Device to detect and remove ice or fluid layer

FIELD: transport.

SUBSTANCE: proposed device comprises, at least, two subnets 2a, 2b of conducting elements. Every said subnet comprises, at least, one line of elements 3. Subnets are arranged so that finger joint between first subnet conducting element 3 and second subnet conducting elements 3 make network of capacitance pickups. Said conducting elements double as heating elements designed to eliminate icing. Conducting elements are buried in insulation material 4. Every subnet of conducting elements is integrated in flexible backing 5, 5a, 5b. The complex proper makes flexible coating. Aircraft comprises above described device connected to crew cab instrumentation panel via switch to display operating parameters and to control said device.

EFFECT: simplified design, optimised electric power consumption.

12 cl, 3 dwg

The present invention relates to a detection device having a layer of ice formed on the outer surface of the aircraft structure, and its removal or detection of the liquid penetrated into the design and / or material of construction, although this can take place on a large surface area, or may be formed locally in the areas of construction.

The presence of frost, ice on the structural elements of the aircraft, is most affected and most important, such as wings, tail fins, stabilizers, can disrupt the operation of the aircraft. As a rule, in the case of the formation of such clusters the weight of ice or snow, added to the weight of the aircraft, leads to worsening of the aircraft as a whole, resulting in the need to increase thrust during takeoff of the aircraft. In addition, a very small surface roughness, even with such a small thickness as 0.4 mm, due to the presence of ice or snow, alters the nature of the flow of air at the level of the carrying capacity and rudders of the aircraft. The consequence of this roughness is a significant reduction in carrying capacity, increasing drag and deteriorating the maneuverability of the aircraft, and the hour of the activity, during takeoff and initial climb.

Another important consequence is that the layers of ice breaking away from the wings or the fuselage during takeoff of the aircraft or set them above, the suction can get inside the engine installed in the rear fuselage, and thereby cause them damage or even lead to the shutdown of the engines. In addition, coming off the layers of ice striking the importance of the surface, in particular stabilizers, can cause damage.

Currently, there are detection, allowing to detect the presence of frost or ice, conducting inspection by feelings or the use of special equipment designed for the detection of ice, such as ground-based apparatus for the detection of ice (GIDS). However, such tools are difficult to use and are not adapted for installation in an aircraft.

In addition, these detection is not associated with the means of de-icing. Currently, there are means of de-icing or de-icing when flying in icing conditions, which provide for the removal of frost, ice formed on the important surfaces of the aircraft before takeoff. To this end, use is made of physico-chemical is such ways, which consist in applying substances on important surface with the purpose to reduce and slow the formation of frost or in the supply of liquid that seeps through the construction. Such tools require the use of special equipment for delivery of these funds to airports. De-icing fluid creates a risk of problems associated with the formation of the seals on the design. In addition, these physico-chemical tools require that the aircraft was stationary on the earth for the production operations to eliminate icing with the all important surfaces. This requires a relatively long time before the departure of the aircraft and the presence of a skilled operator that, as a consequence, leads to a relatively high value.

Also known device de-icing adapted for use during flight of the aircraft, in particular a device that uses pneumatic system, which consists of a tube made of elastic material and fixed to the edges of the attack, alternating inflation and deflation of which leads to the breaking of the frost in the case of its formation; or thermal de-icers, consisting of pipelines, which is served hot in the spirit, taken from the engines. All these tools require to make a selection of a significant amount of air, which leads to increased fuel consumption and deterioration thereby performance turbojet engine. In addition, such a device requires a space sufficient for installation of piping systems and installation of appropriate control devices.

In addition, currently there is no system that would include at the same time and means to detect the presence of a layer of ice, and means for de-icing, providing a peeling layer of ice in real time, in particular during flight of the aircraft.

The present invention aims to offer appropriate device for ice detection and elimination, so that you can monitor important areas of structures that are subject to control, regardless of whether they are accessible or not, and to try to solve the icing in the case of the detection of the presence of a layer of ice.

The device according to the present invention is also capable of removing liquid penetrated into the design, and (or) sometimes penetrated into the material structure, which creates a threat to the reduction of mechanical strength of the structure. The presence of this fluid caused mainly occurring during operation to the reconstruction of the accumulation of infiltrations, and not a design defect arising in the process of its Assembly. This fluid can be at a depth of several centimeters inside the structure. This liquid can be water, accumulated as a result of condensation, or hydraulic fluid, for example oil Skydroll, which is Korroziya fluid structures, and its presence is undesirable, may be associated with leakage at the level of the drive mechanisms.

Problems that need to be addressed for such a device:

- have appropriate means of detection and removal, made with simple laying on the controlled surface structures regardless of whether they are accessible or not, or installed inside structures, and who would preserve a small weight and overall dimensions and their work would need only minor electric power;

- positioning means allowing automatic control to achieve a maximum possible reduction of the operator and the pilot and, accordingly, reduce the cost of maintenance.

To this end the present invention proposes a device for detecting and removing a layer of ice formed on the outer surface of the structure of the aircraft, or liquid penetrated time workinstructions and (or) leaked into the material structure.

According to the invention the device comprises at least two subnets conductive elements, each subnet contains at least one row of conductive elements, and the data subnet are arranged so that the connection in the groove between the conductive elements of the first subnet and the two conductive elements of the second subnet form a network of capacitive sensors, and the data conductive elements are embedded in insulating material, with each subnet conductive elements integrated in the flexible substrate, and the whole complex forms a flexible coating.

According to one variant of the invention, the data of the flexible substrate are perpendicular to the surface of the structure so that the insulating material is or has been in direct contact with the layer of ice, or close to the structure.

According to another variant of the invention, the data of the flexible substrate are arranged in a plane parallel to the plane of the surface of the structure, and the substrate, forming the outer side of the coating is partially porous, so as to give ice or liquid to penetrate into the insulation material.

Removal of the ice layer, this coating preferably is mounted on a part of the external surface of the structure, repeating the shape of the structure.

For fixed is I available the coating liquid, preferably, nested inside the structure, is mounted on the inside surface of the structure or placed in the material constituting the structure.

Preferably, the surface of the structure is divided into a series of sectors, where the device contains a complex network of capacitive sensors for removing ice or liquid for each sector.

The size and position of the conductive elements are defined in such a way that they could detect the capacitance change caused by the presence of ice or liquid that has penetrated into this insulating material.

According to the invention the device also includes front-end electronics mounted on the periphery of the at least one network of capacitive sensors, data management conductive elements (in this case, the electronics includes a control circuit for electronic power data conductive elements), and a microprocessor.

Preferably, the microprocessor comprises a memory containing a table of reference values capacity of the pair of conductive elements, and means of differential analysis of the measured values of the capacitance values of the capacitance of the reference table. The above table reference values capacity is pre-determined by simulation or by experiment.

According to izopet is the means of differential analysis provide a means of forming the state signal S, indicating that the average differential value representing a difference between the reference values and capacity values of capacitance measured by the capacitance sensors exceeds a threshold value, indicating the presence of a layer of ice or the presence of fluid, while the status signal S is transmitted to the data by the microprocessor in the control circuit to turn on the electricity to flow through the aforementioned conductive elements.

According to the invention in an aircraft incorporating such a device, described above, the device may be connected to being in the cockpit instrument panel through the communication unit to display operating parameters and device management.

Other distinctive features and advantages of the invention will become more clear after studying the following description with reference to the accompanying drawings, on which:

- figa and figv represent respectively a top view in partial section of the network capacitive sensors according to two methods of carrying out the invention;

- 2 in schematic form depicts an example configuration of the connection between the front-end electronics and complex of the three networks capacitive sensors.

The invention relates to a device allowing to detect and remove the ice layer, the image is Amy on the outer surface of the aircraft structure, or the presence of fluid inside the structure and/or penetrate into the material of construction, with the present invention, particularly applicable to aircraft structures of complex forms and during flight of the aircraft.

In the implementation of the removal tools in real-time device has the appropriate tools, designed to prevent and detect the formation of a layer of ice or liquids, as well as tools made with the ability to work as a removal device.

Such a device, and its operation is depicted in figure 1 and 2.

On figa depicts a first method embodiment of the invention in which the device contains two subnets conductive elements 2A, 2b.

Two subnets are setting opposite the conductive elements 3, so that the connection in the groove between the elements of the first network elements 2A and the second network 2b forms a network of capacitive sensors.

For example, each conductive element 3 first subnet 2A inserted between two adjacent elements of the second subnet 2b. Thus, two subnets form a network of capacitive sensors 1. The complex conductive elements retracts into the insulation material 4.

As shown in figa, conductive elements 3 are embedded respectively in the upper flexible substrate 5A and the lower g is bcou substrate 5b, which are located in a plane parallel to the plane of the surface of the structure 6. The upper substrate 5A, the side 7 which is directed outwards, is partially porous, allowing ice and liquid to penetrate into the insulating material 4. The complex forms a flexible coating.

On FIGU depicts a second method of carrying out the invention, according to which the flexible substrate 5 are located in a plane perpendicular to the plane of the surface of the structure 6, so that the insulating material 4 placed between the two substrates, is in direct contact with the external environment, in particular, it contacts with potential layer of ice or liquid and placed close to the structure. In addition, the party, which, as stated, will be firmly placed on the surface of the structure contains a thin elastic layer, which integrates a network of capacitive sensors, this complex also forms a flexible coating.

To remove a layer of ice mentioned coating, preferably, mounted on the said outer surface of the structure 6, repeating the shape of the structure.

To delete an existing liquid-mentioned coating is placed inside the structure, is mounted on the inner surface of the structure, or embedded directly in the material of construction, for example, the stage and fabrication.

In both ways the invention, the bottom flexible substrate or a flexible thin layer of strongly bound to the surface of the structure by means of adhesive material.

As shown in figa and 1, the network of capacitive sensors is a means of detecting the presence of a layer of ice or liquid.

Indeed, when ice or liquid penetrate into the insulating material, their presence leads to a change of the dielectric constant ε of the material, in which recessed conductive elements, such dielectric change entails a change in capacitance at the terminals of the capacitor formed by the conductive elements. When comparing the mean values of the measured capacitance values and the average value of the reference capacitance values corresponding to values in the absence of a layer of ice or liquid, the difference allows us to determine quantitatively by the presence of a layer of ice or liquid. Threshold value, indicating the actual presence of a layer of ice or liquid, is fixed.

Preferably, the size and position of the conductive elements are defined so that they were able to detect the capacitance change caused by the change of the dielectric constant of the insulation material. Each conductive element is from another neighboring navigating the element at a distance, sufficient to provide adequate electrical insulation.

Means of de-icing is also formed recessed in the insulating material of the conductive elements are resistive heating elements, is able to dissipate electrical power for Joule heat release when the device operates in the mode of de-icing.

Conductive elements are made of a metallic resistance material such as silver alloy or copper. The network of conductive elements is made by optical lithography made through the stencil, and then connected in pairs at the stage of applying metallic coatings by plasma or by any other means of increasing the layer. The size of the conductive elements is in the order of ten microns.

Insulating material in which are embedded conductive elements are made, preferably, of materials relating to the family of materials having a high permeability.

To control and switch the device on, it contains, in addition, the front-end electronics. Preferably, this front-end electronics can be integrated on the periphery of each network capacitive sensors. This interface contains a control circuit 8, the connecting conductive elements with unit switching-mode power is Tania and microprocessor 9, which connects the network of conductive elements with the block 11. Each line or each column of conductive elements is controlled separately by a control circuit which, in case of failure of the line or column of conductive elements continued network operation.

Figure 2 in schematic form shows an example of the control circuit complex of the three networks, capacitive sensors, covering, for example, one area of the surface of the structure. The power supply unit is connected to three networks 101, 102, 103, respectively, inlet and outlet cables a, 201b, 202a, 202b, 203a, 203b, in this case, the unit is connected to DC voltage source or an AC voltage. The connection wires of each network unit is independent from the connection wires of the neighboring network, thereby minimizing the risk of failure of the device.

Preferably, the surface of the structure which accomplishes the elimination of icing, can be divided into a sequence of sectors for de-icing, a network location of a device on the surface of the structure to implement layer covering the considered surface to ensure the elimination of ice or liquid for each sector. The density of the network depends, on the one hand, from the size of the surface and, on the other hand, the degree of risk this area. Preferably, this network configuration allows you to continue providing the function of removal and de-icing in case of failure of one device.

Figure 2 as an illustration shows a device consisting of three networks, capacitive sensors, which are pressed to each other, but they can also be placed separately on a uniform or arbitrary distance from each other. The complex forms a flexible coating that is mounted on an area of important surface. When the surface is extended, multiple devices are network or arbitrary intervals in the optimal configuration for removing a layer of ice or liquid.

The power supply unit 11 is connected to located in the cockpit instrument panel via the communication unit 10 to display operating parameters and to control the device.

In the scope of protection devices icing or fluid in real time the microprocessor has a memory containing a table of reference values capacity of the pair of conductive elements, and means of differential analysis of measured capacitive sensors values capacity relative to the capacity values of the reference table. Table of reference values capacity in advance predelena by simulation or by experiment.

Means of differential analysis provide a means of forming the state signal S, indicating that the average differential value resulting from the difference between the reference values and capacity values of capacitance measured by the sensor exceeds a threshold value, indicating the presence of a layer of frost on the surface of the structure or fluid in design. The status signal S is transmitted by the microprocessor to the control unit to enable the supply of current through the conductive elements.

Supply current in complex networks capacitive sensors can present a consistent flow, allowing consistent heating. As shown in figure 2, three networks 101, 102 and 103 are heated one after another. This filing may also be carried out in three networks at the same time.

To implement the appropriate de-icing or evaporation of liquids requires the expenditure of a small amount of power. Indeed, depending on the threshold device detection allows early enough to prevent the formation of ice or liquid, in addition, in the process of de-icing the ice layer is in direct contact with a network of conductive elements. The current passing through the conductive elements causes the melting of the ice, directly the NGOs in contact with the surface of the device, which leads to the detachment of the ice layer. To increase the temperature required for surface melting, also requires relatively little power. Typically, the current is supplied to the conductive elements to deliver sufficient de-icing is between 5mA and 10mA.

Preferably, the device according to the invention is associated with means for measuring the degree of humidity and temperature of the plating design of the aircraft during its flight. These tools allow you to automatically turn the device into discovery mode ice depending on the conditions of formation of ice.

At the same time, the device detection and removal of ice or liquid may also be activated by the pilot manually for production of a preventive treatment. In this case, the device is provided directly to an operating mode of elimination, with conductive elements is continuously supplied with current.

The device according to the present invention, in which the front-end electronics interfaced with a network of capacitive sensors, to enable the removal function in the device only with a layer of ice or liquid with optimal response time, allowing you to optimize electricity consumption by the device.

1. Device detection and removal of the ice layer formed on the outer surface and aircraft design (6), or liquid that has penetrated into the design and (or) the material constituting the structure, characterized in that it comprises at least one pair of subnets (2A, 2b) of conductive elements, each subnet contains at least one row of conductive elements (3); however, these subnets are arranged so that the connection in the groove between the conductive elements (3) of the first subnet and conductive elements (3) of the second subnet forms a network of capacitive sensors (1); these conductive elements are resistive heating elements to provide a means for de-icing, and the data conductive elements are embedded in insulating material (4), and each subnet conductive elements integrated into a flexible substrate (5, 5A, 5b); however, the whole complex forms a flexible coating (1).

2. The device according to claim 1, characterized in that the data flexible substrate (5) are perpendicular to the surface of the structure (6) so that the insulating material (4) was in direct contact with the layer of ice close to the surface of the structure.

3. The device according to claim 1, characterized in that the data flexible substrate (5A, 5b) are arranged in a plane parallel to the plane of the surface of the structure (6), the substrate (5A)forming the outer side (7) of this coating is the hour is ichno porous, allowing ice or liquid to penetrate into the insulating material (4).

4. The device according to claim 1, characterized in that said cover is mounted on the said surface of the structure (6), repeating the shape of the structure.

5. The device according to claim 4, characterized in that the said coating is nested inside the structure, is mounted on the inside surface of the structure or placed in the material constituting the structure.

6. The device according to claim 5, characterized in that the surface of the structure is divided into a sequence of sectors de-icing, while the said device contains a complex network of capacitive sensors for removing ice or liquid for each sector.

7. The device according to claim 6, characterized in that the size and position of the conductive elements (3) are defined in such a way that they could detect the capacitance change caused by the presence of ice or liquid that has penetrated into the insulation material.

8. The device according to claim 7, characterized in that the said device also contains the front-end electronics located on the periphery of the at least one network of capacitive sensors, to control the aforementioned conductive elements; these electronics includes at least one control circuit (8) to provide electrical power providing Utah conductive elements, and the microprocessor (9).

9. The device according to claim 8, characterized in that the microprocessor (9) comprises a memory containing a table of reference values capacity of the pair of conductive elements, and means of differential analysis of measured values of capacitance in comparison with the reference values capacity in the table.

10. The device according to claim 9, characterized in that the means of differential analysis have the means of forming the state signal S, indicating that the average differential value resulting from the difference between the reference values and capacity values of capacitance measured at the terminals of the capacitive sensors exceeds a threshold value, indicating the presence of a layer of ice on the surface of the mentioned design or liquid in the design and/or construction material; however, the above-mentioned status signal S is transmitted to the said microprocessor (9) on the control circuit (8) to enable the supply of current through the aforementioned conductive elements.

11. The device according to claim 10, characterized in that the strength of current in said conductive elements is 5-10 mA.

12. Aircraft containing the device detect and remove the presence of the layer of ice or liquid according to any one of the preceding paragraphs, characterized in that the said device is TWT connected to being in the cockpit instrument panel (14) via the communication unit (10) for displaying the operating parameters and to control the said device.