CN111434585B - Aviation five-state attack angle indication and landing indication control system and method - Google Patents
Aviation five-state attack angle indication and landing indication control system and method Download PDFInfo
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- CN111434585B CN111434585B CN201910029078.9A CN201910029078A CN111434585B CN 111434585 B CN111434585 B CN 111434585B CN 201910029078 A CN201910029078 A CN 201910029078A CN 111434585 B CN111434585 B CN 111434585B
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- 230000001629 suppression Effects 0.000 claims description 12
- 230000000452 restraining effect Effects 0.000 claims description 8
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000033228 biological regulation Effects 0.000 description 5
- 238000004132 cross linking Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000001627 detrimental effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
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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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Abstract
The invention relates to an aircraft five-state attack angle indication and landing indication control system and method. The five-state angle of attack indication and landing indication control system comprises an angle of attack indication and landing indication control box, an angle of attack indicator and a landing tri-color lamp, wherein the angle of attack indication and landing indication control box comprises an angle of attack indication power supply functional module, an indication state control functional module and a landing indication power supply functional module. The invention has the beneficial effects that: and the five-state incidence angle indication and landing indication of the aircraft are realized.
Description
Technical Field
The invention relates to an aircraft five-state attack angle indication and landing indication control system and method.
Background
When the carrier-based aircraft is on the ship, a pilot obtains the angle of attack information when the aircraft is on the ship through the angle of attack indication, and a ground director obtains the angle of attack information when the aircraft is on the ship through the ship indication, so that the detailed angle of attack information is the guarantee for the pilot to control the aircraft to safely landing the ship. The indication of the attack angle is realized through the signal lamp display of the attack angle indicator arranged on the cockpit, and the landing indication is realized through the three-color lamp display of the landing arranged on the striking position in front of the aircraft. The current attack angle indication and landing indication states are three states, namely a large attack angle, a normal attack angle and a small attack angle, and the three states are indicated by synchronous lighting of the attack angle indicator and green, yellow and red colored signal lamps of the landing tri-colored lamps. The three-state angle of attack signal indication is detrimental to the aircraft operator in fine adjustment of the aircraft landing angle of attack. Therefore, it is needed to design a five-state attack angle indication and landing indication control box, and to drive the attack angle indicator and the green, yellow and red color signal lamps of the landing tri-color lamp to perform state indication. Meanwhile, the angle of attack indication is used as a part of the display of the cockpit signal lamp, so that the dimming function of the angle of attack indication signal lamp is indispensable for meeting the requirements of the man-machine efficacy of the cockpit.
Disclosure of Invention
The invention aims to solve the technical problem that only three states are indicated in the prior art, and provides an aircraft five-state attack angle indication and landing indication control system and method.
In order to achieve the above object, the technical scheme of the present invention is as follows: an aircraft five-state angle of attack indication and landing indication control system with a dimming function comprises,
a attack angle indicator having an indicator green light, an indicator yellow light, and an indicator red light;
the ship landing tri-colored lamp is provided with a tri-colored lamp green lamp, a tri-colored lamp yellow lamp and a tri-colored lamp red lamp;
the attack angle indication power supply functional module is respectively connected with the positive end of the indicator green light, the positive end of the indicator yellow light and the positive end of the indicator red light;
the indication state control function module is provided with an attack angle indication green light state control driving circuit, an attack angle indication yellow light state control driving circuit, an attack angle indication red light state control driving circuit, a landing indication green light state control driving circuit, a landing indication yellow light state control driving circuit and a landing indication red light state control driving circuit. The input end of the attack angle indication green light state control driving circuit is used for receiving an attack angle large input signal, the output end of the attack angle indication green light state control driving circuit is connected with the negative end of the indicator green light, the input end of the attack angle indication yellow light state control driving circuit is used for receiving an attack angle normal input signal, the output end of the attack angle indication yellow light state control driving circuit is connected with the negative end of the indicator yellow light, the input end of the attack angle indication red light state control driving circuit is used for receiving an attack angle small input signal, and the output end of the attack angle indication red light state control driving circuit is connected with the negative end of the indicator red light.
The landing indication power supply functional module is provided with a landing indication green light power supply driving circuit, a landing indication green light state suppression circuit, a landing indication yellow light power supply driving circuit, a landing indication red light state suppression circuit and a landing indication red light power supply driving circuit, wherein the input end of the landing indication green light state control driving circuit is used for receiving an attack angle large input signal, the output end of the landing indication green light state control driving circuit is connected with the input end of the landing indication green light power supply driving circuit, the output end of the landing indication green light power supply driving circuit is connected with the positive end of the three-color light green light, the input end of the landing indication yellow light state control driving circuit is used for receiving an attack angle normal input signal, the output end of the landing indication yellow light state control driving circuit is respectively connected with the input end of the landing indication yellow light power supply driving circuit, the input end of the landing indication green light state restraining circuit and the input end of the landing indication red light state restraining circuit, the output end of the landing indication yellow light power supply driving circuit is connected with the positive end of the three-color yellow light, the input end of the landing indication red light state control driving circuit is used for receiving an input signal with a small attack angle, the output end of the landing indication red light state control driving circuit is connected with the input end of the landing indication red light power supply driving circuit, the output end of the landing indication red light power supply driving circuit is connected with the negative end of the three-color red light, the negative end of the three-color green light, the negative end of the three-color yellow light and the negative end of the three-color red light are all grounded, the output end of the landing indication green light state restraining circuit is connected with the restraining end of the landing indication green light driving circuit, the output end of the landing indication red light state suppression circuit is connected with the suppression end of the landing indication red light power supply driving circuit.
As a preferable scheme of the five-state angle of attack indication and landing indication control system with the dimming function, the angle of attack indication power supply functional module is provided with a voltage regulation driving circuit, and the voltage regulation driving circuit is used for indicating the output voltage of the angle of attack indication power supply functional module.
The invention also relates to an aviation five-state attack angle indication and landing indication control method with a dimming function, which comprises the following steps,
providing an aircraft five-state attack angle indication and landing indication control system;
if the attack angle of the aircraft is large, only an input signal with a large attack angle is effective, and the indicator green light and the three-color light green light are driven to be synchronously lighted;
if the attack angle of the aircraft is slightly larger, only the input signal with a large attack angle and the input signal with a normal attack angle are effective, and the indicator green light, the indicator yellow light and the three-color lamp yellow light are driven to be synchronously lighted;
if the attack angle of the aircraft is normal, only the normal input signal of the attack angle is valid, and the indicator yellow lamp and the tri-color yellow lamp are driven to be synchronously lighted;
if the attack angle of the aircraft is slightly smaller, only the normal attack angle input signal and the small attack angle input signal are effective, and the indicator yellow light, the indicator red light and the three-color yellow light are driven to be synchronously lighted;
and if the attack angle of the aircraft is small, only the input signal with the small attack angle is effective, and the indicator red light and the three-color red light are driven to synchronously light.
Compared with the prior art, the invention has the beneficial effects that:
1. and the five-state incidence angle indication and landing indication of the aircraft are realized.
2. The five-state angle of attack indication and landing indication provide more detailed angle of attack information for pilots and ground directors.
3. Is compatible with the cross-linking of the angle of attack signal on the current aircraft, and reduces the modification cost.
4. Stepless brightness adjustment of the attack angle indication signal lamp meets the man-machine efficacy requirement of the cockpit, and can be synchronous with the signal indication of the cockpit.
Drawings
FIG. 1 is a schematic diagram of an embodiment of the present invention.
Description of the embodiments
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 invention relates to an aircraft five-state attack angle indication and landing indication control box with a dimming function, which mainly comprises an attack angle indication power supply function module, a landing indication power supply function module and an indication state control function module.
The attack angle indication power supply functional module provides an adjustable voltage source for the attack angle indication signal lamp. The functional module consists of a voltage regulation driving circuit and a sampling feedback circuit, wherein the core of the voltage regulation driving circuit is a three-terminal voltage regulator LM117, the power supply is from an onboard 28VDC, and the output voltage is controlled to continuously change through a brightness regulation signal (voltage). And setting the output voltage range of the functional module to be (10.0-26.0) VDC according to the brightness-voltage curve of the attack angle indication signal lamp and the aviation brightness requirement.
The indication state control function module mainly comprises three paths of attack angle indication state control driving circuits and three paths of landing indication state control driving circuits. The angle of attack signal comes from the cross-linking interface. The green signal lamp is lighted by the control driving circuit module which outputs a ground/open circuit signal according to the large signal of the attack angle and controls the green signal lamp of the indicator to be effectively grounded at the negative end of the green power supply. The principle of the attack angle indication yellow lamp and red lamp state control driving circuit module is the same as that of the previous one, and the description is omitted. The landing indication green light state control driving circuit outputs a high (28 VDC)/open circuit signal according to the attack angle big signal, and controls the landing indication power supply functional module to output a three-color lamp green light power supply, so that the three-color lamp green light is lighted. The principle of the landing indication yellow lamp and the red lamp state control driving circuit module is the same as that of the landing indication yellow lamp and the red lamp state control driving circuit module, and the description is omitted.
The landing indication power supply functional module mainly comprises three paths of landing indication power supply driving circuit modules which respectively output green, yellow and red signal lamp power supplies of landing indication. When the landing indication yellow light state control driving circuit module generates an effective high (28 VDC) signal, the landing indication green light state suppression circuit module and the landing indication red light state suppression circuit module are respectively controlled to generate a green light suppression signal and a red light suppression signal. The landing indication power supply driving circuit module turns off power supply output according to the inhibition signal. The 28VDC input is an onboard 28VDC power supply.
The above description of the invention is not intended to be limiting, and those skilled in the art will appreciate that many changes and modifications can be made to the system architecture and embodiments of the invention without departing from the scope of the invention as defined in the appended claims.
Claims (3)
1. The five-state angle of attack indication and landing indication control system for aviation is characterized by comprising,
a attack angle indicator having an indicator green light, an indicator yellow light, and an indicator red light;
the ship landing tri-colored lamp is provided with a tri-colored lamp green lamp, a tri-colored lamp yellow lamp and a tri-colored lamp red lamp;
the attack angle indication power supply functional module is respectively connected with the positive end of the indicator green light, the positive end of the indicator yellow light and the positive end of the indicator red light;
the system comprises an indication state control function module, a signal processing module and a signal processing module, wherein the indication state control function module is provided with an attack angle indication green light state control driving circuit, an attack angle indication yellow light state control driving circuit, an attack angle indication red light state control driving circuit, an attack angle indication green light state control driving circuit, an attack angle indication yellow light state control driving circuit and an attack angle indication red light state control driving circuit, wherein the input end of the attack angle indication green light state control driving circuit is used for receiving an attack angle large input signal, the output end of the attack angle indication green light state control driving circuit is connected with the negative end of an indicator green light, the input end of the attack angle indication yellow light state control driving circuit is used for receiving an attack angle normal input signal, the output end of the attack angle indication yellow light state control driving circuit is connected with the negative end of the indicator yellow light, and the output end of the attack angle indication red light state control driving circuit is connected with the negative end of the indicator red light; the landing indication power supply functional module is provided with a landing indication green light power supply driving circuit, a landing indication green light state suppression circuit, a landing indication yellow light power supply driving circuit, a landing indication red light state suppression circuit and a landing indication red light power supply driving circuit, wherein the input end of the landing indication green light state control driving circuit is used for receiving an attack angle large input signal, the output end of the landing indication green light state control driving circuit is connected with the input end of the landing indication green light power supply driving circuit, the output end of the landing indication green light power supply driving circuit is connected with the positive end of the three-color light green light, the input end of the landing indication yellow light state control driving circuit is used for receiving an attack angle normal input signal, the output end of the landing indication yellow light state control driving circuit is respectively connected with the input end of the landing indication yellow light power supply driving circuit, the input end of the landing indication green light state restraining circuit and the input end of the landing indication red light state restraining circuit, the output end of the landing indication yellow light power supply driving circuit is connected with the positive end of the three-color yellow light, the input end of the landing indication red light state control driving circuit is used for receiving an input signal with a small attack angle, the output end of the landing indication red light state control driving circuit is connected with the input end of the landing indication red light power supply driving circuit, the output end of the landing indication red light power supply driving circuit is connected with the negative end of the three-color red light, the negative end of the three-color green light, the negative end of the three-color yellow light and the negative end of the three-color red light are all grounded, the output end of the landing indication green light state restraining circuit is connected with the restraining end of the landing indication green light driving circuit, the output end of the landing indication red light state suppression circuit is connected with the suppression end of the landing indication red light power supply driving circuit.
2. The aircraft five-state angle of attack indication and landing indication control system of claim 1 wherein the angle of attack indication power supply functional module has a voltage adjustment drive circuit for the angle of attack indication power supply functional module to output a stable variable angle of attack indicator voltage source in accordance with a brightness adjustment signal.
3. The aircraft five-state attack angle indication and landing indication control method is characterized by comprising the following steps of,
providing an aircraft five state angle of attack indication and landing indication control system of claim 1 or 2;
if the attack angle of the aircraft is large, only an input signal with a large attack angle is effective, and the indicator green light and the three-color light green light are driven to be synchronously lighted;
if the attack angle of the aircraft is slightly larger, only the input signal with a large attack angle and the input signal with a normal attack angle are effective, and the indicator green light, the indicator yellow light and the three-color lamp yellow light are driven to be synchronously lighted;
if the attack angle of the aircraft is normal, only the normal input signal of the attack angle is valid, and the indicator yellow lamp and the tri-color yellow lamp are driven to be synchronously lighted;
if the attack angle of the aircraft is slightly smaller, only the normal attack angle input signal and the small attack angle input signal are effective, and the indicator yellow light, the indicator red light and the three-color yellow light are driven to be synchronously lighted;
and if the attack angle of the aircraft is small, only the input signal with the small attack angle is effective, and the indicator red light and the three-color red light are driven to synchronously light.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910029078.9A CN111434585B (en) | 2019-01-12 | 2019-01-12 | Aviation five-state attack angle indication and landing indication control system and method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910029078.9A CN111434585B (en) | 2019-01-12 | 2019-01-12 | Aviation five-state attack angle indication and landing indication control system and method |
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| CN111434585B true CN111434585B (en) | 2023-06-09 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3569926A (en) * | 1969-03-19 | 1971-03-09 | Singer General Precision | Flight path and speed command display |
| CN102393630A (en) * | 2011-09-26 | 2012-03-28 | 南京航空航天大学 | Carrier aircraft landing guide and control system for inhibiting airflow disturbance of stern and control method for system |
| CN105523172A (en) * | 2016-01-11 | 2016-04-27 | 成都学尚科技有限公司 | Attack angle control system and attack angle control method |
| RU2653414C1 (en) * | 2017-02-02 | 2018-05-08 | Сергей Николаевич Низов | Stalling warning system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9193473B2 (en) * | 2013-09-20 | 2015-11-24 | Safe Flight Instrument Corporation | Angle of attack display |
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- 2019-01-12 CN CN201910029078.9A patent/CN111434585B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3569926A (en) * | 1969-03-19 | 1971-03-09 | Singer General Precision | Flight path and speed command display |
| CN102393630A (en) * | 2011-09-26 | 2012-03-28 | 南京航空航天大学 | Carrier aircraft landing guide and control system for inhibiting airflow disturbance of stern and control method for system |
| CN105523172A (en) * | 2016-01-11 | 2016-04-27 | 成都学尚科技有限公司 | Attack angle control system and attack angle control method |
| RU2653414C1 (en) * | 2017-02-02 | 2018-05-08 | Сергей Николаевич Низов | Stalling warning system |
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| CN111434585A (en) | 2020-07-21 |
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