Electro-hydraulic hybrid turbine system for aircraft and its starting control method

Abstract

This disclosure discloses an electro-hydraulic hybrid turbine system for aircraft and its starting control method. The starting control method for the electro-hydraulic hybrid turbine system for aircraft may include: acquiring the current airspeed of the aircraft; determining whether the acquired current airspeed is higher than an airspeed threshold; in response to determining that the current airspeed is higher than the airspeed threshold, acquiring the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system; determining whether the acquired outlet pressure is within a pressure threshold range and remains stable; and in response to determining that the outlet pressure is within the pressure threshold range and remains stable, driving the generator of the electro-hydraulic hybrid turbine system to connect to the power grid. The starting control method for the electro-hydraulic hybrid turbine system for aircraft according to this disclosure can ensure that the hydraulic pump and generator of the electro-hydraulic hybrid turbine system start quickly under various operating conditions to meet the operational requirements of the aircraft in various states and ensure flight safety.

Description

Technical Field

[0001] This invention relates to the field of aircraft control, and more particularly to an electro-hydraulic hybrid turbine system for aircraft and its starting control method. Background Technology

[0002] With the increasing demands for system safety and redundancy in modern aircraft, electro-hydraulic hybrid turbine systems are widely used as emergency energy devices. These systems utilize airflow during flight to drive a turbine, which in turn powers a generator or hydraulic pump, providing emergency electrical or hydraulic energy to the aircraft. In such systems, the turbine simultaneously drives both the generator and the hydraulic pump, enabling the aircraft to meet its electrical and hydraulic energy needs in extreme situations, such as complete power system failure, thereby enhancing flight safety margins.

[0003] The starting control strategy for electro-hydraulic hybrid turbine systems typically relies on parameters such as the generator's output voltage and frequency as the primary basis for judgment. For example, when parameters such as output voltage and frequency meet preset thresholds, the generator is allowed to connect to the power grid and begin carrying a load. However, as the cruising altitude and speed range of aircraft continue to expand, the flight environment faced by aircraft carrying electro-hydraulic hybrid turbine systems is becoming increasingly complex, and the output capability of electro-hydraulic hybrid turbine systems is correspondingly significantly affected by multiple factors such as airspeed, temperature, and load characteristics.

[0004] Therefore, there is an urgent need to improve the starting control methods for electro-hydraulic hybrid turbine systems so that they can meet the operational requirements of aircraft under various operating conditions. Summary of the Invention

[0005] The following provides a brief overview of one or more aspects to offer a basic understanding of such aspects. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify the key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as an introduction to the more detailed description that follows.

[0006] To address one or more of the aforementioned technical problems, this disclosure proposes an electro-hydraulic hybrid turbine system for aircraft, its starting control method, and the aircraft itself. The starting control method for the electro-hydraulic hybrid turbine system for aircraft determines the aircraft's current airspeed and, provided the current airspeed meets the requirements, detects the pressure build-up status of the hydraulic pump to ensure that the generator is allowed to connect to the power grid when the hydraulic pump's pressure build-up status is stable. This avoids the risk of failure caused by suddenly connecting an electrical load when the turbine's power is insufficient at low airspeed conditions; simultaneously, by utilizing a "airspeed first, pressure second" stepwise judgment, the response time of the electro-hydraulic hybrid turbine system under high airspeed or normal temperature conditions is significantly shortened, improving the timeliness of emergency power / pressure supply.

[0007] The first aspect of this disclosure discloses a starting control method for an electro-hydraulic hybrid turbine system for an aircraft. The starting control method may include: acquiring the current airspeed of the aircraft; determining whether the acquired current airspeed is higher than an airspeed threshold; in response to determining that the current airspeed is higher than the airspeed threshold, acquiring the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system; determining whether the acquired outlet pressure is within a pressure threshold range and remains stable; and in response to determining that the outlet pressure is within the pressure threshold range and remains stable, driving the generator of the electro-hydraulic hybrid turbine system to connect to the power grid.

[0008] In one embodiment, the starting control method may optionally further include: suppressing generator connection to the grid in response to determining that the current airspeed is below an airspeed threshold.

[0009] In one embodiment, the airspeed threshold may optionally be the airspeed at the left envelope boundary.

[0010] In one embodiment, the start-up control method may optionally further include: in response to determining that the outlet pressure is not within the pressure threshold range or has not remained stable, determining whether the outlet pressure being outside the pressure threshold range has continued for more than a first threshold time or whether the outlet pressure not remaining stable has continued for more than a second threshold time; and in response to determining that the outlet pressure being outside the pressure threshold range has continued for more than the first threshold time or the outlet pressure not remaining stable has continued for more than the second threshold time, driving the generator to connect to the power grid.

[0011] A second aspect of this disclosure discloses a non-transient computer-readable storage medium having instructions stored thereon. These instructions can be executed by a processor to perform the startup control method described above.

[0012] A third aspect of this disclosure discloses a starting control device for an electro-hydraulic hybrid turbine system of an aircraft. The starting control device may include: an acquisition module, an airspeed determination module, a pressure determination module, and a drive module. The acquisition module is configured to acquire the current airspeed of the aircraft and the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system. The airspeed determination module is configured to determine whether the current airspeed is higher than an airspeed threshold. The pressure determination module is configured to, in response to determining that the current airspeed is higher than the airspeed threshold, determine whether the acquired outlet pressure is within a pressure threshold range and remains stable. The drive module is configured to, in response to determining that the outlet pressure is within a pressure threshold range and remains stable, drive the generator of the electro-hydraulic hybrid turbine system to connect to the power grid.

[0013] In one embodiment, the acquisition module may optionally be configured to acquire the aircraft’s current airspeed from a remote power distribution unit.

[0014] In one embodiment, optionally, the acquisition module may be configured to acquire the outlet pressure of the hydraulic pump from a pressure sensor located at the outlet of the hydraulic pump.

[0015] In one embodiment, the drive module may optionally be further configured to: suppress generator connection to the grid in response to determining that the current airspeed is below an airspeed threshold.

[0016] In one embodiment, optionally, the pressure determination module may be further configured to: in response to determining that the outlet pressure is not within the pressure threshold range or has not remained stable, determine whether the outlet pressure being outside the pressure threshold range has continued for more than a first threshold time or whether the outlet pressure not remaining stable has continued for more than a second threshold time; and the drive module may be further configured to: in response to determining that the outlet pressure being outside the pressure threshold range has continued for more than the first threshold time or the outlet pressure not remaining stable has continued for more than the second threshold time, drive the generator to connect to the power grid.

[0017] A fourth aspect of this disclosure discloses an aircraft. The aircraft may include the electro-hydraulic hybrid turbine system described above.

[0018] The starting control method for an electro-hydraulic hybrid turbine system for aircraft disclosed herein can ensure rapid start-up and operation of the hydraulic pump and generator of the electro-hydraulic hybrid turbine system under various operating conditions, thereby meeting the operational requirements of the aircraft in various states and ensuring flight safety. Furthermore, the starting control method for an electro-hydraulic hybrid turbine system for aircraft disclosed herein can also allow the generator to connect to the hydraulic pump and drive the generator to connect to the power grid in the event of a hydraulic pump failure, further ensuring flight safety.

[0019] This disclosure is provided to introduce concepts in a simplified form, which will be further described in the detailed description below. This disclosure is not intended to identify key or essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter. Other aspects, features, and / or advantages of the embodiments will be set forth in part in the description which follows, and will be apparent in part from the description, or may be learned by practice of this disclosure. Attached Figure Description

[0020] To gain a more detailed understanding of the features described above in this disclosure, reference can be made to a more specific description of the above-briefly summarized aspects, some of which are illustrated in the accompanying drawings. However, it should be noted that the drawings illustrate only certain typical aspects of this disclosure and should not be considered as limiting its scope, as other equivalent aspects are permissible in this description. In the drawings: Figure 1 An architecture diagram of an electro-hydraulic hybrid turbine system for aircraft is shown.

[0021] Figure 2 A schematic diagram showing the change in hydraulic fluid viscosity of the turbine's hydraulic pump with fluid temperature is shown.

[0022] Figure 3 A functional architecture diagram of a starting control device for an electro-hydraulic hybrid turbine system according to an embodiment of the present disclosure is shown.

[0023] Figure 4 A flowchart of a starting control method for an electro-hydraulic hybrid turbine system according to an embodiment of the present disclosure is shown.

[0024] Figure 5 A block diagram of a starting control device according to an embodiment of the present disclosure is shown.

[0025] Figure 6 A block diagram of an apparatus including a start control device according to an embodiment of the present disclosure is shown. Detailed Implementation

[0026] The specific embodiments described below with reference to the accompanying drawings are intended as descriptions of various configurations and are not intended to represent only the configurations in which the concepts described herein can be practiced. These specific embodiments include detailed descriptions to provide a thorough understanding of the various concepts. However, it will be apparent to those skilled in the art that these concepts can be practiced without these detailed descriptions.

[0027] Based on this teaching, those skilled in the art will appreciate that the scope of this disclosure is intended to cover any aspect of this disclosure, whether implemented independently of or in combination with any other aspect of this disclosure. For example, any number of the aspects described can be used to implement an apparatus or method of practice. Furthermore, the scope of this disclosure is intended to cover such apparatus or methods practiced using other structures, functionalities, or structures and functionalities that complement or differ from the various aspects of this disclosure described.

[0028] While specific aspects are described herein, numerous variations and substitutions of these aspects fall within the scope of this disclosure. Although some benefits and advantages of preferred aspects have been mentioned, the scope of this disclosure is not intended to be limited to a particular benefit, use, or objective. The detailed description and accompanying drawings are merely illustrative and not limiting of this disclosure, the scope of which is defined by the appended claims and their equivalents.

[0029] As mentioned above, the starting control strategy for electro-hydraulic hybrid turbine systems typically relies on parameters such as the generator's output voltage and frequency as the primary basis for judgment. For example, when parameters such as output voltage and frequency meet preset thresholds, the generator is allowed to connect to the power grid and begin carrying a load. However, with the continuous expansion of aircraft cruising altitude and speed ranges, the flight environment faced by aircraft carrying electro-hydraulic hybrid turbine systems is becoming increasingly complex, and the output capability of electro-hydraulic hybrid turbine systems is correspondingly significantly affected by multiple factors such as airspeed, temperature, and load characteristics.

[0030] Figure 1 A schematic diagram 100 illustrates the architecture of an electro-hydraulic hybrid turbine system (e.g., an electro-hydraulic hybrid ram air turbine system, or simply an electro-hydraulic hybrid RAT system). Figure 1 As shown, the electro-hydraulic hybrid turbine system may include a turbine 105 (e.g., an electro-hydraulic hybrid ram air turbine, hereinafter referred to as an electro-hydraulic hybrid RAT), a generator 110, and a hydraulic pump 115, wherein the turbine 105 is coupled to the generator 110 and the hydraulic pump 115, respectively. For ease of description, the following uses an electro-hydraulic hybrid ram air turbine system (hereinafter referred to as an electro-hydraulic hybrid RAT system) as an example to illustrate the technical solution of this application. Those skilled in the art will understand that this example is only for illustrative purposes, and the scope of protection of this application is not limited to the electro-hydraulic hybrid RAT system. Any electro-hydraulic hybrid turbine system that adopts the same or equivalent control principle, including but not limited to other airborne emergency turbines, auxiliary power units, or ground electro-hydraulic hybrid turbine equipment, falls within the scope of protection of this application.

[0031] When an aircraft is in an emergency situation, the electro-hydraulic hybrid RAT system should prioritize ensuring the aircraft's maneuverability. During RAT start-up, the hydraulic pump has the advantage of fast mechanical response because it does not need to overcome electromagnetic inertia or meet grid synchronization requirements. Therefore, the hydraulic pump usually reaches its rated pressure and builds up pressure before the generator, providing energy for aircraft actuation in a timely manner. After the hydraulic pump has completed pressure building, the generator connects to the grid via a contactor, which reduces the impact on the turbine and hydraulic pump, helps to shorten the pressure build-up time, and improves the response rate and system stability.

[0032] However, electro-hydraulic hybrid RAT systems are typically installed in non-temperature-controlled, non-airtight compartments where the ambient temperature can drop as low as -55°C. Low temperatures can affect the viscosity of the hydraulic fluid in the hydraulic pump, increasing the hydraulic load and significantly prolonging the pump's start-up time. Figure 2 The diagram shows a curve illustrating the viscosity of the hydraulic oil in the turbine's hydraulic pump as a function of oil temperature. Although heating or insulation measures, such as generator heaters and hydraulic pump temperature valves, are installed in the compartment to ensure the generator stator and rotor temperatures are above 0°C, correspondingly increasing the hydraulic oil viscosity by nearly 20°C, the viscosity of the hydraulic oil at -30°C is approximately ten times that at room temperature—a significant difference. Figure 2 As shown, the pressure build-up time of the hydraulic pump at -30°C is expected to be about twice as long as that at room temperature. This could lead to the generator completing pressure build-up and connecting to the grid to begin operating the load before the hydraulic pump has stabilized in the low-temperature environment. This not only increases the impact on the turbine but also further prolongs the pressure build-up time of the hydraulic pump, thus affecting the safe operation of the electro-hydraulic hybrid RAT system. Furthermore, the output capacity of the electro-hydraulic hybrid RAT decreases as airspeed decreases. In the event of dual-engine failure during low-speed landing, the output capacity of the electro-hydraulic hybrid RAT is only sufficient to support the hydraulic pump. Generator connection will further strain the turbine, causing the hydraulic pump to be unable to meet the aircraft's maneuvering requirements.

[0033] Therefore, there is an urgent need to optimize the starting strategy for low-temperature or low-speed scenarios so that the electro-hydraulic hybrid RAT can provide the necessary energy supply for aircraft operation under various conditions (e.g., in low-temperature or low-speed conditions) and ensure the flight safety of aircraft.

[0034] To address one or more of the aforementioned technical problems, this disclosure proposes an electro-hydraulic hybrid RAT system for aircraft, its starting control method, and the aircraft itself. The starting control method for the electro-hydraulic hybrid RAT system for aircraft determines the aircraft's current airspeed. Subsequently, provided the current airspeed meets the requirements, the starting control method detects the pressure build-up status of the hydraulic pump to ensure that the generator is allowed to connect to the power grid when the hydraulic pump's pressure build-up status is stable. This avoids the risk of failure caused by suddenly connecting an electrical load when the turbine's power is insufficient at low airspeed conditions; simultaneously, by utilizing a "airspeed first, pressure second" stepwise judgment, the response time of the electro-hydraulic hybrid turbine system under high airspeed or normal temperature conditions is significantly shortened, improving the timeliness of emergency power / pressure supply.

[0035] For ease of description, the following description uses an airplane as an example of an aircraft. Those skilled in the art will appreciate that the electro-hydraulic hybrid turbine system for aircraft and its starting control method according to this disclosure are applicable to various types of aircraft without departing from the scope of this disclosure. In the following description of this disclosure, "aircraft" and "airplane" can be used interchangeably.

[0036] The present disclosure will be further described below with reference to specific embodiments and accompanying drawings, but this should not be construed as limiting the scope of protection of the present disclosure.

[0037] Figure 3 A functional architecture diagram 300 for start-up control of an electro-hydraulic hybrid RAT system according to an embodiment of the present disclosure is shown.

[0038] In one alternative embodiment, such as Figure 3 As shown, the electro-hydraulic hybrid RAT system may include an electro-hydraulic hybrid RAT 305, a generator 310, and a hydraulic pump 315, wherein the electro-hydraulic hybrid RAT 305 may be coupled to the generator 310 and the hydraulic pump 315, respectively. For example, the electro-hydraulic hybrid RAT 305 may be coupled to the generator 310 via a lower gearbox and to the hydraulic pump 315 via an upper gearbox.

[0039] In one alternative embodiment, such as Figure 3 As shown, generator 310 can be coupled to an electrical load to output voltage to the electrical load terminal, wherein a generator contactor 325 is provided between generator 310 and electrical load.

[0040] In one alternative embodiment, such as Figure 3 As shown, the hydraulic pump 315 can be coupled to a hydraulic load to output hydraulic pressure to the hydraulic load end, wherein a pressure sensor 330 is provided between the hydraulic pump 315 and the hydraulic load.

[0041] In an alternative embodiment, the starting control device 320 (e.g., a generator control unit (GCU)) may be configured to perform the starting control method described below, which will be combined with Figure 4 To elaborate in detail.

[0042] Figure 4 A flowchart of a starting control method 400 for an electro-hydraulic hybrid turbine system according to an embodiment of the present disclosure is shown. For example, the starting control method 400 may be provided by... Figure 3 The starting control device 320 shown is used to perform this operation.

[0043] The starting control method 400 may include the following steps.

[0044] In step 405, the start control device 320 can acquire the aircraft's current airspeed. In an optional example, the start control device 320 can be configured to acquire the aircraft's airspeed information, such as the current airspeed, from a Remote Power Distribution Unit (RPDU). Figure 3 As shown.

[0045] In step 410, the starting control device 320 can determine whether the acquired current airspeed is higher than an airspeed threshold. In an optional example, the airspeed threshold can be the left envelope boundary airspeed, such as 60-120 kt, preferably 80-110 kt, more preferably 90 kt, etc. The airspeed threshold can vary depending on the aircraft model. For example, the starting control device 320 can compare the acquired current airspeed with the left envelope boundary airspeed to determine whether the acquired current airspeed is higher than the airspeed threshold. In some cases, the starting control device 320 can judge the airspeed voting signal. When the airspeed voting signal is 1, it indicates that the current airspeed is lower than the left envelope boundary airspeed, and the turbine output capacity cannot simultaneously support the generator and hydraulic pump load. Therefore, the drive port of the generator contactor is locked, and the generator contactor closure is inhibited. When the airspeed voting signal is 0, it indicates that the current airspeed is higher than the left envelope boundary airspeed, and the turbine output capacity meets the requirements.

[0046] In response to determining that the current airspeed is higher than an airspeed threshold, in step 415, the start control device 320 may acquire the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system. In an optional example, the start control device 320 may be configured to couple with and acquire the outlet pressure of the hydraulic pump 315 from the pressure sensor 330 of the hydraulic pump 315, such as... Figure 3 As shown. In some cases, the pressure sensor 330 may be located at the outlet of the hydraulic pump 315. In an alternative embodiment, in response to determining that the current airspeed is below an airspeed threshold, in step 430, the start control device 320 may prevent the generator from connecting to the power grid.

[0047] In an alternative embodiment, the start control device 320 may be further configured to acquire the generator's output voltage (e.g., Point-of-Regulation, or POR). Figure 4 The values ​​are not shown in the diagram. For example, the starting control device 320 may be further configured to: determine whether the frequency of the generator's output voltage is within the expected range; in response to determining that the frequency of the output voltage is within the expected range, determine whether the amplitude of the output voltage is within the expected range and remains stable; and in response to determining that the amplitude of the output voltage is within the expected range and remains stable, continue to execute subsequent step 420. As another example, the starting control device 320 may be further configured to: in response to determining that the frequency of the output voltage is not within the expected range, continue to determine whether the frequency of the generator's output voltage is within the expected range. As yet another example, the starting control device 320 may be further configured to: in response to determining that the amplitude of the output voltage is not within the expected range or has not remained stable, adjust the output voltage. In an alternative embodiment, the determination of the frequency and amplitude of the generator's output voltage may be performed after step 420.

[0048] In step 420, the start control device 320 can determine whether the acquired outlet pressure is within the pressure threshold range and remains stable.

[0049] In response to determining that the outlet pressure is within and remains stable within the pressure threshold range, in step 425, the start control device 320 may drive the generator of the electro-hydraulic hybrid turbine system to connect to the power grid. In an alternative embodiment, the start control device 320 may be configured to output a drive signal to a generator contactor (e.g., a ram air turbine generator line contactor (RGLC) 325) to drive the generator 310 to connect to the power grid, such as... Figure 3 As shown.

[0050] In an alternative embodiment, in response to determining that the outlet pressure is outside the pressure threshold range or has not remained stable, in step 435, the start-up control device 320 may determine whether the outlet pressure being outside the pressure threshold range has lasted for more than a first threshold time or whether the outlet pressure not remaining stable has lasted for more than a second threshold time. In some cases, the first threshold time and the second threshold time may be preset based on the aircraft power outage time. For example, if the aircraft requires the power outage time to be no more than 10 seconds, then the first threshold time and the second threshold time shall not exceed 10 seconds, thereby ensuring normal power access within 10 seconds. For example, the first threshold time may be 7-14 seconds, preferably 8-11 seconds. For example, the second threshold time may be 7-14 seconds, preferably 8-11 seconds. In one example, the first threshold time may be equal to the second threshold time. In another example, the first threshold time may be greater than the second threshold time to ensure peak pressure build-up while improving system efficiency. In an optional embodiment, in response to determining that the outlet pressure being outside the pressure threshold range has lasted for more than the first threshold time or that the outlet pressure not remaining stable has lasted for more than the second threshold time, returning to step 425, the start-up control device 320 may drive the generator to connect to the power grid. In an alternative embodiment, in response to determining that the outlet pressure is not within the pressure threshold range for a period not exceeding a first threshold time or that the outlet pressure has not remained stable for a period not exceeding a second threshold time, the process returns to step 420, where the start-up control device 320 can continue to determine whether the acquired outlet pressure is within the pressure threshold range and remains stable. The start-up control method according to this disclosure utilizes a timeout fault strategy. Even if the hydraulic pump fails to build pressure due to low temperature or internal malfunction, hydraulic energy can be prioritized to maintain the minimum electrical demand, further improving the aircraft's maneuverability and safety under extreme conditions.

[0051] In an optional embodiment, the start control device 320 may receive the outlet pressure, POR voltage, and the frequency and amplitude of the generator POR voltage. A frequency voting signal of 1 for the generator output voltage indicates that the frequency of the current generator POR voltage meets the grid connection requirements. Subsequently, the amplitude of the generator POR voltage and the outlet pressure of the hydraulic pump are determined.

[0052] If all requirements are met, the hydraulic pump is considered to have completed pressure build-up, the generator contactor is closed, and the generator is connected to the power grid. If the hydraulic pump outlet pressure does not meet the requirements, this may be due to a low-temperature environment, which will inhibit the generator from connecting to the power grid until the hydraulic pump has completed pressure build-up. If the hydraulic pump outlet pressure consistently fails to meet the requirements, an internal fault in the hydraulic pump is considered, the generator contactor is closed, and the generator is connected to the power grid.

[0053] In some scenarios, the starting control unit 320 can be configured to identify various operating conditions based on real-time pressure data of the hydraulic pumps of the electro-hydraulic hybrid RAT and aircraft airspeed information, controlling the timing of the generator's connection to the power grid. This reduces the impact on the turbine from simultaneous electro-hydraulic load connection and prioritizes the hydraulic pumps of the electro-hydraulic hybrid RAT to build up pressure faster than the generator, thereby improving the power supply response rate and system safety of the electro-hydraulic hybrid RAT system. These operating conditions include high-airspeed and low-airspeed conditions.

[0054] For example, under high airspeed conditions, priority can be given to ensuring that the hydraulic pump 315 completes pressure build-up. In some cases, under high airspeed conditions, the control unit 320 can track the pressure build-up status of the hydraulic pump and generator by detecting the pressure information from the pressure sensor of the hydraulic pump 315 and the voltage information at the POR point. For example, at normal temperature, the hydraulic oil of the hydraulic pump 315 has low viscosity, low starting resistance, and fast mechanical response, which can quickly build up the system pressure to the required value, taking precedence over the generator in successfully building up pressure. When the generator 310 is connected to the grid, the hydraulic pump 315 can already operate stably at rated pressure, and the impact of the generator starting to carry load on the electro-hydraulic hybrid RAT system is relatively small. For example, at low temperature, the hydraulic oil viscosity of the hydraulic pump 315 increases significantly, the starting resistance increases, and the mechanical response lags, so the generator 310 only needs to meet the voltage amplitude / frequency conditions to complete pressure build-up under no-load conditions. In this scenario, generator 310 will prioritize pressure build-up over hydraulic pump 315. At this point, generator 310 must be prevented from connecting to the grid until hydraulic pump 315 has completed pressure build-up and maintained a stable pressure. Then, generator contactor 325 is closed to complete the electrical load connection. For example, if hydraulic pump 315 fails and cannot successfully build up pressure due to an internal fault, generator 310 is no longer prevented. Generator 310 can then be connected to the grid once its output voltage meets the required quality.

[0055] For example, under low airspeed conditions, priority can be given to ensuring the normal operation of hydraulic pump 315. Start-up control unit 320 can obtain the current airspeed from the remote power distribution unit. When start-up control unit 320 determines that the current airspeed is below the left envelope boundary airspeed, it can prevent generator contactor 325 from closing. At this time, the aircraft is in the landing process, with high control requirements (e.g., main flight control and high lift), and the output capacity of the electro-hydraulic hybrid RAT turbine can be fully used to support the power supply of hydraulic pump 315.

[0056] This disclosure proposes a staggered starting architecture and control method for the generator and hydraulic pump of an electro-hydraulic hybrid RAT system based on aircraft state and load coordination, without changing the existing onboard circuitry and monitoring parameters or increasing the aircraft weight. The starting control method of this disclosure enables the generator and hydraulic pump to be controlled to achieve staggered starting, avoiding simultaneous high-load operation of the hydraulic pump and generator under low-temperature conditions. By suppressing power supply capacity when turbine capacity is insufficient, the maneuverability of the main flight control and high-lift systems is ensured, maximizing power supply to critical onboard equipment and guaranteeing aircraft maneuverability under extreme conditions. This not only improves the reliability of the electro-hydraulic hybrid RAT system under extreme conditions but also effectively solves the problem of conflicting start-up between the generator and hydraulic pump, ensuring aircraft operational safety. The technical solution of this disclosure can be implemented by modifying software or firmware without hardware modification, and has good airworthiness and retrofit compatibility for both existing and newly developed aircraft models. In some cases, the starting control device 320 can be integrated into the aircraft's control unit. Alternatively, the function of the starting control device 320 can also be achieved through hardware, or a combination of hardware and software.

[0057] Figure 5 A block diagram 500 of a start control device 320 according to an embodiment of the present disclosure is shown. Figure 5 As shown, the start-up control device 320 may include: an acquisition module 505, an airspeed determination module 510, a pressure determination module 515, and a drive module 520. The acquisition module 505 may be configured to acquire the aircraft's current airspeed and the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system. The airspeed determination module 510 may be configured to determine whether the current airspeed is higher than an airspeed threshold. The pressure determination module 515 may be configured, in response to determining that the current airspeed is higher than the airspeed threshold, to determine whether the acquired outlet pressure is within a pressure threshold range and remains stable. The drive module 520 may be configured, in response to determining that the outlet pressure is within a pressure threshold range and remains stable, to drive the generator of the electro-hydraulic hybrid turbine system to connect to the power grid.

[0058] Figure 6 A block diagram of a device 600 including a start control device according to one embodiment of the present disclosure is shown. The device illustrates a general hardware environment in which the present disclosure can be applied according to exemplary embodiments thereof.

[0059] Now refer to Figure 6 Device 600 is described as an exemplary embodiment of a hardware device that can be applied to various aspects of this disclosure. Device 600 can be any machine configured to perform processing and / or computation, and can be, but is not limited to, a workstation, server, desktop computer, laptop computer, tablet computer, or any combination thereof. The aforementioned system can be implemented wholly or at least partially by device 600 or similar devices or systems.

[0060] Device 600 may include elements that may be connected to or communicate with bus 602 via one or more interfaces. For example, device 600 may include bus 602, one or more input devices 605, one or more output devices 610, one or more processors 615, and one or more memories 620, etc.

[0061] Processor 615 can be any type of processor and may include, but is not limited to, general-purpose processors and / or special-purpose processors (e.g., special-purpose chips), intelligent hardware devices (e.g., general-purpose processors, DSPs, CPUs, microcontrollers, ASICs, FPGAs, programmable logic devices, discrete gate or transistor logic components, discrete hardware components, or any combination thereof). In some cases, processor 615 may be configured to use a memory controller to operate a memory array. In other cases, a memory controller (not shown) may be integrated into processor 615. Processor 615 may be configured to execute computer-readable instructions stored in memory to perform the various functions described herein.

[0062] Memory 620 can be any storage device capable of storing data. Memory 620 may include, but is not limited to, disk drives, optical storage devices, solid-state storage, floppy disks, hard disks, magnetic tapes or any other magnetic media, optical discs or any other optical media, ROM (read-only memory), RAM (random access memory), cache memory and / or any other memory chip or cartridge, and / or any other medium from which a computer can read data, instructions and / or code. Memory 620 may store computer-executable software 625 including computer-readable instructions that, when executed, cause a processor to perform the various functions described herein. Memory 620 may have various data / instructions / code for implementing the various functions described herein.

[0063] Software 625 may be stored in memory 620 and includes, but is not limited to, an operating system, one or more applications, drivers, and / or other data and code. Instructions for performing the various functions described herein may be included in one or more applications, and the units of the aforementioned device 600 may be implemented by processor 615 reading and executing the instructions of one or more applications. In some cases, software 625 may not be directly executable by the processor, but may (e.g., when compiled and executed) enable the computer to perform the functions described herein.

[0064] Input device 605 can be any type of device that can input information to the computing device.

[0065] The output device 610 can be any type of output device capable of outputting information. In one case, the output device 610 can be any type of image output device capable of displaying information.

[0066] Those skilled in the art will clearly understand from the above embodiments that this disclosure can be implemented by software with the necessary hardware or by hardware, firmware, etc. Based on this understanding, embodiments of this disclosure can be implemented in part in software form. The computer software can be stored on a readable storage medium, such as a floppy disk, hard disk, optical disk, or computer flash memory. The computer software includes a series of instructions to cause a computer (e.g., a personal computer, service station, or network terminal) to perform methods or portions thereof according to various embodiments of this disclosure.

[0067] The word “exemplary” is used herein to mean “serving as an example, embodiment, or illustration.” Any aspect described herein as “exemplary” is not necessarily to be construed as superior to or better than the others.

[0068] The preceding description is provided to enable any person skilled in the art to practice the various aspects described herein. Various modifications to these aspects will readily be understood by those skilled in the art, and the universal principles defined herein may be applied to other aspects. Therefore, the claims are not intended to be limited to the aspects shown herein, but should be granted the full scope consistent with the language of the claims, wherein references to the singular form of an element, unless specifically stated otherwise, are not intended to mean “one and only one,” but rather “one or more.” Unless specifically stated otherwise, the term “some” refers to one or more. All structural and functional equivalents of the elements of the various aspects described throughout this disclosure, whether now or hereafter known to a person skilled in the art, are expressly incorporated herein by reference and are intended to be covered by the claims.

Claims

1. A starting control method for an electro-hydraulic hybrid turbine system for an aircraft, comprising: Obtain the current airspeed of the aircraft; Determine whether the acquired current airspeed is higher than the airspeed threshold; In response to determining that the current airspeed is higher than the airspeed threshold, the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system is obtained; Determine whether the obtained outlet pressure is within the pressure threshold range and remains stable; as well as In response to determining that the outlet pressure is within the pressure threshold range and remains stable, the generator of the electro-hydraulic hybrid turbine system is driven to connect to the power grid.

2. The starting control method as described in claim 1, further comprising: In response to determining that the current airspeed is lower than the airspeed threshold, the generator is prevented from connecting to the power grid.

3. The starting control method as described in claim 2, characterized in that, The airspeed threshold is the airspeed at the left envelope boundary.

4. The starting control method as described in claim 1, characterized in that, The starting control method further includes: In response to determining that the outlet pressure is not within the pressure threshold range or has not remained stable, Determine whether the outlet pressure is outside the pressure threshold range for a sustained period exceeding a first threshold time or whether the outlet pressure has not remained stable for a sustained period exceeding a second threshold time; and In response to determining that the outlet pressure does not continuously exceed the first threshold time within the pressure threshold range or that the outlet pressure does not remain stable for a continuous period exceeding the second threshold time, the generator is driven to connect to the power grid.

5. A non-transient computer-readable storage medium having instructions stored thereon, the instructions being executable by a processor to perform the startup control method as described in any one of claims 1-4.

6. A starting control device for an electro-hydraulic hybrid turbine system of an aircraft, comprising: An acquisition module is configured to acquire the current airspeed of the aircraft and the outlet pressure of the hydraulic pump of the electro-hydraulic hybrid turbine system; An airspeed determination module is configured to determine whether the current airspeed is higher than an airspeed threshold. A pressure determination module is configured to determine whether the acquired outlet pressure is within the pressure threshold range and remains stable in response to determining that the current airspeed is higher than the airspeed threshold. as well as A drive module configured to drive the generator of the electro-hydraulic hybrid turbine system to connect to the power grid in response to determining that the outlet pressure is within the pressure threshold range and remains stable.

7. The starting control device as described in claim 6, characterized in that, The acquisition module is configured to: Obtain the aircraft's current airspeed from the remote power distribution unit; and The outlet pressure of the hydraulic pump is obtained from a pressure sensor located at the outlet of the hydraulic pump.

8. The starting control device as described in claim 6, characterized in that, The drive module is further configured to: in response to determining that the current airspeed is lower than the airspeed threshold, suppress the generator from connecting to the power grid.

9. The starting control device as described in claim 6, characterized in that: The pressure determination module is further configured to: in response to determining that the outlet pressure is not within the pressure threshold range or has not remained stable, determine whether the outlet pressure being outside the pressure threshold range has lasted for more than a first threshold time or whether the outlet pressure not remaining stable has lasted for more than a second threshold time; and The drive module is further configured to drive the generator to connect to the power grid in response to determining that the outlet pressure does not continuously exceed the first threshold time within the pressure threshold range or that the outlet pressure does not remain stable and continuously exceeds the second threshold time.

10. An aircraft comprising a start-up control device as described in any one of claims 6-9.

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