Amphibious aircraft propeller forward and return control system and control method

Abstract

The invention belongs to the field of propeller control system design, and relates to an amphibious aircraft propeller forward and return control system and a control method, the amphibious aircraft propeller forward and return control system comprises a feathering relay box, a manual forward and return control assembly, a feathering timer, a feathering pump and an engine accessory; the manual feathering control assembly is connected with the feathering relay box and the feathering timer, the manual feathering control assembly sends manual feathering operation signals and manual feathering operation signals to the feathering relay box, and the feathering relay box conducts manual feathering control or manual feathering control on the feathering pump according to the manual feathering operation signals and the manual feathering operation signals. Meanwhile, the manual feathering control assembly receives a control signal of the feathering timer, and during feathering control, a manual feathering operation signal is kept for a certain time and then is automatically cut off; the feathering relay box is connected with an engine accessory, and performs automatic feathering control on the feathering pump according to an automatic feathering state signal sent by the engine accessory; the feathering timer receives manual feathering or automatic feathering signals sent by the feathering relay box to perform sequential control, and outputs control signals to a feathering relay in the feathering relay box and a feathering switch holding relay in the manual feathering and returning control assembly to complete time control of the feathering control circuit.

Description

Technical Field

[0001] This invention belongs to the field of propeller control system design, specifically relating to a propeller control system and control method for amphibious aircraft. Background Technology

[0002] As an important subsystem of the propeller control system, the propeller feathering system ensures that the aircraft maintains minimal drag along the flight direction during flight by performing manual feathering, manual retardation, automatic torque feathering, and automatic negative thrust feathering control of the propeller in a timely manner. In other words, it matches the shutdown control required by the aircraft in the event of an engine failure with the propeller status, thereby ensuring flight safety.

[0003] Currently, the propeller control systems commonly used in certain types of engines employ either fully electro-hydraulic or electromechanical control. While their principles are reliable and their operation is simple, they suffer from the following problems:

[0004] The control timing for automatic and manual feathering employs a mechatronic control system. Timing control relies on the constant-speed DC motor of the internal centrifugal governor and the mechanical mounting position of the cams. Signal triggering depends on microswitches. Mechanical performance degradation caused by cam mounting errors and wear can affect the reliability and control accuracy of the equipment. In the typical operating environment of amphibious aircraft, the contacts of the microswitches and motor are prone to oxidation and corrosion, reducing the reliability and lifespan of the equipment. Furthermore, there are issues with electromagnetic interference and the low accuracy of control timing due to manual assembly and adjustment. All of these factors negatively impact the reliability and safety of the aircraft's feathering control.

[0005] Meanwhile, the original propeller return switch used a mechanical pull / push handle with a spring and electromagnet. It was large and the handle was long. When it was installed on the control panel on the top of the cockpit, it would obstruct the pilot's view and movement when operating other buttons and components. The protruding handle caused inconvenience and collision risk for the pilot when getting in and out of the seat. Moreover, when returning the propeller, the pilot had to overcome the attraction of the electromagnet to pull out the handle, which added to the pilot's operational burden.

[0006] The relays and contactors used for manual feathering, automatic feathering, manual swivel, and fault indicator electrical control on aircraft are distributed in a dispersed manner, which makes them less adaptable to the special operating environment of amphibious aircraft and cannot guarantee system reliability and aircraft safety. Summary of the Invention

[0007] The purpose of this invention is to propose a control system and method for the catadioptric propeller of a large amphibious aircraft. This invention can solve the problems of poor adaptability of distributed electrical control components to the special operating environment of this type of aircraft, serious electromagnetic interference from the original automatic catadioptric timer, low accuracy of control signals, low reliability, low maintainability, inconvenient operation of the control handle and obstruction of the pilot. Furthermore, the timing control logic is changed from mechanical and electrical control to microprocessor and software implementation, which greatly improves the system reliability and environmental adaptability while reducing the weight of the equipment.

[0008] The technical solution of the present invention:

[0009] A control system for a feathering propeller of an amphibious aircraft includes a feathering relay box, a manual feathering control component, a feathering timer, a feathering pump, and engine accessories;

[0010] The manual back pitch control component is connected to the pitch relay box and the pitch timer. The manual back pitch control component sends manual back pitch and manual pitch operation signals to the pitch relay box. The pitch relay box performs manual back pitch control or manual pitch control on the pitch pump according to the manual back pitch and manual pitch operation signals. At the same time, the manual back pitch control component receives the control signal of the pitch timer. When performing pitch control, the manual pitch operation signal is held for a certain period of time and then automatically cut off.

[0011] The feathering relay box is connected to the engine accessory and automatically feathers the feathering pump according to the automatic feathering status signal sent by the engine accessory.

[0012] The feathering timer receives manual or automatic feathering signals from the feathering relay box and performs timing control. The output control signal of the feathering timer is sent to the feathering relay in the feathering relay box and the feathering switch holding relay in the manual backflip control component to complete the timing control of the feathering control circuit.

[0013] Furthermore, the system also includes a remote data concentrator, which is connected to both the feathering relay box and the feathering timer. The remote data concentrator receives feathering pump operating signals through the feathering relay box and simultaneously receives fault signals sent by the feathering timer for status recording and display.

[0014] Furthermore, the feathering relay box includes a feathering pump contactor K1, a feathering relay J1, a fault light relay J3, and a return feathering relay J4. One end of the contact of the feathering pump contactor K1 is connected to the feathering pump, and the other end is connected to the emergency busbar. One end of the coil of the feathering pump contactor K1 is grounded, and the other end is connected to one end of contact group 1 of the feathering relay J1, one end of the return feathering button in the manual feathering control assembly, and one end of the contact of the feathering switch holding relay J2. The coil of the feathering relay J1 is connected in parallel with the coil of the fault light relay J3. The other end of contact group 1 of the feathering relay J1 is connected to one end of contact group 1 of the return feathering relay J4. One end of contact group 2 of paddle relay J1 is connected to one end of contact group 3 of feather relay J1, and the other end of contact group 2 of feather relay J1 is connected to one end of contact group 2 of return relay J4. The other end of contact group 3 of feather relay J1 is connected to the coils of feather relay J1 and fault light relay J3. The other ends of contact groups 1 and 2 of return relay J4 are both connected to the emergency busbar. One end of the coil of return relay J4 is grounded, and the other end is connected to the return button in the manual return control component. One end of the contact of fault light relay J3 is connected to the emergency busbar, and the other end is connected to the fault light in the manual return control component.

[0015] Furthermore, the manual return propeller control component includes a return propeller button, a feather propeller button, and a feather propeller switch holding relay J2;

[0016] The return-to-propeller button has two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to the coil of the return-to-propeller relay J4, and the other end of the other contact is connected to the coil of the feather pump contactor K1 and the contact group 1 of the feather relay J1.

[0017] The feathering button includes two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to one contact of the feathering switch holding relay J2, and the other end of the other contact is connected to the coil of the feathering switch holding relay J2 and contact group 2 and contact group 3 of the feathering relay J1. The other end of the contact of the feathering switch holding relay J2 is connected to the coil of the feathering pump contactor K1 and contact group 1 of the feathering relay J1.

[0018] Furthermore, the control signal output terminal of the feathering timer is connected to one end of the coil of the feathering switch holding relay J2, the coil of the feathering relay J1, and the coil of the fault light relay J3, respectively; the feathering signal receiving terminal of the feathering timer is connected to the other end of the coil of the feathering switch holding relay J2, contact group 2 of the feathering relay J1, and contact group 3 of the feathering relay J1, respectively.

[0019] Furthermore, the coils of the engine accessories are connected to the rotor relay J1 and the fault light relay J3.

[0020] Furthermore, the feathering timer includes an electrical connector, a lightning protection filter component, and a control board component; the electrical connector is used to transmit electrical signals between the power system, the feathering relay box, the manual zigzag control component, and the remote data concentrator; the lightning protection filter component is connected to the electrical connector and the control board component to filter the input signal and provide lightning protection, and to suppress surges in the output signal.

[0021] Furthermore, the lightning protection filtering component includes a lightning protection circuit, a surge suppression circuit, and a filtering circuit. It filters the input power ground signal, provides lightning protection for the input manual or automatic feathering signal, the 28V power supply, and the output control signal, and suppresses the output fault reporting signal and the output control signal.

[0022] The control board assembly includes a signal acquisition circuit, a power conversion circuit, a control circuit, a power output circuit, and a fault reporting circuit. The signal acquisition circuit acquires and processes the input manual or automatic feathering signals and sends them to the control circuit as input conditions for program judgment. The power conversion circuit performs secondary conversion on the 28V power supply to become internal working power supplies of 5V and 3.3V. The power output circuit converts the signal output by the processor into a ground / open control signal and outputs it through an electrical connector. The control circuit completes logic calculation, status judgment, periodic self-monitoring, and fault judgment. The fault reporting circuit reports faults existing in the control circuit.

[0023] A control method for the propeller feathering and revving control system of an amphibious aircraft includes: a feathering control method and a revving control method, wherein the feathering control method includes an automatic feathering control method and a manual feathering control method, and the revving control method includes a manual revving control method.

[0024] The automatic feathering control method is as follows:

[0025] The feathering relay box sends an automatic feathering signal to the feathering timer. The control signal at the output of the feathering timer is a ground signal. The feathering relay box receives two electrical signals to complete the automatic feathering operation control. One electrical signal is the torque automatic feathering signal from the engine accessory. When this torque automatic feathering signal enters the feathering relay box, the coils of feathering relay J1 and malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of feathering relay J1 are all closed, and the contacts of malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to feathering pump contactor K1 through contact groups 1 and 2 of feathering relay J4. The contacts of feathering pump contactor K1 are energized, and the emergency busbar supplies power to the feathering pump through the contacts of feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of malfunction indicator lamp relay J3. At this time, feathering relay J1, malfunction indicator lamp relay J3, and feathering pump contactor K1 are all working, the aircraft engine stops, and the propeller feathers simultaneously.

[0026] The other electrical signal is the negative pull high signal from the engine accessory. When this signal enters the feathering relay box, the coils of feathering relay J1 and malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of feathering relay J1 are all closed, and the contacts of malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to feathering pump contactor K1 through contact groups 1 and 2 of feathering relay J4. The contacts of feathering pump contactor K1 are energized, and the emergency busbar supplies power to the feathering pump through the contacts of feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of malfunction indicator lamp relay J3. At this time, feathering relay J1, malfunction indicator lamp relay J3, and feathering pump contactor K1 are all working, the aircraft engine stops, and the propeller feathers simultaneously.

[0027] The feathering relay box outputs a working status signal to a remote data concentrator for indicating and storing the working status of the feathering pump on the aircraft.

[0028] The manual feathering control method is as follows: The feathering relay box sends a manual feathering signal to the feathering timer, and the control signal at the output of the feathering timer is a ground signal; when the feathering button switch is closed, one contact of the feathering button supplies power to one end of the coil of the feathering switch holding relay J2, the control output of the feathering timer outputs a ground signal, the contacts of the feathering switch holding relay J2 are closed, and the emergency busbar supplies power to the feathering pump contactor K1 through the other contact of the feathering button. The coil of the feathering pump contactor K1 is energized, and the contacts of the feathering pump contactor K1... When the contact point is closed, the emergency busbar supplies power to the feather pump through the contacts of the propeller pump contactor K1, and manual feathering control is performed through the feather pump. At this time, since there is no signal input to the feather relay J1 and the fault light relay J3, the coils of the feather relay J1 and the fault light relay J3 are not energized. The contact groups 1, 2, and 3 of the feather relay J1 and the fault light relay J3 are all open. The feather relay J1 and the fault light relay J3 do not work. Only the feather pump contactor K1 works, the aircraft engine stops and the propeller feathers simultaneously.

[0029] The feathering relay box outputs a working status signal to a remote data concentrator for indicating and storing the working status of the feathering pump on the aircraft.

[0030] Manual backspin control method:

[0031] After the automatic and manual feathering control processes are completed, the control signal at the output of the feathering timer is an open signal. When the rotor needs to return to its original position, the rotor return button switch is closed. One contact of the rotor return button supplies power to the coil of the rotor return relay J4. Contact groups 1 and 2 of the rotor return relay J4 are open. At the same time, since there is no signal input to the feathering relay J1 and the fault light relay J3, the coils of the feathering relay J1 and the fault light relay J3 are not energized. Contact groups 1, 2, and 3 of the feathering relay J1 and the fault light relay J3 are all open. The feathering relay J1 and the fault light relay J3 do not work. The other contact of the rotor return button supplies power to the coil of the feathering pump contactor K1. The aircraft engine stops and the propeller returns to its original position.

[0032] The feathering relay box outputs a working status signal to a remote data concentrator for indicating and storing the working status of the feathering pump on the aircraft.

[0033] The beneficial effects of this invention are:

[0034] This invention provides a control system and method for a large amphibious aircraft's feathering propeller. The timing program of the feathering system is controlled by electronic equipment, solving the problem of low system reliability caused by the low stability of components in electrical and mechanical controls. The new equipment, developed based on the expected operating environment of the amphibious aircraft, improves the system's environmental adaptability, reliability, and safety. Software control output improves control precision, and the system possesses self-monitoring capabilities, facilitating fault reporting and isolation, and effectively shortening aircraft maintenance time. The system output signals are displayed centrally, improving the scientific nature of the human-machine interface and enhancing the ease of operation for pilots and ground maintenance personnel. The miniaturization of the control components reduces the pilot's workload, eliminates spatial obstruction and related safety hazards, and also reduces system weight. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the structure of the propeller control system for a large amphibious aircraft provided by the present invention.

[0036] Figure 2 This is a schematic diagram of the structure of the feathering timer provided by the present invention;

[0037] Figure 3 This is a schematic diagram of the internal circuit structure of the propeller return control system for a large amphibious aircraft provided by the present invention.

[0038] Explanation of reference numerals in the attached figures:

[0039] 1—Electrical connector; 2—Surge protection filter assembly; 3—Control board assembly;

[0040] 101—Feeder relay box; 102—Manual featherer control assembly; 103—Feeder timer;

[0041] 104—Pitch pump; 105—Remote data concentrator; 106—Engine accessories;

[0042] K1—Feed pump contactor; J1—Feed relay; J2—Feed switch holding relay;

[0043] J3—Fault light relay; J4—Return propeller relay; Detailed Implementation

[0044] The following description of embodiments provides a more detailed explanation of the specific implementation of the present invention, including the shape and structure of each component, the relative positions and connections between the parts, the function and working principle of each part, the manufacturing process, and the operation and use methods, in order to help those skilled in the art to have a more complete, accurate, and in-depth understanding of the concept and technical solution of the present invention.

[0045] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0046] The first embodiment of the present invention provides a control system for the catenary propeller of an amphibious aircraft, characterized in that it includes a catenary relay box 101, a manual catenary control component 102, a catenary timer 103, a catenary pump 104, a remote data concentrator 105, and an engine accessory 106.

[0047] The manual back pitch control component 102 is connected to the feathering relay box 101 and the feathering timer 103. The manual back pitch control component 102 sends manual back pitch and manual feathering operation signals to the feathering relay box 101. The feathering relay box 101 performs manual back pitch control or manual feathering control on the feathering pump 104 according to the manual back pitch and manual feathering operation signals. At the same time, the manual back pitch control component 102 receives the control signal from the feathering timer 103. When performing feathering control, the manual feathering operation signal is held for a certain period of time and then automatically cut off.

[0048] The feathering relay box 101 is connected to the engine accessory 106 and automatically feathers the feathering pump 104 according to the automatic feathering status signal sent by the engine accessory 106.

[0049] The feathering timer 103 receives the manual or automatic feathering signal sent by the feathering relay box 101 and performs timing control. The output control signal of the feathering timer 103 is sent to the feathering relay in the feathering relay box 101 and the feathering switch holding relay in the manual feathering control component 102 to complete the timing control of the feathering control circuit.

[0050] The remote data concentrator 105 is connected to the feathering relay box 101 and the feathering timer 103 respectively. It receives the working signal of the feathering pump 104 through the feathering relay box 101 and at the same time receives the fault signal sent by the feathering timer 103 for status recording and display.

[0051] In this embodiment, the feathering relay box 101 includes a feathering pump contactor K1, a feathering relay J1, a fault light relay J3, and a return feathering relay J4. One end of the contact of the feathering pump contactor K1 is connected to the feathering pump, and the other end is connected to the emergency busbar. One end of the coil of the feathering pump contactor K1 is grounded, and the other end is connected to one end of the contact group 1 of the feathering relay J1, one end of the return feathering button in the manual return feathering control component 102, and one end of the contact of the feathering switch holding relay J2. The coil of the feathering relay J1 is connected in parallel with the coil of the fault light relay J3. The other end of the contact group 1 of the feathering relay J1 is connected to one end of the contact group 1 of the return feathering relay J4. One end of contact group 2 of paddle relay J1 is connected to one end of contact group 3 of feather relay J1, and the other end of contact group 2 of feather relay J1 is connected to one end of contact group 2 of return relay J4. The other end of contact group 3 of feather relay J1 is connected to the coils of feather relay J1 and fault light relay J3. The other ends of contact groups 1 and 2 of return relay J4 are both connected to the emergency busbar. One end of the coil of return relay J4 is grounded, and the other end is connected to the return button in manual return control component 102. One end of the contact of fault light relay J3 is connected to the emergency busbar, and the other end is connected to the fault light in manual return control component 102.

[0052] The feathering pump contactor K1 is a high-current blow-out arc-extinguishing contactor. When it receives a manual back-feed signal, a manual feathering signal, a torque automatic feathering signal, or a negative tension automatic feathering signal, the contactor coil is energized, the contacts are closed, and electrical energy from the DC power supply system reaches the feathering pump 104 through the contacts, and the feathering pump 104 starts working. At the same time, the remote data concentrator (105) receives the feathering pump working signal for status recording and display.

[0053] The feathering relay box 101 receives two electrical signals to control the operation of the feathering pump contactor K1. One signal is the DC power signal for manual feathering and manual revving, activated when the manual feathering and revving button switches are pressed, which is manually selected by the pilot. The other signal is the DC power signal activated when the feathering relay J1 is activated by either the torque automatic feathering signal or the negative thrust automatic feathering signal.

[0054] The feathering relay J1 operates after receiving the torque status signal from the engine accessory 106. Contact groups 2 and 3 close to achieve self-locking of the relay, and contact group 1 closes to connect the power supply and the circuit between the feathering pump contactor coil.

[0055] The feathering relay J1 operates after receiving the negative thrust status signal from the engine accessory 106. Contact groups 2 and 3 close to achieve self-locking of the relay, and contact group 1 closes to connect the power supply and the circuit between the feathering pump contactor coil.

[0056] After receiving the torque status signal from the engine accessory 106, the fault light relay J3 operates, the contact group 1 closes to connect the fault light circuit, the fault light on the manual zigzag paddle control component 102 illuminates, and at the same time the remote data concentrator 105 receives the fault signal for recording and display.

[0057] After receiving the negative thrust status signal from the engine accessory 106, the fault light relay J3 operates, the contact group 1 closes to connect the fault light circuit, the fault light on the manual zigzag paddle control component 102 illuminates, and at the same time the remote data concentrator 105 receives the fault signal for recording and display.

[0058] After receiving the manual return signal, the return relay J4 operates, and contacts 1 and 2 are disconnected, respectively cutting off the automatic feathering torque signal / automatic feathering signal of the feathering pump contactor K1 and the self-locking circuit of the feathering relay J1, so that the feathering relay J1 and the fault light relay J3 do not work.

[0059] In this embodiment, the manual backstroke control component 102 includes a backstroke button, a feathering button, and a feathering switch holding relay J2;

[0060] The return-to-propeller button has two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to the coil of the return-to-propeller relay J4, and the other end of the other contact is connected to the coil of the feather pump contactor K1 and the contact group 1 of the feather relay J1.

[0061] The feathering button includes two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to one contact of the feathering switch holding relay J2, and the other end of the other contact is connected to the coil of the feathering switch holding relay J2 and contact group 2 and contact group 3 of the feathering relay J1. The other end of the contact of the feathering switch holding relay J2 is connected to the coil of the feathering pump contactor K1 and contact group 1 of the feathering relay J1.

[0062] The control signal output terminal of the feathering timer 103 is connected to one end of the coil of the feathering switch holding relay J2, the coil of the feathering relay J1, and the coil of the fault light relay J3, respectively; the feathering signal receiving terminal of the feathering timer 103 is connected to the other end of the coil of the feathering switch holding relay J2, the contact group 2 of the feathering relay J1, and the contact group 3 of the feathering relay J1, respectively.

[0063] Engine accessory 106 is connected to the coil of the feathering relay J1 and the coil of the fault light relay J3.

[0064] The manual back-row control component 102 sends a manual back-row signal to the feathering relay box 101 via a "back-row" button with a protective cover; or sends a manual feathering operation signal to the feathering relay box 101 via a "feed" button. Simultaneously with the "feed" button being switched on, it receives a control signal output from the feathering timer 103, holds the manual feathering operation signal for 12 seconds, and then automatically cuts it off.

[0065] Finally, the manual feathering and return control assembly 102 uses miniaturized "feed" and "return" buttons with protective covers as the human-machine interface for manual feathering and return operations. The output of the manual feathering signal is controlled by the feathering switch holding relay J2. This design replaces the original pull / push handle with an internal electromagnet, allowing the pilot to complete the return operation without having to overcome the attraction of the electromagnet, and improving the head space restriction for the pilot when the pull / push handle is mounted on the top control panel.

[0066] In this embodiment, the feathering timer 103 includes an electrical connector 1, a lightning protection filter component 2, and a control board component 3. The electrical connector 1 is used to transmit electrical signals between the power system, the feathering relay box 101, the manual rudder control component 102, and the remote data concentrator 105. The lightning protection filter component 2 is connected to the electrical connector 1 and the control board component 3 to filter the input signals and provide lightning protection, and to suppress surges in the output signals.

[0067] The lightning protection filter component 2 includes a lightning protection circuit, a surge suppression circuit, and a filter circuit. It filters the input power ground signal, provides lightning protection for the input manual or automatic feathering signal, the 28V power supply, and the output control signal, and suppresses the output fault reporting signal and the output control signal.

[0068] The control board assembly 3 includes a signal acquisition circuit, a power conversion circuit, a control circuit, a power output circuit, and a fault reporting circuit. The signal acquisition circuit acquires and processes the input manual or automatic feathering signals and sends them to the control circuit as input conditions for program judgment. The power conversion circuit performs secondary conversion on the 28V power supply to become internal working power supplies of 5V and 3.3V. The power output circuit converts the signal output by the processor into a ground / open control signal and outputs it through the electrical connector 1. The control circuit completes logic calculation, status judgment, periodic self-monitoring, and fault judgment. The fault reporting circuit reports faults existing in the control circuit.

[0069] The input signal to the feathering timer 103 is a 28V / feed-on signal, sent via a hardwired direct connection. The signal acquisition circuit converts the feathering signal into an electrical signal recognizable by the MCU main control chip and sends it to the control circuit. The MCU main control chip of the control circuit processes the signal according to logic and timing requirements and outputs it to the power output circuit as its input signal. The power output circuit converts the signal into a device output signal based on the output of the control circuit.

[0070] The feathering relay box 101 sends torque automatic feathering and negative thrust automatic feathering signals to the feathering timer 103 as trigger signals for timing control. The control signal output by the feathering timer 103 is a ground / on signal, which is used to control the operation and disconnection of the feathering relay J1 and fault light relay J3 inside the feathering relay box 101, and simultaneously control the operation and disconnection of the feathering switch holding relay J2 inside the manual feathering control component 102.

[0071] Additionally, the feathering timer 103 is used for time control during the feathering process. When the feathering timer 103 detects a manual feathering operation signal or an automatic feathering signal, it first determines the accuracy of the signal through continuous sampling. If the signal is deemed valid, the timing of the feathering procedure begins. Throughout the entire feathering process, whether it is automatic or manual feathering control, the output control signal is kept electrically grounded to ensure the smooth completion of the feathering procedure. After the feathering procedure is completed, the control output signal is kept electrically floating. That is, when entering the manual return-to-feed control process, its output signal is electrically floating, i.e., an open signal, to prevent erroneous continuous entry into the feathering procedure.

[0072] The feathering timer 103 determines the output signal state based on the state of the input signal. The feathering timer 103 incorporates a logic check to prevent misoperation; it determines the output control signal based on whether the feathering signal state changes within a feathering cycle, preventing the feathering pump from repeatedly starting and stopping when the manual feathering button switch is not deactivated. If the input feathering signal changes from 28V to electrically floating within a feathering cycle, the output control signal is set to electrically ground after 15 seconds. If the input feathering signal remains at 28V throughout the feathering cycle, the output control signal is set to electrically floating (on) after 15 seconds until the input feathering signal changes from 28V to electrically floating, at which point the output control signal is set to electrically ground.

[0073] A second embodiment of the present invention provides a control method for the propeller feathering and revving control system of the amphibious aircraft, comprising: a feathering control method and a revving control method, wherein the feathering control method includes an automatic feathering control method and a manual feathering control method, and the revving control method includes a manual revving control method;

[0074] The automatic feathering control method is as follows:

[0075] The feathering relay box 101 sends an automatic feathering signal to the feathering timer. The control signal at the output of the feathering timer is a ground signal. The feathering relay box 101 receives two electrical signals to complete the automatic feathering operation control. One electrical signal is the torque automatic feathering signal from the engine accessory. When this torque automatic feathering signal enters the feathering relay box 101, the coils of the feathering relay J1 and the malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of the feathering relay J1 are all closed, and the contacts of the malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to the feathering pump contactor K1 through contact groups 1 and 2 of the return feathering relay J4. The contacts of the feathering pump contactor K1 are energized, and the emergency busbar supplies power to the feathering pump through the contacts of the feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of the malfunction indicator lamp relay J3. At this time, the feathering relay J1, the malfunction indicator lamp relay J3, and the feathering pump contactor K1 are all working, and the aircraft engine stops while the propeller feathers.

[0076] The other electrical signal is the negative pull high signal from the engine accessory. When this signal enters the feathering relay box 101, the coils of feathering relay J1 and malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of feathering relay J1 are all closed, and the contacts of malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to feathering pump contactor K1 through contact groups 1 and 2 of feathering relay J4. The contacts of feathering pump contactor K1 are energized, and the emergency busbar supplies power to the feathering pump through the contacts of feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of malfunction indicator lamp relay J3. At this time, feathering relay J1, malfunction indicator lamp relay J3, and feathering pump contactor K1 are all working, the aircraft engine stops, and the propeller feathers simultaneously.

[0077] The feathering relay box 101 outputs a working status signal to the remote data concentrator 105 for indicating and storing the working status of the feathering pump on the aircraft.

[0078] Therefore, the feathering relay box 101 receives the control signal output by the feathering timer 103 and directly controls the connection / disconnection of the feathering relay J1 and the fault light relay J3, thereby controlling the connection / disconnection of the feathering pump contactor K1 in the case of automatic feathering.

[0079] The manual feathering control method is as follows:

[0080] The feathering relay box 101 sends a manual feathering signal to the feathering timer, and the control signal at the output of the feathering timer is a ground signal. When the feathering button switch is closed, one contact of the feathering button supplies power to one end of the coil of the feathering switch holding relay J2. The control output of the feathering timer outputs a ground signal, and the contacts of the feathering switch holding relay J2 are closed. The emergency busbar supplies power to the feathering pump contactor K1 through the other contact of the feathering button. The coil of the feathering pump contactor K1 is energized, and the contacts of the feathering pump contactor K1 are closed. The emergency busbar supplies power to the feather pump through the contacts of the propeller pump contactor K1, enabling manual feathering control via the feather pump. At this time, since there is no signal input to the feather relay J1 and the fault light relay J3, the coils of the feather relay J1 and the fault light relay J3 are not energized. The contact groups 1, 2, and 3 of the feather relay J1 and the fault light relay J3 are all open, so the feather relay J1 and the fault light relay J3 do not work. Only the feather pump contactor K1 works, and the aircraft engine stops while the propeller feathers.

[0081] The feathering relay box 101 outputs a working status signal to the remote data concentrator 105 for indicating and storing the working status of the feathering pump on the aircraft.

[0082] Therefore, the manual feathering control component 102 of the present invention sends the manual feathering signal to the feathering timer 103 as a trigger signal for timing control and a logical judgment signal for the output control signal.

[0083] The manual feathering control component 102 receives the control signal output by the feathering timer 103 and directly controls the internal feathering switch holding relay J2 to turn on / off. When the control signal output by the feathering timer 103 is electrically grounded and the manual feathering button is pressed, the feathering switch holding relay J2 operates, and electrical energy reaches the coil of the feathering pump contactor K1 through its contact group, thereby controlling the feathering pump contactor K1 to turn on in manual feathering mode. When the control signal output by the feathering timer 103 is electrically floating, the feathering switch holding relay J2 does not operate, and its contact group is normally open, thereby controlling the feathering pump contactor K1 to turn off in manual feathering mode.

[0084] Manual backspin control method:

[0085] After the automatic and manual feathering control processes are completed, the control signal at the output of the feathering timer is an open signal. When the rotor needs to return to its original position, the rotor return button switch is closed. One contact of the rotor return button supplies power to the coil of rotor return relay J4, and contact groups 1 and 2 of rotor return relay J4 are open. At the same time, since there is no signal input to feathering relay J1 and fault light relay J3, the coils of feathering relay J1 and fault light relay J3 are not energized. Contact groups 1, 2, and 3 of feathering relay J1 and fault light relay J3 are all open, and feathering relay J1 and fault light relay J3 do not work. The other contact of the rotor return button supplies power to the coil of feathering pump contactor K1, and the aircraft engine stops while the propeller returns to its original position.

[0086] The feathering relay box 101 outputs a working status signal to the remote data concentrator 105 for indicating and storing the working status of the feathering pump on the aircraft.

[0087] The manual feathering signal, the manual swivel signal, the torque automatic feathering signal, and the negative thrust automatic feathering signal all energize the feathering pump 104. The feathering relay box 101 outputs a working status signal to the remote data concentrator 105 for indicating and storing the working status of the feathering pump on the aircraft.

[0088] It should be noted that the above embodiments are merely illustrative examples of the present invention, intended to help understand the technical solution and core ideas of the present invention. Those skilled in the art should understand that any modifications, equivalent substitutions, or improvements made based on the concept of the present invention without departing from its principles should be considered within the scope of protection of the present invention, and the specific scope of protection is determined by the claims.

Claims

1. A control system for a propeller of an amphibious aircraft, characterized in that, Includes a feathering relay box (101), a manual feathering control assembly (102), a feathering timer (103), a feathering pump (104), and engine accessories (106); The manual backplane control component (102) is connected to the feathering relay box (101) and the feathering timer (103). The manual backplane control component (102) sends manual backplane and manual feathering operation signals to the feathering relay box (101). The feathering relay box (101) performs manual backplane control or manual feathering control on the feathering pump (104) according to the manual backplane and manual feathering operation signals. At the same time, the manual backplane control component (102) receives the control signal from the feathering timer (103). When performing feathering control, the manual feathering operation signal is held for a certain period of time and then automatically cut off. The feathering relay box (101) is connected to the engine accessory (106) and automatically feathers the feathering pump (104) according to the automatic feathering status signal sent by the engine accessory (106). The feathering timer (103) receives the manual or automatic feathering signal sent by the feathering relay box (101) and performs timing control. The output control signal of the feathering timer (103) is sent to the feathering relay in the feathering relay box (101) and the feathering switch holding relay in the manual back-feeding control component (102) to complete the time control of the feathering control circuit.

2. The amphibious aircraft propeller clockwise control system according to claim 1, characterized in that, The system also includes a remote data concentrator, which is connected to both the feathering relay box and the feathering timer. The remote data concentrator receives feathering pump operating signals through the feathering relay box and simultaneously receives fault signals sent by the feathering timer for status recording and display.

3. The amphibious aircraft propeller clockwise control system according to claim 2, characterized in that, The feathering relay box includes a feathering pump contactor K1, a feathering relay J1, a fault light relay J3, and a return feathering relay J4. One end of the contact of the feathering pump contactor K1 is connected to the feathering pump, and the other end is connected to the emergency busbar. One end of the coil of the feathering pump contactor K1 is grounded, and the other end is connected to one end of contact group 1 of the feathering relay J1, one end of the return feathering button in the manual return feathering control assembly (102), and one end of the contact of the feathering switch holding relay J2. The coil of the feathering relay J1 is connected in parallel with the coil of the fault light relay J3. The other end of contact group 1 of the feathering relay J1 is connected to one end of contact group 1 of the return feathering relay J4. One end of contact group 2 of J1 is connected to one end of contact group 3 of feathering relay J1, and the other end of contact group 2 of feathering relay J1 is connected to one end of contact group 2 of return relay J4. The other end of contact group 3 of feathering relay J1 is connected to the coils of feathering relay J1 and fault light relay J3. The other ends of contact groups 1 and 2 of return relay J4 are both connected to the emergency busbar. One end of the coil of return relay J4 is grounded, and the other end is connected to the return button in the manual return control component (102). One end of the contact of fault light relay J3 is connected to the emergency busbar, and the other end is connected to the fault light in the manual return control component (102).

4. The amphibious aircraft propeller clockwise control system according to claim 3, characterized in that, The manual backplane control assembly (102) includes a backplane button, a feathering button, and a feathering switch holding relay J2; The return-to-propeller button has two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to the coil of the return-to-propeller relay J4, and the other end of the other contact is connected to the coil of the feather pump contactor K1 and the contact group 1 of the feather relay J1. The feathering button includes two contacts, one end of which is connected to the emergency busbar. The other end of one contact is connected to one contact of the feathering switch holding relay J2, and the other end of the other contact is connected to the coil of the feathering switch holding relay J2 and contact group 2 and contact group 3 of the feathering relay J1. The other end of the contact of the feathering switch holding relay J2 is connected to the coil of the feathering pump contactor K1 and contact group 1 of the feathering relay J1.

5. The amphibious aircraft propeller clockwise control system according to claim 4, characterized in that, The control signal output terminal of the feathering timer (103) is connected to one end of the coil of the feathering switch holding relay J2, the coil of the feathering relay J1, and the coil of the fault light relay J3, respectively; the feathering signal receiving terminal of the feathering timer (103) is connected to the other end of the coil of the feathering switch holding relay J2, the contact group 2 of the feathering relay J1, and the contact group 3 of the feathering relay J1, respectively.

6. The amphibious aircraft propeller clockwise control system according to claim 5, characterized in that, The engine accessories are connected to the coil of the feathering relay J1 and the coil of the fault light relay J3.

7. The amphibious aircraft propeller clockwise control system according to claim 6, characterized in that, The feathering timer (103) includes an electrical connector (1), a lightning protection filter assembly (2), and a control board assembly (3). The electrical connector (1) is used to transmit electrical signals between the power system, the feathering relay box (101), the manual rudder control assembly (102), and the remote data concentrator (105). The lightning protection filter assembly (2) is connected to the electrical connector (1) and the control board assembly (3) to filter the input signals and provide lightning protection, and to suppress surges in the output signals.

8. The amphibious aircraft propeller clockwise control system according to claim 7, characterized in that, The lightning protection filter component (2) includes a lightning protection circuit, a surge suppression circuit and a filter circuit. It filters the input power ground signal, provides lightning protection for the input manual or automatic feathering signal, 28V power supply and output control signal, and suppresses the output fault reporting signal and output control signal. The control board assembly (3) includes a signal acquisition circuit, a power conversion circuit, a control circuit, a power output circuit, and a fault reporting circuit. The signal acquisition circuit acquires and processes the input manual or automatic feathering signals and sends them to the control circuit as input conditions for program judgment. The power conversion circuit performs secondary conversion on the 28V power supply to become internal working power supplies of 5V and 3.3V. The power output circuit converts the signal output by the processor into a ground / open control signal and outputs it through the electrical connector (1). The control circuit completes logic calculation, status judgment, periodic self-monitoring, and fault judgment. The fault reporting circuit reports faults existing in the control circuit.

9. A control method for the propeller control system of an amphibious aircraft as described in claim 8, characterized in that, include: The feathering control method and the swivel control method include automatic feathering control method and manual feathering control method, and the swivel control method includes manual swivel control method. The automatic feathering control method is as follows: The feathering relay box (101) sends an automatic feathering signal to the feathering timer. The control signal at the output of the feathering timer is a ground signal. The feathering relay box (101) receives two electrical signals to complete the automatic feathering operation control. One electrical signal is the torque automatic feathering signal emitted by the engine accessory. When the torque automatic feathering signal enters the feathering relay box (101), the coils of the feathering relay J1 and the malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of the feathering relay J1 are all closed, and the contacts of the malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to the feathering pump contactor K1 through contact groups 1 and 2 of the return feathering relay J4. The contacts of the feathering pump contactor K1 are energized. The emergency busbar supplies power to the feathering pump through the contacts of the feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of the malfunction indicator lamp relay J3. At this time, the feathering relay J1, the malfunction indicator lamp relay J3, and the feathering pump contactor K1 are all working. The aircraft engine stops and the propeller feathers simultaneously. The other electrical signal is the negative pull high signal from the engine accessory. When this signal enters the feathering relay box (101), the coils of feathering relay J1 and malfunction indicator lamp relay J3 are energized. Contact groups 1, 2, and 3 of feathering relay J1 are all closed, and the contacts of malfunction indicator lamp relay J3 are also closed. The emergency busbar supplies power to feathering pump contactor K1 through contact groups 1 and 2 of feathering relay J4. The contacts of feathering pump contactor K1 are energized, and the emergency busbar supplies power to the feathering pump through the contacts of feathering pump contactor K1. At the same time, the emergency busbar supplies power to the malfunction indicator lamp through the contacts of malfunction indicator lamp relay J3. At this time, feathering relay J1, malfunction indicator lamp relay J3, and feathering pump contactor K1 are all working, the aircraft engine stops, and the propeller feathers simultaneously. The feathering relay box (101) outputs a working status signal to a remote data concentrator (105) for indicating and storing the working status of the feathering pump on the aircraft. The manual feathering control method is as follows: the feathering relay box (101) sends a manual feathering signal to the feathering timer, and the control signal at the output of the feathering timer is a ground signal; the feathering button switch is closed, one contact of the feathering button supplies power to one end of the coil of the feathering switch holding relay J2, the control output of the feathering timer outputs a ground signal, the contact of the feathering switch holding relay J2 is closed, the emergency busbar supplies power to the feathering pump contactor K1 through the other contact of the feathering button, the coil of the feathering pump contactor K1 is energized, and the feathering pump contactor K... When contact 1 closes, the emergency busbar supplies power to the feather pump through the contacts of the propeller pump contactor K1, enabling manual feathering control. At this time, since there is no signal input to the feather relay J1 and the fault light relay J3, the coils of the feather relay J1 and the fault light relay J3 are not energized. Contact groups 1, 2, and 3 of the feather relay J1 and the fault light relay J3 are all open, so the feather relay J1 and the fault light relay J3 do not work. Only the feather pump contactor K1 works, and the aircraft engine stops while the propeller feathers. The feathering relay box (101) outputs a working status signal to a remote data concentrator (105) for indicating and storing the working status of the feathering pump on the aircraft. Manual backspin control method: After the automatic and manual feathering control processes are completed, the control signal at the output of the feathering timer is an open signal. When the rotor needs to return to its original position, the rotor return button switch is closed. One contact of the rotor return button supplies power to the coil of the rotor return relay J4. Contact groups 1 and 2 of the rotor return relay J4 are open. At the same time, since there is no signal input to the feathering relay J1 and the fault light relay J3, the coils of the feathering relay J1 and the fault light relay J3 are not energized. Contact groups 1, 2, and 3 of the feathering relay J1 and the fault light relay J3 are all open. The feathering relay J1 and the fault light relay J3 do not work. The other contact of the rotor return button supplies power to the coil of the feathering pump contactor K1. The aircraft engine stops and the propeller returns to its original position. The feathering relay box (101) outputs a working status signal to a remote data concentrator (105) for indicating and storing the working status of the feathering pump on the aircraft.

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