Novel-configuration airplane pitot tube

Abstract

According to the novel aircraft pitot tube provided by the invention, the installation mode between the pitot tube and the aircraft body is improved from the traditional equipotential electrical connection installation to the electrical insulation installation, and the lightning protection and static electricity removal device is additionally arranged between the pitot tube and the aircraft body, so that the pitot tube has the functions of lightning protection and static electricity discharge; in addition, the pitot tube is connected with the fuselage through the lightning protection and static electricity removal device, the negative influence on the pitot tube heating system caused by reduction of insulation performance of the pitot tube heating resistor can be reduced to a great extent, and therefore the reliability of the airplane pitot tube is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aviation technology, and particularly relates to a new configuration aircraft pitot tube. BACKGROUND

[0002] The pitot tube is a key component for measuring airspeed of an aircraft, which can measure the dynamic pressure and static pressure of airflow in flight, and then calculate the flight speed and flight height. Due to low temperature in high altitude, the sampling port of the pitot tube is prone to icing, and if the sampling port is blocked, pressure collection and airspeed calculation cannot be performed. In order to prevent the pitot tube from icing and blocking, the pitot tube is provided with a heating component. The heating component of the pitot tube mainly comprises a sheathed heating wire welded at the sampling port of the pitot tube and a series of ceramic temperature controller assemblies.

[0003] In actual operation, most of the pitot tube failures of civil aviation aircraft are caused by the heating component, and the insulation performance degradation of the heating wire and the pitot tube shell is the main failure cause.

[0004] Therefore, the existing design scheme of the aircraft pitot tube has the problem of low reliability, which leads to the problem that the aircraft pitot tube is prone to failure. SUMMARY

[0005] The present application aims to at least solve the technical problems in the prior art. To this end, the present application provides a new configuration aircraft pitot tube in a first aspect, which comprises: The heating resistance wire wrapped with the insulating material, the pitot tube shell, the air passage pipeline, the insulating assembly and the lightning protection and static electricity elimination device, the lightning protection and static electricity elimination device comprises a gas discharge tube and a static electricity elimination resistor, the resistance value of the static electricity elimination resistor is greater than the resistance value of the heating resistance wire, and the heating resistance wire wrapped with the insulating material is embedded between the pitot tube shell and the air passage pipeline; the insulating assembly and the lightning protection and static electricity elimination device are arranged between the new configuration aircraft pitot tube and the metal structure of the fuselage; The insulating assembly is used for electrically insulating the new configuration aircraft pitot tube from the metal structure of the fuselage when the new configuration aircraft pitot tube is installed; The lightning protection and static electricity elimination device is used for lightning protection and static electricity elimination.

[0006] In a possible implementation, the insulating assembly comprises an insulating pad arranged between the new configuration aircraft pitot tube and the metal structure of the fuselage.

[0007] In a possible implementation, the lightning protection and static electricity elimination device comprises a gas discharge tube and a static electricity elimination resistor, wherein one end of the gas discharge tube is connected with one end of the insulating resistor and one end of the static electricity elimination resistor, and the other end of the gas discharge tube and the other end of the static electricity elimination resistor are connected with one end of the heating resistance wire, and wherein: The gas discharge tube is used for discharging lightning transient overcurrent and limiting overvoltage; Eliminate static resistance, used to eliminate static and discharge tube conduction after closing the residual low voltage.

[0008] In a possible implementation, the lightning protection and static elimination device comprises two parallel gas discharge tubes, a bidirectional transient voltage suppression diode, a first resistor and a second resistor, wherein the first resistor is a cement resistor or a wafer resistor, the first resistor forms a first-stage protection circuit, the bidirectional transient voltage suppression diode and the second resistor form a second-stage protection circuit, the second resistor is a wafer resistor, and the two parallel gas discharge tubes form a third-stage protection circuit.

[0009] In a possible implementation, the first resistor has a resistance of 1KΩ-1MΩ.

[0010] In a possible implementation, the bidirectional transient voltage suppression diode has a breakdown voltage greater than 170V, a clamping voltage of 275V and a peak pulse current of 2.2A, and the second resistor has a resistance of 30Ω-200Ω.

[0011] In a possible implementation, the two parallel gas discharge tubes comprise a first gas discharge tube and a second gas discharge tube, the first gas discharge tube has a pulse breakdown voltage greater than 170V, and the second gas discharge tube has a pulse breakdown voltage greater than 250V.

[0012] In a possible implementation, the new configuration of the aircraft pitot tube further comprises an insulating material base.

[0013] In a possible implementation, the new configuration of the aircraft pitot tube further comprises an insulating material base.

[0014] In a possible implementation, the new configuration of the aircraft pitot tube further comprises an insulating material base.

[0015] The technical scheme provided by the embodiments of the present application can at least achieve the following beneficial effects: The novel aircraft pitot tube configuration provided in this application includes a heating resistance wire wrapped with insulating material, a pitot tube housing, a venting pipe, an insulating component, and a lightning protection and static electricity elimination device. The lightning protection and static electricity elimination device includes a gas discharge tube and a static electricity elimination resistor. The resistance of the static electricity elimination resistor is greater than the resistance of the heating resistance wire. The heating resistance wire wrapped with insulating material is embedded between the pitot tube housing and the venting pipe. The insulating component and the lightning protection and static electricity elimination device are disposed between the novel aircraft pitot tube and the fuselage metal structure. The insulating component ensures electrical insulation between the novel aircraft pitot tube and the fuselage metal structure during installation. The lightning protection and static electricity elimination device protects against lightning strikes and discharges static electricity. This solution improves the installation method between the pitot tube and the aircraft fuselage by changing the traditional equipotential electrical connection to an electrically insulated installation, and adds a lightning protection and static electricity discharge device between them. This enables the pitot tube to have the functions of lightning protection and static electricity discharge. In addition, by connecting the pitot tube to the fuselage with a lightning protection and static electricity discharge device, the negative impact of the decrease in the insulation performance of the pitot tube heating resistance on the pitot tube heating system can be greatly reduced, thereby improving the reliability of the aircraft pitot tube. Attached Figure Description

[0016] Figure 1 This application provides a schematic diagram of the internal structure of a conventional Pitot tube heating resistor. Figure 2 An equivalent schematic diagram of a conventional Pitot tube heating circuit provided in this application embodiment; Figure 3 A system schematic diagram of a novel configuration aircraft pitot tube provided in this application embodiment; Figure 4 An equivalent schematic diagram of a novel configuration of a pitot tube for an aircraft, provided in an embodiment of this application; Figure 5 A schematic diagram of another lightning protection and static electricity elimination device provided in the embodiments of this application; Figure 6 This application provides a schematic diagram of an existing pitot tube mounting configuration for an embodiment of the present application. Figure 7 This is a schematic diagram of the installation configuration of a novel aircraft pitot tube provided in an embodiment of this application. Detailed Implementation

[0017] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0018] likeFigure 1 As shown, Figure 1 This application provides a schematic diagram of the internal structure of a conventional Pitot tube heating resistor, as shown in the embodiments. Figure 1 As shown, after prolonged high-temperature operation, the insulation material around the resistance wire ages, causing a sharp decline in insulation performance. When the insulation material at a certain point c on the heating resistor deteriorates to a very low or even zero insulation value, the heating current passes directly to ground through the pitot tube housing via point c. Since the resistance of segment ac is less than the resistance of the entire segment ab, the current flowing through ac will increase. When the current exceeds its rated current for a long time, the heating resistance wire in segment ac will melt and break due to high temperature, resulting in a heating failure.

[0019] like Figure 2 As shown, the above Figure 1 After simplification to the equivalent schematic diagram, Figure 2 This application provides an equivalent schematic diagram of a conventional Pitot tube heating circuit. Rm represents the insulation resistance between the Pitot tube heating resistor and the casing. Normally, Rm is in the MΩ or GΩ range. When the insulation performance of point c on the heating resistor R0 to the casing (ground) drops to a very low level or even short-circuits to ground (i.e., insulation resistance Rm = 0), the heating current will flow directly into the casing (ground) from point c. Because the resistance of segment ac is less than or equal to the resistance of segment ab, the heating current will increase, and the closer point c is to point a, the greater the current. When the current in segment ac exceeds the rated current value of the heating resistor wire, the resistor wire in segment ac will burn out due to prolonged overpower operation.

[0020] According to traditional aircraft design principles, in order to prevent the charge from failing to dissipate quickly and in a timely manner when metal protruding components such as pitot tubes are struck by lightning, and to prevent localized high-temperature melting at the component joints that could damage the aircraft structure or components, the lap resistance between the component and the fuselage metal structure must be sufficiently small during component installation, i.e., less than or equal to 2 milliohms.

[0021] Based on this, this application proposes a novel configuration of aircraft pitot tubes. This novel configuration includes a heating resistance wire wrapped with insulating material, a pitot tube housing, a venting pipe, an insulating component, and a lightning protection and static electricity elimination device. The lightning protection and static electricity elimination device includes a gas discharge tube and a static electricity elimination resistor. The resistance of the static electricity elimination resistor is greater than the resistance of the heating resistance wire. The heating resistance wire wrapped with insulating material is embedded between the pitot tube housing and the venting pipe. The insulating component and the lightning protection and static electricity elimination device are disposed between the novel configuration aircraft pitot tube and the fuselage metal structure. The insulating component ensures electrical insulation between the novel configuration aircraft pitot tube and the fuselage metal structure during installation. The lightning protection and static electricity elimination device protects against lightning strikes and discharges static electricity. This solution improves the installation method between the pitot tube and the aircraft fuselage by changing the traditional equipotential electrical connection to an electrically insulated installation, and adds a lightning protection and static electricity discharge device between them. This gives the pitot tube lightning protection and static electricity discharge capabilities. Furthermore, by using a lightning protection and static electricity discharge device to connect the pitot tube to the fuselage, the negative impact of decreased insulation performance of the pitot tube heating resistance on the pitot tube heating system can be greatly reduced, thereby improving the reliability of the aircraft pitot tube. The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to limit the application. Unless otherwise defined, the technical or scientific terms used in this application should be understood in their ordinary sense by one of ordinary skill in the art to which this application pertains. The singular forms “a,” “described,” and “the” used in this application specification and appended claims are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any or all possible combinations of one or more associated listed items. In the description of the embodiments of this application, it should be understood that 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., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the embodiments of this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the embodiments of this application.

[0022] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of embodiments of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0023] In the embodiments of this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application according to the specific circumstances.

[0024] In the embodiments of this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0025] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening 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 intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in the embodiments of this application are for illustrative purposes only and do not represent the only implementation.

[0026] Based on this, this application proposes a novel configuration for aircraft pitot tubes, which is described below in conjunction with the appendix. Figures 3-7 The novel configuration of the aircraft pitot tube according to the embodiments of this application will be described by way of example.

[0027] like Figure 3 , Figure 3 This application provides a system schematic diagram of a novel configuration aircraft pitot tube. The new configuration of the aircraft pitot tube includes: a heating resistance wire wrapped with insulating material, a pitot tube housing, a venting pipe, insulating components, and a lightning protection and static electricity elimination device. The lightning protection and static electricity elimination device includes a gas discharge tube and a static electricity elimination resistor. The resistance of the static electricity elimination resistor is greater than the resistance of the heating resistance wire. The heating resistance wire wrapped with insulating material is embedded between the pitot tube housing and the venting pipe. The insulating components and the lightning protection and static electricity elimination device are installed between the new configuration aircraft pitot tube and the fuselage metal structure. The insulating components ensure electrical insulation between the new configuration aircraft pitot tube and the fuselage metal structure during installation. The lightning protection and static electricity elimination device protects against lightning strikes and discharges static electricity.

[0028] By electrically insulating the Pitot tube from the metal structure of the fuselage during installation (i.e., ensuring a lap resistance greater than or equal to 1MΩ) and adding a lightning protection and static electricity discharge device between them, the Pitot tube can be protected against lightning strikes and discharge static electricity, while also greatly reducing the negative impact of the decreased insulation performance of the Pitot tube's heating resistance on the Pitot tube heating system.

[0029] like Figure 4 As shown, Figure 4 An equivalent schematic diagram of a novel configuration of an aircraft pitot tube provided in this application embodiment, wherein, Figure 3 and Figure 4 The dashed box shows an exemplary lightning protection and static electricity elimination device, which includes a gas discharge tube and a static electricity elimination resistor. One end of the gas discharge tube is connected to one end of the insulating resistor, the metal shell of the Pitot tube, and one end of the static electricity elimination resistor. The other ends of the gas discharge tube and the other ends of the static electricity elimination resistor are both connected to one end of the heating resistance wire.

[0030] The gas discharge tube (GDT) is a surge arrester used for overvoltage protection. It discharges instantaneous lightning overcurrent and limits overvoltage. Its characteristics include being in a cutoff state when the voltage across its terminals is low, and having an impedance in the GΩ range. When struck by lightning, the surge voltage across the tube reaches its trigger voltage, causing the tube to break down and begin operation, discharging the energy of the large surge current. The static electricity elimination resistor R1 is used to eliminate static electricity and discharge residual low voltage when the tube is turned on and then off.

[0031] Because of the introduction of the static resistance R1, the decrease in the insulation resistance of the Pitot tube under normal circumstances will not cause the heating resistor of the Pitot tube to burn out, thus ensuring the normal operation of the Pitot tube heating system. However, the resistance value of R1 should be at least one order of magnitude greater than the resistance value of the heating resistor R0. The resistance value of the heating resistor R0 is generally within 50Ω, and the resistance value of R1 should be selected in the KΩ range.

[0032] Therefore, detecting whether the insulation resistance of the pitot tube exceeds the limit becomes very simple. Specifically, while the aircraft is on the ground, it is only necessary to briefly operate the pitot tube heating system and then use a voltage tester or multimeter to measure the AC voltage of the pitot tube casing. Figure 4 The AC voltage at point D can be used to accurately determine whether the insulation impedance of the pitot tube meets the requirements of the maintenance manual. For example, such as Figure 4 If the resistance of R1 is selected as 10KΩ, according to the maintenance manual, the insulation resistance Rm of the Pitot tube should be greater than 1MΩ. Therefore, when the insulation resistance of the Pitot tube drops to Rm=1MΩ, and the Pitot tube is working normally under heating, according to Kirchhoff's voltage law, the voltage measured at point D should be approximately 1.15VAC. Similarly, if the voltage at point D is above 100VAC, it indicates that the insulation performance of the Pitot tube has been completely lost, and the heating resistor R0 has short-circuited to the casing.

[0033] In addition, the insulation resistance of the pitot tube can be checked regularly on the ground according to the above method to ensure that the insulation performance of the pitot tube is maintained in good condition.

[0034] To improve lightning protection and more quickly and reliably discharge the initial surge current of a lightning strike, the lightning protection device has been optimized from a typical two-stage circuit to a three-stage protection circuit. In some optional embodiments, such as... Figure 5 As shown, Figure 5 This is a schematic diagram of another lightning protection and static electricity elimination device provided in an embodiment of this application. The lightning protection and static electricity elimination device includes two gas discharge tubes connected in parallel, a bidirectional transient voltage suppressor diode, a first resistor, and a second resistor. The first resistor R1 forms a first-level protection circuit and is a cement resistor or a wafer resistor. The bidirectional transient voltage suppressor diode (TVS) D1 and the second resistor R2 form a second-level protection circuit and are wafer resistors. The two gas discharge tubes GDT1 and GDT2 connected in parallel form a third-level protection circuit.

[0035] The first level of protection consists of the first resistor R1, whose main functions are: a. to provide current-limiting protection for the heating resistor of the Pitot tube whose insulation performance has deteriorated when there is no lightning strike; b. to release the static electricity adsorbed by the Pitot tube during flight and protect the safety of ground maintenance personnel; c. to discharge the residual voltage after the gas discharge tube and bidirectional transient suppression diode D1 of the Pitot tube are turned off in the later stage of lightning strike.

[0036] Optionally, the resistance of the first resistor is 1KΩ-1MΩ. For example, if the first resistor is a cement resistor, the resistance of the cement resistor can be 10KΩ~50KΩ. Specifically, for the convenience and accuracy of the subsequent ground testing of the Pitot tube insulation critical value (1MΩ), and considering that the discharge rate of static electricity and residual voltage should be as large as possible, the resistance of the first resistor R1 is selected as 10KΩ.

[0037] In extreme cases, the insulation value of the Pitot tube heating resistor Rm = 0Ω, and the short circuit point is at point a where the resistor is applied. At this point, the voltage across resistor R1 is 115V, and its power handling capacity is calculated to be 115V × 115V ÷ 10KΩ = 1.33W. Considering power margin, 5W is sufficient. Therefore, the first resistor R1 can be defined as a 10KΩ / 5W cement resistor.

[0038] Level 2 protection consists of a bidirectional transient voltage suppressor diode D1 and a second resistor R2. Its main function is to accelerate the release of surge energy during the initial stage of a lightning strike. In the initial stage, due to the presence of distributed capacitance, the surge voltage is not instantaneous but gradually increases, albeit at a very rapid rate. During this period, the bidirectional transient voltage suppressor diode should conduct quickly first. Simultaneously, the conduction voltage of the bidirectional transient voltage suppressor diode must take into account the interference from the degradation of the insulation performance of the Pitot tube heating resistor; otherwise, under the same extreme conditions, when Rm=0Ω, 115V... AC The power supply is applied to the bidirectional transient voltage suppressor diode, therefore the breakdown voltage of the bidirectional transient voltage suppressor diode must not be less than 115V. AC The peak voltage is 115 × 1.414 = 162.61V.

[0039] Optionally, the bidirectional transient suppression diode has a breakdown voltage greater than 170V, a clamping voltage of 275V, and a peak pulse current of 2.2A; the second resistor has a resistance of 30Ω-200Ω. The third level of protection consists of two gas discharge tubes with different pulse breakdown voltages connected in parallel, used to discharge transient overcurrents from lightning and limit overvoltage. The two parallel gas discharge tubes include a first gas discharge tube and a second gas discharge tube; the pulse breakdown voltage of the first gas discharge tube is greater than 170V, and the pulse breakdown voltage of the second gas discharge tube is greater than 250V.

[0040] The selection of the resistance value of R2 requires the pulse breakdown voltage of the gas discharge tube. In the third-level protection, GDT1 can be the first gas discharge tube, and GDT2 can be the second gas discharge tube. For example, the pulse breakdown voltage of GDT1 can be selected as 300V, and the pulse breakdown voltage of GDT2 as 350V. The gas discharge tube is inactive until the surge voltage rises to 300V or 350V (when GDT1 fails). During the period from 189V to 300V or 350V, the TVS first performs surge energy release protection. Therefore, the calculation of the resistance value of R2 should also use the larger value of 350V, calculated as: R2 = (350V - 275V) ÷ 2.2A = 34.09Ω. Alternatively, the resistance value of resistor R2 can be selected as 36Ω, and the resistor type should be a leadless face resistor (MELF) wafer resistor, which has good pulse load capability.

[0041] Since the pulse breakdown voltage of GDT1 is 300V and the pulse breakdown voltage of GDT2 is 350V, GDT2 has a higher breakdown voltage. Therefore, GDT2 only provides protection when GDT1 fails. This design ensures the normal operation of the surge protection function.

[0042] Taking all factors into consideration, both GDTs were selected from a reliable company that produced the 2027 series 2-electrode gas discharge tubes with a pulse discharge current of 10kA. The GDT1 model is 2027-07-SM, and the GDT2 model is 2027-15-SM.

[0043] like Figure 6 As shown, Figure 6 This application provides a schematic diagram of an existing pitot tube installation configuration, including screws, a total hydrostatic probe, an electrical plug, and conduit connections. In some optional embodiments, to ensure proper installation of the pitot tube, electrical insulation between the pitot tube housing and the fuselage metal structure must be guaranteed, as well as reliable connection between the input terminal of the surge protector and the pitot tube housing, and reliable connection between the output terminal of the surge protector and the fuselage metal structure. Optionally, the insulation assembly includes an insulating pad disposed between the pitot tube and the fuselage metal structure of the new configuration aircraft.

[0044] like Figure 7 As shown, Figure 7 This is a schematic diagram of the installation configuration of a new type of aircraft pitot tube provided in an embodiment of this application, in which an insulating pad is added and placed between the new type of aircraft pitot tube and the fuselage metal structure.

[0045] In some alternative embodiments, the new configuration aircraft pitot tube also includes an insulating material base. Optionally, the insulating material base can be a ceramic base or other types of insulating material bases. This application embodiment does not specifically limit this.

[0046] In some alternative embodiments, the new configuration aircraft pitot tube also includes an insulating material conduit interface. Optionally, the insulating material conduit interface can be a ceramic conduit interface or other types of insulating material conduit interfaces. This application embodiment does not specifically limit this.

[0047] In some alternative embodiments, the new configuration of the pitot tube also includes a ventilation line with an insulated hose to replace the original rigid tube connection configuration, thereby isolating the pitot tube base pipe interface from the fuselage structure.

[0048] This application provides a novel aircraft pitot tube configuration. The new pitot tube includes a heating resistance wire wrapped with insulating material, a pitot tube housing, a venting pipe, an insulating component, and a lightning protection and static electricity elimination device. The lightning protection and static electricity elimination device includes a gas discharge tube and a static electricity elimination resistor. The resistance of the static electricity elimination resistor is greater than the resistance of the heating resistance wire. The heating resistance wire wrapped with insulating material is embedded between the pitot tube housing and the venting pipe. The insulating component and the lightning protection and static electricity elimination device are disposed between the new aircraft pitot tube and the fuselage metal structure. The insulating component ensures electrical insulation between the new aircraft pitot tube and the fuselage metal structure during installation. The lightning protection and static electricity elimination device protects against lightning strikes and discharges static electricity. This solution improves the installation method between the pitot tube and the aircraft fuselage by changing the traditional equipotential electrical connection to an electrically insulated installation, and adds a lightning protection and static electricity discharge device between them. This enables the pitot tube to have the functions of lightning protection and static electricity discharge. In addition, by connecting the pitot tube to the fuselage with a lightning protection and static electricity discharge device, the negative impact of the decrease in the insulation performance of the pitot tube heating resistance on the pitot tube heating system can be greatly reduced, thereby improving the reliability of the aircraft pitot tube.

[0049] It is readily understood that, based on the several embodiments provided in this application, those skilled in the art can combine, split, or reorganize the embodiments of this application to obtain other embodiments, none of which exceed the protection scope of this application.

[0050] The above detailed embodiments further illustrate the purpose, technical solution, and beneficial effects of the embodiments of this application. It should be understood that the above are merely specific embodiments of the embodiments of this application and are not intended to limit the protection scope of the embodiments of this application. Any modifications, equivalent substitutions, improvements, etc., made on the basis of the technical solutions of the embodiments of this application should be included within the protection scope of the embodiments of this application.

Claims

1. A new configuration pitot tube for an aircraft, characterized in that, The new configuration aircraft pitot tube comprises a heating resistance wire wrapped with insulating material, a pitot tube shell, a breather pipeline, an insulating assembly and a lightning protection and static electricity elimination device, the lightning protection and static electricity elimination device comprises a gas discharge tube and a static electricity elimination resistor, the resistance value of the static electricity elimination resistor is greater than the resistance value of the heating resistance wire, the heating resistance wire wrapped with insulating material is inlaid between the pitot tube shell and the breather pipeline, and the insulating assembly and the lightning protection and static electricity elimination device are arranged between the new configuration aircraft pitot tube and a metal structure of a fuselage. The insulating assembly is used for electrically insulating the new configuration aircraft pitot tube from the metal structure of the fuselage when the new configuration aircraft pitot tube is installed. The lightning protection and static electricity elimination device is used for lightning protection and static electricity elimination. The insulating assembly comprises an insulating pad arranged between the new configuration aircraft pitot tube and the metal structure of the fuselage.

2. The new configuration pitot tube of claim 1, wherein, The lightning protection and static electricity elimination device comprises a gas discharge tube and a static electricity elimination resistor, one end of the gas discharge tube is connected with one end of the insulating resistor and the pitot tube metal shell, and the other end of the gas discharge tube and the other end of the static electricity elimination resistor are connected with one end of the heating resistance wire.

3. The new configuration pitot tube of claim 1 or 2, wherein, The gas discharge tube is used for discharging lightning transient overcurrent and limiting overvoltage. The static electricity elimination resistor is used for eliminating static electricity and discharging residual low voltage when the gas discharge tube is turned on and then turned off. The lightning protection and static electricity elimination device comprises two parallel gas discharge tubes, a bidirectional transient voltage suppression diode, a first resistor and a second resistor, the first resistor is a cement resistor or a wafer resistor, the first resistor forms a first-stage protection circuit, the bidirectional transient voltage suppression diode and the second resistor form a second-stage protection circuit, the second resistor is a wafer resistor, and the two parallel gas discharge tubes form a third-stage protection circuit.

4. The new configuration pitot tube of claim 1 or 2, wherein, The resistance value of the first resistor is 1KΩ-1MΩ.

5. The new configuration pitot tube of claim 4, wherein, The breakdown voltage of the bidirectional transient voltage suppression diode is greater than 170V, the clamping voltage is 275V, and the peak pulse current is 2.2A; and the resistance value of the second resistor is 30Ω-200Ω.

6. The new configuration pitot tube of claim 4, wherein, The two parallel gas discharge tubes comprise a first gas discharge tube and a second gas discharge tube, the pulse breakdown voltage of the first gas discharge tube is greater than 170V, and the pulse breakdown voltage of the second gas discharge tube is greater than 250V.

7. The new configuration pitot tube of claim 4, wherein, The new configuration aircraft pitot tube further comprises an insulating material base.

8. The new configuration pitot tube of claim 2, wherein, The new configuration aircraft pitot tube further comprises an insulating material pipeline interface.

9. The new configuration pitot tube of claim 2, wherein, The new configuration aircraft pitot tube further comprises a breather pipeline with an insulating material hose.

10. The new configuration pitot tube of claim 2, wherein, ​

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