CN112623271B - Test equipment for comprehensive control console of general aircraft - Google Patents
Test equipment for comprehensive control console of general aircraft Download PDFInfo
- Publication number
- CN112623271B CN112623271B CN202011568142.XA CN202011568142A CN112623271B CN 112623271 B CN112623271 B CN 112623271B CN 202011568142 A CN202011568142 A CN 202011568142A CN 112623271 B CN112623271 B CN 112623271B
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- limiter
- landing gear
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- diode
- connecting end
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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
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Emergency Alarm Devices (AREA)
Abstract
The invention discloses general aircraft comprehensive control board test equipment, which comprises a test box, a power input end, a limiter connecting end and a landing gear alarm connecting end, wherein the power input end is connected with the limiter connecting end; the test box is provided with a power circuit breaker, a loudspeaker, a landing gear alarm elimination switch, a flap switch, a limiter prompt lamp, a limiter red lamp and a limiter green lamp; the first diode, the second diode and the third diode are arranged in the test box; the power input end supplies power to the whole test equipment, one end of the power input end is connected with a power supply, and the other end is connected with the test box; one end of the limiter connecting end and one end of the landing gear warning connecting end are connected in the test box, and the other end of the limiter connecting end and the landing gear warning connecting end are connected with the comprehensive control console; the limiter connection and landing gear alert connection have 4 terminals, namely a first terminal, a second terminal, a third terminal and a fourth terminal. The device simulates an airplane cross-linking line, realizes the function test of the comprehensive control console before the airplane is installed, and rapidly locates whether the wire harness inside the comprehensive control console fails.
Description
Technical Field
The invention relates to the technical field of general aviation auxiliary equipment, in particular to general aircraft comprehensive control console test equipment.
Background
The aircraft cockpit integrated control console is provided with an undercarriage warning and elevator limiting wire harness, corresponding functions are realized through a cross-linked line, and in order to verify the functional integrity, the current testing steps are that an operator completes the assembly of the whole aircraft avionics system, and after the system is jointly debugged, the functional test can be performed. Once the wire harness fails, an operator needs to detach the comprehensive control console and repair the wire harness in the comprehensive control console, the whole process is time-consuming and labor-consuming, and test equipment before the aircraft is installed on the comprehensive control console is absent in the prior art.
Disclosure of Invention
The invention aims to provide a test device for a general aircraft comprehensive control console, which simulates an aircraft cross-linking line, realizes a function test of the comprehensive control console before installing an aircraft, and rapidly locates whether an internal wire harness of the comprehensive control console has faults.
The technical scheme for realizing the purpose of the invention is as follows: a general aircraft comprehensive control console test device comprises a test box, a power input end, a limiter connecting end and a landing gear warning connecting end; the test box is provided with a power circuit breaker, a loudspeaker, a landing gear alarm elimination switch, a flap switch, a limiter prompt lamp, a limiter red lamp and a limiter green lamp; the first diode, the second diode and the third diode are arranged in the test box; the power input end supplies power to the whole test equipment, one end of the power input end is connected with a power supply, and the other end is connected with the test box; one end of the limiter connecting end and one end of the landing gear warning connecting end are connected in the test box, and the other end of the limiter connecting end and the landing gear warning connecting end are connected with the comprehensive control console; the limiter connecting end and the landing gear warning connecting end are provided with 4 wiring terminals, namely a first wiring terminal, a second wiring terminal, a third wiring terminal and a fourth wiring terminal;
one wiring end of the power input end is connected with the input end of the power circuit breaker, and the other wiring end is connected with the second wiring end and the third wiring end of the landing gear alarm connecting end;
the output end of the power circuit breaker is respectively connected with the input end of the landing gear alarm elimination switch, the fourth wiring end of the connecting end of the limiter, the input end of the loudspeaker and the positive electrode end of the limiter prompting lamp;
the output end of the landing gear alarm elimination switch is connected with a third wiring end of the connecting end of the limiter; the second terminal of the limiter connecting end is respectively connected with the negative electrode end of the limiter red light and the positive electrode end of the limiter green light; the positive end of the red light of the limiter is connected with the negative end of the first diode, the negative end of the green light of the limiter is connected with the positive end of the second diode, and the positive end of the first diode and the negative end of the second diode are connected with the first wiring end of the connecting end of the limiter;
the output end of the horn is respectively connected with a first wiring end of the landing gear alarm connecting end and the positive electrode end of the third diode; the negative electrode end of the third diode is connected with the input end of the flap switch; the output end of the flap switch is connected with the second wiring end and the third wiring end of the landing gear alarm connecting end;
the output end of the limiter prompting lamp is connected with a fourth wiring terminal of the landing gear alarm elimination switch.
Preferably, the connection is an AWG wire connection.
Preferably, the mobile power supply is a 28V mobile power supply.
Preferably, the limiter prompt lamp, the limiter red lamp and the limiter green lamp are LED lamps.
Preferably, the power circuit breaker is a vacuum circuit breaker.
Compared with the prior art, the invention has the beneficial effects that:
1. the test equipment simulates an airplane cross-linked line, realizes the function test before the comprehensive control console is installed on an airplane, rapidly locates whether the wire harness in the comprehensive control console has faults or not, and avoids the error of the wire harness;
2. the equipment has the advantages of simple principle, easy manufacture, convenient carrying and convenient operation.
Drawings
FIG. 1 is a schematic diagram of a generic aircraft integrated console test rig of the present invention.
Fig. 2 is a top view of the universal aircraft integrated console test apparatus of the present invention.
FIG. 3 is a schematic diagram of the internal structure of the universal aircraft integrated console test device of the present invention.
Marked in the figure as: 1. a test cartridge; 2. a power circuit breaker; 3. a horn; 4. landing gear alarm elimination switch; 5. a flap switch; 6. a limiter indicator light; 7. limiter red light; 8. a limiter green light; 9. a power input; 10. the limiter connecting end; 11. landing gear alarm connection; 12. a first diode; 13. a second diode; 14. and a third diode.
Detailed Description
The present invention will be further described with reference to the following detailed description and the accompanying drawings, in which more details are set forth in order to provide a thorough understanding of the present invention, but it will be apparent that the present invention can be embodied in many other forms than described herein, and that those skilled in the art may make similar generalizations and deductions depending on the actual application without departing from the spirit of the present invention, and therefore should not be limited in scope by the context of this detailed description.
As shown in fig. 1 and 2, a test device for a general aircraft comprehensive control console comprises a test box 1, a power input end 9, a limiter connection end 10 and a landing gear alarm connection end 11; the test box 1 is provided with a power circuit breaker 2, a loudspeaker 3, a landing gear alarm elimination switch 4, a flap switch 5, a limiter prompting lamp 6, a limiter red lamp 7 and a limiter green lamp 8; the limiter prompt lamp 6, the limiter red lamp 7 and the limiter green lamp 8 can be LED lamps; the first diode 12, the second diode 13 and the third diode 14 are arranged in the test box 1; the power input end 9 supplies power to the whole test equipment, one end of the power input end is connected with a power supply or a 28V mobile power supply, and the other end of the power input end is connected with the test box 1; one end of the limiter connecting end 10 and one end of the landing gear warning connecting end 11 are connected inside the test box 1, and the other end of the limiter connecting end is connected with the comprehensive control console; the limiter connection end 10 and the landing gear warning connection end 11 are provided with 4 wiring terminals, namely a first wiring terminal, a second wiring terminal, a third wiring terminal and a fourth wiring terminal;
as shown in fig. 3, one terminal of the power input terminal 9 is connected with the input terminal of the power circuit breaker 2, and the other terminal is connected with the second terminal and the third terminal of the landing gear warning connection terminal 11;
the output end of the power circuit breaker 2 is respectively connected with the input end of the landing gear alarm elimination switch 4, the fourth wiring end of the limiter connecting end 10, the input end of the loudspeaker 3 and the positive electrode end of the limiter prompting lamp 6; the power circuit breaker 2 is a vacuum circuit breaker;
the output end of the landing gear alarm elimination switch 4 is connected with a third wiring terminal of the limiter connecting end 10; the second terminal of the limiter connecting end 10 is respectively connected with the negative electrode end of the limiter red light 7 and the positive electrode end of the limiter green light 8; the positive terminal of the limiter red light 7 is connected with the negative terminal of the first diode 12, the negative terminal of the limiter green light 8 is connected with the positive terminal of the second diode 13, and the positive terminal of the first diode 12 and the negative terminal of the second diode 13 are connected with the first terminal of the limiter connecting terminal 10;
the output end of the loudspeaker 3 is respectively connected with the first wiring end of the landing gear alarm connecting end 11 and the positive electrode end of the third diode 14; the negative terminal of the third diode 14 is connected to the input of the flap switch 5; the output end of the flap switch 5 is connected with a second wiring end and a third wiring end of the landing gear alarm connecting end 11;
the output end of the limiter prompting lamp 6 is connected with a fourth wiring terminal of the landing gear alarm elimination switch 4;
the components of the device are connected by using AWG wires.
The limiter of the aircraft elevator has the function of limiting the elevator to deflect up and down by 13 degrees when the power of throttle rods on two sides of the aircraft comprehensive control console exceeds 20%, so that the aircraft stall is prevented.
The operation method for testing the limiter of the aircraft elevator by the device comprises the following steps: when the power circuit breaker 2 is pressed, two throttle levers on the comprehensive control console move forwards for a certain distance, and when the power of the throttle levers exceeds 20%, the limiter prompt lamp 6 and the limiter red lamp 7 are always on; two throttle levers on the comprehensive control console move backwards for a certain distance, and when the power of the throttle levers exceeds 20%, the limiter prompting lamp 6 and the limiter green lamp 8 are always on; the left throttle lever on the comprehensive control console moves forwards for a certain distance, the right throttle lever moves backwards for a certain distance, and the limiter prompt lamp 6, the limiter red lamp 7 and the limiter green lamp 8 are not on; the left throttle lever on the comprehensive control console moves backwards for a certain distance, the right throttle lever moves forwards for a certain distance, and the limiter prompt lamp 6, the limiter red lamp 7 and the limiter green lamp 8 are not on.
The device uses the functions of the light test integrated control console, when the aircraft is actually operated, the power of throttle levers at two sides of the integrated control console exceeds 20% or is lower than 20%, and the motor of the elevator limiter can respectively rotate forward and backward, so that the elevator is limited to deflect up and down by 13 degrees; the forward rotation and the reverse rotation of the motor are respectively simulated through the limiter red light 7 and the limiter green light 8, and the limiter prompting light 6 has the function of providing load protection for the circuit at any time and preventing the testing device from being damaged due to the circuit problem of the comprehensive control console. When the throttle lever of the integrated control console is operated, whether the integrated control console fails or not is judged by observing the on and off of the limiter red light 7 and the limiter green light 8.
The aircraft landing gear warning function is: when the aircraft is retracted and the landing gear is taken up, and when the throttle levers on two sides of the aircraft comprehensive control console are at the maximum power, the landing gear warning horn reminds a driver, and warning sound can be cancelled by pressing a landing gear warning elimination switch; when the aircraft is retracted and the landing gear is taken up, and the throttle levers on the two sides are at the minimum power, the landing gear warning horn reminds a driver, and warning sound cannot be canceled by pressing a landing gear warning elimination switch; when the landing gear is taken up by the aircraft and the flap is at the landing position, the throttle levers on the two sides are at any positions, and the landing gear alarm elimination switch is pressed down, so that the alarm sound is continuously sounded.
The operation method for testing the landing gear alarming function of the device comprises the following steps: when the power circuit breaker 2 is pressed, the two throttle levers on the comprehensive control console move forwards for a certain distance, and the loudspeaker 3 does not sound; the throttle levers on two sides of the comprehensive control console move backwards for a certain distance, the horn 3 sounds normally, the landing gear alarm elimination switch 4 is pressed down, and the horn 3 sounds normally; the left throttle lever on the throttle lever assembly moves forwards for a certain distance, the right throttle lever moves backwards for a certain distance, the horn 3 sounds normally, the landing gear alarm elimination switch 4 is pressed, and the horn 3 stops sounding; the left throttle lever on the comprehensive control console moves backwards for a certain distance, the right throttle lever moves forwards for a certain distance, the horn 3 sounds normally, the landing gear alarm elimination switch 4 is pressed, and the horn 3 stops sounding; when the flap switch 5 is pressed, the two throttle levers on the integrated console are at any positions, and the landing gear alarm elimination switch 4 is pressed, the alarm sound of the loudspeaker 3 is continuously sounded all the time.
The horn 3, the landing gear alarm elimination switch 4 and the flap switch 5 on the device are in one-to-one correspondence with the horn, the landing gear alarm elimination switch and the flap switch on the airplane, and the functions of the comprehensive control console are tested by using the devices; when an operator tests according to the operation method, once the actual operation phenomenon is inconsistent with the operation method, the comprehensive control console fault can be judged.
Claims (5)
1. The universal aircraft comprehensive control console test equipment is characterized by comprising a test box (1), a power input end (9), a limiter connecting end (10) and a landing gear alarm connecting end (11); the test box (1) is provided with a power circuit breaker (2), a loudspeaker (3), a landing gear alarm elimination switch (4), a flap switch (5), a limiter prompt lamp (6), a limiter red lamp (7) and a limiter green lamp (8); a first diode (12), a second diode (13) and a third diode (14) are arranged in the test box (1); the power input end (9) supplies power to the whole test equipment, one end of the power input end is connected with a power supply, and the other end of the power input end is connected with the test box (1); one end of the limiter connecting end (10) and one end of the landing gear warning connecting end (11) are connected inside the test box (1), and the other end of the limiter connecting end is connected with the comprehensive control console; the limiter connecting end (10) and the landing gear warning connecting end (11) are provided with 4 wiring terminals, namely a first wiring terminal, a second wiring terminal, a third wiring terminal and a fourth wiring terminal;
one wiring end of the power input end (9) is connected with the input end of the power circuit breaker (2), and the other wiring end is connected with the second wiring end and the third wiring end of the landing gear alarm connecting end (11);
the output end of the power circuit breaker (2) is respectively connected with the input end of the landing gear alarm elimination switch (4), the fourth wiring end of the limiter connecting end (10), the input end of the loudspeaker (3) and the positive electrode end of the limiter prompting lamp (6);
the output end of the landing gear alarm elimination switch (4) is connected with a third wiring end of the limiter connecting end (10); the second wiring end of the limiter connecting end (10) is respectively connected with the negative electrode end of the limiter red light (7) and the positive electrode end of the limiter green light (8); the positive electrode end of the limiter red light (7) is connected with the negative electrode end of the first diode (12), the negative electrode end of the limiter green light (8) is connected with the positive electrode end of the second diode (13), and the positive electrode end of the first diode (12) and the negative electrode end of the second diode (13) are connected with the first wiring end of the limiter connecting end (10);
the output end of the horn (3) is respectively connected with a first wiring end of the landing gear alarm connecting end (11) and the positive electrode end of the third diode (14); the negative terminal of the third diode (14) is connected with the input terminal of the flap switch (5); the output end of the flap switch (5) is connected with a second wiring end and a third wiring end of the landing gear alarm connecting end (11);
the output end of the limiter prompting lamp (6) is connected with a fourth wiring terminal of the landing gear alarm elimination switch (4).
2. A universal aircraft integrated console test unit according to claim 1, wherein the connection is an AWG wire connection.
3. The universal aircraft integrated console test appliance of claim 1, wherein the power source is a 28V mobile power source.
4. The universal aircraft integrated console test device of claim 1, wherein the limiter indicator lights (6), limiter red lights (7), and limiter green lights (8) are LED lights.
5. A universal aircraft integrated console testing apparatus according to claim 1, characterized in that the power circuit breaker (2) is a vacuum circuit breaker.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011568142.XA CN112623271B (en) | 2020-12-25 | 2020-12-25 | Test equipment for comprehensive control console of general aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011568142.XA CN112623271B (en) | 2020-12-25 | 2020-12-25 | Test equipment for comprehensive control console of general aircraft |
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| Publication Number | Publication Date |
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| CN112623271A CN112623271A (en) | 2021-04-09 |
| CN112623271B true CN112623271B (en) | 2023-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011568142.XA Active CN112623271B (en) | 2020-12-25 | 2020-12-25 | Test equipment for comprehensive control console of general aircraft |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB457562A (en) * | 1935-09-13 | 1936-12-01 | Fairey Aviat Co Ltd | Improved warning and indicating device particularly for use in aircraft |
| CN104122881A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Tester of alarm control box of airplane |
| GB201420283D0 (en) * | 2014-11-14 | 2014-12-31 | Ge Aviat Systems Ltd | An aircraft assembly with load and position indicator |
| CN105620733A (en) * | 2014-10-28 | 2016-06-01 | 中航通飞研究院有限公司 | Position alarm device for amphibious aircraft undercarriage folding and unfolding mechanism |
| CN205281249U (en) * | 2015-11-30 | 2016-06-01 | 中航飞机股份有限公司西安飞机分公司 | Experimental integrated measurement and control device of fire control system ground crosslinked is synthesized to aircraft |
| CN110456212A (en) * | 2019-08-15 | 2019-11-15 | 中国人民解放军第五七二一工厂 | A kind of aircraft power control harness integrated experiment device |
| CN111204475A (en) * | 2020-03-17 | 2020-05-29 | 南昌航空大学 | Ground off-position detection device and method for airplane ground proximity warning system |
-
2020
- 2020-12-25 CN CN202011568142.XA patent/CN112623271B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB457562A (en) * | 1935-09-13 | 1936-12-01 | Fairey Aviat Co Ltd | Improved warning and indicating device particularly for use in aircraft |
| CN104122881A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Tester of alarm control box of airplane |
| CN105620733A (en) * | 2014-10-28 | 2016-06-01 | 中航通飞研究院有限公司 | Position alarm device for amphibious aircraft undercarriage folding and unfolding mechanism |
| GB201420283D0 (en) * | 2014-11-14 | 2014-12-31 | Ge Aviat Systems Ltd | An aircraft assembly with load and position indicator |
| CN205281249U (en) * | 2015-11-30 | 2016-06-01 | 中航飞机股份有限公司西安飞机分公司 | Experimental integrated measurement and control device of fire control system ground crosslinked is synthesized to aircraft |
| CN110456212A (en) * | 2019-08-15 | 2019-11-15 | 中国人民解放军第五七二一工厂 | A kind of aircraft power control harness integrated experiment device |
| CN111204475A (en) * | 2020-03-17 | 2020-05-29 | 南昌航空大学 | Ground off-position detection device and method for airplane ground proximity warning system |
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| Publication number | Publication date |
|---|---|
| CN112623271A (en) | 2021-04-09 |
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