps of the landing indication device to be on;
the second driving circuit is provided with a green, yellow and red light state control driving circuit for indicating angles of attack, and three paths of independent control signals are respectively output through three paths of GPIO ports of the second CPU, and the green, yellow and red light state control driving circuit for controlling the angles of attack is controlled to output three paths of ground/open-circuit signals so as to control the corresponding signal lamps of the right angle of attack indicator to be lighted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811494112.1A CN111295013B (en) | 2018-12-07 | 2018-12-07 | Attack angle indication dimming and landing indication dimming system based on data bus control |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811494112.1A CN111295013B (en) | 2018-12-07 | 2018-12-07 | Attack angle indication dimming and landing indication dimming system based on data bus control |
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| CN111295013A CN111295013A (en) | 2020-06-16 |
| CN111295013B true CN111295013B (en) | 2023-08-08 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102375461A (en) * | 2010-08-16 | 2012-03-14 | 上海航空电器有限公司 | Bus control-based digital light modulation technology of control panel of airplane driving cabin |
| CN104229126A (en) * | 2014-09-15 | 2014-12-24 | 中国运载火箭技术研究院 | High-reliability landing gear control system |
| CN107462233A (en) * | 2017-07-21 | 2017-12-12 | 中船航海科技有限责任公司 | A kind of repeater compass equipment for concentrating light modulation |
| CN108282930A (en) * | 2018-03-14 | 2018-07-13 | 生迪光电科技股份有限公司 | Light adjusting circuit, lamp assembly, light adjusting system and light-dimming method |
| CN208046966U (en) * | 2018-03-14 | 2018-11-02 | 生迪光电科技股份有限公司 | Light adjusting circuit, lamp assembly and light adjusting system |
-
2018
- 2018-12-07 CN CN201811494112.1A patent/CN111295013B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102375461A (en) * | 2010-08-16 | 2012-03-14 | 上海航空电器有限公司 | Bus control-based digital light modulation technology of control panel of airplane driving cabin |
| CN104229126A (en) * | 2014-09-15 | 2014-12-24 | 中国运载火箭技术研究院 | High-reliability landing gear control system |
| CN107462233A (en) * | 2017-07-21 | 2017-12-12 | 中船航海科技有限责任公司 | A kind of repeater compass equipment for concentrating light modulation |
| CN108282930A (en) * | 2018-03-14 | 2018-07-13 | 生迪光电科技股份有限公司 | Light adjusting circuit, lamp assembly, light adjusting system and light-dimming method |
| CN208046966U (en) * | 2018-03-14 | 2018-11-02 | 生迪光电科技股份有限公司 | Light adjusting circuit, lamp assembly and light adjusting system |
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| CN111295013A (en) | 2020-06-16 |
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