A general aircraft electrical control device

Abstract

The present invention discloses a general aircraft electrical control device, comprising: a plurality of diodes, a plurality of DC contactors, a plurality of DC electromagnetic relays, a grounding module, a cover plate, a box body, a support, and a connector; wherein the diodes, DC contactors, DC electromagnetic relays and grounding module are fixed in the box body by fasteners, the cover plate and the box body constitute the outer shell of the electrical control box, the outer shell has a support connected to the aircraft body, and the cables led out of the diodes, DC contactors and DC electromagnetic relays are connected to the cables of other systems on the body through the connector on the outer shell. The present invention can realize the functions of low voltage alarm of the generator, signal control of landing gear retraction and extension, and control of landing gear electric hydraulic pump, and meet the use requirements of the aircraft. By adding contactors or relays, the functions of flap control and alarm bell stopping can be realized. It has good applicability and is also easy to maintain.

Description

Technical Field

[0001] The present invention relates to the field of aircraft control technology, and more particularly to a general aircraft electrical control device. Background Art

[0002] With the continuous development of aviation technology, various components and equipment on aircraft are becoming more and more complex and sophisticated, especially the electrical control system, whose importance is becoming increasingly prominent. The electrical control box on the aircraft is an important component for realizing the functions of the electrical control system.

[0003] The electrical control box is based on the needs of electrical equipment. Some electrical components such as relays, contactors, fuses, diodes, etc. that control the operation of the equipment are integrated into the control box according to certain control logic to realize the control of the electrical system (for example: flap control system, landing gear retraction and extension signal control, generator mortgage alarm, etc.). Assembling these electrical components into a closed control box can effectively prevent dust, water and shock, and can work normally under harsh environmental conditions.

[0004] The publication number is CN105000172A, and the name is aircraft landing gear retraction and extension pneumatic control system, which includes a landing gear control switch, a display, a plurality of position sensors, an electromechanical management computer, a power drive device, a landing gear hydraulic valve, a guard plate hydraulic valve, a landing gear mechanism and a guard plate mechanism. After the electromechanical management computer receives the retraction and extension command of the landing gear control switch, it collects feedback signals from position sensors installed on the landing gear mechanism and the guard plate mechanism, and outputs corresponding control signals to the power drive device according to logic, thereby controlling the reversing of the landing gear hydraulic valve and the guard plate hydraulic valve to achieve normal retraction and extension of the landing gear mechanism and the guard plate mechanism. At the same time, the electromechanical management computer monitors the status of the landing gear and the guard plate in real time, and sends their position status and fault alarm information to the display.

[0005] The publication number is CN103303463A, and the name is an electrical control method for aircraft flaps. Specifically, it is a flap electrical control method for introducing feedback to form a closed-loop control. Specifically, it is about adopting closed-loop electrical control, and its control component, in addition to marking the scale, also sets mechanical slots or blocks at the corresponding positions according to the several fixed positions used by the flaps. The pilot places the handle on the control component in the corresponding position or slot, and no longer needs to pay attention to the entire retraction and extension process of the flaps. The control component will send the flap retraction and extension position instructions to the computer, and the computer will combine the flap position provided by the position feedback component to accurately drive the actuator to drive the flap to the required position.

[0006] Existing aircraft electrical control devices are all for single equipment components and cannot achieve integrated unified control. They cannot simultaneously realize functions such as generator low voltage alarm, landing gear retraction and extension signal control, and landing gear electric hydraulic pump control, and cannot adapt to the electrical control systems of different models of aircraft.

[0007] Therefore, how to provide an electrical control box with a suitable logic control circuit is a problem that those skilled in the art need to solve urgently. Summary of the invention

[0008] In view of this, the present invention provides a universal aircraft electrical control device, aiming to solve the technical problem that the existing aircraft electrical control devices are all for a single equipment component, cannot achieve integrated unified control, cannot simultaneously realize the functions of generator low voltage alarm, landing gear retraction and extension signal control, landing gear electric hydraulic pump control, etc., and cannot adapt to the electrical control systems of different models of aircraft.

[0009] In order to achieve the above object, the present invention adopts the following technical solution:

[0010] A general aircraft electrical control device, comprising:

[0011] Multiple diodes, multiple DC contactors, multiple DC electromagnetic relays, grounding modules, covers, boxes, supports, connectors;

[0012] The diode, DC contactor, DC electromagnetic relay and grounding module are fixed in the box body by fasteners; the cover plate and the box body constitute the outer shell of the electrical control box; the outer shell is provided with a support member connected to the aircraft body; the cables led out of the diode, DC contactor and DC electromagnetic relay are connected to the cables of other systems on the aircraft body through the connector on the outer shell.

[0013] Furthermore, the grounding module is electrically connected to the connector, the wire dead joint is electrically connected to the connector after being connected in parallel with the first DC contactor, a plurality of the wire dead joints, the second DC contactor, the third DC contactor and the fourth DC contactor are connected in parallel with the connector, the first diode is electrically connected to interface 1 and interface 2 of the first normally open DC electromagnetic relay, the first normally open DC electromagnetic relay is electrically connected to the connector, the wire dead joint, the second diode and the third diode are electrically connected to the connector after being connected in parallel, the fourth diode is electrically connected to interface 1 and interface 2 of the second normally open DC electromagnetic relay, and the second normally open DC electromagnetic relay is electrically connected to the connector.

[0014] Furthermore, the fourth DC contactor, the second diode and the third diode are connected to an external main control device circuit to realize the function of controlling the low voltage alarm of the generator.

[0015] Furthermore, the first DC contactor, the second DC contactor, the second normally open DC electromagnetic relay and the fourth diode are connected to an external electric hydraulic pump, a switch, a landing gear signal light box, an annunciator and a corresponding micro switch to realize the function of the electric hydraulic pump controlling the retraction of the landing gear.

[0016] Furthermore, the third DC contactor, the first normally open DC electromagnetic relay and the first diode are connected to an external electric hydraulic pump, a switch, a landing gear signal light box and related micro switches to realize the function of the electric hydraulic pump controlling the lowering of the landing gear.

[0017] Furthermore, the electrical control box also includes additional DC contactors, DC electromagnetic relays and diodes for flap control and warning bell stopping functions.

[0018] Furthermore, the electrical control box is used to be installed in an electrical control system of a general aircraft.

[0019] The above technical solution includes at least the following technical effects:

[0020] The present invention discloses a novel general-purpose aircraft electrical control device. Compared with the prior art, the present invention can realize the functions of generator low voltage alarm, landing gear retraction and extension signal control, landing gear electric hydraulic pump control, etc., and meet the use requirements of the aircraft. The electrical control box can also be adjusted as needed, and by adding contactors or relays, flap control, alarm bell stop and other functions can be realized. The electrical control box can also be applied to other general-purpose aircraft, has good applicability, and is also easy to maintain. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying creative work.

[0022] Figure 1 The present invention is a schematic diagram of an internal circuit structure.

[0023] Figure 2 The figure is a schematic structural diagram of an appearance of the present invention.

[0024] Among them, 1 is a grounding module, 2 is a wire dead joint, 3 is a first DC contactor, 4 is a second DC contactor, 5 is a third DC contactor, 6 is a fourth DC contactor, 7 is a first normally open DC electromagnetic relay, 8 is a second normally open DC electromagnetic relay, 9 is a first diode, 10 is a second diode, 11 is a third diode, 12 is a fourth diode, 13 is a connector, 14 is a cover plate, 15 is a box body, and 16 is a support. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] A general aircraft electrical control device, comprising:

[0027] A plurality of diodes, a plurality of DC contactors, a plurality of DC electromagnetic relays, a grounding module 1, a cover plate 14, a box body 15, a support member 16, and a connector 13;

[0028] Among them, the diode, DC contactor, DC electromagnetic relay and grounding module 1 are fixed in the box body 15 by fasteners, the cover plate 14 and the box body 15 constitute the shell of the electrical control box, and the shell is provided with a support 16, which is connected to the aircraft body. The cables led out of the diode, DC contactor and DC electromagnetic relay are connected to the cables of other systems on the body through the connector 13 on the shell.

[0029] To further optimize the above technical solution, the grounding module 1 is electrically connected to the connector 13, the wire dead joint 2 is electrically connected to the first DC contactor 3 after being connected in parallel, multiple wire dead joints 2, the second DC contactor 4, the third DC contactor 5 and the fourth DC contactor 6 are connected in parallel and connected to the connector 13, the first diode 9 is electrically connected to the interface 1 and the interface 2 of the first normally open DC electromagnetic relay 7, the first normally open DC electromagnetic relay 7 is electrically connected to the connector 13, the wire dead joint 2, the second diode 10 and the third diode 11 are electrically connected to the connector 13 after being connected in parallel, the fourth diode 12 is electrically connected to the interface 1 and the interface 2 of the second normally open DC electromagnetic relay 8, and the second normally open DC electromagnetic relay 8 is electrically connected to the connector 13.

[0030] To further optimize the above technical solution, the fourth DC contactor 6, the second diode 10 and the third diode 11 are connected to the external main control device circuit to realize the function of controlling the low voltage alarm of the generator.

[0031] To further optimize the above technical solution, the first DC contactor 3, the second DC contactor 4, the second normally open DC electromagnetic relay 8 and the fourth diode 12 are connected to the external electric hydraulic pump, switch, landing gear signal light box, signal device and corresponding micro switch to realize the function of the electric hydraulic pump controlling the retraction of the landing gear.

[0032] To further optimize the above technical solution, the third DC contactor 5, the first normally open DC electromagnetic relay 7 and the first diode 9 are connected to the external electric hydraulic pump, switch, landing gear signal light box and related micro switches to realize the function of the electric hydraulic pump controlling the landing gear to be lowered.

[0033] To further optimize the above technical solution, the electrical control box also includes additional DC contactors, DC electromagnetic relays and diodes for flap control and warning bell stopping functions.

[0034] To further optimize the above technical solution, the electrical control box is used to be installed in the electrical control system of a general aircraft.

[0035] See attached Figure 1-2 The embodiment of the present invention discloses a novel general aircraft electrical control device, comprising:

[0036] like Figure 1 As shown, a schematic diagram of the structure of an electrical control box is disclosed, including a box body 15 and a top cover 16. Support members 16 are arranged around the box body 15, and interfaces are arranged on the side walls of the box body. The box body is fixedly connected to the aircraft body through the support members 16. An electrical control circuit is fixedly arranged in the box body 15, and the electrical control circuit is connected to the main control circuit of the aircraft through the interface. The support member 16 is an L-shaped structural member, and one side of the L-shaped structural member is fixed to the side wall of the box body 15 by bolts, and the other side is fixed to the aircraft body by bolts.

[0037] In this embodiment, if Figure 2 As shown, the fourth DC contactor 6, the second diode 10 and the third diode 11 cooperate with the external main control device circuit to realize the function of controlling the low-voltage alarm of the generator. Normally, the generator switch is not turned on and the generator low-voltage alarm is displayed; when the generator switch is turned on, the fourth DC contactor 6 is activated and the low-voltage alarm of the generator is released.

[0038] The first DC contactor 3, the second DC contactor 4, the second normally open DC electromagnetic relay 8 and the fourth diode 12 cooperate with the external electric hydraulic pump, switch, landing gear signal light box, signal device and corresponding micro switch to realize the function of the electric hydraulic pump controlling the landing gear to be retracted. The first DC contactor 3, the second DC contactor 4 and the second normally open DC electromagnetic relay 8 are actuated, the electric hydraulic pump controls the landing gear to be retracted, and at the same time the landing gear signal light box lights up to indicate the state of the landing gear.

[0039] The third DC contactor 5, the first normally open DC electromagnetic relay 7 and the first diode 9 cooperate with the external electric hydraulic pump, switch, landing gear signal light box and related micro switches to realize the function of the electric hydraulic pump controlling the landing gear to be lowered. The third DC contactor 5 and the first normally open DC electromagnetic relay 7 are activated, the electric hydraulic pump controls the landing gear to be lowered, and the landing gear signal light box lights up at the same time to indicate the state of the landing gear.

[0040] 1. System composition and principle

[0041] The generator low voltage warning function is an important component of the aircraft electrical control system. Its main purpose is to warn the pilot when the generator is working abnormally and the voltage is lower than the preset safety value to ensure flight safety. This function is mainly composed of the fourth DC contactor 6, the second diode 10 and the third diode 11, which are connected to the external main control device circuit.

[0042] The fourth DC contactor 6: as a control element, is responsible for closing the circuit and cutting off the alarm signal when the generator voltage is normal.

[0043] The second diode 10 and the third diode 11 are protection elements to prevent the reverse current from damaging the circuit and provide an alarm signal when the voltage is abnormal.

[0044] 2. Electrical connection and configuration

[0045] In the electrical control box, the fourth DC contactor 6 is fixed in the box body 15 by fasteners, and its pins are connected to the external main control device circuit through wires. The second diode 10 and the third diode 11 are also fixed in the box body and connected to the fourth DC contactor 6 and the connector 13 through wires.

[0046] Wire dead connector 2: connected in parallel with the fourth DC contactor 6 to ensure that when the contactor fails to work due to a fault, the circuit can still be turned on to maintain the basic alarm function.

[0047] Connector 13: Located on the outer shell of the electrical control box, used to connect the internal circuit with the cables of other systems on the aircraft body.

[0048] 3. Control logic and process

[0049] When the generator operates normally and the voltage is maintained within a safe range, the fourth DC contactor 6 is closed, and the current in the circuit flows through the contactor, so that the second diode 10 and the third diode 11 are not conducting, and the alarm signal will not be triggered. If the generator voltage drops below the preset low voltage alarm threshold, the fourth DC contactor 6 will remain open, and the current will flow to the second diode 10 and the third diode 11, triggering the alarm signal.

[0050] Alarm signal triggering condition: generator voltage is lower than the preset value.

[0051] Conditions for releasing the alarm signal: the generator voltage returns to the normal range and the fourth DC contactor 6 is closed.

[0052] 4. Signal display and feedback

[0053] The warning signal is displayed to the pilot through the aircraft's display or other indicating equipment. This may include but is not limited to warning lights, warning messages on the instrument panel, or sound alarms. After receiving the warning signal, the pilot needs to check the generator status and take appropriate measures, such as switching to backup power or making an emergency landing.

[0054] Display: Displays detailed information of generator low voltage alarm, such as voltage value, alarm time, etc.

[0055] Sound alarm: Sounds when the warning signal is triggered to attract the pilot's attention.

[0056] 5. System testing and verification

[0057] During the aircraft maintenance and testing phase, the generator low voltage warning function needs to be verified to ensure that it can work reliably under various voltage conditions.

[0058] Simulation test: By simulating different voltage conditions, verify whether the response of contactors and diodes meets the design requirements.

[0059] Actual flight test: During a safe flight test, the generator voltage is gradually reduced to observe the response of the warning system.

[0060] 6. Fault diagnosis and maintenance

[0061] The design of the electrical control box allows for quick diagnosis and maintenance. If the alarm system fails to work as expected, troubleshooting can be performed by checking the status of the contactors and diodes, and verifying that the wire connections are secure.

[0062] Contactor inspection: Check whether the fourth DC contactor 6 can be closed and opened normally.

[0063] Diode inspection: Check whether the second diode 10 and the third diode 11 show signs of damage or aging.

[0064] Wire inspection: Check whether all relevant wires are firmly connected and whether there is a short circuit or open circuit.

[0065] 7. Safety and reliability considerations

[0066] When designing the low voltage alarm function of the generator, safety and reliability are the most important considerations. The system must be able to work stably in various extreme environments, including high temperature, low temperature, vibration, etc.

[0067] Environmental adaptability: The electrical control box and its internal components must be able to withstand the various environmental conditions that the aircraft may encounter during flight.

[0068] Redundant design: By connecting 2 wires in parallel and using multiple diodes, the redundancy of the system is increased and the reliability of the system is improved.

[0069] A new type of general aircraft electrical control device designed according to the present invention can realize the functions of generator low voltage alarm, landing gear retraction and extension signal control, landing gear electric hydraulic pump control, etc., and meet the use requirements of the aircraft. The electrical control box can also be adjusted as needed, and by adding contactors or relays, flap control, alarm bell stop and other functions can be realized. The electrical control box can also be applied to other general aircraft, has good applicability, is easy to maintain, and has great application value.

[0070] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0071] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A general aircraft electrical control device, characterized in that: include: A plurality of diodes, a plurality of DC contactors, a plurality of DC electromagnetic relays, a grounding module (1), a cover plate (14), a box body (15), a support member (16), and a connector (13); The diode, DC contactor, DC electromagnetic relay and grounding module (1) are fixed in the box body (15) by fasteners; the cover plate (14) and the box body (15) constitute the outer shell of the electrical control box; the outer shell is provided with a support member (16) connected to the aircraft body; the cables led out of the diode, DC contactor and DC electromagnetic relay are connected to the cables of other systems on the aircraft body through the connector (13) on the outer shell.

2. A general aircraft electrical control device according to claim 1, characterized in that: The grounding module (1) is electrically connected to the connector (13); the wire dead joint (2) is electrically connected to the connector (13) after being connected in parallel with the first DC contactor (3); a plurality of the wire dead joints (2), the second DC contactor (4), the third DC contactor (5) and the fourth DC contactor (6) are electrically connected to the connector (13); a first diode (9) is electrically connected to an interface 1 and an interface 2 of a first normally open DC electromagnetic relay (7); the first normally open DC electromagnetic relay (7) is electrically connected to the connector (13); the wire dead joint (2), the second diode (10) and the third diode (11) are electrically connected to the connector (13) after being connected in parallel; a fourth diode (12) is electrically connected to an interface 1 and an interface 2 of a second normally open DC electromagnetic relay (8); the second normally open DC electromagnetic relay (8) is electrically connected to the connector (13).

3. A general aircraft electrical control device according to claim 2, characterized in that: The fourth DC contactor (6), the second diode (10) and the third diode (11) are connected to an external main control device circuit to realize the function of controlling the low voltage alarm of the generator.

4. A general aircraft electrical control device according to claim 2, characterized in that: The first DC contactor (3), the second DC contactor (4), the second normally open DC electromagnetic relay (8) and the fourth diode (12) are connected to an external electric hydraulic pump, a switch, a landing gear signal light box, a signal device and a corresponding micro switch, so as to realize the function of controlling the retraction of the landing gear by the electric hydraulic pump.

5. A general aircraft electrical control device according to claim 2, characterized in that: The third DC contactor (5), the first normally open DC electromagnetic relay (7) and the first diode (9) are connected to an external electric hydraulic pump, a switch, a landing gear signal light box and related micro switches to realize the function of the electric hydraulic pump controlling the lowering of the landing gear.

6. A general aircraft electrical control device according to claim 1, characterized in that: The electrical control box also includes additional DC contactors, DC electromagnetic relays and diodes for flap control and warning bell deactivation functions.

7. A general aircraft electrical control device according to claim 1, characterized in that: The electrical control box is used for being installed in an electrical control system of a general aircraft.

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