CN117508603A - Aircraft air inlet channel anti-icing device and method - Google Patents

Abstract

The invention discloses an anti-icing device and method for an air inlet channel of an aircraft. The wiring terminal component comprises a wiring terminal (2), a wiring lug (1), a hexagonal thin nut (4), a self-locking nut (3) and a wiring terminal (5), wherein the wiring lug (1) is fixedly connected with the wiring terminal (2), the wiring terminal (5) is fixed on the wiring terminal (2) through the hexagonal thin nut (4), and the self-locking nut (3) is used for locking the hexagonal thin nut (4); the wiring lug (1) is also connected with the graphene heating element; the insulation fixing device comprises glass fiber prepreg and resin adhesive; the glass fiber prepreg is bonded through resin glue to be laminated and paved, and meanwhile, the graphene heating element is clamped in the paving layer; the top end of the binding post (2) is exposed out of the paving layer after paving so as to ensure that the binding post can be connected with the binding post (5). The invention improves the safety, reliability and maintainability of the anti-icing device of the metal air inlet passage, and better protects the flight safety of the aircraft.

Description

An anti-icing device and method for aircraft air inlet

Technical field

The invention belongs to the technical field of aircraft electric thermal de-icing, and specifically relates to an aircraft air inlet anti-icing device and method.

Background technique

The aircraft inlet is a complex hyperbolic structural surface. Mild icing in the aircraft inlet will reduce the flight performance of the aircraft and threaten the flight safety of the aircraft. At present, aircraft anti-icing/de-icing is mainly used in typical parts such as wings, tails, and air intakes. For composite material parts, the heating method adopts the heating element mounted thermal anti-icing form. The aircraft wings, tails, and rotors are ordinary curved surfaces. , the curved surface unfolds into a regular plane, the design of anti-icing heating elements is easy, and the coverage is good. However, the shape of the aircraft lip inlet is a complex hyperbolic structural surface, and the installation of heating elements mainly faces the following technical problems:

(1) The heating element inlet is attached and layered

Traditional metal heating elements are covered with colloid. During the laying process of the heating elements, the conformity is poor. The heating elements and the installation position are prone to delamination, and the heat cannot be exported, resulting in hot spots in the heating elements. The hot spots are prone to periodic heat. Due to stress, the heating element will break, seriously affecting the service life of the product.

(2) Poor heating uniformity

Traditional metal heating elements only generate heat sources at the metal energized position during the energization process, and other positions need to transfer heat through thermal conduction for aircraft anti-icing work. For the entire anti-icing protection area, compared to the electron transfer of graphene heating elements through the entire surface of the graphene heating element Heating method has poor heating uniformity.

Contents of the invention

The object of the present invention is to provide an anti-icing device and method for an aircraft inlet. The invention improves the safety, reliability and maintainability of the metal air inlet anti-icing device, and better protects the flight safety of the aircraft.

The technical solution of the present invention is: an anti-icing device for an aircraft air inlet, including a terminal component, a graphene heating element, and an insulating fixing device; the terminal component includes a terminal post, a wiring lug, a hexagonal thin nut, a self-locking nut, and wiring Terminals, wiring lugs are fixedly connected to the wiring posts. The wiring terminals are fixed on the wiring posts through hexagonal thin nuts. The self-locking nuts lock the hexagonal thin nuts to prevent loosening. The wiring lugs are also connected to the graphene heating element. The insulation fixing device includes glass. Fiber prepreg and resin glue; glass fiber prepreg is bonded with resin glue for laminated paving, and graphene heating elements are clamped in the paving layer; after paving, the top of the terminal post is exposed to the paving layer to ensure It can be connected to terminal blocks.

The aforementioned aircraft inlet anti-icing device also includes a temperature feedback and overheating protection device, which is used to feedback and output the temperature signal and ensure power-off protection when the graphene heating device overheats.

In the aforementioned aircraft air inlet anti-icing device, the glass fiber prepreg is 5231/EW180B glass fiber prepreg, and the resin glue is J159-3Ⅲ resin glue.

In the aforementioned aircraft air inlet anti-icing device, the temperature feedback and overheating protection device includes a temperature sensor and a temperature switch; the temperature sensor is connected to the graphene heating element through the temperature switch.

In the aforementioned aircraft inlet anti-icing device, the temperature sensor is a platinum resistor, and the temperature switch is a bimetallic temperature switch.

In the aforementioned aircraft air inlet anti-icing device, the terminals and the terminal lug are fixedly connected by flame brazing, and the graphene heating element and the terminal lug with the terminal post are resistance brazed and welded.

In the aforementioned aircraft air inlet anti-icing device, the included angle of the fiber filaments in each layer of glass fiber prepreg is 45°.

In the aforementioned aircraft air inlet anti-icing device, the temperature sensor and the temperature switch are arranged at a relatively high temperature position.

An installation method of an aircraft inlet anti-icing device as mentioned above, the steps are as follows:

1) Mount glass fiber prepreg on the hyperbolic inlet mold;

2) The graphene heating element is mounted on the surface of the glass fiber prepreg, and the terminal components are fixed. Then a layer of glass fiber prepreg is mounted on the surface of the graphene heating element, and the terminal leads out of the prepreg;

3) After the temperature sensor and temperature switch are mounted on the glass fiber prepreg, 9 layers of glass fiber prepreg are mounted, and the wires are led out, and the terminals are led out layer by layer;

4) After the installation is completed, vacuum the molded parts and place them in an autoclave for heating to ensure that each layer is mounted tightly.

In step 1) of the aforementioned installation method, 2-3 layers of glass fiber prepreg are mounted.

The advantages of the present invention are:

The invention is suitable for anti-icing and de-icing work in aircraft inlets, and uses graphene as a heating element for anti-icing design. The insulation design is made of fiberglass prepreg, the graphene heating element is clamped, and the terminal components are energized and heated to realize the anti-icing heating of the air inlet. Compared with traditional heating metal elements, graphene heating elements are 20% lighter in weight than metal heating elements. They have good heating uniformity, strong binding force between the heating interface and composite materials, and a heat utilization rate of more than 95%.

To sum up, the present invention improves the safety, reliability and maintainability of the metal inlet anti-icing device, and better protects the flight safety of the aircraft.

Description of drawings

Figure 1 is a structural diagram of the aircraft air inlet anti-icing device of the present invention;

Figure 2 is the electrical schematic diagram;

Figure 3 is the product wiring diagram.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and examples, but this does not serve as a basis for limiting the present invention.

Example 1. An anti-icing device for an aircraft air inlet, see Figure 1-3. The insulation fixing device is composed of 5231/EW180B glass fiber prepreg and J159-3Ⅲ resin glue. The terminal components include terminal posts, wiring lugs, hexagonal thin nuts, The hexagonal self-locking nut, temperature feedback and overheating protection device include a temperature sensor and a temperature switch. The temperature sensor is a platinum resistor, and the temperature switch is a bimetallic temperature switch.

The insulation design is made of fiberglass prepreg, and the graphene heating elements are clamped and lead out individually through binding post components.

The terminals and the terminal lug are fixedly connected by flame brazing, and the graphene heating element and the terminal lug are spot welded.

The terminal posts in the terminal assembly extend through the fiberglass prepreg.

The terminal block of the crimped wire is connected to the terminal post and fixed by a hexagonal thin nut and a hexagonal self-locking nut.

The crimped wire is connected in series with the temperature relay and then connected to the power supply. The temperature sensor is connected to the controller. The controller completes the power on and off of the integrated rubber mesh heating device based on the temperature signal transmitted by the temperature sensor. The electrical schematic diagram is shown in Figure 2.

A composite embedded graphene heating element anti-icing method for aircraft inlet, the steps are as follows:

1) Hyperbolic inlet mold, mounted with 2 layers of 5231/EW180B glass fiber prepreg.

2) The graphene heating element is mounted on the surface of the 5231/EW180B glass fiber prepreg, and the terminal components are fixed. Then a layer of 5231/EW180B glass fiber prepreg is mounted on the surface of the graphene heating element, and the terminal leads out of the prepreg. material.

3) After mounting the temperature sensor and temperature relay on the 5231/EW180B glass fiber prepreg, mount 9 layers of glass fiber prepreg, lead out the wires, and lead out the terminals layer by layer.

4) After the installation is completed, vacuum the molded parts and place them in an autoclave for heating to ensure that each layer is mounted tightly.

5) After the product is formed, the terminals of the crimped wires are connected to the terminal posts and fixed with hexagonal thin nuts and hexagonal self-locking nuts.

The composite embedded graphene heating element anti-icing method for an aircraft air inlet disclosed by the invention is mainly divided into four parts, including terminal components, graphene heating elements, insulation fixing devices, temperature feedback and overheating protection devices. Terminal components include terminal posts, wiring lugs, hexagonal thin nuts, and hexagonal self-locking nuts; insulation fixing devices include 5231/EW180B glass fiber prepreg, J159-3Ⅲ resin glue; temperature feedback and overheating protection devices include temperature sensors and temperature switches . The invention is suitable for the anti-icing and de-icing work of the aircraft air inlet. It adopts the insulation design through glass fiber prepreg, clamps the graphene heating element, and conducts electrical heating through the terminal component to realize the anti-icing and heating work of the air inlet.

The technical solution will be further described in detail below in conjunction with the accompanying drawings and examples:

Referring to Figures 1 to 3, a composite embedded graphene heating element aircraft inlet anti-icing method is shown, which includes an insulation fixing device, a graphene heating element, a terminal component, a temperature feedback and an overheating protection device.

The specific implementation steps are as follows:

Step 1: Preparation for component connection

(1) The terminals and terminal lugs in the graphene heating element are fixedly connected by flame brazing.

(2) The graphene heating element and the terminal lug are spot welded.

Step 2: Production of anti-icing device for aircraft inlet

1) Hyperbolic inlet mold, mounted with 2 layers of 5231/EW180B glass fiber prepreg.

2) The graphene heating element is mounted on the surface of the 5231/EW180B glass fiber prepreg, and the terminal components are fixed. Then a layer of 5231/EW180B glass fiber prepreg is mounted on the surface of the graphene heating element, and the terminal leads out of the prepreg. material.

3) After mounting the temperature sensor and temperature relay on the 5231/EW180B glass fiber prepreg, mount 9 layers of glass fiber prepreg, lead out the wires, and lead out the terminals layer by layer.

4) After the installation is completed, vacuum the molded parts and place them in an autoclave for heating to ensure that each layer is mounted tightly.

5) After the product is formed, the terminals of the crimped wires are connected to the terminal posts and fixed with hexagonal thin nuts and hexagonal self-locking nuts. See Figure 3 for details.

Example 2. An anti-icing device for an aircraft air inlet, see Figure 1-3, including a terminal component, a graphene heating element, and an insulating fixing device; the terminal component includes a terminal post 2, a terminal lug 1, a hexagonal thin nut 4, and a self-locking nut 3 and terminal block 5, terminal lug 1 is fixedly connected to terminal block 2, terminal block 5 is fixed on terminal block 2 through hexagonal thin nut 4, self-locking nut 3 locks hexagonal thin nut 4 to prevent loosening; lug 1 is also Connected to the graphene heating element; the insulation fixing device includes fiberglass prepreg and resin glue; the fiberglass prepreg is bonded with resin glue for laminated paving, and the graphene heating element is clamped in the paving layer; After pasting, the top of the terminal post 2 is exposed to the paving layer to ensure that it can be connected to the terminal block 5. Among them, the insulation fixing device is mainly used to ensure the insulation requirements between the graphene heating element and the air inlet, and to ensure that all devices closely cover the air inlet. The graphene heating element is composed of graphene film and bus copper strips.

The aforementioned aircraft inlet anti-icing device also includes a temperature feedback and overheating protection device, which is used to feedback and output the temperature signal and ensure power-off protection when the graphene heating device overheats.

The glass fiber prepreg is 5231/EW180B glass fiber prepreg, and the resin glue is J159-3Ⅲ resin glue. The prepreg can withstand 130°C for a long time and can meet anti-icing heating needs.

The temperature feedback and overheating protection device includes a temperature sensor and a temperature switch; the temperature sensor is connected to the graphene heating element through the temperature switch.

The aforementioned temperature sensor is a platinum resistor, and the temperature switch is a bimetallic temperature switch.

The terminals and the terminal lug are fixedly connected by flame brazing, and the graphene heating element and the terminal lug are connected by resistance brazing.

The fiber fibers in each layer of glass fiber prepreg have an included angle of 45°. To improve the friction between glass fiber prepreg layers and improve the bonding force.

The temperature sensor and temperature switch are arranged at a relatively high temperature position. To prevent the heater temperature from being too high and damaging the fiberglass prepreg.

An installation method of the aircraft air inlet anti-icing device described above, the steps are as follows:

1. Mount glass fiber prepreg on the hyperbolic inlet mold;

2. The graphene heating element is mounted on the surface of the glass fiber prepreg, and the terminal components are fixed. Then a layer of glass fiber prepreg is mounted on the surface of the graphene heating element, and the terminal leads out of the prepreg;

3. After the temperature sensor and temperature switch are mounted on the glass fiber prepreg, 9 layers of glass fiber prepreg are mounted, and the wires are led out, and the terminals are led out layer by layer;

4. After the installation is completed, vacuum the molded parts and place them in an autoclave for heating to ensure that each layer is mounted tightly.

In step 1, 2-3 layers of fiberglass prepreg are mounted. After the molding is completed, the layer can ensure the insulation between the graphene heating element and the outer surface without affecting the thermal conductivity efficiency.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person familiar with the art can easily imagine that within the technical scope disclosed by the present invention, Various equivalent modifications or substitutions should be included within the protection scope of the present invention.

Claims (10)

1. An anti-icing device for aircraft air inlet, characterized in that it includes a terminal component, a graphene heating element, and an insulating fixing device; the terminal component includes a terminal (2), a lug (1), and a hexagonal thin nut ( 4) and the self-locking nut (3) and terminal block (5), the terminal block (1) is fixedly connected to the terminal block (2), and the terminal block (5) is fixed on the terminal block (2) through the hexagonal thin nut (4) , the self-locking nut (3) locks the hexagonal thin nut (4) against looseness; the wiring lug (1) is also connected to the graphene heating element; the insulation fixing device includes fiberglass prepreg and resin glue; the fiberglass prepreg The materials are layered and paved through resin glue bonding, and the graphene heating element is clamped in the paving layer; after paving, the top of the terminal post (2) is exposed to the paving layer to ensure that it can be connected to the terminal block (5) . 2. The aircraft air inlet anti-icing device according to claim 1, further comprising a temperature feedback and overheating protection device for feedback outputting the temperature signal and ensuring that the graphene heating device is powered off when it overheats. Protect. 3. The aircraft air inlet anti-icing device according to claim 1, characterized in that the glass fiber prepreg is 5231/EW180B glass fiber prepreg, and the resin glue is J159-3Ⅲ resin glue. 4. The aircraft air inlet anti-icing device according to claim 1, wherein the temperature feedback and overheating protection device includes a temperature sensor and a temperature switch; the temperature sensor is connected to the graphene heating element through the temperature switch. 5. The aircraft air inlet anti-icing device according to claim 4, wherein the temperature sensor is a platinum resistor and the temperature switch is a bimetallic temperature switch. 6. The aircraft air inlet anti-icing device according to claim 1, wherein the terminals and the terminal lug are fixedly connected by flame brazing, and the graphene heating element and the terminal lug are welded by resistance brazing. 7. The aircraft air inlet anti-icing device according to claim 1, wherein the included angle of the fiber filaments in each layer of glass fiber prepreg is 45°. 8. The aircraft air inlet anti-icing device according to claim 1, wherein the temperature sensor and the temperature switch are arranged at a relatively high temperature position. 9. A method for installing the aircraft air inlet anti-icing device according to any one of claims 1 to 8, the steps are as follows: 1) Mount glass fiber prepreg on the hyperbolic inlet mold; 2) The graphene heating element is mounted on the surface of the glass fiber prepreg, and the terminal components are fixed. Then a layer of glass fiber prepreg is mounted on the surface of the graphene heating element, and the terminal leads out of the prepreg; 3) After the temperature sensor and temperature switch are mounted on the glass fiber prepreg, 9 layers of glass fiber prepreg are mounted, and the wires are led out, and the terminals are led out layer by layer; 4) After the installation is completed, vacuum the molded parts and place them in an autoclave for heating to ensure that each layer is mounted tightly. 10. The installation method according to claim 9, characterized in that in step 1), 2-3 layers of glass fiber prepreg are mounted.