• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    AIR DATA PROBE, E, METHOD FOR MANUFACTURING AN AIR DATA PROBE. An air data probe is described. The air data probe may include a probe body having an internal cavity and lined with a protective hull. A sensing port can be arranged on the air data probe and can extend through the body of the probe. The sensing port can also be aligned with the protective shell. The protective shell can be made of an alloy of nickel - austenitic chromium, or stainless steel, or any relatively corrosion resistant material. The probe body can be made of nickel, or a nickel alloy, or any relatively thermally conductive material. The protective hull can be attached to the probe body by additive manufacturing as well as laser coating. In this way, an air data probe capable of withstanding high temperatures without corrosion and also being relatively thermally conductive is described.
    公开号:BR102016003681B1
    申请号:R102016003681-0
    申请日:2016-02-22
    公开日:2021-05-25
    发明作者:Timothy Thomas Golly；Matthew P. Anderson；Paul Robert Johnson；Greg Seidel
    申请人:Rosemount Aerospace Inc.；
    IPC主号:
    专利说明:

    FIELD
    [001] The present description refers to the data sensing field. More particularly, the present description relates to corrosion resistant air data probes. FUNDAMENTALS
    [002] Typical air data probes, like the air data probe used in aircraft, operate at a range of temperatures. For example, an air data probe like a static pitot probe on an aircraft operates at sea level temperatures as well as extremely high altitude temperatures, such as about 120 degrees Fahrenheit (about 49 degrees Celsius) in desert environments at sea level to about -70 degrees Fahrenheit (about -57 degrees Celsius) at cruising altitudes. To prevent unwanted freezing and/or ice build-up on the air data probe, heaters are incorporated within the probe. However, these heaters can cause the air data probe to get very hot when operating at sea level temperatures, especially during still air or low airflow conditions. Such heat can accelerate corrosion and wear of the air data probe, especially when exposed to contaminants such as compounds containing sulfur, chlorine, sulfur dioxide, and/or the like. Previous efforts to address this challenge include manufacturing air data probes from materials that are resistant to high temperature corrosion; however, such materials often exhibit poor thermal conductivity and are susceptible to freezing. SUMMARY OF THE INVENTION
    [003] In accordance with various aspects of the present invention, an air data probe is described. The air data probe may include a protective hull including a coating of material applied to the probe body and isolating the probe body surface from fluid communication with an environment, and a first sensing port defined by the probe body and positioned therein. a more extreme end of the probe body and in fluid communication with the environment. The air data probe may also include a first internal cavity having a volume defined by the probe body and disposed internally to the probe body, the first internal cavity in fluid communication with the first sensing port. The air data probe may further include a heating element within the first internal cavity in which at least one of the probe body and protective hull is heated.
    [004] The air data probe may also include a second sensing port defined by the probe body and positioned on one side of the probe body and in fluid communication with the environment. The air data probe may include a second internal cavity including a volume defined by the probe body and disposed internally to the probe body. The second internal cavity may be in fluid communication with the second sensing port.
    [005] A method of manufacturing an air data probe is disclosed. The method may include forming a probe body, forming an internal cavity within the probe body, applying a protective shell to the probe body by an additive manufacturing technique, and inserting a heating element into the internal cavity. The method may further include machining a final profile of the air data probe and forming a sensing port having a defined port passage through the body of the probe and aligned by a portion of the protective hull. BRIEF DESCRIPTION OF THE DRAWINGS
    [006] A more complete understanding of the present description can be derived by reference to the detailed description and claims when considered in connection with the Figures, where as reference numbers refer to similar elements throughout the Figures, and: FIG. 1 is a block diagram of various aspects of an air data probe, in accordance with various embodiments; FIG. 2 is a block diagram of various aspects of an air data probe having a sensing port including a sensing port recess, in accordance with various embodiments; FIG. 3 depicts an example air data probe, in accordance with various embodiments; FIG. 4 depicts an example sensing port of an air data probe, in accordance with various embodiments; FIG. 5A-C depicts an exemplary sensing port of an air data port each including a sensing port recess, in accordance with various embodiments; FIG. 6A-B depicts an exemplary protective hull of an air data probe and exemplary drainage holes of an air data probe, in accordance with various embodiments; and FIG. 7 depicts a method for fabricating an air data probe according to various embodiments. DETAILED DESCRIPTION
    [007] The following description is of various embodiments by way of example only, and is not intended to limit the scope, applicability or configuration of this description in any way. Rather, the following description is intended to provide a convenient illustration for implementing various modalities including the best mode. As will become evident, various changes can be made to the function and arrangement of the elements described in these modalities without departing from the scope of the appended claims. Furthermore, any reference to the singular includes multiple modalities, and any reference to more than one component or step can include a singular modality or step. Shading surface lines can be used throughout the figures to denote different parts, but not necessarily to denote the same materials or different materials.
    [008] For the sake of brevity, conditional techniques for fabrication and construction may not be described in detail in this document. In addition, the connecting lines shown in various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between various elements. It should be noted that many alternatives or additional functional relationships or physical connections can be present in a practical method of construction. Likewise, any reference to attachments, affixed, connected or similar may include permanent, removable, temporary, partial, total and/or any other possible attachment option. Additionally, any reference to contactless (or similar phrases) may also include reduced contact or minimal contact.
    [009] The aircraft typically uses air data probes in combination with pressure sensors to sense external air pressures. Both static pressures and dynamic pressures are sensed. For example, static pressure can be sensed by a pitot-static system to determine altitude pressure, while dynamic pressure can be sensed by an airspeed indication system to determine airspeed. Often, additional pressures are measured such that the aircraft's angle of attack and/or aircraft skid angle can also be determined. The air data probe may have sensing ports associated with internal chambers to measure various pressures such as static pressure and/or to determine the angle of attack (AOA). Drainage holes can also be associated with internal chambers, such as to drain collected moisture. External air pressure at air pressure inlet ports during a variety of flight and ground conditions, such as high temperature, low temperature, high humidity, freezing, precipitation, exposure to de-icing chemicals and other harsh chemicals , and the like. As such, with reference to FIG. 1, the air data probe 1 may be desired to be heated and generally thermally conductive, such as to prevent ice buildup, and however, it may also be desired to provide corrosion resistance and durability in very high temperatures. For example, the heater can be set to a power output sufficient to melt ice accumulation in high altitude, low temperature environments, and yet as an adjustment, or often, even a much lower setting, can cause the probe to Air data 1 becomes very hot in low altitude, higher temperature environments such as on land or when there is little or no airflow.
    [0010] In addition, materials with resistance to high-temperature corrosion-resistant materials are generally relatively thermally non-conductive and are generally alloy materials or other materials that are not readily plated onto more thermally conductive materials, such as to provide corrosion-resistant coatings. corrosion. Appropriately, several systems for addressing these considerations, among others, are presented here.
    [0011] With reference to FIGs. 1-2, an air data probe 1 may operate in an environment 2. An air data probe 1 may comprise a structure extending from a mounting structure 20, such as a strut 21 (FIG. 3) associated with an aircraft, in environment 2 where features of environment 2 can be sampled. Thus, the air data probe 1 can be in fluid communication with the environment 2. For example, the air data probe 1 can sample a fluid pressure, such as an air pressure, and such a static pressure for a system that indicates altitude, or pitot pressure for an airspeed indicating system.
    [0012] Environment 2 may comprise a desired region to be tested, such as an airflow area near a mounting structure 20. In additional embodiments, environment 2 may comprise a test chamber, an oven, a vessel a semiconductor processing plant, an oven, and/or any other region where characteristics such as pressure may be desired to be sampled.
    [0013] The air data probe 1 can be connected with a sensor 11. The sensor 11 can be in fluid communication with an internal cavity 10 of the air data probe 1 in which a characteristic of the environment 2 being sampled can be determined . For example, sensor 11 may comprise an air pressure sensor configured to determine the air pressure sampled by the air data probe 1.
    [0014] With reference to FIGs. 1-6B, air data probe 1 may comprise probe body 4. Probe body 4 may comprise a generally hollow cylindrical member which may extend from mounting frame 20 (e.g., an aircraft) to the environment 2. The body of the probe 4 may comprise any mechanism whereby the environment 2 can be sampled and a pressure conveyed to the body of the probe 4 where it is led to a sensor 11. The body of the probe 4 may comprise a structure of vanes, a flat cylinder, such as an oval shape, and/or an airfoil, or any shape as desired. The probe body 4 may comprise a non-cylindrical sensing head probe or a static discharge port probe or semi-discharge air data probe. In various embodiments, the probe body 4 can be made of a relatively thermally conductive material, such as a metal. The metal may comprise nickel. For example, the metal may be a nickel alloy such as nickel 211 which is defined in accordance with a corresponding standard defined by ASTM International. In various embodiments, the metal comprises a low nickel and/or commercially pure nickel alloy, such as nickel 200 or nickel 201 which are each defined herein in accordance with corresponding standards defined by ASTM International.
    [0015] The air data probe 1 may comprise a protective hull 5. A protective hull 5 may comprise a coating of material applied to a surface of the probe body 4 and isolating the surface from fluid communication with the environment 2. For example, a protective shell 5 may comprise a relatively corrosion resistant material such as stainless steel, cobalt chromium, or various chromium-austenitic nickel based alloys. In additional embodiments, the protective shell 5 comprises a chromium-nickel alloy, for example, an austenitic chromium-nickel based alloy such as Inconel® available from Special Metals Corporation of New Hartford, New York, USA. In various embodiments, protective hull 5 comprises Inconel® 625, or the like.
    [0016] Thus, protective hull 5 provides a coating having desired characteristics of hardness, toughness, and high temperature corrosion resistance in addition to exhibiting relatively small galvanic corrosion at the interface of protective hull 5 and probe body 4. By For example, the probe body 4 may be nickel and the protective shell 5 may comprise a chromium-nickel alloy so that the materials are close/adjacent in the galvanic series graph. In addition, as the protective hull 5 comprises substantially less thermal mass than the probe body 4, the desired thermal conductivity characteristics of the probe body 4 are relatively unhampered. As the protective hull 5 is relatively thinner than the probe body (for example, it comprises a relatively shorter thermal conduction path to the environment than that of the probe body 4), the desired thermal conductivity characteristics of the probe body probe 4 are additionally relatively unhindered. Thus, the desired thermal conductivity characteristics of the probe body 4 can be combined with the desired corrosion resistance characteristics of the protective hull 5 in a readily fabricable air data probe (such as by additive manufacturing) 1. Various techniques of fabrication can be implemented, such as additive fabrication methods and/or other fabrication methods in which the integrity of the alloy comprising the protective shell 5 can be maintained. Furthermore, with specific reference to FIGs. 6A-B, the thickness of the protective hull 5 and/or the probe body 4 can be varied locally. The protective hull 5 may comprise regions of increased/decreased thickness such as the local thickness variation of the protective hull 15 and the probe body 4 may comprise regions of increased/decreased thickness such as a local probe body thickness variation 16. Local thinning 15 protective hull thickness variations may correspond with local thinning 16 probe body thickness variations so that the overall profile of air data probe 1 does not vary. In response to the local thickness variation of the protective hull 15 and/or a local probe body thickness variation 16, heat 13 can be conducted through the probe body 4 and the protective hull 5. In this way, the distribution of thermal energy it can be concentrated or spread as desired. For example, local variations in the thickness of protective hull 5 and/or probe body 4 can be implemented to direct heat from a heating element to areas particularly susceptible to freezing, or to direct heat from a heating element away from the heating element to improve even heat distribution, and/or the like.
    [0017] With renewed reference to FIGs. 1-2, and 4-6B, an air data probe 1 may comprise an internal cavity 10. Referring momentarily to FIGs. 5A-C, an air data probe may comprise multiple internal cavities, such as first internal cavity 10-1, second internal cavity 10-2, third internal cavity 10-3, and fourth internal cavity 10-4. Several internal cavities can be separated by bulkheads, such as the first bulkhead 14-1 and the second bulkhead 14-2. With reference returned to FIGs 1-2, and 4-6B, and further reference to FIG. 5A-C, an internal cavity 10 may comprise a volume defined by the body of probe 4 and optionally a bulkhead, such as first bulkhead 14-1 and/or second bulkhead 14-2. In various embodiments, the protective hull 5 extends within the internal cavity 10 and lines a surface of the internal cavity 10. The volume can be configured to provide space for housing other components of the air data probe 1 and can be configured to be in fluid communication with both the environment 2 and a sensor 11. In various embodiments, a heating element 9 is disposed within the internal cavity 10. Thus the internal cavity 10 can receive thermal energy from the heating element 9 and can facilitate the transfer, such as by conduction, convection, and/or radiation, of thermal energy to the body of the probe 4 and/or the protective hull 5, whereby the accumulation of ice in the air data probe 1 can be ameliorated.
    [0018] The air data probe 1 may comprise a heating element 9. The heating element 9 may comprise an electrically heated wire, although the heating element 9 may comprise fluid passages for circulating hot fluid, or it may comprise any apparatus in which the air data probe 1 can be heated. In various embodiments, the protective shell 5 extends into the internal cavity 10 and lines a surface of the heating element 9.
    [0019] The air data probe 1 may comprise a sensing port 3. The sensing port 3 may provide a defined opening through the body of the probe 4 that fluidly connects the internal cavity 10 with the environment 2. While, with reference to FIGs. 1 and 4, a sensing port 3 may provide a defined opening through the body of the probe 4, with reference to FIGs. 2 and 5, a sensing port 3 may comprise additional functionalities. For example, the sensing port 3 may comprise a recess in the sensing port 6. The recess in the sensing port 6 may comprise a notch in the body of the probe 4. The notch may comprise a pit, or a cylindrical groove or a trapezoidal print , or any region of shape of the body of the probe 4 in which at least one discontinuity and/or inflection point on the surface of the body of the probe 4 is disposed. The sensing port recess 6 can be disposed at an outer end of the probe body 4 with respect to environment 2 (for example, the farthest portion of mounting frame 20 (FIG. 1)). In additional embodiments, the sensing port recess 6 is disposed on one side of the probe body 4 (FIG. 3), or at any point in the probe body 4 where environment 2 is desired to be sampled.
    [0020] The sensing port 3 may comprise a protective port hull section 7. The protective port hull section 7 may comprise a protective hull portion 5 having increased thickness (e.g. it traverses a greater distance measured along a normal path with a plane tangent to an adjacent surface of the probe body 4 and extending outwardly therefrom), such as to encompass the recess of the sensing port 6 and also follows the surface of the probe body 4. In in other words, the protective door hull section 7 may comprise a portion of the protective hull that covers the notch comprising the recess of the sensing door 6 so that the protective hull 5 forms a substantially continuous coating (e.g. the inflection point removed). In other words, the notch can be said to be smoothed.
    [0021] Furthermore, the sensing port 3 may comprise a port passage 8. The port passage 8 may comprise an opening defined by at least one of the port protective hull section 7 and the probe body 4 and extending through the protective port hull section 7 and the probe body 4 such that the internal cavity 10 is in fluid communication with the environment 2. In various embodiments, the port passage 8 is aligned coincident with the geometric center of the port recess. sensor 6. However, in various embodiments the port passage 8 can have any shape or position as desired. Thus, it can be seen that at least a portion of the port passage 8 extends through the protective hull 5. Thus, the protective port hull section 7 of the protective hull 5 can align the port passage 8 and improve corrosion of the air data probe 1 near the port passage 8. In various embodiments, the port protective hull section 7 entirely defines the port 8 passage, such that fluid flowing from the environment 2 through the port passage 8 does not contact probe body 4 while transiting port 8 passage. Stated differently, port 8 passage can be defined through probe body 4 and lined with at least a portion of port 7 protective hull section of the protective hull 5. Thus, in this way, the corrosion resistant features of the protective hull 5 can be extended to the passage of the door 8, thereby improving corrosion along the passage of the door 8.
    [0022] With specific reference to FIGs. 3 and 6B, an air data probe 1 can also comprise a drain hole 12. A drain hole 12 can be an opening defined through the protective hull 5 and the body of the probe 4 and allowing accumulated moisture to drain to from the air data probe.
    [0023] Having discussed various aspects of air data probe 1, attention is turned to FIG. 3 for a discussion of various exemplary embodiments of the air data probe having a plurality of internal cavities 10 and sensing ports 3. For example, an air data probe may have a first sensing port 3-1. The first sensing port 3-1 may be in fluid communication with a first internal cavity 10-1. The first sensing port 3-1 can be defined by the probe body and positioned at an outer end of the probe body and in fluid communication with an environment. In this way, the first sensing port 3-1 can receive a dynamic pressure to be sensed by an air velocity indication system to determine the air velocity.
    [0024] The air data probe may have a second sensing port 3-2 and a third sensing port 3-3. The second sensing port 3-2 may be in fluid communication with a second internal cavity 10-2, and a third sensing port 3-3 may be in fluid communication with a third internal cavity 10-3. The second sensing port 3-2 and the third sensing port 3-3 can be arranged on radially opposite taper sides of the air data probe 1. In this way, the second sensing port 3-2 and the third port Sensing devices 3-3 can receive both differential and common-mode pressure components to be sensed by an angle of attack indication system to determine an angle of attack (AOA) with respect to an air stream.
    [0025] Finally, the air data probe may have a fourth sensing port 3-4 and a fifth sensing port 3-5. The fourth sensing port 3-4 and the fifth sensing port 3-5 may be in fluid communication with a fourth internal cavity 10-4. Each of the fourth sensing port 3-4 and the fifth sensing port 3-5 can be arranged on the sides of the air data probe 1. In this way, the fourth sensing port 3-4 and the fifth sensing port 3 -5 can either receive the static pressure to be sensed by an altitude indication system to determine a pressure altitude.
    [0026] Bulkheads can be arranged on air data probe 1 to isolate internal cavities from each other and from other features of air data probe 1, such as drain holes 12. For example, the first bulkhead 14-1 can isolate the first internal cavity 10-1 and the fourth internal cavity 10-4. The second bulkhead 14-2 can seal the fourth internal cavity 10-4 such as to prevent fluid communication with drain holes 12.
    [0027] Each of sensing ports 3-1, 3-2, 3-3, 3-4, and 3-5 can comprise the various features discussed here, such as to improve freezing and/or ice formation and to further improve corrosion.
    [0028] Having discussed various aspects of the air data probe 1, various methods of fabrication of the air data probe 1 are provided. Referring to FIGs. 1-6B and FIG. 7, a method 500 of manufacturing the air data probe 1 may comprise forming the body of the probe 4 (Step 501). The body of the probe 4 can be formed undersized with respect to the final desired size of the air data probe 1, such as to allow the thickness of the protective hull 5 to be added subsequently. In various embodiments, internal cavity 10 is formed, such as by drilling and/or as a portion contemporaneous with the formation of step 501 (Step 503). The internal cavity 10 can be drilled to a final size, or in additional embodiments, it can be drilled undersized, such as to allow for post finishing, or it can be drilled oversized, such as to allow the thickness of a protective hull 5 to be added to the internal cavity 10 later. Protective hull 5 can be added to probe body 4 (Step 505). In various embodiments, the protective hull 5 is additionally added to at least one of the inner cavity 10 and the heating element 9. Components of the air data probe 1 can be inserted into the inner cavity 10 (such as a heating element 9 , bulkheads, pressure lines, etc.) and in various modes, vacuum brazed or otherwise tightened in place (Step 507). At this point, several high temperature processing steps that tend to cause the air data probe 1 to warp have been completed. Thus the final profile of air data probe 1 can be machined (Step 509). Sensing port 3 can be formed (Step 511). For example, a port passage 8 can be perforated as well as any other opening in the air data probe 1, such as drain holes, static ports and the like. The port 8 passage can be defined through the probe body 4 and lined by at least a portion of the port protective hull section 7 of the protective hull 5. Thus, an air data probe 1 can be manufactured having the dimensions of a standard air data probe, but having additionally improved corrosion resistance features. In various embodiments at least some of these steps can be carried out simultaneously and/or the order of steps can be changed. For example, step 507 can be performed earlier than step 505.
    [0029] In various embodiments, the protective hull 5 is added to at least one of the probe body 4, the internal cavity 10 and the heating element 9 by an additive manufacturing technique. For example, the protective hull 5 can be added by laser coating. In additional embodiments, the protective hull 5 can be added by plasma spraying, eg cold spraying (eg dynamic gas cold spraying).
    [0030] In various embodiments, the air data probe 1 may comprise multiple materials, or any suitable material configuration to enhance or enhance the resilience and/or support of the system when subject to wear and tear in an aircraft operating environment or to satisfy other desired material, electromagnetic, physical, or chemical properties, for example, weight, heat tolerance, thermal conductivity, radar signature, ferromagnetic properties, ductility, strength, durability, and other properties.
    [0031] While the systems described here have been described in the context of aircraft applications; however, it can be seen in light of the present description, that the systems described here can be used in various other applications, for example, different vehicles, such as cars, trucks, buses, trains, boats, and submersible vehicles, space vehicles including manned and unmanned orbital and suborbital vehicles, or any other vehicle or device, or in conjunction with industrial processes, or propulsion systems, or any other system or process having the need for pressure sensing in extreme temperature environments and/or environments of extreme humidity.
    [0032] Benefits, other advantages, and solutions to problems have been described here with respect to specific modalities. Additionally, the connecting lines shown in the various figures contained herein are intended to represent examples of functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections can be present in a practical system. However, benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced should not be interpreted as critical, necessary, or essential features or elements of the invention . The scope of the invention is to be appropriately limited by nothing more than the appended claims, in which reference to a singular element is not intended to mean "one and only one" unless explicitly stated so, but instead “one or more”. Furthermore, where a phrase similar to "at least one of A, B, or C" is used in the claims, the phrase is intended to be interpreted to mean that A alone may be present in a modality, B alone may be present in an modality, C alone can be present in an modality, or that any combination of elements A, B, and C can be present in a single modality; for example, A and B, A and C, B and C, or A and B and C.
    [0033] Systems, methods and apparatus are provided here. In the detailed description here, references to "various embodiments", "a modality", "the modality", "an example of a modality", etc., indicate that the described modality may include a particular functionality, structure, or feature, but each modality may not necessarily include the particular functionality, structure or feature. Furthermore, such phrases are not necessarily in reference with the same modality. Additionally, when the particular functionality, structure, or feature is described in conjunction with an embodiment, it is claimed that it is within the knowledge of one skilled in the art to affect that functionality, structure, or feature in conjunction with other embodiments if it is explicitly described or do not. After reading the description, it will be apparent to a person skilled in the relevant art how to implement the description in alternative embodiments.
    [0034] Additionally, no element, component, or method step in this description shall be publicly dedicated regardless of whether the element, component, or method step is explicitly cited in the claims. No claim element here is to be interpreted under the provisions of 35 U.S.C. 112(f), unless the element is explicitly cited using the phrase "means to". As used herein, the terms "comprises", comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus comprising a list of elements does not include only those elements but may include other elements not expressly listed or inherent in such process, method, article, or apparatus.
    权利要求:
    Claims (14)
    [0001]
    1. Air data probe (1), comprising: a protective hull (5) comprising a coating of material applied to a probe body (4) and isolating a surface of the probe body (4) from fluid communication with an environment (two); a first sensing port (3-1) defined by the probe body (4) and positioned at an outermost end of the probe body (4) and in fluid communication with the environment (2); a first internal cavity (10-1) comprising a volume defined by the probe body (4) and disposed internally to the probe body (4), the first internal cavity (10-1) in fluid communication with the first sensing port ( 3-1); and a heating element (9) within the first internal cavity (10-1), whereby at least one of the probe body (4) and the protective hull (5) is heated; and characterized by the fact that the protective hull (5), to control the distribution of thermal energy, comprises a variation of local thickness of the protective hull (15) which comprises a thickening of such protective hull (5) and of the probe body (4 ) comprise a local thickness variation of the probe body (16) which comprises a thinning of such probe body (4) corresponding to the local thickness variation of the protective hull (15).
    [0002]
    2. Air data probe (1) according to claim 1, characterized in that the probe body (4) extends from a mounting structure (20) comprising an aircraft.
    [0003]
    3. Air data probe (1) according to claim 1, characterized in that the probe body (4) comprises nickel and the protective shell (5) comprises at least one of a nickel alloy - austenitic chromium and stainless steel.
    [0004]
    4. Air data probe (1) according to claim 1, characterized in that the protective hull (5) additionally comprises a material coating applied to the first sensing port (3-1) and which isolates a surface of the first sensing port for fluid communication with the environment (2).
    [0005]
    5. Air data probe (1) according to claim 4, characterized in that the protective hull (5) additionally comprises a coating of material applied to the heating element (9) and which insulates a surface of the heating element (9) of fluid communication with the environment (2).
    [0006]
    6. Air data probe (1) according to claim 1, characterized in that it further comprises: a second sensing port (3-2) defined by the probe body (4) and positioned on one side of the body of the probe (4) and in fluid communication with the environment (2); a second internal cavity (10-2) comprising a volume defined by the probe body (4) and disposed internally to the probe body (4), the second internal cavity (10-2) in fluid communication with the second sensing port ( 3-2).
    [0007]
    7. Air data probe (1) according to claim 1, characterized in that the first sensing port (3-1) comprises: a recess of the sensing port (6) comprising a notch formed in the body of the probe (4); a door protective hull section (7) comprising a portion of the protective hull disposed over the sensing door recess (6) and forming a continuous surface over the notch; and a door passage (8) comprising an opening which is defined by the door protective hull section (7) and in fluid communication with the environment (2) and the first internal cavity (10-1), and whereby a portion of the protective door hull lines the door passage (8).
    [0008]
    8. Air data probe (1) according to claim 7, characterized in that the passage of the port (8) is aligned coincident with a geometric center of the recess of the sensing port (6).
    [0009]
    9. Air data probe (1) according to claim 7, characterized in that the notch comprises a depression.
    [0010]
    10. Air data probe (1) according to claim 7, characterized in that the notch comprises at least one inflection point.
    [0011]
    11. Air data probe (1) according to claim 7, characterized in that the probe body (4) and the protective hull (5) comprise adjacent materials in a galvanic series graph.
    [0012]
    12. A method of making (500) an air data probe (1), the method comprising: forming (501) a probe body (4); forming (503) an internal cavity (10-1) within the probe body (4); applying (505) a protective shell (5) to the probe body (4) by an additive manufacturing technique; inserting (507) a heating element (9) into the internal cavity (10-1); machining (509) a final profile of the air data probe (1); and forming (511) a sensing port (3-1) comprising a port passage defined through the probe body (4) and lined with a portion of the protective hull (5); and characterized in that the protective hull (5), to control the distribution of thermal energy, comprises a variation of local thickness of the protective hull (15) which comprises a thickening of such protective hull (5) and of the probe body ( 4) comprise a local thickness variation of the probe body (16) which comprises a thinning of such probe body (4) corresponding to the local thickness variation of the protective hull (15).
    [0013]
    13. Method according to claim 12, characterized in that forming (511) the sensing port further comprises: forming a recess in the sensing port (6) comprising a notch formed in the body of the probe (4); and applying the portion of the protective hull (5) disposed over the recess of the sensing port (6) and forming a continuous surface over the notch, wherein the passage of the port (8) comprises an opening which is defined by the portion of the protective hull (5) and in fluid communication with an environment (2) and the internal cavity.
    [0014]
    14. Method according to claim 13, characterized in that the passage of the door (8) is aligned coincident with a geometric center of the recess of the sensing door (6).
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    CN106052722A|2016-10-26|
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    US20170343576A1|2017-11-30|
    CN106052722B|2019-12-24|
    BR102016003681A2|2016-10-04|
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    法律状态:
    2016-10-04| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2020-07-28| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-12-08| B07A| Technical examination (opinion): publication of technical examination (opinion) [chapter 7.1 patent gazette]|
    2021-03-30| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-05-25| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 22/02/2016, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201562142341P| true| 2015-04-02|2015-04-02|
    US62/142,341|2015-04-02|
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