Airflow injection type icing detector with self-adaptive function

Abstract

According to the airflow ejection type icing detector with the self-adaptive function, the airflow speed in the flow channel can be kept relatively constant by adjusting the ejection airflow pressure, and therefore the detection performance of the icing detector in various flight states of a helicopter is guaranteed; according to the invention, the icing detection effect of the detector can be effectively improved, and the stability of icing detection performance is ensured.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft deicing, and particularly relates to an airflow induction type icing detector with self-adaptive function. BACKGROUND

[0002] The flight height of a helicopter is in the icing cloud layer, and the helicopter performs a special task, and the flight speed is relatively low, so the helicopter is more prone to icing than a fixed-wing aircraft. Meanwhile, the icing of the helicopter causes greater harm and is less safe. Therefore, a helicopter deicing system is necessary, and icing detection is a very important link. The helicopter usually uses an induction type icing detector to detect whether icing occurs. The detector has an air induction device, and through airflow induction, external airflow containing liquid water is introduced into the air duct of the detector, and then the sensitive probe senses icing. Because of the effect of airflow induction, the detector can sense airflow and liquid water even when the helicopter is hovering, side flying or even upside down, although it is not facing the wind.

[0003] However, the pressure of the induced airflow of the current icing detector is a fixed value, which is set to be a certain value and cannot be adjusted. When the helicopter is flying or hovering, the external airflow changes, and the rotor rotation state also greatly affects the airflow, resulting in unstable airflow in the air duct, which affects the icing detection result and causes inaccurate calculation of the liquid water content. SUMMARY

[0004] The application aims to design an airflow induction type icing detector with self-adaptive function, which can maintain the airflow velocity in the flow passage relatively constant by adjusting the induced airflow pressure, thereby ensuring the detection performance of the icing detector under various flight states of the helicopter.

[0005] The application provides an airflow induction type icing detector with self-adaptive function, which comprises a detector rear cover 1, a mounting flange 2, an outer cover support part 3, a probe outer cover 4, a total control module 5, a wind speed calculation module 6, an icing detection module 7, a jet control module 8, a total static pressure probe support part 9, a total static pressure probe 10, an icing probe support part 11, an icing sensitive probe 12, a flow regulating valve 13, a jet pipeline 14, a jet nozzle 15, a detector air source inlet 16, and a detector electrical connector 17. The detector rear cover 1 is fixed on the mounting flange 2; the probe outer cover 4 is connected and fixed with the mounting flange 2 through the outer cover support part 3. The total control module 5, the wind speed calculation module 6, the icing detection module 7, and the jet control module 8 are installed in the detector rear cover 1. The total static pressure probe 10 passes through the outer cover support part 3, is fixed by the total static pressure probe support part 9, and is connected with the wind speed solving module 6, and the pressure signal is introduced into the wind speed solving module 6; The icing sensitive probe 12 is fixed by the icing probe support part 11, and is connected with the icing detection module 7; The total control module 5 is connected with the wind speed solving module 6, the icing detection module 7 and the jet flow control module 8; The jet flow pipeline 14 is connected with the detector gas source inlet 16 through the flow regulating valve 13, and the jet flow pipeline 14 is provided with the jet flow nozzle 15 at the end in the probe outer cover 4.

[0006] Preferably, the wind speed solving module 6 calculates the outflow wind speed by combining the pressure signal acquired by the total static pressure probe 10 with the temperature signal acquired by the aircraft atmospheric data system.

[0007] Preferably, the icing detection module 7 receives the icing information acquired by the icing sensitive probe 12, and converts the icing information into an icing signal, and feeds back the icing detection result to the aircraft main control system.

[0008] Preferably, the total control module 5 judges the wind speed value calculated by the wind speed solving module 6, determines the adjusting trend of the flow regulating valve 13, and sends a control signal to the jet flow control module 8.

[0009] Preferably, the jet flow control module 8 adjusts the opening degree of the flow regulating valve 13 according to the control signal of the total control module 5, so as to control the air pressure in the jet flow pipeline and the jet pressure of the jet flow nozzle, thereby ensuring that the airflow speed in the probe outer cover 4 is relatively constant, and ensuring the stability and accuracy of the detection of the icing sensitive probe 12.

[0010] Preferably, the corresponding relationship between the opening degree of the flow regulating valve 13 and different incoming airflow speeds can be calibrated through an icing wind tunnel test, and a determined numerical curve is obtained.

[0011] Preferably, in the actual use process, the control module realizes pressure control according to the curve relationship calibrated in the early stage.

[0012] Preferably, the jet flow control module 8 can store the determined numerical curve.

[0013] The application has the following technical effects: The application can automatically adjust the opening degree of the flow regulating valve according to the flight speed of the helicopter and other environmental conditions, thereby adjusting the pressure of the jet flow, keeping the airflow speed in the flow passage relatively constant, and ensuring that the icing detector can accurately detect icing in various flight states of the helicopter, effectively improving the icing detection effect, and ensuring the stability of the icing detection performance. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is a structural schematic diagram of the airflow injection type icing detector with self-adaptive function of the present application; In the figure: 1. Detector rear cover; 2. Mounting flange; 3. Cover support part; 4. Probe cover; 5. Total control module; 6. Wind speed solving module; 7. Icing detection module; 8. Jet control module; 9. Total static pressure probe support part; 10. Total static pressure probe; 11. Icing probe support part; 12. Icing sensitive probe; 13. Flow regulating valve; 14. Jet pipeline; 15. Jet nozzle; 16. Detector air source inlet; 17. Detector electrical connector. DETAILED DESCRIPTION The present application belongs to the technical field of aircraft deicing, and relates to an airflow injection type icing detector with self-adaptive function. The airflow injection type icing detector is an icing detector with air injection device, which is used for helicopter icing alarm and liquid water content detection.

[0015] The icing detector includes a detector rear cover, a mounting flange, a cover support part, a probe cover, a total control module, a wind speed solving module, an icing detection module, a jet control module, a total static pressure probe support part, a total static pressure probe, an icing probe support part, an icing sensitive probe, a jet regulating valve, a jet pipeline, a jet nozzle, and a detector air source inlet. The icing detector can automatically adjust the pressure of the injection airflow according to the flight speed and other environmental conditions of the helicopter, so as to keep the airflow speed in the flow passage relatively constant, thereby ensuring that the icing detector can accurately detect icing in various flight states of the helicopter. The present application can effectively improve the icing detection effect of the detector and ensure the stability of the icing detection performance.

[0016] The present application is designed to solve the problem of the existing injection type icing detector, and provides an airflow injection type icing detector with self-adaptive function. The present application is easy to implement and has good implementation effect, and can better ensure the detection effect of the detector in complex working conditions of the helicopter.

[0017] Please refer to Figure 1 , the injection type icing sensor is usually used for icing alarm and liquid water content detection in the flight or hovering state of the helicopter. In order to ensure the icing detection effect of the helicopter in various flight states such as hovering, side flight, and even reverse flight, an airflow injection type icing detector with self-adaptive function is invented.

[0018] The airflow ejection type icing detector with self-adaptive function mainly comprises a detector back cover 1, a mounting flange 2, an outer cover support part 3, a probe outer cover 4, a total control module 5, a wind speed solving module 6, an icing detection module 7, a jet control module 8, a total static pressure probe support part 9, a total static pressure probe 10, an icing probe support part 11, an icing sensitive probe 12, a flow regulating valve 13, a jet pipeline 14, a jet nozzle 15, a detector air source inlet 16, a detector electrical connector 17 and the like. The detector back cover 1 is fixed on the mounting flange 2; the probe outer cover 4 is connected and fixed with the mounting flange 2 through the outer cover support part 3. The total control module 5, the wind speed solving module 6, the icing detection module 7 and the jet control module 8 are installed in the detector back cover 1. The total static pressure probe 10 passes through the outer cover support part 3, is installed and fixed through the total static pressure probe support part 9, and is connected with the wind speed solving module 6, so that the pressure signal is introduced into the wind speed solving module 6. The icing sensitive probe 12 is installed and fixed through the icing probe support part 11, and is connected with the icing detection module 7. The total control module 5 is connected with the wind speed solving module 6, the icing detection module 7 and the jet control module 8. The jet pipeline 14 is connected with the detector air source inlet 16 through the flow regulating valve 13, and the jet nozzle 15 is arranged at the end of the jet pipeline 14 in the probe outer cover 4.

[0019] The wind speed solving module 6 calculates the Mach number M by the total pressure P0 and the static pressure P0 acquired by the total static pressure probe 10, and calculates the corresponding static temperature T0 by combining the total temperature signal T0 acquired by the aircraft atmospheric data system, and finally calculates the flow wind speed V according to the Mach number M and the static temperature T0. s s s The calculation formula is as follows:

[0020]

[0021]

[0022] The icing detection module 7 receives the icing information acquired by the icing sensitive probe 12, converts the icing information into an icing signal, and feeds back the icing detection result to the aircraft main control system.

[0023] The total control module 5 judges the wind speed value calculated by the wind speed solving module 6, determines the adjusting trend of the flow regulating valve 13, and sends a control signal to the jet control module 8.

[0024] ​​The jet flow control module 8 adjusts the opening of the flow regulating valve 13 according to the control signal of the total control module 5, so as to control the air pressure in the jet flow pipeline 14 and the jet pressure of the jet flow nozzle 15, thereby ensuring the relatively constant air flow speed in the probe outer cover 4 and the stability and accuracy of the ice detection sensitive probe 12.

[0025] The corresponding relationship between the opening of the flow regulating valve 13 and different incoming air speeds can be calibrated through an icing wind tunnel test, a certain numerical curve is obtained, and the numerical curve is stored in the jet flow control module 8.

[0026] In actual use, the pressure is controlled according to the calibrated curve relationship in the early stage.

[0027] The present application can automatically adjust the opening of the flow regulating valve according to the flight speed of the helicopter and other environmental conditions, thereby adjusting the pressure of the jet flow, keeping the air flow speed in the flow passage relatively constant, and ensuring that the ice detector can accurately detect ice in various flight states of the helicopter, effectively improving the ice detection effect, and ensuring the stability of the ice detection performance. The present application is suitable for helicopters and can ensure the ice detection effect of the helicopter in various flight states such as hovering, side flight and even reverse flight, and comprises a detector rear cover, a mounting flange, an outer cover support part, a probe outer cover, a total control module, a wind speed solving module, an ice detection module, a jet flow control module, a total static pressure probe support part, a total static pressure probe, an ice detection probe support part, an ice sensitive probe, a flow regulating valve, a jet flow pipeline, a jet flow nozzle, a detector air source inlet, a detector electrical connector and the like. The detector rear cover is fixed on the mounting flange; the probe outer cover is connected and fixed with the mounting flange through the outer cover support part; the total control module, the wind speed solving module, the ice detection module and the jet flow control module are installed in the detector rear cover; the total static pressure probe passes through the outer cover support part, is installed and fixed through the total static pressure probe support part, and is connected with the wind speed solving module, so as to introduce the pressure signal into the wind speed solving module; the ice sensitive probe is installed and fixed through the ice detection probe support part, and is connected with the ice detection module; the total control module is connected with the wind speed solving module, the ice detection module and the jet flow control module; the jet flow pipeline is connected with the detector air source inlet through the flow regulating valve, and the jet flow nozzle is arranged at the end of the jet flow pipeline in the probe outer cover.

[0028] The wind speed solving module calculates the flow wind speed by combining the pressure signal obtained by the total static pressure probe with the total temperature signal collected by the aircraft atmospheric data system. The icing detection module receives the icing information obtained by the icing sensitive probe and converts it into an icing signal, which is fed back to the aircraft main control system to provide the icing detection result. The total control module determines the adjustment trend of the flow regulating valve according to the wind speed value calculated by the wind speed solving module and sends a control signal to the jet flow control module. The jet flow control module adjusts the opening of the flow regulating valve according to the control signal from the total control module to control the pressure of the induced air flow, thereby ensuring the relatively constant air flow speed inside the probe cover and ensuring the stability and accuracy of the detection by the icing sensitive probe.

[0029] The corresponding relationship between the opening of the flow regulating valve and different incoming wind speeds can be calibrated through icing wind tunnel tests to obtain a determined numerical curve, which is stored in the jet flow control module. In actual use, the adaptive airflow induced icing detector controls the pressure according to the calibrated curve relationship.

[0030] In other embodiments of the present application, the wind speed solving module of the adaptive airflow induced icing detector calculates the flow wind speed of 90 m / s by combining the pressure signal obtained by the total static pressure probe with the temperature signal collected by the aircraft atmospheric data system. The total control module determines the adjustment trend of the flow regulating valve according to the wind speed value calculated by the wind speed solving module and sends a control signal to the jet flow control module. The jet flow control module adjusts the opening of the flow regulating valve according to the control signal from the total control module to control the induced air flow pressure to be 1 kgf / cm², at which time the air flow speed inside the probe cover is from 41.3 m / s. When the wind speed solving module calculates the flow wind speed to be 56 m / s, the jet flow control module adjusts the flow regulating valve according to the control signal from the total control module to control the induced air flow pressure to be 2.8 kgf / cm², at which time the air flow speed inside the probe cover is from 41.7 m / s. When the wind speed solving module calculates the flow wind speed to be 30 m / s, the jet flow control module adjusts the flow regulating valve according to the control signal from the total control module to control the induced air flow pressure to be 3.1 kgf / cm², at which time the air flow speed inside the probe cover is from 42.1 m / s. Through the adjustment of the flow regulating valve, the air flow speed inside the probe cover is relatively constant, thereby ensuring the stability and accuracy of the detection by the icing sensitive probe.

Claims

1. A self-adapting airflow-ducted ice detector, characterized in that, The probe comprises a probe back cover (1), a mounting flange (2), a cover support part (3), a probe cover (4), a total control module (5), a wind speed solution module (6), an icing detection module (7), a jet flow control module (8), a total static pressure probe support part (9), a total static pressure probe (10), an icing probe support part (11), an icing sensitive probe (12), a flow regulating valve (13), a jet flow pipeline (14), a jet flow nozzle (15), a probe air source inlet (16), and a probe electrical connector (17). The probe back cover (1) is fixed on the mounting flange (2); the probe cover (4) is connected and fixed with the mounting flange (2) through the cover support part (3). The total control module (5), the wind speed solution module (6), the icing detection module (7), and the jet flow control module (8) are installed in the probe back cover (1). The total static pressure probe (10) passes through the cover support part (3), is installed and fixed through the total static pressure probe support part (9), and is connected with the wind speed solution module (6) to introduce a pressure signal to the wind speed solution module (6). The icing sensitive probe (12) is installed and fixed through the icing probe support part (11) and is connected with the icing detection module (7). The total control module (5) is connected with the wind speed solution module (6), the icing detection module (7), and the jet flow control module (8). The jet flow pipeline (14) is connected with the probe air source inlet (16) through the flow regulating valve (13), and the jet flow nozzle (15) is arranged at the end of the jet flow pipeline (14) in the probe cover (4).

2. The probe of claim 1, wherein, The wind speed solution module (6) calculates the outflow wind speed by combining the pressure signal obtained by the total static pressure probe (10) with the temperature signal collected by the aircraft atmospheric data system.

3. The probe of claim 1, wherein, The icing detection module (7) receives the ice accumulation information obtained by the icing sensitive probe (12), converts the ice accumulation information into an icing signal, and feeds back the icing detection result to the aircraft main control system.

4. The probe of claim 1, wherein, The total control module (5) determines the adjustment trend of the flow regulating valve (13) according to the wind speed value calculated by the wind speed solution module (6) and sends a control signal to the jet flow control module (8).

5. The probe of claim 1, wherein, The jet flow control module (8) adjusts the opening degree of the flow regulating valve (13) according to the control signal of the total control module (5) to control the air pressure in the jet flow pipeline and the jet pressure of the jet flow nozzle, thereby ensuring that the airflow speed inside the probe cover (4) is relatively constant and ensuring the stability and accuracy of the detection of the icing sensitive probe (12).

6. The probe of claim 1, wherein, The corresponding relationship between the opening degree of the flow regulating valve (13) and different incoming flow wind speeds can be calibrated through an icing wind tunnel test to obtain a determined numerical curve.

7. The probe of claim 1, wherein, In actual use, the control module realizes pressure control according to the curve relationship calibrated in advance.

8. The probe of claim 6, wherein, The determined numerical curve can be stored in the jet flow control module (8).

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