Aircraft supercooled large droplet icing detection device and aircraft

Abstract

This invention relates to a device for detecting supercooled large water droplet icing in aircraft and the aircraft itself. The device includes a detector and a support connected to the detector. The detector comprises a head and a sidewall connected to the head. The head is an open cylinder forming a circular detector inlet. The sidewall is conical, and the detector also includes a central cone located within the sidewall. An annular detector outlet is formed between the tail of the sidewall and the tail of the central cone. A spiral resistance wire is arranged inside the sidewall to detect changes in current after the resistance wire encounters water, triggering an alarm. The inlet flow coefficient of the detector is equal to the ratio of the detector outlet area to the detector inlet area, and the inlet flow coefficient is less than 1. Based on the above technical solution, this invention achieves the following beneficial technical effects: it can effectively distinguish water droplet diameters, thereby detecting supercooled large water droplet icing.

Description

Technical Field

[0001] This invention relates to the field of aircraft icing detection technology, specifically to an aircraft supercooled large water droplet icing detection device. Background Technology

[0002] Supercooled large water droplets (SLD) are icing phenomena with droplet diameters exceeding 300 μm to 1000 μm. Compared to conventional icing phenomena, they cause more extensive and severe icing on aircraft surfaces, leading to greater performance losses and significantly impacting flight safety. Conventional flight icing detectors are only applicable to icing phenomena with droplet diameters below 100 μm. However, the European EASA review standards require aircraft icing detectors to be able to distinguish between conventional icing phenomena and SLD icing phenomena, but currently, there are no mature SLD icing detectors available.

[0003] Existing icing detectors typically use icing probes, which are exposed to the air. When they encounter icing weather, ice forms on their surface, causing a change in vibration frequency and thus triggering an icing warning. Alternatively, some aircraft rely on pilots observing icing on the windshield and surrounding area to issue warnings. However, neither of these methods can distinguish between differences in the diameter of water droplets in icing weather, and therefore cannot differentiate between conventional icing weather and SLD (Special Drift Ice) icing weather. Summary of the Invention

[0004] One object of the present invention is to provide a device for detecting supercooled large water droplet icing in aircraft, which can overcome at least some of the defects of the prior art, effectively distinguish the diameter of water droplets, and thus detect supercooled large water droplet icing meteorology.

[0005] The above-mentioned objective of the present invention is achieved by a device for detecting supercooled large water droplet icing in aircraft, the device comprising a detector and a support member connected to the detector;

[0006] The detector includes a head and a sidewall connected to the head. The head is an open cylinder to form a circular detector inlet. The sidewall is conical. The detector also includes a central cone located inside the sidewall. An annular detector outlet is formed between the tail of the sidewall and the tail of the central cone. A spiral resistance wire is arranged inside the sidewall to trigger an alarm by sensing the change in current of the resistance wire when it comes into contact with water.

[0007] The inlet flow coefficient of the detector is equal to the ratio of the detector outlet area to the detector inlet area, and the inlet flow coefficient of the detector is less than 1.

[0008] According to the above technical solution, the aircraft supercooled large water droplet icing detection device of the present invention can achieve the following beneficial technical effects: it can effectively distinguish the diameter of water droplets, thereby detecting supercooled large water droplet icing meteorology.

[0009] Preferably, the supercooled large water droplet icing detection device for the aircraft further includes a ball-head hinge and a flow guide ring. The central cone of the detector is connected to the support member by means of the ball-head hinge. The ball-head hinge is located at the center of mass of the detector. The flow guide ring is located on the outer side of the tail of the detector and surrounds the tail of the sidewall.

[0010] Preferably, the inlet flow coefficient of the detector is 0.3 to 0.7.

[0011] Preferably, the semi-cone angle of the central cone is 20 to 45 degrees.

[0012] Preferably, the semi-cone angle of the sidewall is 10 to 35 degrees.

[0013] Preferably, the supercooled large water droplet icing detection device is installed at the nose of the aircraft.

[0014] Preferably, both the sidewall and the central cone are provided with heaters.

[0015] Preferably, the central cone includes a front wall, a rear wall, and a static pressure cavity located between the front wall and the rear wall. The supercooled large water droplet icing detection device for the aircraft also includes a static pressure hole that connects the static pressure cavity to the outside of the aircraft. The central cone also includes an elastic element disposed between the front wall and the rear wall.

[0016] The front and rear walls of the central cone are slidably and sealingly connected, forming a static pressure chamber between them. This chamber is only connected to the outside atmosphere through a static pressure orifice. Under the combined action of inlet dynamic pressure, static pressure within the chamber, and the elastic element, the front wall of the central cone can move back and forth. When the inlet dynamic pressure is low, the front wall moves forward, reducing the distance between it and the side walls, thus better capturing low-velocity splashing water droplets. When the inlet dynamic pressure is high, the front wall moves backward, increasing the distance between it and the side walls, thus better capturing high-velocity splashing water droplets. This design ensures that the side walls have the same or similar capture rate for water droplets of different velocities.

[0017] Preferably, the flow guide ring is connected to the tail of the side wall via a support arm, and the static pressure hole passes through the flow guide ring, the support arm and the tail of the side wall in sequence, thereby communicating with the static pressure cavity.

[0018] The above-mentioned objectives of the present invention are also achieved by an aircraft comprising an aircraft supercooled large water droplet icing detection device as described in any of the above aspects.

[0019] According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: it can effectively distinguish the diameter of water droplets, thereby detecting the icing of supercooled large water droplets. Attached Figure Description

[0020] Figure 1 This is a schematic diagram (including a front view and a cross-sectional view) of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention.

[0021] Figure 2 This is a schematic diagram of the structure of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention.

[0022] Figure 3 This is a functional schematic diagram of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention.

[0023] Figure 4 This is a circuit diagram of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention.

[0024] Figure 5 This is a schematic diagram of the structure of a supercooled large water droplet icing detection device for aircraft, according to another embodiment of the present invention.

[0025] List of reference numerals

[0026] 10: Detector;

[0027] 11: Head;

[0028] 12: Side wall;

[0029] 13: Central cone;

[0030] 14: Spiral resistance wire;

[0031] 15: Ball joint hinge;

[0032] 16: Flow guide ring;

[0033] 17: Heater;

[0034] 18: Alarm device;

[0035] 19: Static pressure hole;

[0036] 20: Supporting components;

[0037] 21: Outrigger;

[0038] 31: Detector entrance;

[0039] 32: Detector exit;

[0040] 131: Anterior wall of the central cone;

[0041] 132: Posterior wall of the central cone;

[0042] 133: Static pressure chamber;

[0043] 134: Elastic component. Detailed Implementation

[0044] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0045] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The terms "an" or "a" and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms "comprising" or "including" and similar terms mean that the element or object preceding "comprising" or "including" encompasses the element or object listed following "comprising" or "including" and its equivalents, and do not exclude other elements or objects. The terms "connected" or "linked" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0046] In the following description, in order to clearly demonstrate the structure and operation of the present invention, a number of directional terms will be used. However, terms such as "front," "rear," "left," "right," "outer," "inner," "outward," "inward," "up," and "down" should be understood as convenient terms and not as limiting terms. In particular, it should be noted that "front" and "rear" are determined according to the heading of the aircraft.

[0047] Figure 1This is a schematic diagram (including a front view and a cross-sectional view) of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention. Figure 2 This is a schematic diagram of the structure of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention. Figure 3 This is a functional schematic diagram of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention. Figure 4 This is a circuit diagram of an aircraft supercooled large water droplet icing detection device according to an embodiment of the present invention. Figure 5 This is a schematic diagram of the structure of a supercooled large water droplet icing detection device for aircraft, according to another embodiment of the present invention.

[0048] like Figure 1 - Figure 4 As shown, an embodiment of the aircraft supercooled large water droplet icing detection device of the present invention includes a detector 10 and a support member 20 connected to the detector 10.

[0049] In some embodiments, such as Figure 1 - Figure 4 As shown, the support member 20 is in the form of an inverted L-shaped strut to support the detector 10 on the aircraft.

[0050] In some embodiments, the supercooled large water droplet icing detection device is installed at the nose of the aircraft. Of course, the supercooled large water droplet icing detection device can also be installed in other icing-sensitive areas of the aircraft.

[0051] The detector 10 includes a head 11 (also referred to as the front part) and a side wall 12 connected to the head 11 (i.e., the side wall 12 is located in the middle and rear part). The head 11 is open cylindrical (i.e. cylindrical) to form a circular detector inlet 31. The side wall 12 is conical (i.e., gradually expands conically from front to back). The detector 10 also includes a central cone 13 located inside the side wall 12. An annular detector outlet 32 ​​is formed between the tail of the side wall 12 and the tail of the central cone 13. A spiral resistance wire 14 is arranged inside the side wall 12 to trigger an alarm by sensing the change in current of the resistance wire when it comes into contact with water.

[0052] In some embodiments, such as Figure 4 As shown, the spiral resistance wire 14 is electrically connected to the alarm 18, so that when the current changes after the resistance wire comes into contact with water and exceeds the current threshold, the alarm 18 will issue an alarm.

[0053] The detector inlet 31 has a circular cross-section with an area of ​​Si; the detector outlet 32 ​​has an annular cross-section with an area of ​​So. The inlet flow coefficient of the detector 10 is equal to the ratio of the detector outlet area to the detector inlet area (So / Si). In this invention, the inlet flow coefficient of the detector 10 is adjusted to be less than 1.

[0054] Due to the significant difference in inertia between large and small water droplets, the method of reducing the inlet flow coefficient (adjusting the detector's inlet flow coefficient to less than 1) can effectively reduce the capture rate of small water droplets at the detector inlet (i.e., some small water droplets fly out of the detector, while all large water droplets enter the detector). See [link to relevant documentation]. Figure 3 ①. After large water droplets and some small water droplets enter the detector, the large water droplets, upon impacting the central cone, will bounce and splash onto the spiral resistance wire on the side wall, causing a change in resistance and thus generating an alarm. See [link to relevant documentation]. Figure 3 ②; and the remaining small water droplets will fly out of the detector's exit with the airflow, see Figure 3 ③.

[0055] According to the above technical solution, the aircraft supercooled large water droplet icing detection device of the present invention can achieve the following beneficial technical effects: it can effectively distinguish the diameter of water droplets, thereby detecting supercooled large water droplet icing weather, and supporting the airworthiness certification of aircraft operating under icing weather conditions.

[0056] Specifically, the aircraft supercooled large water droplet icing detection device of the present invention utilizes the difference in the airflow characteristics of large and small water droplets. It effectively separates large and small water droplets primarily through two methods: inlet flow coefficient control (inlet flow coefficient less than 1) and a central cone, thus providing an alarm only for supercooled large water droplets. The present invention employs an inlet / outlet area ratio parameter condition to control the inlet flow coefficient to be less than 1, reducing the detector's capture rate of small water droplets and thus more effectively capturing supercooled large water droplets for primary droplet separation. The present invention uses a central cone structure, utilizing the rebound and splashing characteristics of large water droplets to separate them, causing them to bounce onto the sidewall, while small water droplets are unaffected by the central cone and smoothly fly out of the detector exit, allowing for better identification of large water droplets. The present invention also arranges a spiral resistance wire on the inner sidewall; the resistance change caused by supercooled large water droplets triggers an alarm for supercooled large water droplets.

[0057] In some embodiments, such as Figure 1 - Figure 4 As shown, the supercooled large water droplet icing detection device for aircraft also includes a ball-head hinge 15 and a flow guide ring 16. The central cone 13 of the detector 10 is connected to the support member 20 via the ball-head hinge 15, which is located at the center of mass of the detector 10. The flow guide ring 16 is located on the outer side of the tail of the detector 10, surrounding the tail of the sidewall 12. Due to the conical shape of the detector's sidewall, the aerodynamic force during flight mainly acts on the flow guide ring. Therefore, the aerodynamic pressure center of the detector is mainly located at the flow guide ring, behind the center of mass. Thus, the detector deflects with the airflow direction and points in real time towards the local airflow direction on the outer surface, ensuring that water droplets are successfully captured by the detector during flight. Compared with existing detectors, this device has better capture performance.

[0058] In some embodiments, such as Figure 1 - Figure 4As shown, the inlet flow coefficient of detector 10 is 0.3–0.7. That is, because the inlet flow coefficient of detector 10 is 0.3–0.7, approximately 30%–70% of small water droplets exit the detector directly at the detector inlet (without entering the detector inlet), achieving effective primary droplet separation, reducing the detector's capture rate of small water droplets, and thus more effectively capturing supercooled large water droplets. Preferably, the inlet flow coefficient of detector 10 is 0.5.

[0059] In some embodiments, such as Figure 1 - Figure 4 As shown, the semi-cone angle of the central cone 13 is 20–45 degrees. It should be noted that the "semi-cone angle" here refers to the angle between the generatrix of the central cone's surface and the central axis. It should also be noted that the "semi-cone angle of the central cone" refers to the semi-cone angle of the front wall of the central cone. Preferably, the semi-cone angle of the central cone 13 is 30 degrees.

[0060] In some embodiments, such as Figure 1 - Figure 4 As shown, the semi-cone angle of sidewall 12 is 10–35 degrees. It should be noted that the "semi-cone angle" here is similar to the semi-cone angle of the central cone mentioned above, referring to the angle between the generatrix of the cone surface (the cone surface formed by the sidewalls) and the central axis. Preferably, the semi-cone angle of sidewall 12 is 20 degrees.

[0061] In some embodiments, such as Figure 1 - Figure 4 As shown, the semi-cone angle of the central cone 13 is 5 to 15 degrees larger than that of the side wall 12. Therefore, the supercooled large water droplets will bounce and splash on the front wall of the central cone 13, thereby separating the large water droplets from the small water droplets. The supercooled large water droplets will further bounce onto the spiral resistance wire 14 of the side wall 12. Preferably, the semi-cone angle of the central cone 13 is 10 degrees larger than that of the side wall 12.

[0062] In some embodiments, such as Figure 4 As shown, heaters 17 are provided on both the sidewall 12 and the central cone 13. Therefore, icing inside the detector can be prevented from affecting detection performance, especially preventing icing on the sidewall 12 and the central cone 13. The heater 17 can be, for example, an electric heater.

[0063] In some embodiments, such as Figure 5As shown, the central cone 13 includes a front wall 131, a rear wall 132, and a static pressure cavity 133 located between the front wall 131 and the rear wall 132. Preferably, the front wall 131 and the rear wall 132 are connected by a sleeve to form the static pressure cavity 133 therebetween. Preferably, the rear wall 132 is connected to the support member 20 by means of a ball joint hinge 15. The aircraft supercooled large water droplet icing detection device also includes a static pressure port 19, which connects the static pressure cavity 133 to the outside of the aircraft. The central cone also includes an elastic member 134 (e.g., a spring) disposed between the front wall 131 and the rear wall 132. That is, the elastic member 134 is disposed within the static pressure cavity 133, with its two ends abutting against the front wall 131 and the rear wall 132 of the central cone, respectively.

[0064] In some embodiments, such as Figure 5 As shown, the flow guide ring 16 is connected to the tail of the side wall 12 via the support arm 21, and the static pressure hole 19 passes through the flow guide ring 16, the support arm 21 and the tail of the side wall 12 in sequence, thereby communicating with the static pressure chamber 133.

[0065] This invention employs a central cone to capture the total pressure of flight at the front, while the rear static pressure chamber contains the static pressure of flight. Combined with an elastic element within the static pressure chamber, the front wall of the central cone can move back and forth. Under low dynamic pressure conditions, the forward movement of the central cone's front wall reduces the flow channel, which is beneficial for capturing water droplets. The elastic element can adjust the forward extension or retraction of the central cone's front wall based on the difference between the static pressure within the static pressure chamber and the total pressure of flight at the inlet. Therefore, it exhibits good adaptability to capturing water droplets at varying airspeeds (flight speeds).

[0066] In some embodiments, such as Figure 1 - Figure 5 As shown, the ratio of the width (front-to-back direction) of the guide ring 16 to the width (front-to-back direction) of the detector head is 0.4 to 0.6:1. Preferably, the ratio is 0.5:1.

[0067] The installation method of the aircraft supercooled large water droplet icing detection device of the present invention can be as follows:

[0068] (1) First, a spiral resistance wire is arranged on the inner side of the detector sidewall;

[0069] (2) Assemble the sidewalls and central cone of the detector;

[0070] (3) Connect the detector and the support rod;

[0071] (4) The detector is mounted on the aircraft using a support rod;

[0072] (5) Connect the heating device circuit of the detector;

[0073] (6) Connect the detector's resistance alarm line.

[0074] According to an embodiment of the present invention, the aircraft includes an aircraft supercooled large water droplet icing detection device as described in any of the above aspects. Based on the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: it can effectively distinguish water droplet diameters, thereby detecting supercooled large water droplet icing weather.

[0075] The specific embodiments of the present invention have been described above. However, those skilled in the art will understand that the above specific embodiments do not constitute a limitation on the present invention. Those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.

Claims

1. A device for detecting icing of supercooled large water droplets in aircraft, characterized in that, The aircraft supercooled large water droplet icing detection device includes a detector and a support component connected to the detector; The detector includes a head and a sidewall connected to the head. The head is an open cylinder to form a circular detector inlet. The sidewall is conical and gradually expands from the inlet to the outlet. The detector also includes a central cone located within the sidewall. An annular detector outlet is formed between the tail of the sidewall and the tail of the central cone. A spiral resistance wire is arranged on the inner side of the sidewall to trigger an alarm by sensing changes in current when the resistance wire comes into contact with water. The inlet flow coefficient of the detector is equal to the ratio of the detector outlet area to the detector inlet area, and the inlet flow coefficient of the detector is less than 1.

2. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, The supercooled large water droplet icing detection device for the aircraft also includes a ball-head hinge and a flow guide ring. The central cone of the detector is connected to the support member by means of the ball-head hinge. The ball-head hinge is located at the center of mass of the detector. The flow guide ring is located on the outer side of the tail of the detector and surrounds the tail of the sidewall.

3. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, The inlet flow coefficient of the detector is 0.3 to 0.

7.

4. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, The semi-cone angle of the central cone is 20 to 45 degrees.

5. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, The semi-cone angle of the sidewall is 10 to 35 degrees.

6. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, The supercooled large water droplet icing detection device is installed at the nose of the aircraft.

7. The aircraft supercooled large water droplet icing detection device as described in claim 1, characterized in that, Both the sidewall and the central cone are equipped with heaters.

8. The aircraft supercooled large water droplet icing detection device as described in claim 2, characterized in that, The central cone includes a front wall, a rear wall, and a static pressure cavity located between the front wall and the rear wall. The supercooled large water droplet icing detection device for the aircraft also includes a static pressure hole that connects the static pressure cavity to the outside of the aircraft. The central cone also includes an elastic element disposed between the front wall and the rear wall.

9. The aircraft supercooled large water droplet icing detection device as described in claim 8, characterized in that, The flow guide ring is connected to the tail of the side wall via a support arm, and the static pressure hole passes through the flow guide ring, the support arm and the tail of the side wall in sequence, thereby communicating with the static pressure cavity.

10. An aircraft comprising an aircraft supercooled large water droplet icing detection device as claimed in any one of claims 1-9.

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