Aircraft and Its Ice Detector and Ice Warning Method

Abstract

The present invention provides an aircraft, an icing detector thereof, and an icing warning method. The icing probe includes: a main body in a warhead shape, the main body including a head and a tail; two side wings respectively disposed on both sides of the main body and both connected to the tail; a first sensor disposed on a side of the head of the main body facing away from the tail; a second sensor disposed on a side of the side wing facing the head; the icing detector includes a housing, the above-mentioned icing probe, and an angle adjustment mechanism. The angle adjustment mechanism includes an angle of attack adjustment mechanism and a sideslip angle adjustment mechanism. The angle of attack adjustment mechanism drives the icing probe to rotate in a first plane, and the sideslip angle adjustment mechanism drives the icing probe to rotate in a second plane; the aircraft includes the above-mentioned icing detector; the icing warning method uses the above-mentioned icing detector. The aircraft, the icing probe, the icing detector, and the icing warning method provided by the present invention can improve the recognition and monitoring ability for supercooled large droplets.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft icing warning, and particularly to an aircraft, an icing detector thereof, and an icing warning method. Background Art

[0002] An icing detector is an important part of an aircraft icing protection system, and its recognition accuracy directly determines the icing situation before the aircraft icing protection is activated. At present, Clause EASACS - 25.1420 puts forward requirements for aircraft to cope with supercooled large droplet conditions. An aircraft needs to have the ability to recognize the supercooled large droplet environment in order to escape from this environment. At present, there is no mature detector for supercooled large droplet icing conditions.

[0003] Therefore, how to improve the recognition and monitoring ability of an aircraft for supercooled large droplets urgently needs to be studied. Summary of the Invention

[0004] The purpose of the present invention is to provide an aircraft, an icing detector thereof, and an icing warning method, so as to improve the recognition and monitoring ability for supercooled large droplets.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] An icing detector for an aircraft, the icing detector comprising:

[0007] A housing having a receiving cavity, the housing being adapted to be disposed on the aircraft;

[0008] An icing probe disposed outside the housing;

[0009] An angle adjustment mechanism, one end of which is fixedly connected to the icing probe and the other end of which is movably connected to the receiving cavity;

[0010] Wherein, the angle adjustment mechanism includes an angle of attack adjustment mechanism and a sideslip angle adjustment mechanism. The angle of attack adjustment mechanism drives the icing probe to rotate in a first plane, and the sideslip angle adjustment mechanism drives the icing probe to rotate in a second plane. The first plane and the second plane are perpendicular to each other; a first direction of the icing probe is located in the first plane, and a second direction of the icing probe is located in the second plane;

[0011] The icing probe has a first direction and a second direction perpendicular to each other, and includes:

[0012] A main body in a bullet - head shape, the main body including a head and a tail connected in sequence along the first direction;

[0013] Two wings respectively disposed on both sides of the main body in the second direction and both connected to the tail;

[0014] The first sensor is disposed on one side of the head of the main body away from the tail;

[0015] The second sensor is disposed on one side of the winglet facing the head.

[0016] In some embodiments of the present invention, the angle of attack adjusting mechanism includes:

[0017] An angle of attack adjusting driving member, connected to the housing;

[0018] A first connecting member, fixedly connected to the icing probe and connected to the angle of attack adjusting driving member;

[0019] Wherein, the angle of attack adjusting driving member drives the first connecting member to rotate in the first plane, and then the icing probe rotates in the first plane.

[0020] In some embodiments of the present invention, the angle of attack adjusting mechanism further includes:

[0021] A second connecting member, connected between the angle of attack adjusting driving member and the first connecting member;

[0022] A third connecting member, movably sleeved on the outer periphery of the first connecting member and rotatably connected to the second connecting member;

[0023] Wherein, the angle of attack adjusting driving member is actuated by the angle of attack adjusting driving member to drive the second connecting member to rotate in the first plane, and then the second connecting member drives the third connecting member to rotate in the first plane.

[0024] In some embodiments of the present invention, the second connecting member includes two relatively arranged and connected ends, and a through hole is respectively provided on each of the two ends, and the two ends rotate in the first plane;

[0025] The third connecting member includes a sleeve structure and two protrusions provided on the outer peripheral surface of the sleeve structure, the two protrusions are respectively located on both sides in the radial direction of the sleeve structure, and a through opening is provided along the longitudinal direction of the sleeve structure, and the first connecting member passes through the through opening;

[0026] The third connecting member is located between the two ends of the second connecting member, and each protrusion is respectively inserted into the through hole on one end.

[0027] In some embodiments of the present invention, the fixed part and the movable part of the angle of attack adjusting driving member are movably connected;

[0028] The fixed part of the angle of attack adjustment driving member is fixedly connected to the outside of the housing, a first through hole is formed in the housing, and the movable part of the angle of attack adjustment driving member passes through the first through hole and is fixedly connected to the second connecting member;

[0029] Alternatively, the fixed part of the angle of attack adjustment driving member is located in the receiving cavity and is fixedly connected to the housing, and the movable part of the angle of attack adjustment driving member is fixedly connected to the second connecting member.

[0030] In some embodiments of the present invention, the sideslip angle adjustment mechanism includes:

[0031] A sideslip angle adjustment driving member, which is received in the receiving cavity, the fixed part and the movable part of the sideslip angle adjustment driving member are movably connected, the fixed part of the sideslip angle adjustment driving member is fixedly connected to the third connecting member, and the movable part of the sideslip angle adjustment driving member is fixedly connected to the first connecting member.

[0032] In some embodiments of the present invention, the housing has an opening, and the opening communicates the receiving cavity with the outside of the housing;

[0033] The icing detector further includes a soft covering member, and the soft covering member is covered on the opening;

[0034] A second through hole is provided on the soft covering member, the first connecting member passes through the second through hole, and the angle of attack adjustment driving member, a part of the first connecting member, the second connecting member, the third connecting member, and the sideslip angle adjustment driving member are all received in the receiving cavity.

[0035] In some embodiments of the present invention, a window structure is provided on the first connecting member, the window structure penetrates the first connecting member along the radial direction of the first connecting member, and the depth direction of the window structure is the same as the first direction of the icing probe;

[0036] The icing detector further includes pressure sensors, and the pressure sensors include a first pressure sensor, a second pressure sensor, a third pressure sensor, and a fourth pressure sensor;

[0037] The first pressure sensor and the second pressure sensor are respectively arranged on one inner wall of the window structure close to the icing probe and one inner wall far from the icing probe;

[0038] The third pressure sensor and the fourth pressure sensor are arranged on opposite inner walls of the window structure and are adapted to the two sides in the second direction of the icing probe.

[0039] To achieve the above object, the present invention also provides the following technical solutions:

[0040] An aircraft, the aircraft includes a body and an icing detector provided on the body as described above.

[0041] To achieve the above object, the present invention also provides the following technical solutions:

[0042] An icing warning method for an aircraft, the warning method uses the icing detector as described above and a controller electrically connected to the icing detector;

[0043] The warning method includes the following steps:

[0044] The controller receives a feedback signal from the icing detector, and controls an angle adjustment mechanism in the icing detector according to the feedback signal, thereby controlling the icing probe to rotate in the first plane and / or the second plane, and determines whether the outside of the aircraft is iced according to the feedback signal.

[0045] In some embodiments of the present invention, the feedback signal includes an angle feedback signal sent by the angle adjustment mechanism of the icing detector;

[0046] The warning method further includes:

[0047] The controller receives flight condition parameters from the aircraft and outputs an angle adjustment signal to the icing detector according to the flight condition parameters, and then the controller receives the angle feedback signal;

[0048] If the angle adjustment signal and the angle feedback signal are equal, it continues to determine whether the outside of the aircraft is iced. If the angle adjustment signal and the angle feedback signal are not equal, the controller outputs a fault signal.

[0049] In some embodiments of the present invention, the angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjustment mechanism, and the angle feedback signal includes an angle of attack feedback signal from the angle of attack adjustment mechanism;

[0050] The warning method further includes:

[0051] The controller outputs the angle of attack adjustment signal to the angle of attack adjustment mechanism and receives the angle of attack feedback signal;

[0052] If the angle of attack adjustment signal and the angle of attack feedback signal are equal, it continues to determine whether the outside of the aircraft is iced. If the angle of attack adjustment signal and the angle of attack feedback signal are not equal, the controller outputs a fault signal.

[0053] In some embodiments of the present invention, the angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjustment mechanism, and the angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjustment mechanism;

[0054] The warning method further includes:

[0055] The controller outputs the sideslip angle adjustment signal to the sideslip angle adjustment mechanism and receives the sideslip angle feedback signal;

[0056] If the sideslip angle adjustment signal is equal to the sideslip angle feedback signal, continue to determine whether the exterior of the aircraft is iced. If the sideslip angle adjustment signal is not equal to the sideslip angle feedback signal, the controller outputs a fault warning.

[0057] In some embodiments of the present invention, the feedback signal further includes a first icing signal from the first sensor and a second icing signal from the second sensor;

[0058] The warning method further includes:

[0059] The controller receives the first icing signal and the second icing signal;

[0060] When determining whether the exterior of the aircraft is iced, if the first icing signal indicates icing, the controller outputs a first icing warning. If the second icing signal indicates icing, the controller outputs a second icing warning.

[0061] In some embodiments of the present invention, the angle of attack adjustment mechanism includes: an angle of attack adjustment driving member connected to the housing; a first connecting member fixedly connected to the icing probe and connected to the angle of attack adjustment driving member; the angle of attack adjustment driving member drives the first connecting member to rotate in the first plane, and then the icing probe rotates in the first plane; a window structure is provided on the first connecting member, the window structure penetrates the first connecting member along the radial direction of the first connecting member, and the depth direction of the window structure is the same as the first direction of the icing probe; the icing detector further includes a pressure sensor, and the pressure sensor includes a first pressure sensor, a second pressure sensor, a third pressure sensor, and a fourth pressure sensor; the first pressure sensor and the second pressure sensor are respectively arranged on one inner wall of the window structure close to the icing probe and one inner wall far from the icing probe; the third pressure sensor and the fourth pressure sensor are arranged on opposite inner walls of the window structure and are adapted to the two sides in the second direction of the icing probe;

[0062] In the warning method described above, the feedback signal includes a pressure signal from the pressure sensor. The controller receives the pressure signal and compares the absolute value of the first pressure difference between the pressure signal of the first pressure sensor and the pressure signal of the second pressure sensor with a first preset pressure difference. The controller also compares the absolute value of the second pressure difference between the pressure signal of the third pressure sensor and the pressure signal of the fourth pressure sensor with a second preset pressure difference;

[0063] The controller outputs the angle adjustment signal according to the comparison result. Alternatively, the controller determines the icing condition outside the aircraft according to the comparison result and the received first icing signal and second icing signal.

[0064] In some embodiments of the present invention, in the warning method described above:

[0065] The angle feedback signal includes an angle of attack feedback signal from the angle of attack adjustment mechanism, and the angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjustment mechanism;

[0066] The angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjustment mechanism, and the angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjustment mechanism;

[0067] If the absolute value of the first pressure difference is greater than the first preset pressure difference, the controller sends the angle of attack adjustment signal to the angle of attack adjustment mechanism, and then the angle of attack adjustment mechanism adjusts the angle of attack of the icing probe;

[0068] If the absolute value of the second pressure difference is greater than the second preset pressure difference, the controller sends the sideslip angle adjustment signal to the sideslip angle adjustment mechanism, and then the sideslip angle adjustment mechanism adjusts the sideslip angle of the icing probe;

[0069] If the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, the controller determines the icing condition outside the aircraft according to the first icing signal and the second icing signal.

[0070] In some embodiments of the present invention, in the warning method described above:

[0071] If the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, and the first icing signal is icing, the controller outputs a first icing warning;

[0072] And / or, if the absolute value of the first pressure difference is less than the first preset pressure difference, the absolute value of the second pressure difference is less than the second preset pressure difference, and the second icing signal indicates icing, the controller outputs a second icing warning.

[0073] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0074] 1. The icing probe of the aircraft provided by the present invention can accurately identify the existence of supercooled large droplets, and can judge whether the composition of the oncoming flow towards the icing probe is pure supercooled small droplets or a mixture of large and small droplets, so as to accurately identify whether the oncoming flow outside the aircraft is supercooled large droplets or supercooled small droplets, thereby improving the icing warning ability of the aircraft equipped with this icing probe and enhancing safety.

[0075] 2. The icing detector provided by the present invention adopts an angle of attack adjustment mechanism and a sideslip angle adjustment mechanism to respectively adjust the angle of attack direction and the sideslip angle direction of the icing probe in the icing detector, so that when the angle of attack and / or the sideslip angle of the aircraft changes during flight, the angle of attack and / or the sideslip angle of the icing probe can be adaptively adjusted and changed to ensure that the sensor provided on the icing probe can always face the oncoming flow of supercooled water droplets, thereby improving the accuracy of the identification and monitoring of the sensor on the icing probe.

[0076] 3. The aircraft provided by the present invention has higher icing warning ability and accuracy due to the adoption of the above-mentioned icing probe.

[0077] 4. The aircraft provided by the present invention enables the icing probe to make adaptive adjustments as the flight attitude changes due to the adoption of the above-mentioned icing detector, thereby obtaining a more accurate icing warning.

[0078] 5. The icing warning method provided by the present invention has the characteristics of simple and efficient logic. BRIEF DESCRIPTION OF THE DRAWINGS

[0079] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are only some embodiments of the present invention. For those skilled in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0080] Figure 1 It is a schematic diagram of the icing probe provided by the first embodiment of the present invention when encountering small droplets;

[0081] Figure 2 For Figure 1 the schematic diagram of the icing probe in

[0082] Figure 3 Schematic diagram of the icing probe in Figure 1 when the angle of attack of the aircraft changes;

[0083] Figure 4 Schematic diagram of the icing probe in Figure 1 when the sideslip angle of the aircraft changes;

[0084] Figure 5 Schematic structural diagram of the icing detector provided by the second embodiment of the present invention;

[0085] Figure 6 Schematic diagram of the enlarged view of the window structure in Figure 5 another perspective;

[0086] Figure 7 Schematic flow diagram of the icing warning method provided by the third embodiment of the present invention;

[0087] Figure 8 Schematic flow diagram of the icing warning method provided by the fourth embodiment of the present invention;

[0088] Figure 9 Schematic flow diagram of the icing warning method provided by the fifth embodiment of the present invention. The main reference numerals in the drawings of the present invention are described as follows:

[0089] X - First plane; Y - Second plane; Z - First direction; W - Second direction; H - Third direction;

[0090] 0 - Oncoming flow direction;

[0091] 1 - Housing; 10 - Receiving cavity; 11 - Opening;

[0092] 2 - Icing probe; 21 - Main body; 211 - Head; 212 - Tail; 22 - Flank; 23 - First sensor; 24 - Second sensor;

[0093] 31 - Angle of attack adjustment mechanism; 311 - Angle of attack adjustment driving member; 312 - First connecting member; 3121 - Window structure; 313 - Second connecting member; 3131 - End; 3132 - Through hole; 314 - Third connecting member; 3141 - Sleeve structure; 31410 - Through opening; 3142 - Protrusion; 32 - Sideslip angle adjustment mechanism;

[0094] 41 - First pressure sensor; 42 - Second pressure sensor; 43 - Third pressure sensor; 44 - Fourth pressure sensor. Detailed implementation manners

[0095] The technical solutions in the embodiments of the present invention will be described clearly and completely below. Apparently, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0096] The technical solution of the present invention provides an aircraft and its icing probe, icing detector, and icing warning method, which will be described in detail below. It should be noted that the description order of the following embodiments does not limit the preferred order of the embodiments of the present invention; and in the following embodiments, each embodiment has its own emphasis. For the parts not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0097] It should be understood that in the description of the present invention, the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation of the present invention.

[0098] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features; therefore, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0099] In the present invention, unless otherwise clearly defined and limited, the terms "mount", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0100] In the present invention, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or simply indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "beneath" and "underneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or simply indicates that the horizontal height of the first feature is less than that of the second feature.

[0101] It should be noted that when an element is referred to as "fixed to" or "disposed on" another element, it can be directly on the other element or there may also be an intermediate element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intermediate element at the same time. The terms "vertical", "horizontal", "upper", "lower", "left", "right" and similar expressions used herein are only for illustrative purposes and do not represent the only embodiments.

[0102] In the embodiments of the present invention, "parallel" means a state where the angle formed by a straight line and a straight line, a straight line and a plane, or a plane and a plane is -10° to 10°, "vertical" means a state where the angle formed by a straight line and a straight line, a straight line and a plane, or a plane and a plane is 80° to 100°, and equal distance means a state where the tolerance range is -10% to 10%.

[0103] Reference Figures 3 to 5 , in the description of the present invention, the oncoming flow direction 0 refers to the direction in which supercooled water droplets strike the icing probe 2.

[0104] Reference Figure 5 , in the description of the present invention, the first direction Z and the second direction W are both located in the second plane Y, and the first direction Z and the third direction H are both located in the first plane X.

[0105] Embodiment 1

[0106] In some embodiments of the present invention, reference Figures 1 to 4, an icing probe 2 for an aircraft, having a first direction Z and a second direction W that are perpendicular to each other, and comprising: a main body 21, having a warhead shape, the main body 21 including a head 211 and a tail 212 that are sequentially connected along the first direction Z; two side wings 22, respectively disposed on both sides of the main body 21 in the second direction W, and both connected to the tail 212; a first sensor 23, disposed on a side of the head 211 of the main body 21 facing away from the tail 212, so that oncoming supercooled small water droplets can directly impact or directly adhere to the first sensor 23 and thus be detected by the first sensor 23; a second sensor 24, disposed on a side of the side wing 22 facing the head 211, so that oncoming supercooled large water droplets can directly impact or directly adhere to the second sensor 24 and thus be detected by the second sensor 24. Specifically, referring to Figure 1 and Figure 2 , Figure 1 shows the movement of small water droplets when encountering the icing probe 2. It can be understood that due to the small self-weight of the small water droplets, when they pass by the icing probe 2 at high speed, they are diverted to both sides in the second direction W due to the guiding effect of the head 211 of the icing probe 2, so that the side of the side wing 22 facing the head 211 is hardly directly impacted or directly adhered to by small water droplets; while Figure 2 shows the movement of large water droplets when encountering the icing probe 2. Obviously, due to the large self-weight of the large water droplets, when they pass by the icing probe 2 at high speed, even if the head 211 of the icing probe 2 has a certain guiding effect, the large water droplets can directly impact or adhere to the side of the side wing 22 facing the head 211 along the Figure 2 shown flow trend. Therefore, the present invention utilizes the principle that "the warhead-shaped icing probe 2 can divide supercooled small and large water droplets with different self-weights", and a second sensor 24 is respectively disposed on the side of the side wing 22 facing the head 211, so that the first sensor 23 and the second sensor 24 can respectively detect the presence of supercooled small water droplets and supercooled large water droplets, so that the icing probe 2 can detect more accurate situations regarding supercooled large water droplets and supercooled small water droplets, and further enables the icing probe 2 to have the ability to issue more accurate warnings for supercooled large and small water droplets. It should be noted that Figure 1 and Figure 2 the L1 area in is the area where supercooled small water droplets directly impact or directly adhere to the icing probe 2, Figure 2 the L2 area in is the area where supercooled large water droplets directly impact or directly adhere to the icing probe 2. Obviously, the supercooled large water droplets directly impact or directly adhere to the side of the side wing 22 close to the head 211, and the L2 area is hardly impacted by supercooled small water droplets due to the guiding effect of the head 211 of the icing probe 2. It should be noted that Figure 3 and Figure 4The "0" in refers to the flow direction of supercooled large and small water droplets, that is, the direction in which the supercooled large and small water droplets approach the icing probe 2; Figure 3 It means that when there is an angle of attack α between the orientation of the icing probe 2 (i.e., the first direction Z) and the flow direction 0 (at this time, the aircraft can be flying with its nose facing upward relative to the ground); Figure 4 It means that when there is a sideslip angle β between the orientation of the icing probe 2 (i.e., the first direction Z) and the flow direction 0 (at this time, the aircraft can be flying with its nose facing left relative to the ground).

[0107] The icing probe 2 provided by the present invention can accurately identify supercooled large and small water droplets, and can judge whether the composition of the flow approaching the icing probe 2 is pure supercooled small water droplets or a mixture of large and small water droplets, improving the recognition and monitoring ability of the icing probe 2 for supercooled large water droplets, thereby improving the icing warning ability of the aircraft using the icing probe 2 and enhancing safety.

[0108] It can be understood that for the icing probe 2 provided by the present invention, its specific shape, size parameters, and the specific material used for processing can all be selected and adjusted according to the actual application scenario.

[0109] In some embodiments of the present invention, the aircraft includes an airplane.

[0110] Embodiment 2

[0111] In some embodiments of the present invention, refer to Figure 5, An icing detector for an aircraft, comprising: a housing 1 having a receiving cavity 10, the housing 1 being adapted to be provided on the aircraft, specifically, it can be provided outside the aircraft so that the icing detector can accurately detect the icing condition outside the aircraft; an icing probe 2 as described in Embodiment 1, provided outside the housing 1; an angle adjustment mechanism (not labeled), one end fixedly connected to the icing probe 2 and the other end movably connected to the receiving cavity 10; wherein, the angle adjustment mechanism includes an angle of attack adjustment mechanism 31 and a sideslip angle adjustment mechanism 32, the angle of attack adjustment mechanism 31 drives the icing probe 2 to rotate in the first plane X, and the sideslip angle adjustment mechanism 32 drives the icing probe 2 to rotate in the second plane Y, the first plane X and the second plane Y are perpendicular to each other; the first direction Z of the icing probe 2 is located in the first plane X, and the second direction W of the icing probe 2 is located in the second plane Y. It should be noted that when the aircraft changes its flight angle of attack (located in the first plane X) and / or flight sideslip angle (located in the second plane Y), an angle of attack α and / or a sideslip angle β will be formed between the first sensor 23 and the second sensor 24 on the icing probe 2 and the oncoming flow direction 0. This kind of included angle will reduce the detection ability of the sensor, thereby resulting in a decrease in the detection ability of the icing probe 2. In order to ensure the accuracy of the detection result of the icing probe 2, the present invention provides the above-mentioned icing detector, especially the angle adjustment mechanism in the icing detector, and uses the above-mentioned angle adjustment mechanism to adjust the angle of attack α and the sideslip angle β of the icing probe 2, so as to ensure that the icing probe 2 can adaptively change its own angle of attack α and sideslip angle β when the angle of attack and / or sideslip angle of the aircraft changes, so that the angle of attack and / or sideslip angle of the icing probe 2 can not change with the change of the angle of attack and / or sideslip angle of the aircraft, so that the first direction Z of the icing detector can always be the same as or parallel to the oncoming flow direction 0 of supercooled water droplets in the first plane X and / or the second plane Y, thereby ensuring that the first sensor 23 and the second sensor 24 on the icing probe 2 can always maintain a posture facing the oncoming flow of supercooled water droplets, so as to ensure that the sensor can accurately identify and monitor the size of supercooled water droplets in the oncoming flow.

[0112] It should be noted that in the description of the present invention, the "angle of attack α of the icing probe 2" refers to the included angle between the first direction Z of the icing probe 2 and the oncoming flow direction 0 of supercooled water droplets in the first plane X, and the "sideslip angle β of the icing probe 2" refers to the included angle between the first direction Z of the icing probe 2 and the oncoming flow direction 0 of supercooled water droplets in the second plane Y.

[0113] The icing detector provided by the present invention adopts an angle of attack adjusting mechanism 31 and a sideslip angle adjusting mechanism 32 to respectively adjust the angle of attack direction and the sideslip angle direction of the icing probe 2 in the icing detector, so as to realize that when the flight angle of attack and / or the flight sideslip angle of the aircraft change, the angle of attack and / or the sideslip angle of the icing probe 2 can be adaptively adjusted to ensure the accuracy of the identification and monitoring of the sensors provided on the icing probe 2.

[0114] In some embodiments of the present invention, referring to Figure 5 , the angle of attack adjusting mechanism 31 includes: an angle of attack adjusting driving member 311, connected to the housing 1; a first connecting member 312, fixedly connected to the icing probe 2 and connected to the angle of attack adjusting driving member 311; wherein, the angle of attack adjusting driving member 311 drives the first connecting member 312 to rotate in the first plane X, and then the icing probe 2 rotates in the first plane X. Obviously, the above structural design and transmission relationship design have the advantages of simplicity and high efficiency, and can effectively ensure that the icing probe 2 can adaptively adjust its own angle of attack direction.

[0115] In some embodiments of the present invention, referring to Figure 5 , the angle of attack adjusting mechanism 31 further includes: a second connecting member 313, connected between the angle of attack adjusting driving member 311 and the first connecting member 312; and a third connecting member 314, movably sleeved on the outer periphery of the first connecting member 312 and rotatably connected to the second connecting member 313; wherein, the angle of attack adjusting driving member 311 is actuated by the angle of attack adjusting driving member 311 to drive the second connecting member 313 to rotate in the first plane X, and then the second connecting member 313 drives the third connecting member 314 to rotate in the first plane X. Obviously, the above structural design and transmission relationship design have the advantages of simplicity and high efficiency, and can effectively ensure that the icing probe 2 can adaptively adjust its own angle of attack direction.

[0116] In some embodiments of the present invention, referring to Figure 5, the second connecting member 313 includes two end portions 3131 that are oppositely arranged and connected. Through holes 3132 are respectively provided on the two end portions 3131. The two end portions 3131 rotate within the first plane X. The third connecting member 314 includes a sleeve structure 3141 and two protrusions 3142 provided on the outer peripheral surface of the sleeve structure 3141. The two protrusions 3142 are respectively located on both sides in the radial direction of the sleeve structure 3141. A through opening 31410 is provided along the longitudinal direction of the sleeve structure 3141. The first connecting member 312 passes through the through opening 31410. The third connecting member 314 is located between the two end portions 3131 of the second connecting member 313, and each protrusion 3142 is respectively inserted into the through hole 3132 on one end portion 3131. Obviously, the above structural design and transmission relationship design have the advantages of simplicity and high efficiency, and can effectively ensure that the icing probe 2 can adaptively adjust its own angle of attack direction.

[0117] In some embodiments of the present invention, refer to Figure 5 , the fixed portion and the movable portion of the angle of attack adjustment driving member 311 are movably connected. The fixed portion of the angle of attack adjustment driving member 311 is fixedly connected to the outside of the housing 1. A first through hole is provided on the housing 1. The movable portion of the angle of attack adjustment driving member 311 passes through the first through hole and is fixedly connected to the second connecting member 313. Or, the fixed portion of the angle of attack adjustment driving member 311 is located in the receiving cavity 10 and is fixedly connected to the housing 1. The movable portion of the angle of attack adjustment driving member 311 is fixedly connected to the second connecting member 313. Obviously, the above structural design and transmission relationship design have the advantages of simplicity and high efficiency, and can effectively ensure that the icing probe 2 can adaptively adjust its own angle of attack direction.

[0118] In some embodiments of the present invention, a motor can be used as the angle of attack adjustment driving member 311. The specific specifications and parameters of the motor can be selected and adjusted according to the actual application scenario. Of course, other forms of power sources can also be used as the angle of attack adjustment driving member 311.

[0119] In some embodiments of the present invention, refer to Figure 5, the sideslip angle adjustment mechanism 32 includes: a sideslip angle adjustment driving member received in the receiving cavity 10, with the fixed part and the movable part of the sideslip angle adjustment driving member being movably connected. The fixed part of the sideslip angle adjustment driving member is fixedly connected to the third connecting member 314, and the movable part of the sideslip angle adjustment driving member is fixedly connected to the first connecting member 312. Specifically, the movable part of the sideslip angle adjustment driving member rotates, thereby driving the first connecting member 312 to rotate around its longitudinal direction, and further driving the icing probe 2 to rotate in the second plane Y, so as to change the sideslip angle of the icing probe 2 and the orientation of the icing probe 2 in the second plane Y. Furthermore, it can be realized that the icing probe 2 can be aligned with the oncoming flow direction 0 in the second plane Y, so as to improve the detection ability of the sensor located on the icing probe 2. Obviously, the above structural design and transmission relationship design have the advantages of simplicity and high efficiency, and can effectively ensure that the icing probe 2 can adaptively adjust its own sideslip angle direction.

[0120] In some embodiments of the present invention, referring to Figure 5 , the housing 1 has an opening 11, and the opening 11 communicates the receiving cavity 10 with the outside of the housing 1; it can be understood that the shape and size parameters of the opening 11 can be selected and adjusted according to the actual application scenario. In addition, the design of the opening 11 also facilitates the assembly, disassembly and subsequent maintenance of the components of the icing detector as a whole.

[0121] In some embodiments of the present invention, the icing detector further includes a soft covering member, and the soft covering member is covered on the opening 11; a second through hole is provided on the soft covering member, and the first connecting member 312 passes through the second through hole. The angle of attack adjustment driving member 311, a part of the first connecting member 312, the second connecting member 313, the third connecting member 314 and the sideslip angle adjustment driving member are all received in the receiving cavity 10. It can be understood that the soft covering member can adapt to the rotation of the icing probe 2 and the rotation operation of the angle adjustment mechanism; compared with the hard covering member, the soft covering member does not have the problem of jamming, thus ensuring the flexible operation of the icing probe 2 and the angle adjustment mechanism, and ultimately ensuring the detection accuracy of the sensor.

[0122] Embodiment 3

[0123] The icing detector of the aircraft provided in this embodiment is basically the same as the icing detector of the aircraft in Embodiment 2, except that: referring to Figure 5 , a window structure 3121 is provided on the first connecting member 312. The window structure 3121 penetrates the first connecting member 312 along the radial direction of the first connecting member 312, and the depth direction of the window structure 3121 is the same as the first direction Z of the icing probe 2; referring to Figure 6, the icing detector further includes a pressure sensor, and the pressure sensor includes a first pressure sensor 41, a second pressure sensor 42, a third pressure sensor 43 and a fourth pressure sensor 44; the first pressure sensor 41 and the second pressure sensor 42 are respectively arranged on the inner walls of the window structure 3121 on the side close to the icing probe 2 and the side far from the icing probe 2; the third pressure sensor 43 and the fourth pressure sensor 44 are arranged on the opposite inner walls of the window structure 3121 and are adapted to the two sides of the icing probe 2 in the second direction W.Specifically, when the angle of attack and / or sideslip angle of the aircraft change, the orientation of the first connecting member 312 and the window structure 3121 located on the first connecting member 312 will also change accordingly. When the aircraft flies horizontally forward relative to the ground, the oncoming flow direction 0 is parallel to the above four pressure sensors, and the pressures received by the four pressure sensors are almost the same. There will be no large pressure difference between the relatively two-side sensors (such as the first pressure sensor 41 and the second pressure sensor 42, the third pressure sensor 43 and the fourth pressure sensor 44). When the aircraft flies upward relative to the ground, the pressure of the oncoming flow on the first pressure sensor 41 located above the window structure 3121 increases, but the pressure on the second pressure sensor 42 located below the window structure 3121 decreases. At this time, the icing detector can know the change of the angle of attack of the aircraft at this time according to the change of the pressure values detected by these two pressure sensors and the magnitude of the pressure difference between the two pressure sensors, and control the angle-of-attack adjusting mechanism 31 to adjust the angle of attack of the icing probe 2 to make a change. When the aircraft flies downward relative to the ground, the pressure of the oncoming flow on the first pressure sensor 41 located above the window structure 3121 decreases, but the pressure on the second pressure sensor 42 located below the window structure 3121 increases. At this time, the icing detector can know the change of the angle of attack of the aircraft at this time according to the change of the pressure values detected by these two pressure sensors and the magnitude of the pressure difference between the two pressure sensors, and control the angle-of-attack adjusting mechanism 31 to adjust the angle of attack of the icing probe 2 to make a change. When the aircraft flies forward to the left relative to the ground, the pressure of the oncoming flow on the third pressure sensor 43 located on one side of the window structure 3121 increases, but the pressure on the fourth pressure sensor 44 located on the other side of the window structure 3121 decreases. At this time, the icing detector can know the change of the sideslip angle of the aircraft at this time according to the change of the pressure values detected by these two pressure sensors and the magnitude of the pressure difference between the two pressure sensors, and control the sideslip-angle adjusting mechanism 32 to adjust the sideslip angle of the icing probe 2 to make a change. When the aircraft flies forward to the right relative to the ground, the pressure of the oncoming flow on the fourth pressure sensor 44 located on one side of the window structure 3121 increases, but the pressure on the third pressure sensor 43 located on the other side of the window structure 3121 decreases. At this time, the icing detector can know the change of the sideslip angle of the aircraft at this time according to the change of the pressure values detected by these two pressure sensors and the magnitude of the pressure difference between the two pressure sensors, and control the sideslip-angle adjusting mechanism 32 to adjust the sideslip angle of the icing probe 2 to make a change.

[0124] Obviously, the icing detector provided in Embodiment 3 has the ability to detect whether the flight attitude of the aircraft has changed by itself. Because the icing detector in this embodiment is provided with a window structure 3121 capable of self-sensing the change of oncoming flow air pressure and air pressure sensors respectively arranged at four different orientations within the window structure 3121. These four air pressure sensors can detect the changes in the angle of attack and / or sideslip angle of the icing detector itself after the aircraft changes its flight attitude, and then adaptively adjust the angle of attack and / or sideslip angle of the icing probe 2, so that the supercooled water droplet sensor on the icing probe 2 can always be directly facing the oncoming flow of supercooled water droplets, thereby ensuring the accuracy and continuous accuracy of the monitoring results of the supercooled water droplet sensor.

[0125] Embodiment 4

[0126] In some embodiments of the present invention, an aircraft includes a body and an icing probe provided on the body as described in Embodiment 1; Obviously, due to the adoption of the icing probe as described in Embodiment 1, the aircraft has a higher ability to identify and distinguish supercooled large and small droplets, and thus also has a more accurate early warning ability.

[0127] Embodiment 5

[0128] In some embodiments of the present invention, an aircraft includes a body and an icing detector provided on the body as described in Embodiment 2 or Embodiment 3; Obviously, due to the adoption of the icing detector as described in Embodiment 2 or Embodiment 3, the aircraft has a higher ability to identify and distinguish supercooled large and small droplets, and thus also has a more accurate early warning ability; Moreover, due to the adoption of the above-mentioned icing detector, when the angle of attack and / or sideslip angle of the aircraft changes, the angle of attack and / or sideslip angle of the icing probe in the icing detector can also change accordingly, so as to ensure that the detection results of the icing probe are more accurate and further improve the early warning ability of the aircraft.

[0129] Embodiment 6

[0130] In some embodiments of the present invention, refer to Figure 7, An icing warning method for an aircraft, the warning method using an icing detector as described in Embodiment 2 or 3 and a controller electrically connected to the icing detector; the warning method includes the following steps: the controller receives a feedback signal from the icing detector and controls an angle adjustment mechanism in the icing detector according to the feedback signal, thereby controlling the icing probe 2 to rotate within the first plane X and / or the second plane Y, and further determines whether the exterior of the aircraft is iced based on the feedback signal. Specifically, the icing warning method provided by the present invention is based on the icing probe 2 as described in Embodiment 1 or on the icing detector as described in Embodiment 2 or 3; when the flight attitude of the aircraft changes, the angle of attack and / or sideslip angle of the aircraft also change. At this time, the icing detector gives a feedback signal, and the controller controls the angle adjustment mechanism in the icing detector according to this feedback signal, thereby changing the angle of attack direction and / or sideslip angle direction of the icing probe 2. Obviously, the icing warning method provided by the present invention has the characteristics of simple and efficient logic.

[0131] Embodiment 7

[0132] The icing warning method in this embodiment is basically the same as the icing warning method described in Embodiment 6, with the only difference being: Refer to Figure 8 , the feedback signal includes an angle feedback signal sent by the angle adjustment mechanism of the icing detector; the warning method further includes: the controller receives flight condition parameters from the aircraft and outputs an angle adjustment signal to the icing detector according to the flight condition parameters, and then the controller receives the angle feedback signal; if the angle adjustment signal and the angle feedback signal are equal, it continues to determine whether the exterior of the aircraft is iced, and if the angle adjustment signal and the angle feedback signal are not equal, the controller outputs a fault signal.

[0133] In some embodiments of the present invention, refer to Figure 8 , the angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjustment mechanism 31, and the angle feedback signal includes an angle of attack feedback signal from the angle of attack adjustment mechanism 31; the warning method further includes: the controller receives the flight condition parameters and outputs an angle of attack adjustment signal to the icing detector according to the flight condition parameters and receives the angle of attack feedback signal; if the angle of attack adjustment signal and the angle of attack feedback signal are equal, it continues to determine whether the exterior of the aircraft is iced, and if the angle of attack adjustment signal and the angle of attack feedback signal are not equal, the controller outputs a fault signal.

[0134] In some embodiments of the present invention, refer to Figure 8, the angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjustment mechanism 32, and the angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjustment mechanism 32; the warning method further includes: the controller receives the flight condition parameters, and outputs a sideslip angle adjustment signal to the icing detector according to the flight condition parameters and receives the sideslip angle feedback signal; if the sideslip angle adjustment signal is equal to the sideslip angle feedback signal, it continues to determine whether the exterior of the aircraft is iced; if the sideslip angle adjustment signal is not equal to the sideslip angle feedback signal, the controller outputs a fault signal.

[0135] In some embodiments of the present invention, refer to Figure 8 , the feedback signal further includes a first icing signal from the first sensor 23 and a second icing signal from the second sensor 24; the warning method further includes: the controller receives the first icing signal and the second icing signal; when determining whether the exterior of the aircraft is iced, if the first icing signal indicates icing, the controller outputs a first icing warning, and if the second icing signal indicates icing, the controller outputs a second icing warning. It should be noted that the first icing signal refers to the existence of supercooled small water droplets outside the aircraft, the second icing signal refers to the existence of supercooled large water droplets outside the aircraft, and the fault warning refers to a fault in the icing detector, which may be a malfunction in a certain part of the angle adjustment mechanism.

[0136] In some embodiments of the present invention, refer to Figure 8, in the said warning method: First, the controller samples from the flight condition parameters of the aircraft. Specifically, it collects the initial flight angle A_0 and the real-time flight angle A_i of the aircraft. At the same time, it sets the time count i to 0 and the adjustment count j to 0. The controller calculates the collected initial flight angle A_0 (sampling time is t_0) and the real-time flight angle A_i (sampling time is t_i = t_0 + i*Δt, where Δt represents the sampling interval); if the absolute value of the difference between these two angles is greater than the preset angle difference K, then increase the adjustment count j by one. At this time, if the adjustment count j reaches the preset adjustment times Z, then in the angle adjustment signal B, make the change value of the angle of the icing probe 2 be the opposite number of the real-time flight angle A_i of the aircraft (i.e., -A_i), and then the controller outputs this angle adjustment signal B to the angle adjustment mechanism in the icing detector; if the absolute value of the difference between the initial flight angle A_0 and the real-time flight angle A_i of the aircraft (i.e., |A_i - A_0|) is less than or equal to the preset angle difference K, then increase the time count i by one (i.e., i = i + 1) and make the controller re-sample from the flight condition parameters of the aircraft in real time and perform the next round of operations; if the adjustment count j does not reach the preset adjustment times Z, then increase the time count i by one (i.e., i = i + 1) and make the controller re-sample from the flight condition parameters of the aircraft in real time and perform the next round of operations to maintain continuous sampling. And, after the controller outputs the angle adjustment signal B to the angle adjustment mechanism, it is also necessary to obtain the angle feedback signal C from the angle adjustment mechanism, and also obtain the first icing signal D1 and the second icing signal D2 from the first sensor 23 and the second sensor 24 respectively; if the controller determines that the angle adjustment signal B it issues is equal to the received angle feedback signal C, then it will further judge the icing situation outside the aircraft according to D1 and D2. Otherwise, if the angle adjustment signal B and the angle feedback signal C are not equal, it will output a fault warning, indicating that there may be a problem with the angle adjustment mechanism of the icing detector at this time; if the first icing signal D1 is icing, the controller outputs the first icing warning. If the second icing signal D2 is icing, the controller outputs the second icing warning; among them, the first icing warning indicates that the first sensor 23 has detected the existence of supercooled small water droplets, and the second icing warning indicates that the second sensor 24 has detected the existence of supercooled large water droplets.

[0137] More specifically, in some embodiments of the present invention, refer to Figure 8, first, the controller samples the angle-of-attack parameter of the aircraft from the flight condition parameters of the aircraft. Specifically, it collects the initial flight angle of attack A1_0 of the aircraft (the sampling time is t_0) and the real-time flight angle of attack A1_i1 (the sampling time is t_i1 = t_0 + i1*Δt). At the same time, it sets the angle-of-attack time count i1 to 0 and the angle-of-attack adjustment count j1 to 0. The controller calculates the collected initial flight angle of attack A1_0 and the real-time flight angle of attack A1_i1. If the absolute value of the difference between the two angles (i.e., |A1_i1 - A1_0|) is greater than the preset angle-of-attack difference K1, then the angle-of-attack adjustment count j1 is incremented by one. At this time, if the angle-of-attack adjustment count j1 reaches the preset angle-of-attack adjustment times Z1, then in the angle-of-attack adjustment signal B1, the change value of the angle of attack of the icing probe 2 is set to the opposite number of the real-time flight angle of attack A1_i1 of the aircraft (i.e., -A1_i1). Then the controller outputs this angle-of-attack adjustment signal B1 to the angle-of-attack adjustment mechanism 31 in the icing detector. If the absolute value of the difference between the initial flight angle of attack A1_0 and the real-time flight angle of attack A1_i1 of the aircraft (i.e., |A1_i1 - A1_0|) is less than or equal to the preset angle-of-attack difference K1, then the angle-of-attack time count i1 is incremented by one (i.e., i1 = i1 + 1), and the controller is commanded to resample from the flight condition parameters of the aircraft in real time and perform the next round of operations. If the angle-of-attack adjustment count j1 does not reach the preset angle-of-attack adjustment times Z1, then the angle-of-attack time count i1 is incremented by one (i.e., i1 = i1 + 1), and the controller is commanded to resample from the flight condition parameters of the aircraft in real time and perform the next round of operations. And, after the controller outputs the angle-of-attack adjustment signal B1 to the angle-of-attack adjustment mechanism 31, it is also necessary to obtain the angle-of-attack feedback signal C1 from the angle-of-attack adjustment mechanism 31, and also obtain the first icing signal D1 and the second icing signal D2 from the first sensor 23 and the second sensor 24 respectively. If the controller determines that the angle-of-attack adjustment signal B1 it issues is equal to the received angle-of-attack feedback signal C1, then it will further judge the icing situation outside the aircraft according to D1 and D2. Otherwise, if the angle-of-attack adjustment signal B1 and the angle-of-attack feedback signal C1 are not equal, a fault alarm will be output. It should be noted that the controller controls the angle of attack of the icing probe 2 to decrease by A1_i1, so that the change value of the angle of attack of the icing probe 2 (-A1_i1) can cancel out the flight angle of attack (A1_i1) of the aircraft, thereby ensuring that the sensor on the icing probe 2 can be directly facing the oncoming supercooled water droplets and ensuring the detection accuracy of the sensor. Finally, after the angle of attack of the icing probe 2 is changed at this time, the real-time flight angle of attack A1_i1 of the aircraft at this moment needs to be used as the initial flight angle of attack A1_0 to be used in the calculation logic of the controller at the next moment, so as to ensure that the icing probe 2 makes real-time adjustments according to the changes in the flight conditions of the aircraft at all times, so as to ensure that the sensor on the icing probe 2 is always directly facing the supercooled water droplets, thereby ensuring the real-time accuracy of the detection results of the sensor.In the above logic process, if the absolute value of the difference between the above initial flight angle of attack A1_0 and the real-time flight angle of attack A1_i1 is less than or equal to the preset angle of attack difference K1, the angle of attack time count i1 is incremented by one, that is, the controller is made to collect the flight condition parameters of the aircraft at the next moment and then re-execute the above process; in addition, if the angle of attack adjustment count j1 has not reached the preset number of angle of attack adjustment times Z1, the angle of attack time count i1 is incremented by one, that is, the controller is made to collect the flight condition parameters of the aircraft at the next moment and then re-execute the above process. It should be noted that the core idea of the above method process is to make the controller receive the flight condition parameters from the aircraft. If there is a large change in the real-time flight condition parameters of the aircraft compared with its initial flight condition parameters, the angle of attack of the icing probe 2 is rotated by a negative value accordingly, so as to achieve the rotational cancellation between the angle of attack of the icing probe 2 and the flight angle of attack of the aircraft, ensuring that the icing probe 2 can always face the oncoming supercooled water droplets, and ultimately ensuring the accuracy of the detection results of the sensors on the icing probe 2.

[0138] More specifically, in some embodiments of the present invention, referring to Figure 8, first, the controller samples the sideslip angle parameter of the aircraft from the flight condition parameters of the aircraft. Specifically, it collects the initial flight sideslip angle A2_0 of the aircraft (the sampling time is t_0) and the real-time flight sideslip angle A2_i2 (the sampling time is t_i2 = t_0 + i2 * Δt). At the same time, it sets the sideslip angle time count i2 to 0 and the sideslip angle adjustment count j2 to 0. The controller calculates the collected initial flight sideslip angle A2_0 and the real-time flight sideslip angle A2_i2. If the absolute value of the difference between these two angles (i.e., |A2_i2 - A2_0|) is greater than the preset sideslip angle difference K2, then the sideslip angle adjustment count j2 is incremented by one. At this time, if the sideslip angle adjustment count j2 reaches the preset sideslip angle adjustment times Z2, then in the sideslip angle adjustment signal B2, the change value of the sideslip angle of the icing probe 2 is set to the opposite number of the real-time flight sideslip angle A2_i2 of the aircraft (i.e., -A2_i2). Then the controller outputs this sideslip angle adjustment signal B2 to the sideslip angle adjustment mechanism 32 in the icing detector. If the absolute value of the difference between the initial flight sideslip angle A2_0 and the real-time flight sideslip angle A2_i2 of the aircraft (i.e., |A2_i2 - A2_0|) is less than or equal to the preset sideslip angle difference K2, then the sideslip angle time count i2 is incremented by one (i.e., i2 = i2 + 1) and the controller re-samples from the flight condition parameters of the aircraft in real time and performs the next round of operations. If the sideslip angle adjustment count j2 does not reach the preset sideslip angle adjustment times Z2, then the sideslip angle time count i2 is incremented by one (i.e., i2 = i2 + 1) and the controller re-samples from the flight condition parameters of the aircraft in real time and performs the next round of operations. And, after the controller outputs the sideslip angle adjustment signal B2 to the sideslip angle adjustment mechanism 32, it is also necessary to obtain the sideslip angle feedback signal C2 from the sideslip angle adjustment mechanism 32, and also obtain the first icing signal D1 and the second icing signal D2 from the first sensor 23 and the second sensor 24 respectively. If the controller determines that the sideslip angle adjustment signal B2 it issues is equal to the received sideslip angle feedback signal C2, then it will further determine the icing situation outside the aircraft according to D2 and D2. Otherwise, if the sideslip angle adjustment signal B2 and the sideslip angle feedback signal C2 are not equal, a fault alarm will be output.It should be noted that the controller controls the sideslip angle of the icing probe 2 to decrease by A2_i2, so that the change value (-A2_i2) of the sideslip angle of the icing probe 2 can cancel out the flight sideslip angle (A2_i2) of the aircraft, thereby ensuring that the sensor on the icing probe 2 is directly facing the oncoming supercooled water droplets and ensuring the detection accuracy of the sensor; finally, after changing the sideslip angle of the icing probe 2 this time, the real-time flight sideslip angle A2_i2 of the aircraft at this moment needs to be used as the initial flight sideslip angle A2_0 to be used in the calculation logic of the controller at the next moment, so as to ensure that the icing probe 2 makes real-time adjustments according to the changing flight conditions of the aircraft at all times, so as to ensure that the sensor on the icing probe 2 is always directly facing the supercooled water droplets, thereby ensuring the real-time accuracy of the detection results of the sensor. In the above logical process, if the absolute value of the difference between the above initial flight sideslip angle A2_0 and the real-time flight angle of attack A2_i2 is less than or equal to the preset sideslip angle difference K2, the sideslip angle time count i2 is increased by one bit, that is, the controller is made to collect the flight condition parameters of the aircraft at the next moment and then re-execute the above process; in addition, if the sideslip angle adjustment count j2 does not reach the preset sideslip angle adjustment times Z2, the sideslip angle time count i2 is increased by one bit, that is, the controller is made to collect the flight condition parameters of the aircraft at the next moment and then re-execute the above process. It should be noted that the core idea of the above method process is to make the controller receive the flight condition parameters from the aircraft. If the real-time flight condition parameters of the aircraft change too much from its initial flight condition parameters, the sideslip angle of the icing probe 2 is correspondingly rotated by a negative value, so as to realize the rotational cancellation between the sideslip angle of the icing probe 2 and the flight sideslip angle of the aircraft, so as to ensure that the icing probe 2 can always be directly facing the oncoming supercooled water droplets, and finally ensure the accuracy of the detection results of the sensor on the icing probe 2.

[0139] Embodiment 8

[0140] The icing warning method in this embodiment is basically the same as the icing warning method described in Embodiment 7, except that: Refer to Figure 5, the angle of attack adjusting mechanism 31 includes: an angle of attack adjusting driving member 311 connected to the housing 1; a first connecting member 312 fixedly connected to the icing probe 2 and connected to the angle of attack adjusting driving member 311; the angle of attack adjusting driving member 311 drives the first connecting member 312 to rotate in the first plane X, and then the icing probe 2 rotates in the first plane X; a window structure 3121 is provided on the first connecting member 312, the window structure 3121 penetrates the first connecting member 312 along the radial direction of the first connecting member 312, and the depth direction of the window structure 3121 is the same as the first direction Z of the icing probe 2; the icing detector further includes a pressure sensor, and the pressure sensor includes a first pressure sensor 41, a second pressure sensor 42, a third pressure sensor 43 and a fourth pressure sensor 44; the first pressure sensor 41 and the second pressure sensor 42 are respectively arranged on one inner wall of the window structure 3121 close to the icing probe 2 and one inner wall far from the icing probe 2; the third pressure sensor 43 and the fourth pressure sensor 44 are arranged on opposite inner walls of the window structure 3121 and are adapted to both sides in the second direction W of the icing probe 2; also refer to Figure 9 , in the warning method, the feedback signal includes a pressure signal from the pressure sensor, the controller receives the pressure signal, and compares the absolute value of the first pressure difference between the pressure signal of the first pressure sensor 41 and the pressure signal of the second pressure sensor 42 with a first preset pressure difference, and also compares the absolute value of the second pressure difference between the pressure signal of the third pressure sensor 43 and the pressure signal of the fourth pressure sensor 44 with a second preset pressure difference; the controller outputs the angle adjustment signal according to the comparison result, or the controller judges the icing condition outside the aircraft according to the comparison result and the received first icing signal and second icing signal.

[0141] In some embodiments of the present invention, refer to Figure 9, in the warning method described above: the angle feedback signal includes an angle of attack feedback signal from the angle of attack adjusting mechanism 31, and the angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjusting mechanism 31; the angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjusting mechanism 32, and the angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjusting mechanism 32; if the absolute value of the first pressure difference is greater than the first preset pressure difference, the controller sends the angle of attack adjustment signal to the angle of attack adjusting mechanism 31, and then the angle of attack adjusting mechanism 31 adjusts the angle of attack of the icing probe 2; if the absolute value of the second pressure difference is greater than the second preset pressure difference, the controller sends the sideslip angle adjustment signal to the sideslip angle adjusting mechanism 32, and then the sideslip angle adjusting mechanism 32 adjusts the sideslip angle of the icing probe 2; if the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, the controller determines the icing condition outside the aircraft according to the first icing signal and the second icing signal.

[0142] In some embodiments of the present invention, refer to Figure 9 , in the warning method described above: if the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, and the first icing signal is icing, the controller outputs a first icing warning, indicating that the aircraft has encountered supercooled small water droplets outside at this time; and / or, if the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, and the second icing signal is icing, the controller outputs a second icing warning, indicating that the aircraft has encountered supercooled large water droplets outside at this time.

[0143] In some embodiments of the present invention, refer to Figure 6 and Figure 9, in the described warning method, the controller receives the pressure signal P1 from the first pressure sensor 41 and the pressure signal P2 from the second pressure sensor 42, and then calculates the difference between P1 and P2; if (P1 - P2) is greater than the positive first pressure difference (M1), the angle of attack adjustment signal B1 includes the information of "increasing the angle of attack α"; if (P1 - P2) is less than the negative first pressure difference (-M1), the angle of attack adjustment signal B2 includes the information of "decreasing the angle of attack α"; if the absolute value of the difference between P1 and P2 is less than or equal to the first pressure difference (i.e., |P1 - P2| ≤ M1), then the icing condition outside the aircraft is judged according to the first icing signal D1 from the first sensor 23 and the second icing signal D2 from the second sensor 24; if the first icing signal D1 indicates icing, the controller outputs a first icing warning, indicating that the outside of the aircraft has encountered supercooled small water droplets at this time; if the second icing signal D2 indicates icing, the controller outputs a second icing warning, indicating that the outside of the aircraft has encountered supercooled large water droplets at this time.

[0144] In some embodiments of the present invention, refer to Figure 6 and Figure 9 , in the described warning method, the controller receives the pressure signal P3 from the third pressure sensor 43 and the pressure signal P4 from the fourth pressure sensor 44, and then calculates the difference between P3 and P4; if (P3 - P4) is greater than the positive second pressure difference (i.e., (P3 - P4) > M2), the sideslip angle adjustment signal B2 includes the information of "increasing the sideslip angle β"; if (P3 - P4) is less than the negative first pressure difference (i.e., (P3 - P4) < -M1), the sideslip angle adjustment signal B2 includes the information of "decreasing the sideslip angle β"; if the absolute value of the difference between P3 and P4 is less than or equal to the second pressure difference (i.e., |P3 - P4| ≤ M2), then the icing condition outside the aircraft is judged according to the first icing signal D1 from the first sensor 23 and the second icing signal D2 from the second sensor 24; if the first icing signal D1 indicates icing, the controller outputs a first icing warning, indicating that the outside of the aircraft has encountered supercooled small water droplets at this time; if the second icing signal D2 indicates icing, the controller outputs a second icing warning, indicating that the outside of the aircraft has encountered supercooled large water droplets at this time.

[0145] It should be noted that the icing warning method in Embodiment 7 of the specification of the present invention can directly obtain the flight condition parameters of the aircraft from the central control system of the aircraft, so that the icing detector can adjust the attitude of the icing probe 2 according to the flight condition parameters of the aircraft to ensure the accuracy of monitoring; while the icing warning method in Embodiment 8 of the specification of the present invention can directly adjust the attitude of the icing probe 2 through the window structure 3121 provided in the icing detector and four pressure sensors provided on the window structure 3121. It can be understood that in some embodiments of the present invention, these two technical features can exist simultaneously to adapt to specific flight scenarios and improve the icing warning ability and safety of the aircraft.

[0146] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims. In addition, specific examples are used in the specification to elaborate on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention, and the content of this specification should not be construed as a limitation to the present invention.

Claims

1. An ice detector for an aircraft, characterized in that, The ice detector includes: A housing (1) having a receiving cavity (10), and the housing (1) is configured to be disposed on the aircraft; An ice probe (2) disposed outside the housing (1); An angle adjustment mechanism, one end of which is fixedly connected to the ice probe (2), and the other end is movably connected in the receiving cavity (10); Wherein, the angle adjustment mechanism includes an angle of attack adjustment mechanism (31) and a sideslip angle adjustment mechanism (32). The angle of attack adjustment mechanism (31) drives the ice probe (2) to rotate in a first plane (X), and the sideslip angle adjustment mechanism (32) drives the ice probe (2) to rotate in a second plane (Y). The first plane (X) and the second plane (Y) are perpendicular to each other; a first direction (Z) of the ice probe (2) is located in the first plane (X), and a second direction (W) of the ice probe (2) is located in the second plane (Y); The ice probe (2) has a first direction (Z) and a second direction (W) that are perpendicular to each other, and includes: A main body (21) in a warhead shape, and the main body (21) includes a head (211) and a tail (212) connected in sequence along the first direction (Z); Two side wings (22) respectively disposed on both sides of the main body (21) in the second direction (W), and both are connected to the tail (212); A first sensor (23) disposed on a side of the head (211) of the main body (21) facing away from the tail (212); A second sensor (24) disposed on a side of the side wing (22) facing the head (211).

2. The icing detector according to claim 1, wherein, The angle of attack adjustment mechanism (31) includes: An angle of attack adjustment driving member (311) connected to the housing (1); A first connecting member (312) fixedly connected to the ice probe (2) and connected to the angle of attack adjustment driving member (311); Wherein, the angle of attack adjustment driving member (311) drives the first connecting member (312) to rotate in the first plane (X), and further the ice probe (2) rotates in the first plane (X).

3. The icing detector according to claim 2, characterized in that, The angle of attack adjustment mechanism (31) further includes: A second connecting member (313) connected between the angle of attack adjustment driving member (311) and the first connecting member (312); A third connecting member (314) movably sleeved on the outer periphery of the first connecting member (312) and rotatably connected to the second connecting member (313); Wherein, the angle of attack adjustment driving member (311) is actuated by the angle of attack adjustment driving member (311) to drive the second connecting member (313) to rotate in the first plane (X), and further the second connecting member (313) drives the third connecting member (314) to rotate in the first plane (X).

4. The icing detector according to claim 3, wherein, The second connecting member (313) includes two opposite and connected ends (3131), and a through hole (3132) is respectively provided on each of the two ends (3131), and the two ends (3131) rotate in the first plane (X); The third connecting member (314) includes a sleeve structure (3141) and two protrusions (3142) provided on the outer peripheral surface of the sleeve structure (3141). The two protrusions (3142) are respectively located on both sides in the radial direction of the sleeve structure (3141). The sleeve structure (3141) is provided with a through hole (31410) along its longitudinal direction, and the first connecting member (312) passes through the through hole (31410). The third connecting member (314) is located between the two ends (3131) of the second connecting member (313), and each protrusion (3142) is respectively inserted into the through hole (3132) on one end (3131).

5. The icing detector according to claim 4, wherein The fixed part and the movable part of the angle of attack adjusting driving member (311) are movably connected. The fixed part of the angle of attack adjusting driving member (311) is fixedly connected to the outside of the housing (1). A first through hole is formed in the housing (1). The movable part of the angle of attack adjusting driving member (311) passes through the first through hole and is fixedly connected to the second connecting member (313). Alternatively, the fixed part of the angle of attack adjusting driving member (311) is located in the receiving cavity (10) and is fixedly connected to the housing (1), and the movable part of the angle of attack adjusting driving member (311) is fixedly connected to the second connecting member (313).

6. The icing detector according to claim 5, characterized in that, The sideslip angle adjusting mechanism (32) includes: A sideslip angle adjusting driving member, which is received in the receiving cavity (10). The fixed part and the movable part of the sideslip angle adjusting driving member are movably connected. The fixed part of the sideslip angle adjusting driving member is fixedly connected to the third connecting member (314), and the movable part of the sideslip angle adjusting driving member is fixedly connected to the first connecting member (312).

7. The icing detector according to claim 6, characterized in that, The housing (1) has an opening (11), and the opening (11) communicates the receiving cavity (10) with the outside of the housing (1). The detector further includes a soft covering member, and the soft covering member is covered on the opening (11). A second through hole is formed in the soft covering member. The first connecting member (312) passes through the second through hole. The angle of attack adjusting driving member (311), a part of the first connecting member (312), the second connecting member (313), the third connecting member (314), and the sideslip angle adjusting driving member are all received in the receiving cavity (10).

8. The icing detector according to claim 2, characterized in that, A window structure (3121) is provided on the first connecting member (312). The window structure (3121) penetrates the first connecting member (312) along the radial direction of the first connecting member (312), and the depth direction of the window structure (3121) is the same as the first direction (Z) of the icing probe (2). The icing detector further includes a pressure sensor. The pressure sensor includes a first pressure sensor (41), a second pressure sensor (42), a third pressure sensor (43), and a fourth pressure sensor (44). The first pressure sensor (41) and the second pressure sensor (42) are respectively arranged on the inner wall of the window structure (3121) close to the icing probe (2) and on the inner wall far from the icing probe (2); The third pressure sensor (43) and the fourth pressure sensor (44) are arranged on the opposite inner walls of the window structure (3121) and are adapted to the two sides in the second direction (W) of the icing probe (2).

9. An aircraft, characterized in that, The aircraft includes a body and an icing detector provided on the body and as described in any one of claims 1-8.

10. An icing warning method for an aircraft, characterized in that, The warning method adopts the icing detector as described in claim 1 and a controller electrically connected to the icing detector; The warning method includes the following steps: The controller receives a feedback signal from the icing detector, controls an angle adjustment mechanism in the icing detector according to the feedback signal, and thus controls the rotation of the icing probe (2) in the first plane (X) and / or the second plane (Y), and judges whether the outside of the aircraft is iced according to the feedback signal.

11. The icing warning method according to claim 10, characterized in that, The feedback signal includes an angle feedback signal sent by the angle adjustment mechanism of the icing detector; The warning method further includes: The controller receives flight condition parameters from the aircraft and outputs an angle adjustment signal to the icing detector according to the flight condition parameters, and then the controller receives the angle feedback signal; If the angle adjustment signal is equal to the angle feedback signal, continue to judge whether the outside of the aircraft is iced. If the angle adjustment signal is not equal to the angle feedback signal, the controller outputs a fault signal.

12. The icing warning method according to claim 11, wherein The angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjustment mechanism (31), and the angle feedback signal includes an angle of attack feedback signal from the angle of attack adjustment mechanism (31); The warning method further includes: The controller outputs the angle of attack adjustment signal to the angle of attack adjustment mechanism (31) and receives the angle of attack feedback signal; If the angle of attack adjustment signal is equal to the angle of attack feedback signal, continue to judge whether the outside of the aircraft is iced. If the angle of attack adjustment signal is not equal to the angle of attack feedback signal, the controller outputs a fault signal.

13. The icing warning method according to claim 11, characterized in that, The angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjustment mechanism (32), and the angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjustment mechanism (32); The warning method further includes: The controller outputs the sideslip angle adjustment signal to the sideslip angle adjustment mechanism (32) and receives the sideslip angle feedback signal; If the sideslip angle adjustment signal is equal to the sideslip angle feedback signal, continue to judge whether the outside of the aircraft is iced. If the sideslip angle adjustment signal is not equal to the sideslip angle feedback signal, the controller outputs a fault warning.

14. The icing warning method according to claim 11, wherein The feedback signal further includes a first icing signal from the first sensor (23) and a second icing signal from the second sensor (24); The warning method further includes: The controller receives the first icing signal and the second icing signal; When determining whether the exterior of the aircraft is icing, if the first icing signal indicates icing, the controller outputs a first icing warning, and if the second icing signal indicates icing, the controller outputs a second icing warning.

15. The icing warning method according to claim 14, characterized in that, The angle of attack adjustment mechanism (31) includes: an angle of attack adjustment driving member (311) connected to the housing (1); a first connecting member (312) fixedly connected to the icing probe (2) and connected to the angle of attack adjustment driving member (311); the angle of attack adjustment driving member (311) drives the first connecting member (312) to rotate within the first plane (X), and thus the icing probe (2) rotates within the first plane (X); a window structure (3121) is provided on the first connecting member (312), the window structure (3121) penetrates the first connecting member (312) along the radial direction of the first connecting member (312), and the depth direction of the window structure (3121) is the same as the first direction (Z) of the icing probe (2); the icing detector further includes pressure sensors, and the pressure sensors include a first pressure sensor (41), a second pressure sensor (42), a third pressure sensor (43), and a fourth pressure sensor (44); the first pressure sensor (41) and the second pressure sensor (42) are respectively arranged on one inner wall of the window structure (3121) close to the icing probe (2) and one inner wall away from the icing probe (2); the third pressure sensor (43) and the fourth pressure sensor (44) are arranged on opposite inner walls of the window structure (3121) and are adapted to both sides in the second direction (W) of the icing probe (2); In the warning method, the feedback signal includes a pressure signal from the pressure sensor, the controller receives the pressure signal, and compares the absolute value of the first pressure difference between the pressure signal of the first pressure sensor (41) and the pressure signal of the second pressure sensor (42) with a first preset pressure difference, and also compares the absolute value of the second pressure difference between the pressure signal of the third pressure sensor (43) and the pressure signal of the fourth pressure sensor (44) with a second preset pressure difference; The controller outputs the angle adjustment signal according to the comparison result, or the controller determines the icing condition of the exterior of the aircraft according to the comparison result and the first icing signal and the second icing signal received.

16. The warning method according to claim 15, wherein In the warning method: The angle feedback signal includes an angle of attack feedback signal from the angle of attack adjustment mechanism (31), and the angle adjustment signal includes an angle of attack adjustment signal received by the angle of attack adjustment mechanism (31); The angle feedback signal includes a sideslip angle feedback signal from the sideslip angle adjustment mechanism (32), and the angle adjustment signal includes a sideslip angle adjustment signal received by the sideslip angle adjustment mechanism (32); If the absolute value of the first pressure difference is greater than the first preset pressure difference, the controller sends the angle of attack adjustment signal to the angle of attack adjustment mechanism (31), and then the angle of attack adjustment mechanism (31) adjusts the angle of attack of the icing probe (2); If the absolute value of the second pressure difference is greater than the second preset pressure difference, the controller sends the sideslip angle adjustment signal to the sideslip angle adjustment mechanism (32), and then the sideslip angle adjustment mechanism (32) adjusts the sideslip angle of the icing probe (2); If the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, the controller determines the icing condition outside the aircraft according to the first icing signal and the second icing signal.

17. The warning method according to claim 16, wherein In the warning method described above: If the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, and the first icing signal indicates icing, the controller outputs a first icing warning; And / or, if the absolute value of the first pressure difference is less than the first preset pressure difference and the absolute value of the second pressure difference is less than the second preset pressure difference, and the second icing signal indicates icing, the controller outputs a second icing warning.

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