Icing detector installed on air inlet channel of engine and icing detection method

Abstract

The invention belongs to the technical field of ice prevention and removal, and relates to an icing detector installed on an air inlet channel of an engine and an icing detection method. The icing detector comprises a vibrator assembly, a windward side heater assembly, a vibrator mounting rack, a socket mounting plate, a power supply circuit board assembly, a signal driving circuit board assembly, a base and a shell. The base and an aircraft skin are installed in a conformal mode, the shell is connected with the base and arranged on the inner side of the skin, and the socket installation plate, the power circuit board assembly and the signal driving circuit board assembly are installed in the shell. The vibrator mounting frame is connected with the base and is arranged in an engine air inlet channel; a windward side heater assembly is mounted in the vibrator mounting frame; a vibrator assembly is mounted at the bottom of the vibrator mounting frame; the vibration frequency of the vibrator assembly is monitored through the signal driving circuit board assembly so as to judge whether freezing occurs or not.

Description

Technical Field

[0001] The invention belongs to the technical field of anti-icing and deicing, and relates to an ice detector installed in an engine air intake duct and an ice detection method. Background Art

[0002] In modern aircraft technology, the icing problem of aircraft has always been an important factor affecting flight safety. When an aircraft flies under icing weather conditions, ice will appear on the nose, wings, windshield, various temperature and pressure sensors, and engine air intakes. When the aircraft is frozen, it will increase its own weight and destroy its aerodynamic shape, thus affecting flight safety. With the development of aircraft technology, the importance of icing in various parts of the aircraft has increased. Among them, whether the aircraft engine is frozen directly affects whether the aircraft mission can be successfully performed. The old-fashioned ice detectors are mostly installed on the nose or wings to detect the icing of the nose or wings, and the radar cross-sectional area is large, which cannot meet the requirements of new aircraft. Summary of the invention

[0003] In order to meet the requirements of modern aircraft for detecting icing conditions at the engine air inlet while taking into account the radar cross-sectional area, the present invention provides an icing detector installed at the engine air inlet and an icing detection method.

[0004] An ice detector installed in an engine air intake duct comprises: a vibrator assembly, a windward surface heater assembly, a vibrator mounting frame, a socket mounting plate, a power circuit board assembly, a signal drive circuit board assembly, a base and a housing;

[0005] The base is conformally mounted with the aircraft skin, the shell is connected to the base and arranged on the inner side of the skin, and the socket mounting plate, the power circuit board assembly, and the signal drive circuit board assembly are installed in the shell;

[0006] The vibrator mounting frame is connected to the base and is arranged in the engine air intake duct;

[0007] A windward side heater assembly is installed inside the vibrator mounting frame;

[0008] The vibrator assembly is installed at the bottom of the vibrator mounting frame;

[0009] The signal driving circuit board assembly monitors the vibration frequency of the vibrator assembly to determine whether ice is formed.

[0010] Further, the vibrator assembly includes: a vibration head assembly and an electromagnetic oscillation unit;

[0011] The vibration head assembly includes a vibration head and a vibration cylinder. The top shell of the vibration head is a constant elastic alloy round tube. A vibration head heater is arranged inside to heat the vibration head. The vibration cylinder is located below the vibration head.

[0012] The electromagnetic oscillation unit consists of five parts: an excitation coil, a feedback coil, an isolation gasket, a magnet and a support spring. The excitation coil, the feedback coil, the isolation gasket and the support spring are installed in the vibration cylinder, and the magnet is fixed to the outside of the vibration cylinder by an adhesive.

[0013] Furthermore, the vibrator mounting frame is a quadrangular pyramid; the upper and lower surfaces of the quadrangular pyramid are both rhombus-shaped; and the four side surfaces of the quadrangular pyramid are not perpendicular to the upper and lower surfaces.

[0014] Used for the installation and protection of vibrator assemblies and windward heater assemblies, it adopts a diamond frame and is designed with sharp edges to reduce mirror radiation. At the same time, a certain inclination angle is designed to avoid the edge of the ice detector being perpendicular to the aircraft surface, reduce secondary reflection, and minimize the exposed area.

[0015] Furthermore, the angles between the four side surfaces of the quadrangular pyramid and the upper and lower surfaces are 87° to 93°.

[0016] Furthermore, the shell is made of aluminum alloy and is fastened to the base by screws to shield the magnetic field and enhance the internal magnetic field strength, while also achieving isolation from various external interfering magnetic fields.

[0017] Furthermore, the windward surface heater assembly is arranged in the vibrator mounting frame and is located between two side surfaces on one side of the windward surface.

[0018] Furthermore, the power circuit board assembly and the signal drive circuit board assembly are fixed on the base through pillars, and the two circuit board assemblies are installed horizontally inside the product, achieving a balanced layout of circuit board components and reasonable use of the internal space of the shell.

[0019] Furthermore, the base is made of aluminum alloy, which acts as a "bridge" in the structure, connecting the vibrator assembly and the circuit board assembly, realizing the organic unity of the detector functions, and is conformally installed on the air inlet skin by screws.

[0020] An ice detection method installed in an engine intake duct is implemented based on the ice detector, and the method comprises the following steps:

[0021] The power circuit board assembly supplies power to the signal driver circuit board assembly;

[0022] The signal driving circuit board assembly collects the voltage signal sent by the vibrator assembly;

[0023] The frequency of the voltage signal is obtained by sampling the single chip microcomputer;

[0024] If the frequency of the voltage signal is lower than the threshold value a, it is determined that the vibrator assembly is frozen, and an ice warning signal is sent to the aircraft;

[0025] When the frequency of the voltage signal is lower than the threshold value b or lower than the threshold value a for more than T time, the vibrator assembly and the windward surface heater assembly are driven to heat for t time and then stop.

[0026] Furthermore, a is 0.3% to 0.5%, and b is 0.6% to 1%.

[0027] The present invention has at least the following advantages and beneficial effects:

[0028] The ice detector installed in the engine air inlet and the ice detection method proposed by the present invention can detect the ice condition at the engine air inlet of the aircraft in real time and inform the crew in time, thereby improving the safety of the aircraft. The vibrator mounting frame and the vibrator assembly are exposed in a certain direction after adopting a diamond frame design, which ensures that the radar scattering cross-sectional area of ​​the ice detector is small and does not affect the execution of the aircraft's combat mission. It is suitable for all kinds of new aircraft that need to detect the ice condition of the engine air inlet. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is the overall structural diagram of the present invention.

[0030] Figure 2 A diagram of a vibrator assembly according to the present invention.

[0031] Figure 3 It is the judgment logic diagram of the present invention. DETAILED DESCRIPTION

[0032] In order to make the objectives, technical solutions and advantages of the present invention more clear, the technical solutions of the present invention will be described in more detail below in conjunction with the accompanying drawings of the present invention.

[0033] In view of the current requirements for ice detection at the engine air inlet and radar cross-sectional area of ​​new aircraft, an ice detector installed in the engine air inlet and an ice detection method are designed. The ice detector installed in the engine air inlet consists of a vibrator assembly 8, a windward surface heater assembly 7, a vibrator mounting frame 6, a socket mounting plate 1, a power circuit board assembly 2, a signal drive circuit board assembly 3, a base 5 and a shell 4.

[0034] The vibrator assembly consists of a vibration head assembly and an electromagnetic oscillation unit. The vibration head assembly consists of a vibration head 802 and a vibration cylinder 808. The vibration head is a sensitive element for ice detection and is the key to the design of the detector. The material used is a constant elastic alloy, which has a low frequency temperature coefficient, a high mechanical quality factor, and strong anti-oxidation and anti-corrosion capabilities. The vibration head heater 803 installed inside heats the ice layer on the vibration head through a U-shaped heating wire to facilitate the next ice detection. The vibration cylinder is the support structure of the vibrator assembly.

[0035] The electromagnetic oscillation unit consists of five parts: an excitation coil 804, a feedback coil 806, an isolation gasket 805, a magnet 801 and a support spring 807. It generates an alternating magnetic field under the drive of an electrical signal. The vibration head generates magnetostriction under the action of the alternating magnetic field, thereby generating an exciting force to make it vibrate. When ice is deposited on the vibration head, its mass gradually increases, and its vibration frequency decreases accordingly.

[0036] The windward surface heater assembly has an integrated heating resistor wire, which is mainly used to remove ice accumulation on the vibrator mounting frame.

[0037] The vibrator mounting frame is used for the installation and protection of the vibrator assembly and the windward heater assembly. It is the main exposed part. The material used is 7075 aluminum alloy to ensure the structural strength. The surface is sprayed with paint that is the same color as the aircraft air inlet skin for corrosion protection. It adopts a diamond frame and is designed with sharp edges to reduce mirror radiation. At the same time, a certain inclination angle is designed to avoid icing. The edge of the detector is perpendicular to the aircraft surface, reducing secondary reflections, and reducing the exposed area as much as possible to reduce the radar scattering cross-sectional area of ​​the detector.

[0038] The socket mounting plate is mainly used for installing the electrical connector and connecting the base and the housing.

[0039] The power circuit board assembly and the signal drive circuit board assembly are electrically connected through the inter-board connector, and the relative position between the two is fixed through the support, which improves the reliability of the ice detector. The power circuit board assembly is mainly used to power the internal circuit of the ice detector, and converts the 28V on the aircraft into 5V and 3.3V for use by other chips through the power module.

[0040] The signal driving circuit board assembly is mainly used to provide a driving signal to the vibrator assembly and to sample the voltage signal output by the vibrator assembly to obtain the frequency. When the frequency of the voltage signal is lower than the threshold value a, it is determined that the vibrator assembly is frozen, and an ice warning signal is sent to the aircraft through ARINC429.

[0041] The base is made of 7075 aluminum alloy to ensure good structural strength, and connects the vibrator assembly with the circuit board assembly. 10 mounting holes are reserved around the base, and are conformally mounted to the air inlet skin by screws.

[0042] The housing is made of 7075 aluminum alloy and is fastened to the base by screws, forming a closed structure together with the socket mounting plate to protect the circuit board components inside the detector.

[0043] The above-mentioned ice detection method installed in the engine intake duct is implemented based on the above-mentioned ice detector, and the method includes the following steps:

[0044] The power circuit board assembly supplies power to each chip in the signal driver circuit board assembly;

[0045] The signal driving circuit board assembly drives the vibration head in the vibrator assembly to vibrate, and collects and amplifies the voltage signal of the vibrator assembly;

[0046] The frequency of the voltage signal is obtained by sampling the single chip microcomputer of the signal driving circuit board assembly;

[0047] If the frequency of the voltage signal is lower than the threshold value a, it is determined that the vibrator assembly is frozen, and an ice warning signal is sent to the aircraft through ARINC429;

[0048] When the frequency of the voltage signal is lower than the threshold value b or lower than the threshold value a for more than T time, the vibrator assembly and the windward surface heater assembly are driven to heat for t time and then stop.

[0049] a is 0.3% to 0.5%, and b is 0.6% to 1%.

[0050] In summary, an ice detector installed in an engine air intake and an ice detection method, the structural parts are made of high-strength materials to ensure the structural strength, the ice detector vibrator mounting frame and the vibrator assembly are partially exposed in a certain direction after adopting a diamond frame design to ensure that the radar scattering cross-section is small, when ice is deposited on the vibrator head in the ice detector vibrator assembly, the vibration frequency decreases accordingly, and when the frequency is lower than the set threshold, an ice warning signal is sent to the aircraft through ARINC429, and heating and de-icing are performed to remove the ice accumulated on the vibrator assembly and the heater assembly.

[0051] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the scope disclosed in the present invention should be covered within the protection scope of the present invention.

Claims

1. An ice detector installed in an engine air intake, characterized in that: include: A vibrator assembly, a windward heater assembly, a vibrator mounting bracket, a socket mounting plate, a power circuit board assembly, a signal drive circuit board assembly, a base and a housing; The base is conformally mounted with the aircraft skin, the shell is connected to the base and arranged on the inner side of the skin, and the socket mounting plate, the power circuit board assembly, and the signal drive circuit board assembly are installed in the shell; The vibrator mounting frame is connected to the base and is arranged in the engine air intake duct; A windward side heater assembly is installed inside the vibrator mounting frame; The vibrator assembly is installed at the bottom of the vibrator mounting frame; The signal driving circuit board assembly monitors the vibration frequency of the vibrator assembly to determine whether ice is formed.

2. The ice detector according to claim 1, characterized in that: The vibrator assembly includes: a vibration head assembly and an electromagnetic oscillation unit; The vibration head assembly includes a vibration head and a vibration cylinder. The top shell of the vibration head is a constant elastic alloy round tube. A vibration head heater is arranged inside to heat the vibration head. The vibration cylinder is located below the vibration head. The electromagnetic oscillation unit consists of five parts: an excitation coil, a feedback coil, an isolation gasket, a magnet and a support spring. The excitation coil, the feedback coil, the isolation gasket and the support spring are installed in the vibration cylinder, and the magnet is fixed to the outside of the vibration cylinder by an adhesive.

3. The ice detector according to claim 1, characterized in that: The vibrator mounting frame is a quadrangular platform; the upper and lower surfaces of the quadrangular platform are both rhombus-shaped; and the four side surfaces of the quadrangular platform are not perpendicular to the upper and lower surfaces.

4. The ice detector according to claim 3, characterized in that: The angles between the four sides of the tetrahedron and the upper and lower surfaces are 87° to 93°.

5. The ice detector according to claim 1, characterized in that: The housing is made of aluminum alloy.

6. The ice detector according to claim 1, characterized in that: The windward surface heater assembly is arranged in the vibrator mounting frame and is located between two side surfaces in the windward direction.

7. An ice detection method installed in an engine intake duct, implemented based on the ice detector according to any one of the above claims, characterized in that: The method comprises the following steps: The power circuit board assembly supplies power to the signal driver circuit board assembly; The signal driving circuit board assembly collects the voltage signal sent by the vibrator assembly; The frequency of the voltage signal is obtained by sampling the single chip microcomputer; If the frequency of the voltage signal is lower than the threshold value a, it is determined that the vibrator assembly is frozen, and an ice warning signal is sent to the aircraft; When the frequency of the voltage signal is lower than the threshold value b or lower than the threshold value a for more than T time, the vibrator assembly and the windward surface heater assembly are driven to heat for t time and then stop.

8. The ice detector according to claim 1, characterized in that: a is 0.3% to 0.5%, and b is 0.6% to 1%.

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