Supercooled large droplet icing detector capable of automatically adapting to sideslip angle of aircraft, and aircraft

Abstract

A supercooled large droplet icing detector capable of automatically adapting to a sideslip angle of an aircraft, and an aircraft. The supercooled large droplet icing detector capable of automatically adapting to a sideslip angle of an aircraft comprises a probe (1), a wind vane structure (2), a transition structure (3), a support structure (4), a bearing (6), and a rotating shaft (7), wherein a first icing sensor (21) and a second icing sensor (22) are arranged on the probe (1), and are used for detecting an icing condition and distinguishing a supercooled large droplet icing condition; the wind vane structure (2) is connected between the probe (1) and the transition structure (3), and is used for automatically adjusting the probe (1) to follow the airflow direction under the action of wind; the transition structure (3) is connected between the wind vane structure (2) and the rotating shaft (7), and is used for generating an eccentric effect, so that the rotating shaft (7) can be driven to rotate under the force of the wind vane structure (2); the support structure (4) is mounted to an aircraft skin (5), and is used for supporting the supercooled large droplet icing detector; the bearing (6) is sleeved on the outer side of the rotating shaft (7), and is used for supporting and lubricating the rotating shaft (7) to rotate.

Description

Automatically adaptable supercooled large water droplet icing detector and aircraft Technical Field

[0001] This invention relates to the field of aircraft icing detection technology, and more specifically to a supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle. Background Technology

[0002] Icing detectors are a crucial component of aircraft icing protection systems, and their accuracy directly determines the icing condition before icing protection is activated. EASA CS-25.1420 specifies requirements for aircraft to handle supercooled large water droplet conditions; aircraft must be able to identify supercooled large water droplet environments in order to escape from them. Currently, there is no mature detector for supercooled large water droplet icing conditions.

[0003] Existing icing detectors typically consist of an aluminum alloy cylinder mainly composed of a front shuttle, a groove, and a rear shuttle, exhibiting a structure that is pointed at the front and rear and concave in the middle. This detector is mounted externally on the wing. A fiber optic icing sensor (referred to as the "front sensor") is installed on each of the left and right side walls of the front shuttle to detect conventional icing; a fiber optic icing sensor (referred to as the "rear sensor") is installed on each of the left and right side walls of the rear shuttle to detect icing of supercooled large water droplets. The groove is frosted to increase the frictional resistance as supercooled large water droplets flow through, thereby improving the detector's freezing coefficient for supercooled large water droplets.

[0004] Existing icing detector structures cannot maintain alignment with the incoming flow direction when the aircraft's sideslip angle changes, which can easily lead to measurement errors. Summary of the Invention

[0005] One objective of this invention is to provide a supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle. This detector overcomes at least some of the shortcomings of the prior art and can automatically adjust its angle as the aircraft sideslip angle changes, always maintaining consistency with the direction of the incoming flow.

[0006] The above-mentioned objective of the present invention is achieved by an overcooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle. The overcooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle includes a probe, a weather vane structure, a transition structure, a support structure, a bearing, and a rotating shaft.

[0007] The probe is equipped with a first icing sensor and a second icing sensor to detect icing conditions and distinguish between icing conditions of supercooled large water droplets. The wind vane structure is connected between the probe and the transition structure to automatically adjust the probe to the direction of the airflow under wind force. The transition structure is connected between the wind vane structure and the rotating shaft to generate an eccentric effect so that the force on the wind vane structure can drive the rotating shaft to rotate. The support structure is installed on the aircraft skin to support the supercooled large water droplet icing detector. The bearing is sleeved on the outside of the rotating shaft to support and lubricate the rotation of the rotating shaft.

[0008] According to the above technical solution, the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle of the present invention can achieve the following beneficial technical effects: it can automatically adjust its own angle as the aircraft sideslip angle changes, and always maintain the same direction as the incoming flow.

[0009] Preferably, the cross-section of the weather vane structure is an isosceles triangle.

[0010] Preferably, the vertex angle of the isosceles triangle in the cross-section of the weather vane structure is 20 to 40 degrees.

[0011] Preferably, the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle further includes an angle transmitting device, an angle receiving device, and a controller. The angle transmitting device is used to transmit the rotation angle of the rotating shaft to the angle receiving device. The angle receiving device is used to receive the rotation angle of the rotating shaft and output it to the controller. The controller is used to receive a first icing signal from the first icing sensor, a second icing signal from the second icing sensor, and an angle signal from the angle receiving device, and determine whether to output a normal icing alarm signal and / or a supercooled large water droplet icing alarm signal.

[0012] Preferably, when the first icing signal is icing, the controller outputs a normal icing alarm signal; otherwise, it re-receives the first icing signal and the second icing signal.

[0013] Preferably, when both the first icing signal and the second icing signal are icing, the controller calculates and determines (A) i+1 -A i Is A less than M1, where A i+1 It is the angle at time i+1, A i M1 is the angle at time i, and M1 is the angle difference threshold. When the controller calculates and determines (A... i+1 -A i When the value is less than M1, an alarm signal for large, overcooled water droplets freezing is output; otherwise, the angle signal is received again.

[0014] Preferably, the angle difference threshold M1 is 0.5 to 1.5 degrees.

[0015] Preferably, the probe includes:

[0016] The main body is bullet-shaped and includes a head and a tail connected in sequence.

[0017] Two side wings are respectively located on both sides of the main body, and both are connected to the tail.

[0018] The first icing sensor is disposed on the head of the main body on the side opposite to the tail.

[0019] The second icing sensor is located on the side of the wing facing the head.

[0020] Preferably, the ratio of the vertical height to the horizontal length of the transition structure is 0.3 to 0.5:1.

[0021] The above-mentioned objectives of the present invention are also achieved by an aircraft comprising a supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle as described in any of the above aspects.

[0022] According to the above technical solution, the aircraft of the present invention can achieve the following beneficial technical effects: it can automatically adjust the angle of the supercooled large water droplet icing detector (probe) according to the change of the aircraft sideslip angle, and always keep it consistent with the direction of the incoming flow. Attached Figure Description

[0023] Figure 1 is a schematic diagram of the structure of an automatic adaptive aircraft sideslip angle supercooled large water droplet icing detector according to an embodiment of the present invention (including front view and cross-sectional views).

[0024] Figure 2 is a schematic diagram of the probe structure of an automatic adaptive aircraft sideslip angle supercooled large water droplet icing detector according to an embodiment of the present invention.

[0025] Figure 3 is a schematic diagram of the signal input and output of an automatic adaptive aircraft sideslip angle supercooled large water droplet icing detector according to an embodiment of the present invention.

[0026] Figure 4 is a flowchart of the operation of an automatic adaptive supercooled large water droplet icing detector according to an embodiment of the present invention.

[0027] List of reference numerals: 1: Probe; 2: Weather vane structure; 3: Transition structure; 4: Support structure; 5: Aircraft skin; 6: Bearing; 7: Rotating shaft; 8: Angle transmitting device; 9: Angle receiving device; 10: Controller; 11: Main body; 12: Side wing; 21: First icing sensor; 22: Second icing sensor; 111: Head; 112: Tail. Detailed Implementation

[0028] 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.

[0029] 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.

[0030] 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.

[0031] Figure 1 is a structural schematic diagram (including a front view and cross-sectional views) of a supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle according to an embodiment of the present invention. Figure 2 is a schematic diagram of the probe structure of the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle according to an embodiment of the present invention. Figure 3 is a schematic diagram of the signal input and output of the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle according to an embodiment of the present invention. Figure 4 is a flowchart of the operation of the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle according to an embodiment of the present invention.

[0032] As shown in Figures 1-4, an embodiment of the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle according to the present invention includes a probe 1, a weather vane structure 2, a transition structure 3, a support structure 4, a bearing 6, and a rotating shaft 7.

[0033] In some embodiments, as shown in Figures 1-4, a first icing sensor 21 and a second icing sensor 22 are arranged on the probe 1 to detect icing conditions and distinguish between icing conditions of supercooled large water droplets. A wind vane structure 2 is connected between the probe 1 and the transition structure 3 to automatically adjust the probe 1 to the direction of the airflow under the action of wind force. The transition structure 3 is connected between the wind vane structure 2 and the rotating shaft 7 to generate an eccentric effect so that the force on the wind vane structure 2 can drive the rotating shaft 7 to rotate. A support structure 4 is installed on the aircraft skin 5 to support the supercooled large water droplet icing detector. A bearing 6 is sleeved on the outside of the rotating shaft 7 to support and lubricate the rotation of the rotating shaft 7.

[0034] According to the above technical solution, the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle of the present invention can achieve the following beneficial technical effects: it can automatically adjust its own angle as the aircraft sideslip angle changes, and always maintain the same direction as the incoming flow.

[0035] Specifically, due to the presence of components such as the weather vane structure, transition structure, bearings, and rotating shaft, the supercooled large water droplet icing detector of the present invention, which automatically adapts to the aircraft sideslip angle, can automatically adjust its own angle as the aircraft sideslip angle changes, always maintaining consistency with the incoming flow direction. The front end of the weather vane structure always points to the incoming flow direction, thus automatically adjusting the probe angle to be in the direction of the airflow according to the incoming flow, which facilitates the adjustment of the icing detector angle and improves detection accuracy.

[0036] In some embodiments, as shown in Figure 1, the cross-section of the weather vane structure 2 is an isosceles triangle. With a suitable cross-sectional shape, the rear wind-receiving area of ​​the weather vane structure is larger than that of the front. If both the front and rear of the weather vane structure are exposed to wind, the rear of the weather vane structure will be pushed back by the wind, causing the front of the weather vane structure to move towards the source of the wind. That is, the front end of the weather vane structure always points in the direction of the incoming flow. Therefore, the supercooled large water droplet icing detector (probe) can better adjust its own angle automatically with the change of the aircraft sideslip angle and always remain consistent with the direction of the incoming flow.

[0037] In some embodiments, as shown in Figure 1, the apex angle of the isosceles triangle in the cross-section of the weather vane structure 2 is 20–40 degrees. By appropriately designing the apex angle of the isosceles triangle in the cross-section of the weather vane structure, the supercooled large water droplet icing detector (probe) can better automatically adjust its angle according to changes in the aircraft's sideslip angle, always maintaining alignment with the incoming flow direction. Preferably, the apex angle of the isosceles triangle in the cross-section of the weather vane structure 2 is 30 degrees.

[0038] In some embodiments, as shown in FIG1, the transition structure 3 connects the weather vane structure 2 and the rotating shaft 7 to generate an eccentric effect, so that the force on the weather vane structure 2 can drive the rotating shaft 7 to rotate. That is, due to the presence of the transition structure 3, the vertical central axis of the weather vane structure 2 is offset (eccentric) relative to the vertical central axis of the rotating shaft 7. Therefore, the force on the weather vane structure 2 can drive the rotating shaft 7 to rotate, so that the supercooled large water droplet icing detector (probe) can better automatically adjust its own angle with the change of the aircraft sideslip angle and always remain consistent with the direction of the incoming flow.

[0039] In some embodiments, as shown in FIG1, the support structure 4 is mounted to the aircraft skin 5 to support the supercooled large water droplet icing detector. Preferably, the support structure 4 can be plate-shaped, such as a circular plate, for mounting to the aircraft skin 5. The support structure 4 may have a through hole at its center for the lower end of the transition structure 3 and / or the upper end of the rotating shaft 7 to pass through. That is, the presence of the support structure 4 makes the entire installation of the supercooled large water droplet icing detector more stable.

[0040] In some embodiments, as shown in FIG1, the bearing 6 is sleeved on the outside of the rotating shaft 7 to support and lubricate the rotation of the rotating shaft 7. Preferably, the bearing 6 is a rolling bearing, such as a ball bearing or roller bearing. Preferably, the bearing 6 is installed at or near the bottom surface of the support structure 4.

[0041] In some embodiments, as shown in FIG1, the rotation center axis of the rotating shaft 7 is vertical. That is, due to the presence of the bearing 6 and the rotating shaft 7, the force on the wind vane structure 2 can drive the rotating shaft 7 to rotate, so that the supercooled large water droplet icing detector (probe) can better automatically adjust its own angle with the change of the aircraft sideslip angle and always remain consistent with the direction of the incoming flow.

[0042] In some embodiments, as shown in Figures 1-3, the supercooled large droplet icing detector that automatically adapts to the aircraft sideslip angle further includes an angle transmitting device 8, an angle receiving device 9, and a controller 10. The angle transmitting device 8 transmits the rotation angle of the rotating shaft to the angle receiving device 9. The angle receiving device 9 receives the rotation angle of the rotating shaft and outputs it to the controller 10. The controller 10 receives a first icing signal from the first icing sensor 21, a second icing signal from the second icing sensor 22, and an angle signal from the angle receiving device 9, and determines whether to output a normal icing alarm signal and / or a supercooled large droplet icing alarm signal. Therefore, the supercooled large droplet icing detector that automatically adapts to the aircraft sideslip angle of the present invention can sense changes in its own angle (probe rotation angle), filter the selectable probe rotation angle measurement results, and reduce the detection error of supercooled large droplet icing conditions.

[0043] Preferably, the angle transmitting device 8 and the angle receiving device 9 can be magnetic sensors, Hall sensors, or other types of sensors suitable for sensing angles.

[0044] As shown in Figures 3 and 4, the working process of the supercooled large water droplet icing detector that automatically adapts to the aircraft sideslip angle of the present invention can be as follows:

[0045] The controller 10 receives icing signals B1 and B2 (i.e., the first icing signal B1 and the second icing signal B2) (it should be noted that the icing signal has two states: icing and non-icing).

[0046] Controller 10 receives angle signal A;

[0047] If the icing signal B1 indicates icing, the controller 10 outputs a normal icing alarm signal C1.

[0048] If the icing signal B1 indicates no icing, the controller 10 will re-receive the icing signals B1 and B2.

[0049] When both icing signal B1 and icing signal B2 indicate icing, controller 10 calculates and determines (A... i+1 -A i Is A less than M1, where A i+1 It is the angle at time i+1, A i M1 is the angle at time i, and M1 is the angle difference threshold. When controller 10 calculates and determines (A... i+1 -A i When the value is less than M1, output an alarm signal C2 for large, overcooled water droplets freezing; otherwise, re-receive angle signal A.

[0050] When icing signal B1 indicates icing and icing signal B2 indicates no icing, controller 10 re-receives icing signals B1 and B2.

[0051] In some embodiments, the angle difference threshold M1 is 0.5 to 1.5 degrees. That is, the supercooled large water droplet icing detector of the present invention, which automatically adapts to the aircraft sideslip angle, can sense changes in its own angle (probe rotation angle), filter available probe rotation angle measurement results, and directly discard probe rotation angle measurement results exceeding the angle difference threshold M1, and then re-receive the angle signal, thereby reducing detection errors under supercooled large water droplet icing conditions. Preferably, the angle difference threshold M1 is 1.0 degree.

[0052] In some embodiments, as shown in Figures 1-2, the probe 1 includes: a main body 11, shaped like a bullet, the main body 11 including a head 111 and a tail 112 connected in sequence; two side wings 12, respectively disposed on both sides of the main body 11 and both connected to the tail 112; a first icing sensor 21 disposed on the side of the head 111 of the main body 11 facing away from the tail 112; and a second icing sensor 22 disposed on the side wing 12 facing the head 111. Through appropriate probe structure design and icing sensor arrangement, the supercooled large water droplet icing detector of the present invention, which automatically adapts to the aircraft sideslip angle, can better detect icing conditions and better distinguish between ordinary icing conditions and supercooled large water droplet icing conditions.

[0053] Preferably, the first icing sensor 21 and the second icing sensor 22 should meet the following functional requirements:

[0054] Measure the icing conditions on each surface (ice thickness, icing rate, etc.);

[0055] Detection should be carried out simultaneously, and icing information should be output.

[0056] It should be able to eliminate surface ice and prevent interference with subsequent detection.

[0057] In some embodiments, as shown in Figure 1, the ratio of the vertical height to the horizontal length of the transition structure 3 is 0.3 to 0.5:1. With a suitable ratio of vertical height to horizontal length of the transition structure, the supercooled large water droplet icing detector (probe) can better automatically adjust its angle according to changes in the aircraft's sideslip angle, always maintaining alignment with the incoming flow direction. It should be noted that the horizontal length of the transition structure here refers to the horizontal projection length of the transition structure on the horizontal plane, which is equal to the sum of the eccentricity of the weathervane structure, the radius of the rotation axis, and half the horizontal length of the weathervane structure. Preferably, the ratio of the vertical height to the horizontal length of the transition structure 3 is 0.4:1.

[0058] According to one embodiment of the present invention, the aircraft includes a supercooled large water droplet icing detector that automatically adapts to the aircraft's sideslip angle 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 automatically adjust the angle of the supercooled large water droplet icing detector (probe) according to changes in the aircraft's sideslip angle, always maintaining alignment with the incoming flow direction.

[0059] 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 supercooled large droplet icing detector that automatically adapts to the sideslip angle of an aircraft, characterized in that, The supercooled large droplet icing detector automatically adapting to the aircraft sideslip angle comprises a probe, a wind vane structure, a transition structure, a support structure, a bearing and a rotating shaft; The first icing sensor and the second icing sensor are arranged on the probe to detect icing conditions and distinguish supercooled large droplet icing conditions; the wind vane structure is connected between the probe and the transition structure to automatically adjust the probe to the airflow direction under the action of wind force; the transition structure is connected between the wind vane structure and the rotating shaft to generate an eccentric effect so that the force acting on the wind vane structure can drive the rotating shaft to rotate; the support structure is installed to the aircraft skin to support the supercooled large droplet icing detector; and the bearing is sleeved outside the rotating shaft to support and lubricate the rotating shaft.

2. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle of claim 1, wherein, The cross section of the wind vane structure is isosceles triangle.

3. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle of claim 2, wherein, The top angle of the isosceles triangle is 20-40 degrees.

4. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle of claim 1, wherein, The supercooled large droplet icing detector further comprises an angle sending device, an angle receiving device and a controller; the angle sending device is used to send the rotating angle of the rotating shaft to the angle receiving device; the angle receiving device is used to receive the rotating angle of the rotating shaft and output to the controller; and the controller is used to receive the first icing signal from the first icing sensor, the second icing signal from the second icing sensor and the angle signal from the angle receiving device, and judge whether to output the general icing alarm signal and / or the supercooled large droplet icing alarm signal.

5. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle as defined in claim 4, wherein, When the first icing signal is icing, the controller outputs the general icing alarm signal, otherwise the first icing signal and the second icing signal are received again.

6. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle as defined in claim 4, wherein, When both the first icing signal and the second icing signal are icing, the controller calculates and determines (A) i+1 -A i Is A less than M1, where A i+1 It is the angle at time i+1, A i M1 is the angle at time i, and M1 is the angle difference threshold. When the controller calculates and determines (A... i+1 -A i When the value is less than M1, an alarm signal for large, overcooled water droplets freezing is output; otherwise, the angle signal is received again.

7. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle as defined in claim 6, wherein, M1 is 0.5-1.5 degrees.

8. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle of claim 1, wherein, The probe comprises: a main body in the shape of a bullet, the main body comprising a head and a tail connected in sequence; two wings respectively arranged on both sides of the main body and connected with the tail; the first icing sensor arranged on one side of the head of the main body away from the tail; the second icing sensor arranged on one side of the wing facing the head.

9. The supercooled large droplet ice detector that automatically accommodates aircraft sideslip angle of claim 1, wherein, The ratio of the vertical height to the horizontal length of the transition structure is 0.3-0.5:

1.

10. An aircraft comprising the supercooled large droplet icing detector automatically adapting to the aircraft sideslip angle according to any one of claims 1-9.

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