Power supply control method and device of aircraft pod control system and electronic equipment

Abstract

The invention relates to the technical field of aircraft pod power supply, in particular to a power supply control method and device of an aircraft pod control system and electronic equipment. According to the method, under the conditions that aircraft performance parameters meet the openable condition of an aircraft pod and the pod temperature is within a preset openable temperature interval, whether the rotating speed of a stamping turbine within a preset time period after an air inlet control valve is opened conforms to a rotating speed range corresponding to a rotating speed stable state or not is determined; whether the aircraft pod meets the opening condition or not is judged, so that a high-voltage contactor is closed to connect a generator with a load, and series-parallel connection of a stamping main power generation network and an energy storage power supply network is controlled in real time according to changes of the rotating speed of a turbine. The problems of instability and uncertainty of power supply caused by mismatching of the power generation capacity of the stamping turbine and the flight state of the aircraft in the prior art are reduced, and the operation stability of pod equipment is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft power supply system control. Specifically, the present application relates to a power supply control method, device and electronic equipment for an aircraft pod control system. Background Art

[0002] A pod is a streamlined, short section mounted under the fuselage or wings, carrying a weapon or device. Adding a pod can add capabilities not inherent to an aircraft, thereby expanding its application scope without affecting the overall aircraft design and meeting diverse functional requirements at a lower cost. The development of pods of varying forms and functions has become a key development direction for the aviation industry worldwide. Adding a pod requires only two considerations: the pod's external design, specifically its impact on the aircraft's overall aerodynamics; and information exchange between the pod and the aircraft, typically achieved through a communication bus. Traditional pods have low energy consumption, and the small amount of power required during operation can be directly supplied by the onboard power system, requiring only a standard power supply port on the fuselage. However, as pod functionality expands, energy consumption also increases. Peak power consumption often exceeds the power capacity reserved by the onboard power system. Therefore, ensuring a stable power supply for pod equipment is a crucial consideration in new pod designs.

[0003] Existing pod power systems typically use a hole in the top or middle of the pod to introduce ram air, which in turn drives the ram turbine, which in turn drives the generator. Because the ram turbine's power generation capacity is closely related to the aircraft's flight state, and existing pod power systems don't take this into account, this power supply method is subject to significant instability and uncertainty, significantly detrimental to the stable operation of the pod equipment. Summary of the Invention

[0004] This application provides a power supply control method, device, and electronic device for an aircraft pod control system, which can solve the problem of poor power supply stability in aircraft pods. The technical solution is as follows:

[0005] In a first aspect, a power supply control method for an aircraft pod control system is provided. The aircraft pod control system includes a stamping main power generation grid and an energy storage power supply grid. The stamping main power generation grid is connected to a high-voltage DC return bar via a high-voltage contactor. The energy storage power supply grid is connected to the high-voltage DC return bar via a bidirectional DC-to-DC rectifier. The method includes:

[0006] When it is detected that the aircraft performance parameters meet the conditions for opening the aircraft pod, the pod temperature is determined;

[0007] When the pod temperature is within a preset openable temperature range, the air intake control valve of the ramjet main power grid is opened and then a first speed of the ramjet turbine within a preset time period is determined;

[0008] When the first speed is within a speed range corresponding to a preset speed stable state, closing the high-voltage contactor and determining a second speed of the ramjet turbine, the speed range being an interval greater than a preset second threshold and less than a preset first threshold;

[0009] When it is detected that the second speed is outside the speed range corresponding to the speed stable state, the series and parallel power supply of the ram main power generation grid and the energy storage power supply grid are controlled by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier.

[0010] In a second aspect, a power supply control device for an aircraft pod control system is provided. The aircraft pod control system includes a stamping main power generation grid and an energy storage power supply grid. The stamping main power generation grid is connected to a high-voltage DC return bar via a high-voltage contactor, and the energy storage power supply grid is connected to the high-voltage DC return bar via a bidirectional DC-to-DC rectifier. The device includes:

[0011] A pod temperature determination module is used to determine the pod temperature when it is detected that the aircraft performance parameters meet the conditions for opening the aircraft pod;

[0012] a turbine speed determination module, configured to determine a first speed of the ramjet turbine within a preset time period after opening the air intake control valve when the nacelle temperature is within a preset openable temperature range;

[0013] a load speed determination module, configured to close the high-voltage contactor and determine a second speed of the ramjet turbine when the first speed is within a speed range corresponding to a preset speed stable state, wherein the speed range is an interval greater than a preset second threshold and less than a preset first threshold;

[0014] The collaborative power supply control module is used to control the series and parallel power supply of the ramjet main power generation grid and the energy storage power supply grid by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier when detecting that the second speed is outside the speed range corresponding to the speed stable state.

[0015] According to a third aspect, an electronic device is provided. The electronic device includes a processor and a memory, wherein the memory stores computer-readable instructions, and the processor is configured to execute the computer-readable instructions, wherein the computer-readable instructions execute the above method when executed.

[0016] In a fourth aspect, a computer-readable storage medium is provided, storing computer-executable instructions for executing the above method.

[0017] In an embodiment of the present application, when aircraft performance parameters meet the aircraft pod opening conditions and the pod temperature is within a preset opening temperature range, whether the aircraft pod meets the opening conditions is determined by determining whether the ramjet turbine speed meets the speed range corresponding to the speed stability state within a preset time period after the air intake control valve is opened. The high-voltage contactor is then closed to connect the generator to the load, the ramjet turbine power generation capacity is associated with the aircraft flight state, and the series and parallel connection of the ramjet main power generation grid and the energy storage power supply grid is controlled according to the turbine speed detected in real time. This reduces the occurrence of power supply instability and uncertainty problems caused by the mismatch between the ramjet turbine power generation capacity and the aircraft flight state in the prior art, thereby improving the stability of pod equipment operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for describing the embodiments of the present application.

[0019] Figure 1 A schematic diagram of the structure of a power supply control method for an aircraft pod control system provided in an embodiment of the present application;

[0020] Figure 2 Various thresholds set for the power supply control method of the aircraft pod control system provided in the embodiment of the present application;

[0021] Figure 3 A schematic block diagram of an aircraft pod control system according to an embodiment of the present application;

[0022] Figure 4 A schematic diagram of the structure of a power supply control device for an aircraft pod control system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0023] The following describes embodiments of the present application in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application and are not to be construed as limiting the present application.

[0024] The embodiment of the present application provides a power supply control method for an aircraft pod control system, wherein the aircraft pod control system includes a stamping main power generation network and an energy storage power supply network, the stamping main power generation network is connected to a high-voltage DC return bar through a high-voltage contactor, and the energy storage power supply network is connected to a high-voltage DC return bar through a bidirectional DC-DC rectifier. Figure 1 As shown, the method includes: steps S101 to S104.

[0025] Step S101: When it is detected that the aircraft performance parameters meet the conditions for opening the aircraft pod, the pod temperature is determined.

[0026] Specifically, aircraft performance parameters generally include speed and altitude. For the power supply system, speed is particularly sensitive. When speed is too low, the front-to-rear pressure ratio of the ramjet is too low, making it virtually inoperable. Forced opening can only be supported by energy storage devices for a short period of time. When speed is too high, the airflow energy per unit flow is high, requiring high control precision for the intake valve. Even the smallest control error can lead to a mismatch between air supply and power consumption, resulting in insufficient or excessive power, frequent system switching, and even excessive voltage, which can compromise system safety. Therefore, when the aircraft's speed and altitude meet preset conditions, the flight performance is determined to meet the pod's opening conditions, and a corresponding opening signal is generated. This opening signal can be used to generate a corresponding prompt, specifically a visual output for the pilot to read, allowing the pilot to manually open the pod. Similarly, when the aircraft's speed and altitude do not meet the preset conditions, the pod does not meet the opening conditions, and a corresponding feedback message indicating that the pod cannot be opened can be generated.

[0027] Specifically, the temperature inside the pod can be obtained through a preset temperature sensor, and the temperature can be compared with a preset temperature threshold range. When the temperature is greater than the upper limit of the threshold range, feedback information can be generated that the temperature is too high to be opened, and the pod temperature can be waited for to drop. When the temperature is less than the lower limit of the threshold range, feedback information can be generated that the temperature is too low to be opened, and the onboard power grid can be controlled to power and heat the pod, especially the energy storage device. When applied, the temperature detection before the pod is opened is mainly aimed at the energy storage power supply network. The safety of energy storage equipment is greatly reduced in high temperature environments, and there is a risk of explosion and fire. The electrical performance of energy storage equipment is greatly reduced under low temperature conditions, and the available capacity and output power are significantly reduced. Therefore, it is necessary to ensure that the temperature inside the pod is within a certain range before opening the pod. In actual use, the pod is often in a low-temperature state at high altitudes. At this time, the aircraft power grid can be used to heat the pod instead of the energy storage device itself. On the one hand, the existing aircraft power grid interface can be utilized, and on the other hand, the volume, weight, and design capacity of the energy storage device can be greatly reduced. In a few cases, the pod may also be in a state of excessive temperature. For example, when the ground environment is high and the aircraft rises rapidly after takeoff, the pod temperature does not have time to drop and exceeds the allowable range of the energy storage device. Such working conditions are relatively rare and the pod will automatically cool down after flying for a period of time. In addition, a cooling system is usually designed for electronic equipment in the pod. When necessary, the energy storage device can share the cooling capacity of the system, so there is no need to design a dedicated cooling system for the energy storage device.

[0028] Step S102: when the nacelle temperature is within a preset openable temperature range, the air intake control valve of the ramjet main power grid is opened and a first speed of the ramjet turbine within a preset time period is determined.

[0029] Specifically, when the intake control valve is opened, since the high-voltage contactor remains in the open state, the generator is not connected at this time, and the ram air turbine performs no-load acceleration. The turbine power is adjusted by adjusting the opening of the intake control valve to achieve the purpose of adjusting the turbine speed. In actual use, due to reasons such as continuously changing intake conditions and limited response speed of the intake control valve, the turbine speed is in a continuously fluctuating state. Therefore, as long as the turbine speed r continuously satisfies r2 < r < r1 within the time Δt, it can be considered that the stable state is reached, and at this time, the intake control valve does not need to be actuated for adjustment.

[0030] Step S103: When the first speed is within the speed range corresponding to the preset speed stable state, close the high-voltage contactor and determine the second speed of the ram air turbine. The speed range is an interval greater than the preset second threshold and less than the preset first threshold.

[0031] Specifically, when the intake control valve is opened, since the high-voltage contactor remains in the open state, the generator is not connected at this time, and the ram air turbine performs no-load acceleration. The turbine power is adjusted by adjusting the opening of the intake control valve, so that the turbine speed r is stabilized near the rated speed, that is: the turbine speed r remains r2 < r < r1 within the preset time Δt1. At this time, it is determined that the turbine speed meets the opening condition of the aircraft pod, otherwise, feedback information that the aircraft pod does not meet the opening condition is generated.

[0032] Since the high-voltage contactor is closed and the generator is connected to the load, the turbine speed drops instantaneously during the loading. At this time, it is necessary to increase the opening of the intake control valve to increase the turbine speed, so that the turbine speed can meet r2 < r < r1 again, so that the system enters a stable operation state. However, due to reasons such as changes in the power consumption of the load and changes in flight speed, the turbine speed will change, and the turbine speed will slow down or speed up, and it is necessary to readjust the turbine speed.

[0033] Step S104: When it is detected that the second speed is outside the speed range corresponding to the speed stable state, control the series-parallel connection of the ram main power grid and the energy storage power grid by controlling the intake control valve, the closed high-voltage contact, and the bidirectional DC-to-DC rectifier for power supply.

[0034] When the turbine speed is too high or too low, continuing to supply power in parallel by the ram main power grid and the energy storage power grid will affect the stable operation of the aircraft pod equipment. Therefore, it is necessary to switch between the coordinated power supply mode and the individual power supply mode in real time according to the change of the turbine speed.

[0035] In an embodiment of the present application, when aircraft performance parameters meet the aircraft pod opening conditions and the pod temperature is within a preset opening temperature range, whether the aircraft pod meets the opening conditions is determined by determining whether the ramjet turbine speed meets the speed range corresponding to the speed stability state within a preset time period after the air intake control valve is opened. The high-voltage contactor is then closed to connect the generator to the load, the ramjet turbine power generation capacity is associated with the aircraft flight state, and the series and parallel connection of the ramjet main power generation grid and the energy storage power supply grid is controlled according to the turbine speed detected in real time. This reduces the occurrence of power supply instability and uncertainty problems caused by the mismatch between the ramjet turbine power generation capacity and the aircraft flight state in the prior art, thereby improving the stability of pod equipment operation.

[0036] In some embodiments, step S104 further includes:

[0037] Step S1041 (not shown): When the second speed is not less than the first threshold, the speed of the ramjet turbine is decelerated according to a preset fast coordinated control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the coordinated power supply according to the deceleration result.

[0038] Step S1042 (not shown): When the second speed is not greater than the second threshold, the speed of the ramjet turbine is increased according to a preset low-speed collaborative control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the collaborative power supply according to the speed-increasing result.

[0039] Specifically, the speed of the ramjet turbine is generally adjusted by adjusting the opening of the intake control valve. When the opening increases, the turbine power increases and the turbine speed increases accordingly; when the opening decreases, the turbine power decreases and the turbine speed decreases.

[0040] Specifically, the closing and opening of the high-voltage contactor is used to control whether the generator voltage is output, thereby playing a role in controlling whether the coordinated power supply is provided.

[0041] In some embodiments, step S1041 further includes:

[0042] When the second speed continues to increase and maintain within the preset speed-increasing cooperative power supply speed range after reducing the intake control valve opening, the step of reducing the intake control valve opening is continued until the preset minimum opening value is reached, and the speed-increasing cooperative power supply speed range is an interval not less than the first threshold value and not greater than the fifth threshold value;

[0043] When the second speed continues to increase after reducing the opening of the intake control valve and is greater than the preset speed range of the energy storage grid's independent power supply, the opening of the intake control valve is reduced until the intake control valve is closed and after disconnecting the high-voltage contactor, it is detected that the high-voltage DC bus voltage returns to zero and continues for a preset voltage zero time period, and then the bidirectional DC-to-DC rectifier is turned on to connect the energy storage power supply grid in a constant voltage mode.

[0044] Specifically, the minimum opening value of the intake control valve is set based on control accuracy to avoid oscillation, which can occur when the minimum opening value falls below the control accuracy and leads to failure in the intake control valve's opening control. In practice, if the intake control valve's control accuracy is 99%, the corresponding minimum opening value is no greater than 1%. Because the minimum opening value is set, the intake control valve will not completely close after the opening is reduced to the minimum value, thus avoiding oscillation of the intake control valve and problems with the intake control valve opening or closing due to frequent opening reduction operations.

[0045] Specifically, the upper limit of the speed range of the accelerated coordinated power supply is generally the lower limit of the speed range of the fast energy storage grid alone. That is, whether the turbine speed is too high is determined by the extent to which the turbine speed is greater than the first threshold r1. If the speed is too high, continuing to connect the ram main power generation grid and the energy storage power supply grid in parallel for coordinated power supply will cause the generator output electromotive force to be too high, thereby exceeding the adjustment capability of the generator controller, causing damage to the generator controller and affecting its operational stability.

[0046] In the embodiment of the above step S1041, the method further includes:

[0047] The speed-increasing cooperative power supply speed range includes a first fast interval and a second fast interval. The first fast interval is a range not less than a first threshold and not greater than a third threshold, and the second fast interval is a range greater than the third threshold and not greater than a preset fifth threshold. When the second speed continues to increase and remains in the preset speed-increasing cooperative power supply speed range after the intake control valve opening is reduced, the step of reducing the intake control valve opening is continued until the preset minimum opening value is reached, including: when the speed of the ramjet turbine is in the first fast interval after the intake control valve opening is reduced, the generator controller is controlled to output voltage according to a preset first stable voltage value by adjusting the duty cycle of the switch tube; when the speed of the ramjet turbine is in the second fast interval after the intake control valve opening is reduced, the generator controller is controlled to control the output voltage from the first stable voltage value to the second stable voltage value by adjusting the duty cycle of the switch tube according to the preset second stable voltage value.

[0048] Specifically, the first stable voltage value is generally set to 270V.

[0049] Specifically, the second stable voltage value is generally set to 280V.

[0050] The embodiment of the present application controls the output voltage of the generator controller by setting the first fast interval and the second fast interval, thereby avoiding adjusting the output voltage of the generator controller when the speed is too fast and the generator electromotive force is too high.

[0051] In some embodiments, step S1042 further includes:

[0052] When the second speed continues to decrease and remains within the preset deceleration cooperative power supply speed range after the intake control valve opening is increased, the step of continuing to increase the intake control valve opening until a preset maximum opening is reached, and the deceleration cooperative power supply speed range is not less than a preset sixth threshold value and not greater than the second threshold value;

[0053] When the second speed continues to decrease and maintains the preset speed range of the deceleration energy storage grid power supply after the intake control valve opening is increased, the intake control valve opening is continued to increase until the preset maximum opening value is reached and the high-voltage contactor is disconnected, so that the energy storage power supply network is connected to the high-voltage DC bus in a constant voltage mode, and the speed range of the deceleration energy storage grid power supply is less than the preset sixth threshold.

[0054] Specifically, when the second speed continues to decrease to less than the sixth threshold range after the intake control valve opening is increased, that is, the speed is in the speed range where the deceleration energy storage grid is solely powered, on the one hand, the turbine power is increased by increasing the intake control valve opening until the intake control valve opening reaches the maximum value, and on the other hand, the high-voltage contactor is disconnected and the energy storage grid is solely powered. The energy storage grid solely supplies power to the high-voltage DC bus in a constant voltage mode.

[0055] Specifically, the corresponding maximum opening degree can be determined according to the type of the intake control valve. The maximum opening degree is used to control the amount of air flowing into the ram turbine, thereby achieving maximum power control of the ram turbine.

[0056] Specifically, the settings for the deceleration coordinated power supply speed range and the speed range for independent power supply from the energy storage grid determine whether power is supplied solely by the ramjet main power grid or the energy storage grid, or whether the main ramjet power grid and the energy storage grid are connected in parallel for coordinated power supply. In application, when the ramjet turbine speed is within the independent power supply speed range from the energy storage grid, the high-voltage contactor is disconnected to disconnect the load and increase the ramjet turbine speed.

[0057] The above-mentioned step S1042 further includes: the deceleration cooperative power supply speed range includes a first slow speed interval and a second slow speed interval, the first slow speed interval is a range not less than the fourth threshold and not greater than the second threshold, and the second slow speed interval is a range not less than the sixth threshold and less than the fourth threshold; when the second speed continues to decrease and maintains the preset deceleration cooperative power supply speed range after the intake control valve opening is increased, the step of continuing to increase the intake control valve opening until the preset maximum opening is reached, including: when the speed of the ramjet turbine is in the first slow speed interval after the intake control valve opening is increased, controlling the generator controller to output voltage according to the preset third stable voltage value by adjusting the duty cycle of the switch tube; when the speed of the ramjet turbine is in the second slow speed interval after the intake control valve opening is increased, controlling the generator controller to control the output voltage to decrease from the third stable voltage value to the fourth stable voltage value by adjusting the duty cycle of the switch tube according to the preset fourth stable voltage value.

[0058] Specifically, the third stable voltage value is generally set to 270V.

[0059] Specifically, the fourth stable voltage value is generally set to U.

[0060] During application, when the speed of the ramjet turbine is in the second slow speed range, the output voltage is controlled to drop from 270V to U, that is, by setting the voltage drop U, energy loss is reduced to ensure normal operation of the equipment.

[0061] In the above-mentioned step S1042, when the second speed continues to decrease and maintains the preset deceleration cooperative power supply speed range after the intake control valve opening is increased, the step of continuing to increase the intake control valve opening until the preset maximum opening value is reached also includes: when the speed of the ramjet turbine reaches a sixth threshold after the intake control valve opening is increased, the bidirectional DC-to-DC rectifier is turned on, so that the energy storage power supply network is connected in a constant voltage mode to the ramjet main power generation network and the energy storage power supply network in parallel for cooperative power supply.

[0062] Specifically, the control of the conduction of the bidirectional DC-DC rectifier plays a role in controlling the parallel connection of the stamping main power generation grid and the energy storage power supply grid, thereby achieving the purpose of coordinated power supply of the two in parallel.

[0063] The following combination Figure 2 and Figure 3 This application is described in detail. Aircraft pod control system Figure 2As shown, it includes a ramjet main power grid and an energy storage power grid. The ramjet main power grid includes an intake control valve, a ramjet turbine, a generator, and a generator controller. The intake control valve controls the air flow into the ramjet turbine. In practice, the control valve can be installed directly at the intake port, acting as the intake control valve, while the exhaust port is not equipped with a control valve. Under the same flight conditions, a larger intake control valve opening increases the intake volume, which in turn increases the acceleration force on the turbine and increases the speed. Conversely, a smaller intake control valve opening decreases the intake volume, which in turn decreases the acceleration force on the turbine and decreases the speed. Adjusting the intake control valve opening controls the ramjet turbine's power, thereby driving the generator. The generator controller also provides backflow prevention, preventing current from flowing from the high-voltage DC busbar to the generator. This isolates the power output of the generator and energy storage device from the onboard main grid, ensuring that the safety of the ramjet main power grid is not affected in the event of a pod failure. Before the high-voltage contactor closes, the ramjet turbine accelerates at no load. After closing, the generator is connected to the load (i.e., user equipment). The energy storage power supply network includes an energy storage device thermal management system for managing the energy storage device. The energy storage device is connected to the high-voltage DC busbar through a bidirectional DC-DC rectifier. Specifically, Figure 3 Six thresholds are set, namely r1, r2, r3, r4, r5 and r6. Assume that the speed range corresponding to the speed stable state of the rated speed r0 is (r2, r1). When applied, the rated speed, the speed range corresponding to the speed stable state and the six thresholds can be set as follows: rated speed r0 = 20000r / min (determined by the material properties of the turbine and generator), r1 = 21000r / min (r0×1.05~1.1), r2 = 19000r / min (r0×0.9~0.95), r3 = 25000r / min (r0×1.3~1.5, determined by the voltage regulation capability of the generator controller), r4 = 15000r / min (r0×0.6~0.8, determined by the voltage regulation capability of the generator controller), r5 = 27000r / min ( r0×1.35~1.55, determined by the voltage regulation capability of the generator controller), r6=12000r / min(r0×0.55~0.75, determined by the voltage regulation capability of the generator controller), △t1=1~5s, △t2=10~30ms(△t2+high-voltage contactor actuation time+DCDC state switching time<50ms), U=255V (theoretically, it can be between 250V and 270V. A value too close to 270V will result in frequent activation of the energy storage device, which cannot fully utilize the ram air energy and requires a larger design capacity of the energy storage device. A value too close to 250V will increase the risk of short-term low voltage).

[0064] When applied, the system includes steps S10 to S110.

[0065] S10: After the aircraft takes off, the pod control system obtains the flight speed and altitude information from the aircraft. After meeting the pod opening conditions, it feeds back the information that it can be opened to the aircraft. At this time, the pilot can manually open the pod system. After opening, it enters S20; otherwise, it feeds back the information that it cannot be opened to the aircraft. At this time, the pilot cannot open the pod system;

[0066] S20: The pod control system judges whether its own temperature is within the operable range through the temperature sensor group in the pod. If so, it directly enters S30; if the temperature is too high, it feeds back to the aircraft that the temperature is too high and it cannot be opened temporarily, and waits for the temperature to drop; if the temperature is too low, the on-board power grid supplies power to heat the pod, especially to heat the energy storage device. After its temperature rises to the operable range, it enters S30;

[0067] S30: The intake control valve opens, the high-voltage contactor disconnects to keep the generator from being connected to the system, the turbine accelerates unloaded, and the opening of the intake control valve is adjusted to make the turbine speed r stable near the rated speed r0, that is, to meet that the turbine speed r remains r2 < r < r1 within the time △t1, and then it enters S40. If this condition cannot be met, it maintains this state, and after the duration t1, it feeds back the information to the aircraft: the turbine speed does not meet the pod opening conditions;

[0068] S40: Close the high-voltage contactor, connect the generator to the load. At the moment of loading, the turbine speed drops, and the system controller increases the opening of the intake control valve to make the speed r meet r2 < r < r1 again, and the system enters the stable operation state; when the turbine speed increases above r1 due to factors such as the reduction of the power consumed by the load and the increase of the flight speed, it enters S50; when the turbine speed drops below r2 due to factors such as the increase of the power consumed by the load and the decrease of the flight speed, it enters S80;

[0069] S50: r ≥ r1, the turbine speed is too fast. The turbine power is reduced by reducing the opening of the intake control valve. If the speed drops below r1, it returns to S40. If the speed continues to increase above r3, it enters S60. If the speed remains between r1 and r3, this step is repeated until the opening of the intake control valve reaches the minimum value; in this step, the generator controller outputs a stable 270V voltage by adjusting the duty cycle of the switching tube.

[0070] S60: r > r3. The turbine speed is relatively fast. The turbine power is reduced by decreasing the opening degree of the intake control valve. If the speed drops below r3, return to S50. If the speed continues to increase above r5, enter S70. If the speed remains between r3 and r5, repeat this step until the opening degree of the intake control valve reaches the minimum value. In this step, since the speed is too fast and the electromotive force of the generator is too high, the generator controller can no longer stabilize the output voltage at 270V. As the speed increases from r3 to r5, the output voltage of the generator controller increases from 270V to 280V, and this voltage still meets the requirements of GJB181B for aviation power supply. Therefore, the system architecture can remain unchanged.

[0071] S70: r > r5. The turbine speed is too fast. On the one hand, the turbine power is reduced by decreasing the opening degree of the intake control valve until the intake control valve is closed to avoid breakdown of the switching tube in the generator controller. On the other hand, the high-voltage contactor is disconnected. After detecting that the busbar voltage is zero and lasts for △t2, the bidirectional DCDC conducts, and the energy storage device is connected in a constant-voltage mode to supply power to the busbar alone. When r < r5, the bidirectional DCDC is disconnected. After detecting that the busbar voltage is zero and lasts for △t2, the high-voltage contactor closes, and return to S60, or when the energy of the energy storage device is exhausted, the system shuts down.

[0072] S80: r < r2. The turbine speed is relatively slow. The turbine power is increased by increasing the opening degree of the intake control valve. If the speed rises above r2, return to S40. If the speed continues to drop below r4, enter S90. If the speed remains between r2 and r4, repeat this step until the opening degree of the intake control valve reaches the maximum value. In this step, the generator controller outputs a stable voltage of 270V by adjusting the duty cycle of the switching tube.

[0073] S90: r < r4. The turbine speed is slow. The turbine power is increased by increasing the opening degree of the intake control valve. If the speed rises above r4, return to S80. If the speed continues to drop below r6, enter S100. If the speed remains between r4 and r6, repeat this step until the opening degree of the intake control valve reaches the maximum value. In this step, since the speed is too slow and the electromotive force of the generator is too high, the generator controller can no longer stabilize the output voltage at 270V. As the speed increases from r3 to r5, the output voltage of the generator controller decreases from 270V to U, and this voltage still meets the requirements of GJB181B for aviation power supply. Therefore, the system architecture can remain unchanged.

[0074] S100: r = r6, the turbine speed is slow. On the one hand, the turbine power is increased by increasing the opening degree of the intake control valve until the opening degree of the intake control valve reaches the maximum value. On the other hand, the bidirectional DCDC conducts and is connected to the system in a constant voltage mode. The constant voltage is U and is powered in parallel with the generator. At this time, the generator controller outputs power at voltage U, and the insufficient part is supplemented by the energy storage device. The output power of the turbine power generation system can fluctuate between 100% and 0 while the speed remains unchanged. After r > r6, return to S90, or when the energy of the energy storage device is exhausted and cannot provide supplementary energy, and the turbine power generation system itself is not sufficient to support all load requirements, the speed further decreases, r < r6, and enter S110.

[0075] S110: r < r6, the turbine speed is too slow. Even when the energy storage device undertakes all the power output, the turbine speed still drops below r6, indicating that at this time the turbine power is not even sufficient to overcome its own and rotational resistance. At this time, on the one hand, the turbine power is increased by increasing the opening degree of the intake control valve until the opening degree of the intake control valve reaches the maximum value. On the other hand, the high-voltage contactor is disconnected, and the parallel state ends. The energy storage device supplies power to the busbar alone in a constant voltage mode until r = r6, and then return to S100, or when the energy of the energy storage device is exhausted, the system shuts down.

[0076] In application, the generator can be a permanent magnet generator or a three-stage generator. The former is small in size, light in weight, and high in power generation efficiency. The latter has good stability and high safety. Due to the large restrictions on volume and weight in the nacelle and the small impact on the safety of the aircraft body after nacelle failure, a permanent magnet generator is usually preferred. The rotor of the permanent magnet generator is directly connected rigidly to the ram air turbine, and their speeds are proportional. The electromotive force formed by the permanent magnet generator is directly determined by the turbine speed and is constantly changing. The generator controller needs to stabilize the voltage. Usually, a full-control type controller is used. By adjusting the duty cycle of the switching tube in the controller, the voltage output by the generator controller to the high-voltage DC busbar is adjusted. When the turbine speed is between r4 and r3, the generator controller can maintain the output voltage stable at 270V. When the turbine speed is between r6 and r5, the generator controller can maintain the output voltage stable within the stable voltage range specified by GBJ181B. In addition, the switching tube in the generator controller should also have strong insulation ability. In S70, when the turbine speed is too high, the output electromotive force of the generator is too high, exceeding the adjustment ability of the generator controller. After disconnecting the high-voltage contactor, the load disappears, and the turbine speed will further increase, thus forming an extremely high electromotive force, which requires high insulation ability of the switching tube.

[0077] None of the above steps S10 to S90 involve charging the energy storage device. In theory, charging the energy storage device when the turbine speed is too high can consume some power and thus slow down the increase in turbine speed. However, in actual applications, the frequent switching between charging and discharging of the energy storage device has a significant impact on the lifespan and working stability. In addition, the maximum power allowed during the charging process is often less than the maximum discharge power, and the charging process has little impact on power regulation. Therefore, the energy storage device should be confirmed to be fully charged before takeoff. During flight, it can only be charged at a lower power when operating in steady state, which is equivalent to a low-power electrical load.

[0078] Energy storage devices operate in two modes: constant voltage mode and charging mode. In constant voltage mode, the constant voltage can be set to U, and the bidirectional DC-DC system only allows current to flow out. In theory, charging the energy storage device when the turbine speed is too high can consume some power, thereby slowing the increase in turbine speed. However, in actual applications, the frequent switching between charging and discharging of energy storage devices has a significant impact on lifespan and operational stability. Moreover, the maximum power allowed during the charging process is often less than the maximum discharge power, and the charging process has little impact on power regulation. Therefore, the energy storage device should be confirmed to be fully charged before takeoff. During flight, it can only operate in charging mode at a lower power during steady-state operation, equivalent to a low-power electrical load. In terms of parameter design, the maximum power of the energy storage device is basically consistent with the load power demand and the rated power of the generator. Its capacity is determined by the maximum power and the independent power supply time required by the system. The latter is determined by the aircraft status, mission, attitude, etc.

[0079] Another embodiment of the present application provides a power supply control device for an aircraft pod control system, wherein the aircraft pod control system includes a stamping main power generation network and an energy storage power supply network, the stamping main power generation network is connected to a high-voltage DC return bar through a high-voltage contactor, and the energy storage power supply network is connected to a high-voltage DC return bar through a bidirectional DC-DC rectifier. Figure 4 As shown, the device 40 includes: a pod temperature determination module 401 , a turbine speed determination module 402 , a load speed determination module 403 and a coordinated power supply control module 404 .

[0080] The cabin temperature determination module 401 is used to determine the cabin temperature when a signal indicating that the aircraft cabin can be opened is detected;

[0081] The turbine speed determination module 402 is configured to determine a first speed of the ramjet turbine within a preset time period after opening the air intake control valve of the ramjet main power grid when the nacelle temperature is within a preset openable temperature range;

[0082] a load speed determination module 403, configured to close the high-voltage contactor and determine a second speed of the ramjet turbine when the first speed is within a preset speed range corresponding to a stable speed state, wherein the speed range is an interval between a preset second threshold value and a preset first threshold value;

[0083] The collaborative power supply control module 404 is used to control the series and parallel power supply of the ramjet main power generation grid and the energy storage power supply grid by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier when it detects that the second speed is outside the speed range corresponding to the speed stable state.

[0084] In an embodiment of the present application, when aircraft performance parameters meet the aircraft pod opening conditions and the pod temperature is within a preset opening temperature range, whether the aircraft pod meets the opening conditions is determined by determining whether the ramjet turbine speed meets the speed range corresponding to the speed stability state within a preset time period after the air intake control valve is opened. The high-voltage contactor is then closed to connect the generator to the load, the ramjet turbine power generation capacity is associated with the aircraft flight state, and the series and parallel connection of the ramjet main power generation grid and the energy storage power supply grid is controlled according to the turbine speed detected in real time. This reduces the occurrence of power supply instability and uncertainty problems caused by the mismatch between the ramjet turbine power generation capacity and the aircraft flight state in the prior art, thereby improving the stability of pod equipment operation.

[0085] Furthermore, the coordinated power supply control module 404 includes:

[0086] a speed reduction processing coordination submodule, configured to, when the second speed is not less than the first threshold, decelerate the speed of the ramjet turbine according to a preset fast coordinated control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the coordinated power supply according to the deceleration result;

[0087] The speed increase processing collaborative submodule is used to increase the speed of the ramjet turbine according to a preset low-speed collaborative control strategy for the ramjet main power generation grid and the energy storage power supply grid when the second speed is not greater than the second threshold, so as to control the collaborative power supply according to the speed increase result.

[0088] Furthermore, the speed reduction processing coordination submodule includes:

[0089] a first speed reduction coordinated processing unit, configured to continue the step of reducing the intake control valve opening until a preset minimum opening value is reached when the second speed continues to increase and maintain within a preset speed-increasing coordinated power supply speed range after reducing the intake control valve opening, wherein the speed-increasing coordinated power supply speed range is an interval that is not less than the first threshold value and not greater than a fifth threshold value;

[0090] The second speed reduction collaborative processing unit is used to reduce the opening of the intake control valve until the intake control valve is closed and the high-voltage contactor is disconnected, when the second speed continues to increase after the opening of the intake control valve is reduced and is greater than the preset speed range of the speed-increasing energy storage grid alone. After detecting that the high-voltage DC bus voltage returns to zero and continues for a preset voltage zero time period, the bidirectional DC-to-DC rectifier is turned on, so that the energy storage power supply network is connected to the high-voltage DC bus in a constant voltage mode to supply power, and the speed range of the speed-increasing energy storage grid alone is a range greater than the fifth threshold.

[0091] Furthermore, the speed-increasing collaborative power supply speed range includes a first fast interval and a second fast interval, the first fast interval is a range not less than the first threshold and not greater than the third threshold, and the second fast interval is a range greater than the third threshold and not greater than the preset fifth threshold. The first speed-down collaborative processing unit includes: a first speed-down voltage processing subunit, which is used to control the generator controller to output voltage according to a preset first stable voltage value by adjusting the duty cycle of the switching tube when the speed of the ramjet turbine is in the first fast interval after the opening of the intake control valve is reduced; and a second speed-down voltage processing subunit, which is used to control the generator controller to control the output voltage from the first stable voltage value to the second stable voltage value by adjusting the duty cycle of the switching tube when the speed of the ramjet turbine is in the second fast interval after the opening of the intake control valve is reduced.

[0092] Furthermore, the second speed reduction collaborative processing unit is also used to control the bidirectional DC-to-DC rectifier to open the circuit when it detects that the speed of the ramjet turbine is less than the fifth threshold value, and after detecting that the high-voltage DC bus voltage returns to zero and continues for a voltage zero time period, close the high-voltage contactor and supply power from the ramjet main power generation grid.

[0093] Furthermore, the speed-up processing coordination submodule includes:

[0094] a first speed-increasing cooperative processing unit, configured to, when the second speed continues to decrease and maintain within a preset deceleration cooperative power supply speed range after the intake control valve opening is increased, continue to increase the intake control valve opening until a preset maximum opening is reached, wherein the deceleration cooperative power supply speed range is not less than a preset sixth threshold value and not less than the second threshold value;

[0095] The second speed-increasing collaborative processing unit is configured to, when the second speed continues to decrease and maintain within a preset speed range for independent power supply of the deceleration energy storage grid after the opening of the intake control valve is increased, continue to increase the opening of the intake control valve until a preset maximum opening is reached and disconnect the high-voltage contactor, so that the energy storage power supply grid is connected to the high-voltage DC bus in a constant voltage mode, and the speed range for independent power supply of the deceleration energy storage grid is less than a preset sixth threshold value.

[0096] Furthermore, the deceleration cooperative power supply speed range includes a first slow speed interval and a second slow speed interval, the first slow speed interval is a range not less than the fourth threshold and not greater than the second threshold, and the second slow speed interval is a range not less than the sixth threshold and less than the fourth threshold, and the first speed increase cooperative processing unit includes: a first speed increase voltage processing subunit, which is used to control the generator controller to output voltage according to a preset third stable voltage value by adjusting the duty cycle of the switch tube when the speed of the ramjet turbine is in the first slow speed interval after the intake control valve opening is increased; and a second speed increase voltage processing subunit, which is used to control the generator controller to control the output voltage from the third stable voltage value to the fourth stable voltage value by adjusting the duty cycle of the switch tube when the speed of the ramjet turbine is in the second slow speed interval after the intake control valve opening is increased.

[0097] Furthermore, the first deceleration collaborative processing unit is also used to turn on the bidirectional DC-to-DC rectifier when the speed of the ramjet turbine reaches a sixth threshold after the opening of the intake control valve is increased, so that the energy storage power supply network is connected in a constant voltage mode to the ramjet main power generation network and the energy storage power supply network in parallel for collaborative power supply.

[0098] The power supply control device of the aircraft pod control system provided in the embodiment of the present application can execute the power supply control method of the aircraft pod control system provided in the embodiment of the present application. The implementation principles are similar and will not be repeated here.

[0099] Yet another embodiment of the present application provides a terminal, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the above method when executing the computer program.

[0100] Specifically, a processor may be a CPU, a general-purpose processor, a DSP, an ASIC, an FPGA, or other programmable logic device, a transistor logic device, a hardware component, or any combination thereof. It may implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this application. A processor may also be a combination that implements computing functions, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, and the like.

[0101] Specifically, the processor is connected to the memory via a bus. The bus may include a path for transmitting information. The bus may be a PCI bus or an EISA bus. The bus may be divided into an address bus, a data bus, a control bus, etc.

[0102] The memory may be a ROM or other type of static storage device that can store static information and instructions, a RAM or other type of dynamic storage device that can store information and instructions, or an EEPROM, CD-ROM or other optical disk storage, optical disc storage (including compact disc, laser disc, optical disc, digital versatile disc, Blu-ray disc, etc.), magnetic disk storage medium or other magnetic storage device, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and can be accessed by a computer, but is not limited to these.

[0103] Optionally, the memory is used to store the code of the computer program that executes the solution of the present application, and the execution is controlled by the processor. The processor is used to execute the application program code stored in the memory to implement the actions of the device provided by the above embodiment.

[0104] Another embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which implements the above method when executed by a processor.

[0105] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, i.e., they may be located in one place or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of this embodiment.

[0106] Those skilled in the art will appreciate that all or some of the steps and systems in the method disclosed above can be implemented as software, firmware, hardware, and appropriate combinations thereof. Some physical components or all physical components can be implemented as software executed by a processor, such as a central processing unit, a digital signal processor, or a microprocessor, or implemented as hardware, or implemented as an integrated circuit, such as an application-specific integrated circuit. Such software can be distributed on a computer-readable medium, and the computer-readable medium can include computer storage media (or non-transitory media) and communication media (or temporary media). As known to those skilled in the art, the term computer storage media is included in any method or technology for storing information (such as computer-readable instructions, data structures, program modules, or other data) and is volatile and non-volatile, removable, and non-removable. Computer storage media includes, but is not limited to, RAM, ROM, EEPROM, flash memory, or other memory technology, CD-ROM, digital versatile disks (DVD), or other optical disk storage, magnetic cassettes, magnetic tapes, disk storage, or other magnetic storage devices, or any other medium that can be used to store desired information and can be accessed by a computer. Furthermore, as is well known to those skilled in the art, communication media typically embodies computer-readable instructions, data structures, program modules, or other data in a modulated data signal such as a carrier wave or other transport mechanism, and may include any information delivery media.

[0107] The above is a specific description of the preferred implementation of the present application, but the present application is not limited to the above implementation mode. Technical personnel familiar with the field can also make various equivalent modifications or substitutions without violating the spirit of the present application. These equivalent modifications or substitutions are all included in the scope defined by the claims of the present application.

Claims

1. A power supply control method for an aircraft pod control system, characterized in that: The aircraft pod control system comprises a stamping main power generation grid and an energy storage power supply grid, wherein the stamping main power generation grid is connected to the high-voltage DC return bar via a high-voltage contactor, and the energy storage power supply grid is connected to the high-voltage DC return bar via a bidirectional DC-to-DC rectifier, and the method comprises: When it is detected that the aircraft performance parameters meet the conditions for opening the aircraft pod, the pod temperature is determined; When the nacelle temperature is within a preset openable temperature range, an air intake control valve of the ramjet main power generation grid is opened and a first speed of the ramjet turbine within a preset time period is determined; When the first speed is within a speed range corresponding to a preset speed stable state, closing the high-voltage contactor and determining a second speed of the ramjet turbine, wherein the speed range is an interval greater than a preset second threshold value and less than a preset first threshold value; When it is detected that the second speed is outside the speed range corresponding to the speed stable state, the series and parallel power supply of the ramming main power generation grid and the energy storage power supply grid are controlled by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier.

2. The method according to claim 1, characterized in that When it is detected that the second speed is outside the speed range corresponding to the speed stable state, controlling the series-parallel power supply of the stamping main power generation grid and the energy storage power supply grid by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier, includes: When the second speed is not less than the first threshold, the speed of the ramjet turbine is decelerated according to a preset fast coordinated control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the coordinated power supply according to the deceleration result; When the second speed is not greater than the second threshold, the speed of the ramjet turbine is increased according to a preset low-speed collaborative control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the collaborative power supply according to the increase in speed result.

3. The method according to claim 2, characterized in that When the second speed is not less than the first threshold, the speed of the ramjet turbine is decelerated according to a preset fast coordinated control strategy for the ramjet main power generation grid and the energy storage power supply grid, so as to control the coordinated power supply according to the deceleration result, including: When the second speed continues to increase and maintains the preset speed-increasing coordinated power supply speed range after reducing the intake control valve opening, the step of reducing the intake control valve opening is continued until the preset minimum opening value is reached, and the speed-increasing coordinated power supply speed range is an interval not less than the first threshold value and not greater than the fifth threshold value; When the second speed continues to increase after reducing the opening of the intake control valve and is greater than the preset speed range of the speed-increasing energy storage grid alone, the opening of the intake control valve is reduced until the intake control valve is closed and after disconnecting the high-voltage contactor, after detecting that the high-voltage DC bus voltage returns to zero and continues for a preset voltage zero time period, the bidirectional DC-to-DC rectifier is turned on so that the energy storage power supply network is connected in a constant voltage mode to supply power to the high-voltage DC bus, and the speed range of the speed-increasing energy storage grid alone is a range greater than the fifth threshold.

4. The method according to claim 3, characterized in that The speed-increasing coordinated power supply speed range includes a first rapid interval and a second rapid interval, the first rapid interval is a range not less than the first threshold value and not greater than a third threshold value, the second rapid interval is a range greater than the third threshold value and not greater than a preset fifth threshold value, and when the second speed continues to increase and maintain the preset speed-increasing coordinated power supply speed range after reducing the intake control valve opening, the step of reducing the intake control valve opening is continued until a preset minimum opening value is reached, including: When the speed of the ramjet turbine is in the first fast range after the opening of the intake control valve is reduced, the generator controller is controlled to output voltage according to a preset first stable voltage value by adjusting the duty cycle of the switch tube; When the speed of the ramjet turbine is in the second fast range after the opening of the intake control valve is reduced, the generator controller is controlled to increase the output voltage from the first stable voltage value to the second stable voltage value according to a preset second stable voltage value by adjusting the duty cycle of the switching tube.

5. The method according to claim 3, characterized in that: After detecting that the voltage of the high-voltage DC busbar returns to zero and continues for a preset voltage zero time period, the bidirectional DC-to-DC rectifier is turned on, so that the energy storage power supply network is connected in a constant voltage mode to supply power to the high-voltage DC busbar, and further includes: When it is detected that the rotation speed of the ramjet turbine is less than the fifth threshold value, the bidirectional DC-to-DC rectifier is controlled to be disconnected, and after it is detected that the high-voltage DC bus voltage returns to zero and lasts for the voltage zero time period, the high-voltage contactor is closed and power is supplied by the ramjet main power generation grid.

6. The method according to claim 2, characterized in that When the second speed is not greater than the second threshold, the speed of the ramjet turbine is increased according to a preset low-speed coordinated control strategy for the intake control valve and the high-voltage contactor, including: When the second speed continues to decrease and remains in a preset deceleration cooperative power supply speed range after increasing the intake control valve opening, the step of continuing to increase the intake control valve opening until a preset maximum opening is reached, and the deceleration cooperative power supply speed range is not less than a preset sixth threshold value and not greater than the second threshold value; When the second speed continues to decrease and maintains the preset deceleration energy storage grid power supply speed range after increasing the intake control valve opening, the intake control valve opening continues to increase until the preset maximum opening value is reached and the high-voltage contactor is disconnected, so that the energy storage power supply network is connected in a constant voltage mode to supply power to the high-voltage DC bus, and the deceleration energy storage grid power supply speed range is less than a preset sixth threshold.

7. The method according to claim 6, characterized in that The deceleration cooperative power supply speed range includes a first slow speed interval and a second slow speed interval, the first slow speed interval is a range not less than a preset fourth threshold value and not greater than a second threshold value, the second slow speed interval is a range not less than the sixth threshold value and less than the fourth threshold value, and when the second speed continues to decrease and maintain the preset deceleration cooperative power supply speed range after increasing the intake control valve opening, the step of continuing to increase the intake control valve opening until a preset maximum opening value is reached includes: When the speed of the ramjet turbine is in the first slow speed range after the opening of the intake control valve is increased, the generator controller is controlled to output voltage according to a preset third stable voltage value by adjusting the duty cycle of the switch tube; When the speed of the ramjet turbine is in the second slow speed range after the intake control valve opening is increased, the generator controller is controlled to control the output voltage to decrease from the third stable voltage value to the fourth stable voltage value according to a preset fourth stable voltage value by adjusting the duty cycle of the switch tube.

8. The method according to claim 6, characterized in that When the second speed continues to decrease and maintains the preset deceleration cooperative power supply speed range after increasing the intake control valve opening, the step of continuing to increase the intake control valve opening until reaching a preset maximum opening value also includes: When the speed of the ramjet turbine reaches the sixth threshold after increasing the opening of the intake control valve, the bidirectional DC-to-DC rectifier is turned on, so that the energy storage power supply network is connected in a constant voltage mode to supply power in parallel with the ramjet main power generation network and the energy storage power supply network for coordinated power supply.

9. A power supply control device for an aircraft pod control system, characterized in that: The aircraft pod control system includes a stamping main power generation network and an energy storage power supply network, wherein the stamping main power generation network is connected to the high-voltage DC return bar via a high-voltage contactor, and the energy storage power supply network is connected to the high-voltage DC return bar via a bidirectional DC-to-DC rectifier, and the device includes: The cabin temperature determination module is used to determine the cabin temperature when it is detected that the aircraft performance parameters meet the conditions for opening the aircraft cabin; a turbine speed determination module, configured to determine a first speed of the ramjet turbine within a preset time period after opening an air intake control valve of the ramjet main power generation grid when the nacelle temperature is within a preset openable temperature range; a load speed determination module, configured to close the high-voltage contactor and determine a second speed of the ramjet turbine when the first speed is within a speed range corresponding to a preset speed stable state, wherein the speed range is an interval greater than a preset second threshold value and less than a preset first threshold value; The collaborative power supply control module is used to control the series-parallel power supply of the ramming main power generation grid and the energy storage power supply grid by controlling the intake control valve, the closed high-voltage contact and the bidirectional DC-to-DC rectifier when it is detected that the second speed is outside the speed range corresponding to the speed stable state.

10. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer-readable instructions, and the processor is used to execute the computer-readable instructions, wherein the computer-readable instructions execute the method according to any one of claims 1 to 7 when executed.

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