Speed ​​reduction mechanism, maneuvering flap system, control method, device and medium

Abstract

The present invention provides a deceleration mechanism, a maneuvering flap system, a control method, a device and a medium, wherein the deceleration mechanism includes a deceleration plate, the deceleration plate is hinged to the trailing edge of the wing and connected to a power unit; when the trailing edge flap of the wing is folded up, the deceleration plate is opened relative to the wing under the drive of the power unit; when the trailing edge flap is lowered, the deceleration plate is closed relative to the wing under the drive of the power unit. The mechanism, system, method, device and medium provided by the present invention effectively weaken the influence of the separation vortex during flight by setting a deceleration plate hinged to the trailing edge of the wing and controlling the deceleration plate to open or close based on the state of the trailing edge flap, which helps to ensure flight safety.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a deceleration mechanism, a maneuverable flap system, a control method, a device and a medium. Background Art

[0002] The maneuvering flap system is an integrated electromechanical and hydraulic system that assists in control. It has the dual functions of lift-enhancing flaps for takeoff and landing and subsonic maneuvering flaps. During operation, the maneuvering flap system can control the flap deflection to a specified angle based on the electro-hydraulic servo position system, receiving atmospheric engine commands and manual switch commands from the pilot.

[0003] When the trailing edge flap is deflected downward, although it can increase the velocity of the airflow on the upper wing surface, thereby increasing the lift coefficient, it will also increase the local angle of attack of the airflow at the leading edge of the wing, generating a separation vortex. The generation of a separation vortex will cause a large nose-up moment, and the control circuit resistor of the electronically controlled pressure sensing part of the maneuvering flap system may fuse, causing control circuit failure or even failure of the control circuit. Therefore, it is necessary to optimize the various problems caused by the separation vortex in the maneuvering flap system. Summary of the invention

[0004] The present invention provides a deceleration mechanism, a maneuverable flap system, a control method, a device and a medium, which are used to solve the defects in the prior art that a separated vortex causes poor stability of the maneuverable flap system and poses a hidden danger to flight safety.

[0005] The present invention provides a deceleration mechanism, comprising a deceleration plate, wherein the deceleration plate is hinged to the trailing edge of a wing and connected to a power device;

[0006] When the trailing edge flap of the wing is retracted, the speed brake is opened relative to the wing under the drive of the power plant;

[0007] When the trailing edge flap is lowered, the air brake is closed relative to the wing under the drive of the power plant.

[0008] The present invention also provides a maneuverable flap system, comprising a control module, a power device, and the deceleration mechanism as described above; the control module is connected to the power device, and the control module is used to control the power device to drive the deceleration plate in the deceleration mechanism to open or close.

[0009] A maneuvering flap system according to the present invention further includes a noise sensing device, wherein the noise sensing device is disposed on the speed brake and connected to the control module;

[0010] The noise sensing device is used to collect noise signals;

[0011] The control module is further configured to control the power plant to adjust a position of a trailing edge flap of a wing based on the noise signal.

[0012] According to a maneuvering flap system provided by the present invention, the noise sensing device comprises a main noise sensing device, the main noise sensing device is arranged in a first area of ​​the speed brake, and the first area is determined based on the position of the separation vortex;

[0013] The main noise sensing device is used to collect a first noise signal in the area where the separation vortex is located.

[0014] According to a maneuvering flap system provided by the present invention, the noise sensing device further comprises an auxiliary noise sensing device, the auxiliary noise sensing device is arranged in a second area of ​​the speed brake, and the second area is an area outside the first area of ​​the speed brake;

[0015] The auxiliary noise sensing device is used to collect a second noise signal outside the area where the separation vortex is located.

[0016] According to a motorized flap system provided by the present invention, the control module is specifically used for:

[0017] Determining noise sound field distribution information based on the first noise signal and the second noise signal;

[0018] Based on the noise field distribution information, the power device is controlled to adjust the position of the trailing edge flap of the wing.

[0019] The present invention also provides a control method, comprising:

[0020] Get the trailing edge flap status of the wing;

[0021] When the trailing edge flap is in the retracted state, the power device is controlled to drive the air brake to open relative to the wing, and the air brake is hinged to the trailing edge of the wing;

[0022] When the trailing edge flap is in the down state, the power plant is controlled to drive the air brake to close relative to the wing.

[0023] A control method provided by the present invention further includes:

[0024] Acquiring a noise signal collected by a noise sensing device, wherein the noise sensing device is disposed on the speed plate;

[0025] Based on the noise signal, the power plant is controlled to adjust the position of a trailing edge flap of the wing.

[0026] The present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements any of the control methods described above when executing the program.

[0027] The present invention also provides a non-transitory computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the control method described above is implemented.

[0028] The present invention also provides a computer program product, comprising a computer program, wherein when the computer program is executed by a processor, the computer program implements any of the control methods described above.

[0029] The deceleration mechanism, maneuverable flap system, control method, equipment and medium provided by the present invention effectively weaken the influence of the separation vortex during flight by setting a deceleration plate hinged to the trailing edge of the wing and controlling the deceleration plate to open or close based on the state of the trailing edge flap, thereby helping to ensure flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0031] Figure 1 This is one of the structural schematic diagrams of the speed reduction mechanism provided by the present invention;

[0032] Figure 2 This is the second structural schematic diagram of the speed reduction mechanism provided by the present invention;

[0033] Figure 3 It is one of the structural schematic diagrams of the motorized flap system provided by the present invention;

[0034] Figure 4 This is the second structural schematic diagram of the motorized flap system provided by the present invention;

[0035] Figure 5 It is a flow chart of the control method provided by the present invention;

[0036] Figure 6 It is a structural schematic diagram of the electronic device provided by the present invention.

[0037] Reference numerals:

[0038] 110: air brake; 120: wing;

[0039] 210: control module; 220: power device; 230: speed reduction mechanism. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] The maneuverable flap system is an electromechanical-hydraulic integrated system for auxiliary control. The electronically controlled pressure sensing part is relatively weak and can easily cause the torque generated by the separation vortex to melt the resistor, resulting in failure of the control circuit of the electronically controlled pressure sensing part, posing a flight safety hazard.

[0042] In order to solve the stability problem of the maneuvering flap system caused by the separation vortex, the present invention provides a speed reduction mechanism. Figure 1 , Figure 2 Schematic diagram of the structure of the speed reduction mechanism provided by the present invention. Figure 1 , 2 As shown, the deceleration mechanism includes a deceleration plate 110, which is hinged to the trailing edge of the wing 120 and connected to the power unit;

[0043] When the trailing edge flap of the wing 120 is retracted, the air brake 110 is opened relative to the wing 120 under the drive of the power plant;

[0044] When the trailing edge flap is lowered, the air brake 110 is closed relative to the wing 120 under the drive of the power plant.

[0045] Specifically, in actual flight, the pilot may feel that the aircraft pitches up suddenly, and must push the stick hard to return to the original position. The wind tunnel model force measurement experiment can also confirm that the aircraft generates a large nose-up moment increment during the lift-off process. When the horizontal tail is not in the speed blocking area of ​​the separation vortex, the nose-up moment is caused by the negative lift increment generated by the horizontal tail when the low pressure of the separation vortex induces a large downwash at the horizontal tail. In order to eliminate or reduce the impact of the separation vortex on flight safety, the embodiment of the present invention adds a speed brake 110 to the trailing edge of the wing 120.

[0046] It is understandable that the speed brake 110 can be arranged at the trailing edge of the wing 120 and hinged to the trailing edge of the wing 120. Based on the hinged structure, under the drive of the power device connected to the speed brake 110, the speed brake 110 can be deflected relative to the wing 120, thereby realizing opening or closing relative to the wing 120. Further, Figure 1 The structure of the deceleration mechanism when the deceleration plate 110 is in a closed state relative to the wing 120 is shown. Figure 1 As shown, in the closed state, the air brake 110 and the wing 120 form an integrated streamlined state; Figure 2 The structure of the deceleration mechanism of the air brake 110 relative to the wing 120 when the air brake 110 is opened is shown. Figure 2 As shown, the open state refers to a state in which the air brake 110 is deflected around the hinge, and the air brake 110 and the wing 120 no longer form an integrated streamlined shape.

[0047] In the case of manually controlling the maneuvering flap system, the pilot can place the rear flap control switch in the retracted position, and the maneuvering flap system retracts the trailing edge flaps through the left and right rear servo actuators under the oil pressure of the hydraulic system. When the trailing edge flaps are retracted, the power device can drive the air brake 110 to open relative to the wing 120. At this time, opening the air brake 110 can shift the wind force point of the maneuvering flap system, thereby reducing the separation vortex strength and moving the separation vortex downward so that the separation vortex can be away from the horizontal tail, thereby reducing the induced downwash angle at the horizontal tail and suppressing the increment of the nose-up moment.

[0048] In addition, the pilot can also place the rear flap control switch in the down position. When the maneuverable flap system lowers the trailing edge flap, there is no need to transfer the wind force point. At this time, the power unit can drive the speed brake 110 to close relative to the wing 120.

[0049] The deceleration mechanism provided in the embodiment of the present invention effectively weakens the influence of the separation vortex during flight by providing a deceleration plate hinged to the trailing edge of the wing and controlling the opening or closing of the deceleration plate based on the state of the trailing edge flap, thereby helping to ensure flight safety.

[0050] Based on the above embodiments, Figure 3 Schematic diagram of the structure of the motorized flap system provided by the present invention, such as Figure 3 As shown, the maneuverable flap system includes a control module 210, a power device 220, and a deceleration mechanism 230; the control module 210 is connected to the power device 220, and the control module 210 is used to control the power device 220 to drive the deceleration plate in the deceleration mechanism 230 to open or close.

[0051] Specifically, the control module 210 is used to control the opening and closing states of the air brake in the deceleration mechanism 230 when the trailing edge flap is in different states during flight. The control module 210 is electrically connected to the power device 220, and the control module 210 can transmit the control instruction for the opening or closing of the air brake to the power device 220. After receiving the above control instruction, the power device 220 can drive the air brake to deflect around the hinge between the air brake and the wing based on the above control instruction, thereby realizing the opening or closing of the air brake relative to the wing.

[0052] It can be understood that the control command for opening or closing the speed brake issued by the control module 210 is generated after determining the state of the trailing edge flap of the wing, that is, when the control module 210 determines that the trailing edge flap of the wing is retracted, the control module 210 generates a control command for opening the speed brake, so that the power unit 220 can drive the speed brake to open relative to the wing, thereby shifting the wind force point and reducing the strength of the separation vortex; when the control module 210 determines that the trailing edge flap of the wing is lowered, the control module 210 generates a control command for closing the speed brake, so that the power unit 220 can drive the speed brake to close relative to the wing, thereby avoiding the influence of the separation vortex without shifting the wind force point.

[0053] The system provided by the embodiment of the present invention achieves the effect of weakening the influence of the separation vortex during flight and ensures flight safety by hingedly connecting a speed brake to the trailing edge of the wing and applying a control module and a power device to control the state adjustment of the speed brake based on the state of the trailing edge flap.

[0054] Based on any of the above embodiments, the maneuvering flap system further includes a noise sensing device, wherein the noise sensing device is disposed on the speed brake and connected to the control module;

[0055] The noise sensing device is used to collect noise signals;

[0056] The control module is further configured to control the power plant to adjust a position of a trailing edge flap of a wing based on the noise signal.

[0057] Specifically, in the maneuvering flap system, the speed brake can not only be switched to open or close as the state of the trailing edge flap changes, thereby reducing the strength of the separation vortex, but can also serve as a structure that carries a noise sensing device, so that a noise sensing device can be added to collect noise signals without affecting the normal operation of other components on the maneuvering flap system.

[0058] The noise sensing device here is a sound pickup device, which can be a microphone or a microphone array, and the embodiment of the present invention does not specifically limit this. The noise signal is the audio in the environment where the trailing edge of the wing is located collected by the noise sensing device, and the noise signal can be used to reflect the sound field distribution of the noise caused by the separation vortex in the environment where the trailing edge of the wing is located.

[0059] The noise sensing device can be connected to the control module. After collecting the noise signal, the noise sensing device can transmit the noise signal to the control module. After receiving the noise signal, the control module can analyze the sound field distribution of the noise caused by the separation vortex according to the noise signal, and control the power device to adjust the position of the trailing edge flap accordingly. The effect of avoiding the separation vortex is achieved by adjusting the position of the trailing edge flap.

[0060] The system provided by the embodiment of the present invention is equipped with a noise sensing device to collect noise signals, and then adjust the position of the trailing edge flap based on the noise signals, so as to achieve the effect of avoiding the separation vortex, so as to further improve the flight safety. Here, the noise sensing device is arranged on the speed brake, so as to avoid the influence of the setting of the noise sensing device on the operation of various components in the maneuvering flap system, and the speed brake is reused, which effectively reduces the overall scale of the system.

[0061] Based on any of the above embodiments, the noise sensing device includes a main noise sensing device, the main noise sensing device is arranged in a first area of ​​the speed brake, and the first area is determined based on the position of the separation vortex;

[0062] The main noise sensing device is used to collect a first noise signal in the area where the separation vortex is located.

[0063] Specifically, the noise sensing device includes a main noise sensing device arranged in the first area. Here, the first area is an area demarcated on the speed brake according to the position of the separation vortex. It can be understood that the first area is an area on the speed brake that can scan and sense the noise of the environment in which the separation vortex is located. The main noise sensing device arranged in the first area, that is, a sound pickup device dedicated to collecting and sensing the noise in the environment in which the separation vortex is located, can directly collect the noise signal in the environment in which the separation vortex is located, which is recorded as the first noise signal.

[0064] Accordingly, the control module can analyze the sound field distribution of the noise caused by the separation vortex based on the first noise signal, and control the power device to adjust the position of the trailing edge flap accordingly.

[0065] Based on any of the above embodiments, the noise sensing device further includes an auxiliary noise sensing device, and the auxiliary noise sensing device is arranged in a second area of ​​the speed brake, and the second area is an area outside the first area of ​​the speed brake;

[0066] The auxiliary noise sensing device is used to collect a second noise signal outside the area where the separation vortex is located.

[0067] Specifically, after the first area is demarcated on the speed plate based on the position of the separation vortex, the second area on the speed plate can be obtained, that is, the whole or part of the area on the speed plate except the first area. In addition to the main noise sensing device arranged in the first area, the noise sensing device is also provided with an auxiliary noise sensing device in the second area. Here, the auxiliary noise sensing device arranged in the second area, that is, the sound pickup device for collecting noise outside the environment where the separation vortex is located, can collect noise signals outside the environment where the separation vortex is located, which is recorded as the second noise signal here.

[0068] Accordingly, the control module can combine the first noise signal and the second noise signal to analyze the sound field distribution of the noise caused by the separation vortex, and control the power device to adjust the position of the trailing edge flap accordingly.

[0069] The system provided by the embodiment of the present invention combines the main noise sensing device and the auxiliary noise sensing device to collect noise in the first area and the second area respectively, so as to achieve more comprehensive and rich noise signal collection, thereby improving the reliability of trailing edge flap position adjustment based on noise signals.

[0070] Based on any of the above embodiments, the control module is specifically used for:

[0071] Determining noise sound field distribution information based on the first noise signal and the second noise signal;

[0072] Based on the noise field distribution information, the power device is controlled to adjust the position of the trailing edge flap of the wing.

[0073] Specifically, in the case where the noise sensing device includes a main noise sensing device and an auxiliary noise sensing device, the control module can receive a first noise signal collected by the main noise sensing device and a second noise signal collected by the auxiliary noise sensing device. It can be understood that due to the difference in the positions of the main noise sensing device and the auxiliary noise sensing device on the speed brake, the first noise signal and the second noise signal also reflect noise signals in different environments, that is, the first noise signal reflects the noise signal in the environment where the separation vortex is located, and the second noise signal reflects the noise signal outside the environment where the separation vortex is located.

[0074] After obtaining the first noise signal and the second noise signal, the control module can combine the two to perform sound field analysis, thereby obtaining noise field distribution information. The noise field distribution information here can reflect the distribution of the noise field caused by the separation vortex with space. After obtaining the noise field distribution information, the optional trailing edge flap position in order to avoid the influence of the separation vortex in this case can be determined based on the noise field distribution information, thereby controlling the power unit to adjust the trailing edge flap to the above trailing edge flap position; or the noise field distribution information and the predetermined separation vortex position can be combined to determine the optional trailing edge flap position in order to avoid the influence of the separation vortex, thereby controlling the power unit to adjust the trailing edge flap to the above trailing edge flap position, and the embodiment of the present invention does not make specific limitations on this.

[0075] It can be understood that the correspondence between the noise field distribution information and the trailing edge flap position, or the correspondence between the noise field distribution information and the separation vortex position and the trailing edge flap position, can be pre-set. Therefore, when performing trailing edge flap position control, it is only necessary to apply the noise field distribution information and the pre-set correspondence; or, the preferred trailing edge flap positions under various noise field distribution information can be collected in advance, so as to perform model training based on various noise field distribution information and their preferred trailing edge flap positions to obtain a flap position control model. Subsequently, it is only necessary to input the latest determined noise field distribution information into the flap position control model to obtain the trailing edge flap position that needs to be adjusted.

[0076] The system provided by the embodiment of the present invention combines the first noise signal and the second noise signal to determine the noise field distribution information, and adjusts the trailing edge flap position accordingly to achieve dynamically controllable trailing edge flap adjustment, thereby further avoiding the influence of the separation vortex.

[0077] Based on any of the above embodiments, Figure 4 FIG. 2 is a second structural diagram of the motorized flap system provided by the present invention, as shown in FIG. Figure 4 As shown, the motorized flap system includes components such as an actuator, a solenoid valve, a control module, an operating switch, a pressure signal receiver, and an emergency switch. Among them, the control module can be specifically a central processing unit; the actuator can be specifically a flap servo actuator, and the motorized flap system can include two flap servo actuators; the operating switch can be specifically a rear flap control switch. There are two operating modes of the motorized flap system, namely, automatic mode and manual mode.

[0078] Specifically in the automatic mode, the control module can give corresponding control signals according to the aircraft's flight angle of attack, M number (Mach number) and speed indicator, and automatically adjust the front and rear flaps to a response angle of 0 to 25° according to the control signals. Specifically, when M>1.0, the front and rear flaps exit the automatic control state and are retracted to 0°. In addition, when the control module fails, the pressure sensor outputs a pressure signal to ensure that the front and rear flaps are retracted to 0° to avoid danger caused by excessive aircraft speed. When M≤0.98, the front and rear flaps return to the automatic working state. In addition, within the use range of the automatic working state (M≤0.98), when the front flap emergency 25° release switch is placed in the emergency release position, the front flap will be lowered 25°. When it exceeds the use range of the automatic state (M>1.0), the emergency function of the front flap emergency 25° release switch does not work.

[0079] Specifically, in manual mode, the rear flap control switch is placed in the retracted position, and the control module outputs a control signal to the left and right flap servo action collectors to retract the trailing edge flaps, and outputs a control signal to the flap control box and solenoid valve.

[0080] Furthermore, when the flap control switch is in the retracted position, the YDF-22A solenoid valve (three-position four-way solenoid valve) does not work, the automatic pipeline and the lowering pipeline of the YDF-22A solenoid valve are both connected to the oil return pipe, and the two control pipes on the flap servo actuator are connected to the oil return pipe. When the left and right rear servo actuators are both under the oil pressure of the aircraft hydraulic system to retract the trailing edge flaps, the speed brake is opened. At this time, opening the speed brake not only reduces the separation vortex strength, but also moves the separation vortex downward and away from the horizontal tail, thereby further reducing the induced downwash angle at the horizontal tail.

[0081] When the rear flap operation switch is in the lowered position, when the lowering pipeline on the YDF-22A solenoid valve is connected to the oil inlet pipeline, the left and right rear flap servo actuators close the speed brakes under the action of oil pressure, thereby avoiding the influence of the separation vortex. In addition, considering the problem of the trailing edge flap falling off under normal circumstances, that is, the clearance between the locking valve core and the valve sleeve in the maneuvering flap system is too large, under the action of the deadweight of the trailing edge flap, the oil flows out from the locking valve gap, directly returns through the return oil pipeline, enters the servo valve through the conversion valve core, and returns to the system from the return oil pipeline of the servo valve. Especially in winter, due to the influence of thermal expansion and contraction, the shrinkage rates of the rubber ring and the shell are different, resulting in oil leakage between the two chambers of the actuator cylinder. It is necessary to select a suitable valve core and valve sleeve, and grind the valve port and valve seat when necessary.

[0082] In addition, when the rear flap operating switch is in the lowered position and the speed brake is closed relative to the wing, the main noise sensing device arranged at the first area of ​​the speed brake in the maneuvering flap system, and the negative noise sensing device arranged at the second area of ​​the speed brake, can respectively take on the tasks of collecting the first noise signal in the environment where the separation vortex is located, and collecting the second noise signal outside the separation environment, thereby enabling the control module to perform noise sound field analysis in combination with the first noise signal and the second noise signal, and adjust the position of the trailing edge flap based on the noise sound field distribution information obtained from the analysis, so as to further avoid the influence of the separation vortex.

[0083] The control method of the motorized flap system provided by the present invention is described below. The control method of the motorized flap system described below and the motorized flap system described above can be referred to each other.

[0084] Figure 5 It is a flow chart of the control method provided by the present invention, such as Figure 5 As shown, the method can be applied to the control module of the above-mentioned maneuvering flap system, and the method may include:

[0085] Step 510, obtaining the state of the trailing edge flap of the wing;

[0086] Specifically, the control method is used to control the speed brake connected to the trailing edge of the wing to open or close relative to the wing, thereby weakening the impact of the separation vortex during flight. In the specific implementation process, the control module can monitor the state of the trailing edge flap of the wing, and the trailing edge flap state here is used to indicate whether the current state of the trailing edge flap of the wing is folded up or down, and the specific angle value of folding up or down.

[0087] Step 520, when the trailing edge flap is in the retracted state, controlling the power device to drive the air brake to open relative to the wing, the air brake being hinged to the trailing edge of the wing;

[0088] Step 530, when the trailing edge flap is in the down state, controlling the power device to drive the speed brake to close relative to the wing.

[0089] Specifically, after the trailing edge flap state is obtained, the corresponding control method for the speed brake can be executed according to different trailing edge flap states:

[0090] When the trailing edge flaps are retracted, the control module can control the power unit to drive the speed brake to open relative to the wing. At this time, opening the speed brake can shift the wind force point of the maneuvering flap system, thereby reducing the strength of the separation vortex and moving the separation vortex downward so that the separation vortex can be away from the horizontal tail, thereby reducing the induced downwash angle at the horizontal tail and suppressing the increase in the nose-up moment.

[0091] When the trailing edge flaps are lowered, there is no need to transfer the wind force points. At this time, the control module controls the power unit to drive the speed brake to close relative to the wing.

[0092] The control method provided in the embodiment of the present invention effectively weakens the influence of the separation vortex during flight by controlling the speed brake hinged to the trailing edge of the wing to open or close based on the state of the trailing edge flap, thereby helping to ensure flight safety.

[0093] Based on any of the above embodiments, the method further includes:

[0094] Acquiring a noise signal collected by a noise sensing device, wherein the noise sensing device is disposed on the speed plate;

[0095] Based on the noise signal, the power plant is controlled to adjust the position of a trailing edge flap of the wing.

[0096] Specifically, the noise sensing device, i.e., the sound pickup device, may be a microphone or a microphone array, which is not specifically limited in the embodiments of the present invention. The noise sensing device arranged on the speed brake can collect the audio in the environment where the trailing edge of the wing is located, i.e., the noise signal. The noise signal can be used to reflect the sound field distribution of the noise caused by the separation vortex in the environment where the trailing edge of the wing is located.

[0097] After receiving the noise signal, the sound field distribution of the noise caused by the separation vortex can be analyzed according to the noise signal, and the power device can be controlled to adjust the position of the trailing edge flap accordingly, so as to achieve the effect of avoiding the separation vortex by adjusting the position of the trailing edge flap.

[0098] Furthermore, in the case of manually controlling the maneuvering flap system, if the trailing edge flap is in the down position, the speed brake is closed relative to the wing. At this time, the speed brake and the wing form an integrated streamlined state. At this time, the noise signal collected by the noise sensing device can be obtained, and the specific angle of the trailing edge flap in the down position can be controlled accordingly.

[0099] The method provided by the embodiment of the present invention adds a noise sensing device to collect noise signals, and then adjusts the position of the trailing edge flap based on the noise signals, thereby achieving the effect of avoiding the separation vortex, so as to further improve flight safety. Here, the noise sensing device is set on the speed brake, which avoids the setting of the noise sensing device affecting the operation of various components in the maneuvering flap system, and realizes the reuse of the speed brake, effectively reducing the overall scale of the system.

[0100] Based on any of the above embodiments, the noise sensing device includes a main noise sensing device and an auxiliary noise sensing device, the main noise sensing device is arranged in a first area of ​​the speed brake, and the auxiliary noise sensing device is arranged in a second area of ​​the speed brake, the first area is determined based on the position of the separation vortex, and the second area is an area outside the first area on the speed brake.

[0101] Accordingly, the step of obtaining the noise signal collected by the noise sensing device includes:

[0102] Acquire a first noise signal collected by a primary noise sensing device and a second noise signal collected by an auxiliary noise sensing device;

[0103] The step of controlling the power device to adjust the position of the trailing edge flap of the wing based on the noise signal comprises:

[0104] Determining noise sound field distribution information based on the first noise signal and the second noise signal;

[0105] Based on the noise field distribution information, the power device is controlled to adjust the position of the trailing edge flap of the wing.

[0106] Specifically, in the case where the noise sensing device includes a main noise sensing device and an auxiliary noise sensing device, the control module can receive a first noise signal collected by the main noise sensing device and a second noise signal collected by the auxiliary noise sensing device. It can be understood that due to the difference in the positions of the main noise sensing device and the auxiliary noise sensing device on the speed brake, the first noise signal and the second noise signal also reflect noise signals in different environments, that is, the first noise signal reflects the noise signal in the environment where the separation vortex is located, and the second noise signal reflects the noise signal outside the environment where the separation vortex is located.

[0107] After obtaining the first noise signal and the second noise signal, the control module can combine the two to perform sound field analysis, thereby obtaining noise field distribution information. The noise field distribution information here can reflect the distribution of the noise field caused by the separation vortex with space. After obtaining the noise field distribution information, the optional trailing edge flap position in order to avoid the influence of the separation vortex in this case can be determined based on the noise field distribution information, thereby controlling the power unit to adjust the trailing edge flap to the above trailing edge flap position; or the noise field distribution information and the predetermined separation vortex position can be combined to determine the optional trailing edge flap position in order to avoid the influence of the separation vortex, thereby controlling the power unit to adjust the trailing edge flap to the above trailing edge flap position, and the embodiment of the present invention does not make specific limitations on this.

[0108] The method provided by the embodiment of the present invention combines the first noise signal and the second noise signal to determine the noise field distribution information, and adjusts the trailing edge flap position accordingly to achieve dynamically controllable trailing edge flap adjustment, thereby further avoiding the influence of the separation vortex.

[0109] Figure 6 An example of a physical structure diagram of an electronic device is shown in FIG. Figure 6 As shown, the electronic device may include: a processor 610, a communication interface 620, a memory 630 and a communication bus 640, wherein the processor 610, the communication interface 620 and the memory 630 communicate with each other through the communication bus 640. The processor 610 may call the logic instructions in the memory 630 to execute the control method, which includes: obtaining the trailing edge flap state of the wing; when the trailing edge flap state is retracted, controlling the power device to drive the speed brake to open relative to the wing, and the speed brake is hinged to the trailing edge of the wing; when the trailing edge flap state is down, controlling the power device to drive the speed brake to close relative to the wing.

[0110] In addition, the logic instructions in the above-mentioned memory 630 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0111] On the other hand, the present invention also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the control methods provided by the above-mentioned methods, which include: obtaining the trailing edge flap state of the wing; when the trailing edge flap state is retracted, controlling the power device to drive the speed brake to open relative to the wing, and the speed brake is hinged to the trailing edge of the wing; when the trailing edge flap state is lowered, controlling the power device to drive the speed brake to close relative to the wing.

[0112] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the control method provided by the above-mentioned methods, the method comprising: obtaining the state of the trailing edge flap of the wing; when the trailing edge flap is in the retracted state, controlling the power device to drive the speed brake to open relative to the wing, the speed brake being hinged to the trailing edge of the wing; when the trailing edge flap is in the lowered state, controlling the power device to drive the speed brake to close relative to the wing.

[0113] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0114] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0115] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A speed reduction mechanism, characterized in that: It includes a speed brake and a noise sensing device, wherein the speed brake is hinged to the trailing edge of the wing and connected to the power device, and the noise sensing device is arranged on the speed brake; When the trailing edge flap of the wing is retracted, the speed brake is opened relative to the wing under the drive of the power device to reduce the strength of the separation vortex and move the separation vortex downward; When the trailing edge flap is lowered, the air brake is closed relative to the wing under the drive of the power plant; The noise sensing device is used to collect noise signals, and the noise signals are used to adjust the position of the trailing edge flap.

2. A maneuverable flap system, characterized in that: It comprises a control module, a power device, and the deceleration mechanism as claimed in claim 1; the control module is connected to the power device, and the control module is used to control the power device to drive the deceleration plate in the deceleration mechanism to open or close; The noise sensing device in the speed reduction mechanism is connected to the control module; The control module is also used to control the power device to adjust the position of the trailing edge flap of the wing based on the noise signal collected by the noise sensing device.

3. The motorized flap system according to claim 2, characterized in that: The noise sensing device comprises a main noise sensing device, the main noise sensing device is arranged in a first area of ​​the speed brake, the first area is determined based on the position of the separation vortex; The main noise sensing device is used to collect a first noise signal in the area where the separation vortex is located.

4. The motorized flap system according to claim 3, characterized in that: The noise sensing device further comprises an auxiliary noise sensing device, wherein the auxiliary noise sensing device is arranged in a second area of ​​the speed brake, and the second area is an area outside the first area of ​​the speed brake; The auxiliary noise sensing device is used to collect a second noise signal outside the area where the separation vortex is located.

5. The motorized flap system according to claim 4, characterized in that: The control module is specifically used for: Determining noise sound field distribution information based on the first noise signal and the second noise signal; Based on the noise field distribution information, the power device is controlled to adjust the position of the trailing edge flap of the wing.

6. A control method, characterized in that: include: Get the trailing edge flap status of the wing; When the trailing edge flap is in the retracted state, the power device is controlled to drive the air brake to open relative to the wing, and the air brake is hinged to the trailing edge of the wing; When the trailing edge flap is in the down position, controlling the power device to drive the air brake to close relative to the wing; Also includes: Acquiring a noise signal collected by a noise sensing device, wherein the noise sensing device is disposed on the speed plate; Based on the noise signal, the power plant is controlled to adjust the position of a trailing edge flap of the wing.

7. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the control method according to claim 6 is implemented.

8. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the control method according to claim 6 is implemented.

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