CN117401183A - Control device is terminated in civilian helicopter ground joint test bench redundancy test - Google Patents

Control device is terminated in civilian helicopter ground joint test bench redundancy test Download PDF

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Publication number
CN117401183A
CN117401183A CN202311507216.2A CN202311507216A CN117401183A CN 117401183 A CN117401183 A CN 117401183A CN 202311507216 A CN202311507216 A CN 202311507216A CN 117401183 A CN117401183 A CN 117401183A
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CN
China
Prior art keywords
relay
control unit
switch box
switch
control
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202311507216.2A
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Chinese (zh)
Inventor
林炜清
章猛
吴本强
郭聪
汤永
刘文琦
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China Helicopter Research and Development Institute
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China Helicopter Research and Development Institute
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Filing date
Publication date
Application filed by China Helicopter Research and Development Institute filed Critical China Helicopter Research and Development Institute
Priority to CN202311507216.2A priority Critical patent/CN117401183A/en
Publication of CN117401183A publication Critical patent/CN117401183A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G—PHYSICS
    • G08—SIGNALLING
    • G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
    • G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
    • G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
    • 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
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Automation & Control Theory (AREA)
  • Testing Electric Properties And Detecting Electric Faults (AREA)

Abstract

The utility model provides a civilian helicopter ground joint test bench redundancy test termination control device, the device includes measurement and control room switch box 1, on-the-spot wireless controller 5, rack power supply module 6, termination control unit 7, direct current output control unit 11, cockpit switch box 13, wherein: the measurement and control room switch box 1 is connected with the termination control unit 7, the direct current output control unit 11 is connected with the cockpit switch box 13, the cockpit switch box 13 is connected with the termination control unit 7, the cockpit switch box 13 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10, and the termination control unit 7 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10; the field wireless controller 5 is connected to the termination control unit 7 by a wireless mode.

Description

Control device is terminated in civilian helicopter ground joint test bench redundancy test
Technical Field
The invention belongs to the technical field of helicopter ground combined tests, and relates to a surplus test termination control device of a civil helicopter ground combined test bed.
Background
The ground combined test bed for the helicopter is large-scale test equipment for carrying out matching, functionality and durability by combining and assembling three large-scale moving parts (a rotor system, a transmission system and a power system) of the helicopter, bears various dynamic scientific research operation test tasks before the first flight of the helicopter, provides reliable ground test basis and safety guarantee for the first flight of the helicopter model and scientific research test flight tasks, shortens the development period to a certain extent in the model development process, reduces the test flight risk and reduces the development cost.
In a series of ground test tasks carried out on the ground combined test bed, the body structure, the rotor wing system, the transmission system and the like of the helicopter are all in the state of the check limit, various emergency situations can occur in the test bed and the test machine, and various uncertainty and safety risks exist. The civil helicopter ground combined test bed is complete in structure and installation equipment of the test machine in order to more truly examine performance parameters of power, a rotor wing, a transmission system and the like, and a professional in an adopted control mode completes control of the test machine through a cockpit. Therefore, the safety guarantee in the test process is more important, and the safety of the test personnel and the test machine participating in the test machine cannot be endangered. The key point of handling the unexpected situation of sudden high risk encountered in the ground combined test process is how to stop the test safely, namely stop the test machine and stop the rotor wing.
Disclosure of Invention
The purpose of the invention is that: the device can also ensure the safety of the test machine and field test personnel, protect important test pieces and test equipment from being damaged, and ensure the successful development of subsequent tests.
The technical scheme of the invention is as follows: the utility model provides a civilian helicopter ground joint test bench redundancy test termination control device, the device includes measurement and control room switch box 1, on-the-spot wireless controller 5, rack power supply module 6, termination control unit 7, direct current output control unit 11, cockpit switch box 13, wherein:
the measurement and control room switch box 1 is connected with the termination control unit 7, the direct current output control unit 11 is connected with the cockpit switch box 13, the cockpit switch box 13 is connected with the termination control unit 7, the cockpit switch box 13 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10, and the termination control unit 7 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10; the field wireless controller 5 is connected to the termination control unit 7 by a wireless mode.
Specifically, the termination control unit 7 includes a relay a, a relay B, a relay C, a relay D, a relay E, a relay F, a wireless communication module, a connector a, and a connector B, where the relay a and the relay B are a set of relays, the relay C and the relay D are a set of relays, and the relay E and the relay F are a set of relays.
Specifically, the connection relation between the relay A and the relay B is as follows: the coil of the control relay A is connected with the f pin of the A connector of the termination control unit, the a pin of the A connector of the termination control unit is connected with the wireless module output terminal A, the B pin of the A connector of the termination control unit is connected with the contact A2 of the control relay 1, the contact A3 is connected with the a pin of the B aviation plug, the C pin of the A connector of the termination control unit is connected with the contact B2 of the control relay 1, the contact B3 is connected with the B pin of the B aviation plug, the contact A1 of the control relay B is connected at the same time, the d pin of the A connector of the termination control unit is connected with the contact C2 of the control relay A, the contact C1 of the control relay A is connected with the coil of the control relay B, the e pin of the A connector of the termination control unit is connected with the coil of the control relay A, B, the f pin of the A connector of the termination control unit is connected with the contact A2 of the control relay B, the g pin of the A connector of the termination control unit is connected with the contact B2 of the control relay B, the h pin of the contact of the A connector of the termination control unit is connected with the contact B2 of the control relay B, and the contact C1 of the contact C connector of the termination unit is connected with the contact B.
Specifically, the rack power supply assembly 6 comprises a direct-current stabilized voltage supply, a 28V storage battery, a circuit breaker, a diode and a binding post; the rack power supply assembly 6 is used for providing stable direct current power supply input, and the rack power supply assembly 6 has dual-redundancy direct current input, so that the operation of the test termination device can be ensured not to be influenced by commercial power and airborne equipment; the circuit breaker is used for power supply line protection, and the protection current of circuit breaker is 10A, and the output terminal 1, the output wiring 2 of rack power supply module are connected with the A connector of termination control unit.
Specifically, the cockpit switch box 13 is mechanically mounted on the cockpit control panel, and the cockpit switch box 13 is provided with 37Q switches, 38Q switches, 39Q switches, wherein: the contacts A1 and A2 of the 37Q switch are connected with the pins a and b of the aviation plug A of the cockpit switch box, the contacts A1 and A2 of the 38Q switch are connected with the pins c and d of the aviation plug A of the cockpit switch box, and the contacts A1 and A2 of the 39Q switch are connected with the pins e and f of the aviation plug A of the cockpit switch box; the pins a, c and e of the A aviation plug of the cockpit switch box 13 are externally short-circuited by leads and then are respectively connected with the wiring terminal 1 of the direct current load output control unit; the switch state of the cockpit switch box 13 is normally closed, and the operation state is open.
Specifically, the inter-measurement and control switch box 1 is provided with a 34Q switch, a 35Q switch, and a 36Q switch, wherein: the contacts A2 and A3 of the 36Q switch are connected with the pins a and b of the A aviation plug of the measurement and control room switch box 1, the contacts A2 and A3 of the 36Q switch are connected with the pins c and d of the A aviation plug of the measurement and control room switch box 1, and the contacts A2 and A3 of the 37Q switch are connected with the pins e and f of the A aviation plug of the measurement and control room switch box 1.
Specifically, two ends of the indicator lamp L1 are respectively connected with g pins and h pins of the A aviation plug of the switch box 1 between measurement and control; two ends of the indicator lamp L2 are respectively connected with j pins and k pins of the A aviation plug of the switch box 1 between measurement and control; the two ends of the indicator lamp L3 are respectively connected with m pins and n pins of the A aviation plug of the switch box 1 between measurement and control.
Specifically, pins a, c and e of the A aviation plug of the measurement and control switch box 1 are externally short-circuited by leads and then are respectively connected with a direct current load output binding post 2, and pins a, c, d, g, j, m of the A aviation plug of the measurement and control switch box 1 are respectively connected with a, j, v, g, s, aa of the A aviation plug of the termination control unit; the 34Q switch, the 35Q switch and the 36Q switch are in a normally open state, and the working state is closed.
The technical effects are as follows:
the technical scheme of the invention has the beneficial effects that: 1. the invention provides a surplus test termination control device of a civil helicopter ground combined test bed, which can realize the emergency control treatment of a test machine through a measurement and control room switch box, a cockpit switch box and a field wireless controller, wherein the surplus test termination control device is used for controlling the test machine; 2. the method comprises the steps of reasonably configuring processing authorities according to fault processing levels, and having a multi-level dangerous case processing mechanism, wherein three control authority levels are that site test observers take precedence over cockpit personnel, test commanders take precedence over cockpit personnel and site test observers; 3. the device of the invention is not influenced by the outside, including the power supply of the tester equipment and the power failure of the on-site commercial power. 4. The control switches are designed to prevent misoperation, are provided with protective covers and switch limiting positions, and provide bright-colored spraying.
Drawings
FIG. 1 is a schematic diagram of a control device for terminating a redundancy test of a ground combined test bed of a civil helicopter;
FIG. 2 is a schematic diagram of the electrical principle of a termination control device for a redundancy test of a ground combined test bed of a civil helicopter provided by the embodiment of the invention;
FIG. 3 is a schematic diagram of a local circuit of a termination control unit according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a partial circuit of a gantry power assembly provided by an embodiment of the present invention;
FIG. 5 is a schematic diagram of a local circuit of the switch box between measurement and control according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a partial circuit of a cabin switch box provided by an embodiment of the present invention;
FIG. 7 is a schematic diagram of a partial circuit of a first electrically operated valve provided by an embodiment of the present invention;
the system comprises a 1-measurement and control room switch box, a 2-test bench A, a 3-test bench B, a 4-test bench C, a 5-field wireless controller, a 6-bench power supply assembly, a 7-termination control unit, an 8-first electric valve, a 9-second electric valve, a 10-third electric valve, an 11-direct current output control unit, a 12-cable and a 13-cabin switch box.
Detailed Description
The invention will be described in further detail by means of the following detailed description and with reference to the accompanying drawings.
The invention provides a surplus test termination control device of a civil helicopter ground combined test bed, which is used for reliably terminating tests of the civil helicopter ground combined test bed in response to various special test conditions and guaranteeing the safety of a tester and field testers.
As shown in fig. 1-2, the application provides a surplus test termination control device of a ground combined test bed of a civil helicopter, which comprises a measurement and control room switch box 1, a field wireless controller 5, a rack power supply assembly 6, a termination control unit 7, a direct current output control unit 11 and a cockpit switch box 13, wherein:
the measurement and control room switch box 1 is connected with the termination control unit 7, the direct current output control unit 11 is connected with the cockpit switch box 13, the cockpit switch box 13 is connected with the termination control unit 7, the cockpit switch box 13 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10, and the termination control unit 7 is respectively connected with the first electric valve 8, the second electric valve 9 and the third electric valve 10; the field wireless controller 5 is connected to the termination control unit 7 by a wireless mode.
Specifically, the termination control unit 7 includes a relay a, a relay B, a relay C, a relay D, a relay E, a relay F, a wireless communication module, a connector a, and a connector B, where the relay a and the relay B are a set of relays, the relay C and the relay D are a set of relays, and the relay E and the relay F are a set of relays.
More specifically, the connection relationship between the relay a and the relay B is: the coil of the control relay A is connected with the f pin of the A connector of the termination control unit, the a pin of the A connector of the termination control unit is connected with the wireless module output terminal A, the B pin of the A connector of the termination control unit is connected with the contact A2 of the control relay 1, the contact A3 is connected with the a pin of the B aviation plug, the C pin of the A connector of the termination control unit is connected with the contact B2 of the control relay 1, the contact B3 is connected with the B pin of the B aviation plug, the contact A1 of the control relay B is connected at the same time, the d pin of the A connector of the termination control unit is connected with the contact C2 of the control relay A, the contact C1 of the control relay A is connected with the coil of the control relay B, the e pin of the A connector of the termination control unit is connected with the coil of the control relay A, B, the f pin of the A connector of the termination control unit is connected with the contact A2 of the control relay B, the g pin of the A connector of the termination control unit is connected with the contact B2 of the control relay B, the h pin of the contact of the A connector of the termination control unit is connected with the contact B2 of the control relay B, and the contact C1 of the contact C connector of the termination unit is connected with the contact B.
Specifically, the internal connection principle of the relay C and the relay D, the relay E and the relay F is the same as the connection relation between the relay a and the relay B, and the detailed internal connection relation can be referred to fig. 3.
It should be noted that, independent work does not influence each other between three sets of combination relays of termination control unit 7 for realize the effective independent control to power combination output under the different experimental operating mode, the wireless communication module of internal design can communicate and control with on-the-spot wireless controller, guarantees that on-the-spot ground observer can be quick effectual intervention treatment experimental unexpected condition.
Specifically, the rack power supply assembly 6 comprises a direct-current stabilized voltage supply, a 28V storage battery, a circuit breaker, a diode and a binding post; the rack power supply assembly 6 is used for providing stable direct current power supply input, and the rack power supply assembly 6 has dual-redundancy direct current input, so that the operation of the test termination device can be ensured not to be influenced by commercial power and airborne equipment; the circuit breaker is used for power supply line protection, and the protection current of circuit breaker is 10A, and the output terminal 1, the output wiring 2 of rack power supply module are connected with the A connector of termination control unit.
Specifically, the cockpit switch box 13 is mechanically mounted on the cockpit control panel, and the cockpit switch box 13 is provided with 37Q switches, 38Q switches, 39Q switches, wherein: the contacts A1 and A2 of the 37Q switch are connected with the pins a and b of the aviation plug A of the cockpit switch box, the contacts A1 and A2 of the 38Q switch are connected with the pins c and d of the aviation plug A of the cockpit switch box, and the contacts A1 and A2 of the 39Q switch are connected with the pins e and f of the aviation plug A of the cockpit switch box. The pins a, c and e of the A aviation plug of the cockpit switch box 13 are externally short-circuited by leads and then are respectively connected with the direct-current load output binding post 1; the switch state of the cockpit switch box 13 is normally closed, and the operation state is open.
In practical application, the cockpit switch box 13 is provided with a protective cover, so that false touching and false touching can be prevented.
Specifically, the inter-measurement and control switch box 1 is provided with a 34Q switch, a 35Q switch, and a 36Q switch, wherein: the contacts A2 and A3 of the 36Q switch are connected with the pins a and b of the A aviation plug of the measurement and control room switch box 1, the contacts A2 and A3 of the 36Q switch are connected with the pins c and d of the A aviation plug of the measurement and control room switch box 1, and the contacts A2 and A3 of the 37Q switch are connected with the pins e and f of the A aviation plug of the measurement and control room switch box 1.
Specifically, two ends of the indicator lamp L1 are respectively connected with g pins and h pins of the A aviation plug of the switch box 1 between measurement and control; two ends of the indicator lamp L2 are respectively connected with j pins and k pins of the A aviation plug of the switch box 1 between measurement and control; the two ends of the indicator lamp L3 are respectively connected with m pins and n pins of the A aviation plug of the switch box 1 between measurement and control.
Specifically, pins a, c and e of the A aviation plug of the measurement and control switch box 1 are externally short-circuited by leads and then are respectively connected with a direct current load output binding post 2, and pins a, c, d, g, j, m of the A aviation plug of the measurement and control switch box 1 are respectively connected with a, j, v, g, s, aa of the A aviation plug of the termination control unit; the 34Q switch, the 35Q switch and the 36Q switch are in a normally open state, and the working state is closed.
The switch types of the 34Q switch, the 35Q switch and the 36Q switch are resettable button switches, so that the operation of terminating the test can be completed rapidly in emergency.
All equipment in the device is grounded and connected with the testing machine, and the testing machine is grounded and connected with the bench.
In summary, the test device provided by the application is a redundancy test termination control device based on a civil helicopter ground combined test bed test design, and comprises: the system comprises a rack power supply assembly, a termination control unit, a measurement and control room switch box, a cockpit switch box, a field wireless controller, a direct current output control unit, an inter-equipment connecting cable and the like. The control room switch box is connected with the termination control unit through a cable, the direct current output control unit is connected with the cockpit switch box through a cable, the cockpit switch box is connected with the termination control unit through a cable, the on-site wireless controller is connected with the termination control unit through a wireless way, the cockpit switch box is connected with the first electric valve, the second electric valve and the third electric valve through cables, and the termination control unit is connected with the first electric valve, the second electric valve and the third electric valve through cables.
Under the condition that accident dangerous situations occur or the test needs to be stopped immediately in the test process, the power output can be stopped immediately through three different switch control boxes arranged on the device, and the operation of the testing machine is stopped. Experiments show that the test device can realize the termination test operation of redundancy, multiple directions and multiple persons, the operation can process special conditions according to set and divided levels, and the control logic is strict and correct, and the control mode is stable and reliable.
In summary, the surplus test termination control device of the civil helicopter ground combined test bed solves the problem of emergency risk avoidance in the test process, improves the dangerous situation processing capacity of test personnel, perfects the processing method of multiple persons, multiple directions and surplus, effectively ensures the safety and reliability of the civil helicopter ground combined test bed and the test personnel, and provides powerful guarantee for the ground combined test to be carried out smoothly.

Claims (8)

1. The utility model provides a civilian helicopter ground joint test bench redundancy test termination control device, its characterized in that, the device includes measurement and control room switch box (1), on-the-spot wireless controller (5), rack power supply unit (6), termination control unit (7), direct current output control unit (11), cockpit switch box (13), wherein:
the measurement and control room switch box (1) is connected with the termination control unit (7), the direct current output control unit (11) is connected with the cockpit switch box (13), the cockpit switch box (13) is connected with the termination control unit (7), the cockpit switch box (13) is respectively connected with the first electric valve (8), the second electric valve (9) and the third electric valve (10), and the termination control unit (7) is respectively connected with the first electric valve (8), the second electric valve (9) and the third electric valve (10); the on-site wireless controller (5) is connected with the termination control unit (7) through a wireless mode.
2. The device according to claim 1, characterized in that the termination control unit (7) comprises a relay a, a relay B, a relay C, a relay D, a relay E, a relay F, a wireless communication module and a connector a, a connector B, the relay a and the relay B being a set of relays, the relay C and the relay D being a set of relays, the relay E and the relay F being a set of relays.
3. The device according to claim 2, wherein the connection relationship between relay a and relay B is: the coil of the control relay A is connected with the coil of the control relay A by the pin a of the connector A of the termination control unit (7), the pin f of the connector A of the termination control unit (7) is connected with the output terminal A of the wireless module, the pin B of the connector A of the termination control unit (7) is connected with the coil A2 of the control relay 1, the pin A3 of the connector A of the termination control unit (7) is connected with the pin a of the control relay 1, the pin C of the connector A of the termination control unit (7) is connected with the pin B of the control relay 1, the pin d of the connector A of the termination control unit (7) is connected with the contact C2 of the control relay A, the pin C of the connector A of the control relay A is connected with the coil of the control relay B, the pin f of the connector A of the termination control unit (7) is connected with the pin f of the connector A of the control unit (7) is connected with the contact C2 of the control relay B (7), the pin f of the connector A of the connector of the control unit (7) is connected with the contact C2 of the control relay B is connected with the contact C1 of the contact B (7), and the pin B of the contact B is connected with the contact C2 of the contact (7) is connected with the contact C2 of the relay B.
4. The device according to claim 1, characterized in that the bench power supply assembly (6) comprises a direct current regulated power supply, a 28V battery, a circuit breaker, a diode, a terminal; the rack power supply assembly (6) is used for providing stable direct current power supply input, and the rack power supply assembly (6) has dual-redundancy direct current input, so that the operation of the test termination device can be ensured not to be influenced by commercial power and airborne equipment; the circuit breaker is used for power supply line protection, and the protection current of circuit breaker is 10A, and output terminal 1, the output wiring 2 of rack power supply module (6) are connected with the A connector of termination control unit.
5. The device according to claim 1, characterized in that the cockpit switch box (13) is mechanically mounted on the cockpit control panel, the cockpit switch box (13) being provided with a 37Q switch, a 38Q switch, a 39Q switch, wherein: the contacts A1 and A2 of the 37Q switch are connected with the pins a and b of the A aviation plug of the cockpit switch box (13), the contacts A1 and A2 of the 38Q switch are connected with the pins c and d of the A aviation plug of the cockpit switch box (13), and the contacts A1 and A2 of the 39Q switch are connected with the pins e and f of the A aviation plug of the cockpit switch box (13); pins a, c and e of the A aviation plug of the cockpit switch box (13) are externally short-circuited by leads and then are respectively connected with the direct current load output binding post 1; the switch state of the cockpit switch box (13) is a normally closed state, and the working state is an open state.
6. The device according to claim 1, characterized in that the inter-measurement and control switch box (1) is provided with 34Q switch, 35Q switch, 36Q switch, wherein: the contacts A2 and A3 of the 36Q switch are connected with the pins a and b of the A aviation plug of the measurement and control room switch box (1), the contacts A2 and A3 of the 36Q switch are connected with the pins c and d of the A aviation plug of the measurement and control room switch box (1), and the contacts A2 and A3 of the 37Q switch are connected with the pins e and f of the A aviation plug of the measurement and control room switch box (1).
7. The device according to claim 1, wherein the two ends of the indicator light L1 are respectively connected with g and h pins of an a aviation plug of the switch box (1) between measurement and control; two ends of the indicator lamp L2 are respectively connected with j and k pins of the A aviation plug of the switch box (1) between measurement and control; the two ends of the indicator lamp L3 are respectively connected with m pins and n pins of the A aviation plug of the switch box (1) between measurement and control.
8. The device according to claim 1, characterized in that the pins a, c and e of the a-aviation plug of the inter-measurement and control switch box (1) are externally short-circuited by leads and then respectively connected with the binding post 2 of the direct current load output control unit (11), and the pins a, c, d, g, j, m of the a-aviation plug of the inter-measurement and control switch box (1) are respectively connected with the a, j, v, g, s, aa of the a-aviation plug of the termination control unit (7); the 34Q switch, the 35Q switch and the 36Q switch are in a normally open state, and the working state is closed.
CN202311507216.2A 2023-11-13 2023-11-13 Control device is terminated in civilian helicopter ground joint test bench redundancy test Pending CN117401183A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202311507216.2A CN117401183A (en) 2023-11-13 2023-11-13 Control device is terminated in civilian helicopter ground joint test bench redundancy test

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202311507216.2A CN117401183A (en) 2023-11-13 2023-11-13 Control device is terminated in civilian helicopter ground joint test bench redundancy test

Publications (1)

Publication Number Publication Date
CN117401183A true CN117401183A (en) 2024-01-16

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ID=89494367

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202311507216.2A Pending CN117401183A (en) 2023-11-13 2023-11-13 Control device is terminated in civilian helicopter ground joint test bench redundancy test

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