Temperature sensor assembly

Abstract

The invention relates to a temperature sensor assembly comprising: a mounting seat fixed to and passing through a housing, the mounting seat partially passing through a housing through-hole of the housing and comprising a temperature transfer portion located outside an aircraft and a seat portion located inside the aircraft, at least a portion of the temperature transfer portion fits an outer surface of the housing, and a temperature sensor fixed to the seat portion and measuring a temperature of the temperature transfer portion.

Description

Technical Field

[0001] The present invention relates to a temperature sensor assembly, in particular to a temperature sensor assembly for measuring the outer surface temperature of a shell of an aircraft. The present invention belongs to the field of aircraft flight test. Background Art

[0002] When testing a new model of aircraft, in order to meet the requirements of the test flight subjects, it is necessary to measure the temperature of the outer surface of the aircraft shell.

[0003] At present, when conducting temperature tests on the outer surface of an aircraft, a temperature sensor is usually installed on the outer surface of the aircraft, that is, the temperature sensor is pasted and sealed on the outer surface of the aircraft. In this process, it is necessary to install temperature sensors and cables on the outer surface of the aircraft, open holes in the aircraft skin, and seal the holes in the skin.

[0004] At the same time, it is necessary to evaluate the impact of installing equipment on the aircraft's outer surface on the aerodynamic shape, and to process the temperature sensors to be installed on the aircraft's outer surface to reduce the impact on the aircraft's aerodynamic shape. This has the disadvantages of complex process and adverse effects on the aircraft's aerodynamic shape.

[0005] In addition, the sensor is attached to the outer surface of the aircraft by adhesive, and the poor fit with the aircraft leads to low accuracy in measuring the temperature of the outer surface of the aircraft. The performance of the adhesive deteriorates with the change of the external ambient temperature (high temperature, low temperature, etc.), so the installation life of the sensor is limited and periodic maintenance is required.

[0006] The method of installing temperature sensors on the outer surface of an aircraft has problems such as complex process, adverse effect on the aerodynamic shape of the aircraft, reduced measurement accuracy, and shortened installation life due to the decrease in adhesive performance as the temperature environment decreases. In order to solve the above problems, the invention was created.

[0007] Therefore, there is an urgent need to propose a temperature sensor assembly that has a simple structure, is easy to install, has little impact on the aerodynamic shape of the aircraft, and has a long installation life. Summary of the invention

[0008] In view of the above problems in the prior art, the inventor provides a temperature sensor assembly for measuring the temperature of the outer surface of the aircraft shell to meet the requirements of flight test subjects.

[0009] In a first example of the temperature sensor assembly, the temperature sensor assembly includes: a mounting base, which is fixed to and passes through the shell, the mounting base partially passes through the shell through hole of the shell and includes a temperature transfer part located outside the aircraft and a seat part located inside the aircraft, at least a part of the temperature transfer part is attached to the shell outer surface of the shell, and a temperature sensor, which is fixed to the seat part and measures the temperature of the temperature transfer part.

[0010] In a second example of the temperature sensor assembly, optionally including the first example, the temperature transfer portion and the seat portion of the mount are integrally formed.

[0011] In a third example of the temperature sensor assembly, optionally including one or more of the first and second examples, the temperature transfer portion and the seat portion of the mounting seat are independent components from each other, and the temperature transfer portion is in direct contact with a portion of the seat portion that passes through the shell through-hole of the shell.

[0012] In a fourth example of the temperature sensor assembly, optionally including one or more of the first to third examples, the temperature transfer portion of the mount has a convex first side facing the environment and / or a second side that fits the outer surface of the housing of the housing.

[0013] In a fifth example of the temperature sensor assembly, optionally including one or more of the first to fourth examples, the mounting seat has a rivet shape as a whole, wherein the temperature transfer portion has a rivet head shape, and the seat portion has a rivet body shape. The first side of the temperature transfer portion is exposed to the environment, forming a rivet head shape with high structural strength and aerodynamic properties.

[0014] In a sixth example of the temperature sensor assembly, which optionally includes one or more of the first to fifth examples, the seat portion of the mounting seat has a clamping pattern portion on its outer peripheral surface that is adapted to the shape of the tool, thereby making it easy to clamp the seat portion of the mounting seat manually or with a tool.

[0015] In a seventh example of the temperature sensor assembly, optionally including one or more of the first to sixth examples, the outer peripheral surface of the seat portion of the mounting seat is at least partially cylindrical, and the seat portion has threads on the outer peripheral surface near the temperature transfer portion, and the temperature sensor assembly further includes a nut that cooperates with the threads. The mounting seat is held in position by a threaded fastener.

[0016] In an eighth example of the temperature sensor assembly, optionally including one or more of the first to seventh examples, the temperature sensor assembly further includes a gasket disposed between the nut and the inner surface of the shell to prevent the inner surface of the shell from being damaged by the nut.

[0017] In a ninth example of the temperature sensor assembly, optionally including one or more of the first to eighth examples, a seat portion of the mount includes an open cavity for accommodating the temperature sensor so as to easily place a box to access the temperature sensor.

[0018] In a tenth example of the temperature sensor assembly, optionally including one or more of the first to ninth examples, a sensor cable of the temperature sensor extends away from the mounting seat, so as to facilitate the wiring and installation of the cable.

[0019] Compared with the existing structure of adding temperature sensors, the temperature sensor assembly of the present invention can closely fit the outer surface of the aircraft to improve the stability of temperature measurement; can reduce the installation of equipment and accessories on the outer surface of the aircraft to reduce the adverse effects on the aerodynamic shape of the aircraft; can meet the requirements of aircraft structural integrity and avoid temporary problems in the installation of test cables for flight tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to describe the implementation of the above and other features of the present invention, a more particular description of the invention briefly described above will be presented with reference to the exemplary embodiments of the invention shown in the accompanying drawings. It will be understood that these drawings only depict exemplary embodiments of the invention and should not be considered as limiting the scope thereof. The invention will be described and explained through the use of the accompanying drawings and with additional features and details. In the drawings:

[0021] Figure 1 is a side view of a temperature sensor assembly according to an embodiment of the present invention in an installed state; and

[0022] Figure 2 is a side cross-sectional view of a temperature sensor assembly according to an embodiment of the present invention.

[0023] The drawings are roughly drawn to scale, however, the dimensions in the drawings are only schematic and not necessarily drawn strictly to scale, but are intended to provide a clearer description. In other embodiments, other relative dimensions may be used.

[0024] Here and throughout the following, identical features appearing in different figures are denoted by identical or similar reference numerals.

[0025] List of reference numerals:

[0026] 1 Temperature sensor assembly

[0027] 2 Housing

[0028] 2a Shell outer surface

[0029] 2b Inner surface of the shell

[0030] 2c Shell through hole

[0031] 100 Mount

[0032] 110 Temperature transfer section

[0033] 110a First side

[0034] 110b Second side

[0035] 120 Seat Section

[0036] 120a outer peripheral surface

[0037] 120b Open chamber

[0038] 121 Thread

[0039] 122 Clamping pattern part

[0040] 200 Temperature Sensor

[0041] 210 Temperature sensor cable

[0042] 300 Nut

[0043] 400 Gasket DETAILED DESCRIPTION

[0044] Firstly, the present invention mainly relates to tools related to temperature measurement in any mechanical field. In particular, the present invention relates to the field of aircraft temperature measurement, for example, the temperature measurement at the outer surface of the aircraft shell, but not limited to the temperature measurement at this location. Determining where the temperature needs to be measured, for example based on the requirements of the test items during the test flight of the aircraft, is not within the scope of the present invention.

[0045] As used herein, the term “fixed” is intended to describe a component that is connected to another component and is capable of maintaining a constant relative position to each other so that forces, torques, etc. can be transferred from one component to the other.

[0046] "Shape adaptation" in the context of the present invention is intended to describe that the shape of at least a portion of one component and the shape of at least a portion of another component can match each other. The "shape adaptation" does not require complete shape matching, but can be partial shape matching. For example, one component is convex and can be received in a curved recess of another component, or the key of one component can be partially received in the groove of another component. As long as there is a force transmission path, no matter how many, it is within the scope of the present invention.

[0047] Directional terms used herein, such as "top", "bottom", "upper", "lower", "inner", "inward", "outer", and "outward", are used to assist in describing the present invention according to the orientation of the embodiments shown in the drawings. Unless otherwise specified, such as "horizontal direction", "direction of gravity", etc., directional terms are not absolute up, down, horizontal, vertical, etc., and should not be interpreted as limiting the present invention to any particular direction.

[0048] As used herein, the term "axial" and variations thereof refer to a direction extending generally along an axis of symmetry, a central axis, an axis of rotation, or the elongated direction of a specific component or system. For example, an axially extending feature of a component may be a feature extending generally along a direction parallel to the axis of symmetry or the elongated direction of the component. Further, for example, axially aligned components may be configured so that their axes of rotation are aligned. Similarly, as used herein, the term "radial" and variations thereof refer to a direction generally perpendicular to a corresponding axial direction. For example, a radially extending structure of a component may extend generally, at least partially, along a direction perpendicular to the longitudinal or central axis of the component. As used herein, the term "circumferential" and variations thereof refer to a direction extending around the periphery of an object, or around an axis of symmetry, an axis of rotation, a central axis, or the elongated direction of a specific component or system.

[0049] As used herein, the terms "comprising," "having," "including," and variations thereof are intended to serve as open-ended transitional phrases, terms or words requiring the presence of specified elements / steps and also allowing for the presence of other elements / steps.

[0050] In the present invention, unless explicitly stated to the contrary, the terms "first", "second", etc. are not intended to indicate any difference in order, position, quantity or importance, but are merely used as labels to distinguish different positions and components, and to distinguish one element, component, region and / or position from another element, component, region and / or position.

[0051] In a non-limiting example, the temperature sensor assembly 1 of the present invention includes a mount 100 .

[0052] The mount 100 may include a temperature transfer portion 110 and a seat portion 120 , wherein the temperature transfer portion 110 and the seat portion 120 may be a single component formed integrally, or may be two components that are independent of each other and in direct contact.

[0053] The outer peripheral surface 120 a of the seat portion 120 of the mounting seat 100 may have a clamping pattern portion 122 adapted to the shape of a tool, so as to facilitate the positioning and fixing of the temperature sensor 200 and the operation of the installer.

[0054] The clamping pattern 122 may include a plurality of clamping patterns 122, such as two, three, four or more, optionally equally spaced in the circumferential direction around the seat portion 120. The clamping pattern 122 may be, but is not limited to, a flat, raised striped, raised grained area.

[0055] The outer peripheral surface 120a of the seat portion 120 of the mounting seat 100 may be at least partially cylindrical, and the seat portion 120 has a thread 121 on the outer peripheral surface 120a near the temperature transfer portion 110 for mating with the nut 300 of the temperature sensor assembly 1, which will be described in detail below. The thread 121 may be a female thread or a male thread, and has a pitch suitable for tightening the nut 300.

[0056] The seat portion 120 of the mounting seat 100 may have an open cavity 120b for accommodating the temperature sensor 200 of the temperature sensor assembly 1, which will be described in detail below. The open cavity 120b may be a blind hole in the seat portion 120 and the bottom of the blind hole is formed by the temperature transfer portion 110 or contacts the temperature transfer portion 110.

[0057] In a non-limiting example, the temperature sensor assembly 1 of the present invention includes a temperature sensor 200. The temperature sensor 200 may be a commercially available temperature sensor, which acquires the temperature of the location to be measured and converts it into a test signal, which is transmitted to the acquisition device through the temperature sensor cable 210.

[0058] The temperature sensor 200 is shaped to fit and be fixable to the seat portion 120 of the mount 100 described above.

[0059] The temperature sensor 200 may be disposed in the open cavity 120b as described above in order to be fixed to the seat portion 120. Preferably, the gap between the temperature sensor 200 and the open cavity 120b is within 1 mm, ensuring the test accuracy of the components and the ease of installation of the temperature sensor 200 in the open cavity 120b.

[0060] When the temperature transfer portion 110 and the seat portion 120 of the mounting seat 100 are integrally formed, the bottom of the blind hole of the open chamber 120b is formed by the temperature transfer portion 110, and the temperature sensor 200 directly contacts the temperature transfer portion 110, measures the temperature of the temperature transfer portion 110, and indirectly measures the temperature of the shell outer surface 2a of the shell 2 of the aircraft.

[0061] When the temperature transfer portion 110 and the seat portion 120 of the mounting base 100 are independent components, the bottom of the blind hole is formed by the seat portion 120 and contacts the temperature transfer portion 110, and the temperature sensor 200 indirectly contacts the temperature transfer portion 110, and also indirectly measures the temperature of the shell outer surface 2a of the aircraft's shell 2.

[0062] In addition, the form in which the temperature sensor 200 is fixed to the seat portion 120 of the mounting seat 100 is not limited thereto. For example, the seat portion 120 may be a frame structure or a single or multiple pillars, or other structural forms suitable for fixing the temperature sensor 200, so that the temperature sensor 200 can be grounded to measure the temperature of the outer shell surface 2a of the shell 2 of the aircraft.

[0063] The present invention will be further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0064] Figure 1 The figure schematically shows a side view of a temperature sensor assembly according to an embodiment of the present invention in an installed state.

[0065] The temperature sensor assembly 1 of the present invention includes a mounting seat 100, which is fixed to and passes through the shell 2 (e.g., the outer skin) of the aircraft, the mounting seat 100 partially passes through the shell through hole 2c of the shell 2 and includes a temperature transfer portion 110 located outside the aircraft and a seat portion 120 located inside the aircraft, wherein at least a portion of the temperature transfer portion 110 is in contact with the shell outer surface 2a of the shell 2 for transferring the temperature of the shell outer surface 2a.

[0066] Preferably, the mounting seat 100 may have a rivet shape as a whole, wherein the temperature transfer portion 110 has a rivet head shape, and the seat portion 120 has a rivet body shape. Considering that the temperature transfer portion 110 will be exposed to the environment during normal use of the temperature sensor assembly 1, the temperature transfer portion 110 in the nail head shape may have a convex first side 110a facing the environment, wherein the first side 110a may be the sensing side of the temperature sensor 200, which may have a higher structural strength than a flat shape and minimize the adverse effect on the aerodynamic shape of the aircraft.

[0067] The temperature sensor 200 can be fixed to the seat portion 120 and measure the temperature of the temperature transfer portion 110 of the mounting seat 100, and the temperature transfer portion 110 can have a second side 110b that fits the shell outer surface 2a of the shell 2, wherein the second side 110b can be the sensing side of the temperature sensor 200, and the second side 110b fits tightly with the shell outer surface 2a of the aircraft section to be tested. Therefore, compared with the existing structure of an externally mounted temperature sensor, the temperature sensor 200 can have higher testing accuracy.

[0068] Preferably, the outer peripheral surface 120 a of the seat portion 120 of the mount 100 may have a cylindrical shape near the temperature transfer portion 110 , and the seat portion 120 has a thread 121 (not shown) on the outer peripheral surface 120 a near the temperature transfer portion 110 .

[0069] The temperature sensor assembly 1 may further include a self-locking nut 300 , which cooperates with the thread 121 .

[0070] The temperature sensor assembly 1 may further include a gasket 400 , which is disposed between the nut 300 and the inner surface 2 b of the housing 2 and is used in conjunction with the self-locking nut 6 to prevent loosening during installation.

[0071] As shown in the figure, the temperature sensor cable 210 of the temperature sensor 200 extends away from the mounting seat 100 toward the interior of the aircraft, wherein the temperature sensor cable 210 is a signal transmission path of the temperature sensor 200 .

[0072] Figure 2 A side cross-sectional view of a temperature sensor assembly according to an embodiment of the present invention is schematically shown, wherein the thread 121 of the seat portion 120 on the outer peripheral surface 120a is shown. The use of fine threads here can improve the reliability of installation.

[0073] The temperature transfer portion 110 and the seat portion 120 of the mounting seat 100 in this embodiment are independent components, and the temperature sensor 200 is inserted into the open cavity 120b in the form of a blind hole, against the bottom of the blind hole formed by the seat portion 120, and the temperature sensor 200 indirectly contacts the temperature transfer portion 110, indirectly measuring the temperature of the shell outer surface 2a of the shell 2 of the aircraft.

[0074] The invention also discloses a method for installing the temperature sensor assembly.

[0075] In the first step, a rivet hole for installation connection at a position to be tested on the aircraft shell 2 can be selected as a test position, and additional holes can be avoided to ensure the structural integrity of the aircraft.

[0076] In the second step, the seat portion 120 of the mounting seat 100 is placed from outside the aircraft through the aircraft shell 2 to the ready installation position, so that the temperature transfer portion 110 of the mounting seat 100 fits the outer surface of the aircraft shell 2, so that the temperature sensor 200 can have a higher test accuracy.

[0077] In the third step, the gasket 400 and the self-locking nut 300 are pre-connected to the seat portion 120 of the mounting seat 100 inside the aircraft, and then clamped to the clamping pattern portion 122 with a clamp (such as pliers or a wrench, etc.), and then the nut 300 is installed and tightened. After the installation of the temperature sensor assembly is completed, the temperature test work can be carried out.

[0078] With the temperature sensor assembly according to the present invention, by providing a mounting seat penetrating the aircraft shell, the temperature sensor is fixed to the interior of the aircraft and still can measure the temperature of the outer surface of the aircraft shell.

[0079] Compared with the existing structure of adding temperature sensors externally, the temperature sensors of the temperature sensor assembly of the present invention can be closely attached to the outer surface of the aircraft to improve the stability of temperature measurement.

[0080] The temperature sensor assembly of the present invention has only a part of the mounting seat structure on the outer surface of the aircraft shell, and its convex shape minimizes the adverse effect on the aircraft aerodynamic shape while ensuring the structural strength.

[0081] The temperature sensor assembly of the present invention can preset skin openings and cable grooves. For example, the rivet holes at the position to be tested can be selected as the test position without additional openings, so as to ensure the structural integrity of the aircraft and the integrity of the aircraft's own cables, and avoid temporary problems such as re-layout and installation of test cables during flight tests.

[0082] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention is clearly and completely described above in combination with the specific embodiments of the present invention and the accompanying drawings.

[0083] Although various embodiments have been described above, it should be understood that the embodiments described are part of the embodiments of the present invention, rather than all embodiments, and they are presented in an exemplary rather than limiting manner. It is obvious to those skilled in the relevant art that the disclosed subject matter can be implemented in other specific forms without departing from its spirit and essential features.

[0084] In the process, various elements that are important to the present invention or are conducive to further developing the present invention will be mentioned in the content of specific examples, but some of these elements can also be used to further develop the present invention when they are separated from the content of the corresponding examples and other features of the corresponding examples. Therefore, the embodiments described above are considered to be illustrative and non-restrictive in all aspects and are not used as a basis for any limitation of the present invention.

[0085] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention. The present disclosure also includes various modifications and modifications within the equivalent scope. In addition, various combinations and methods, further including only one element, more than one or less than one other combinations and methods also belong to the scope and scope of thought of the present disclosure.

Claims

1. A temperature sensor assembly for measuring the temperature of an outer shell surface (2a) of a shell (2) of an aircraft, characterized in that: The temperature sensor assembly (1) comprises a mounting seat (100) fixed to and passing through the shell (2), the mounting seat (100) partially passing through the shell through hole (2c) of the shell (2) and comprising a temperature transfer portion (110) located outside the aircraft and a seat portion (120) located inside the aircraft, at least a portion of the temperature transfer portion (110) being in contact with the shell outer surface (2a) of the shell (2), A temperature sensor (200) is fixed to the seat portion (120) and measures a temperature of the temperature transferring portion (110).

2. The temperature sensor assembly according to claim 1, characterized in that: The temperature transfer portion (110) and the seat portion (120) of the mounting seat (100) are integrally formed.

3. The temperature sensor assembly according to claim 1, characterized in that: The temperature transfer portion (110) and the seat portion (120) of the mounting seat (100) are components independent of each other, and the temperature transfer portion (110) is in direct contact with a portion of the seat portion (120) that passes through the shell through hole (2c) of the shell (2).

4. The temperature sensor assembly according to claim 1, characterized in that: The temperature transfer portion (110) of the mounting base (100) has a convex first side (110a) facing the environment and / or a second side (110b) that fits the housing outer surface (2a) of the housing (2).

5. The temperature sensor assembly according to claim 1, characterized in that: The mounting seat (100) has a rivet shape as a whole, wherein the temperature transfer portion (110) has a rivet head shape, and the seat portion (120) has a rivet body shape.

6. The temperature sensor assembly according to claim 1, characterized in that: The outer peripheral surface (120a) of the seat portion (120) of the mounting seat (100) is provided with a clamping pattern portion (122) adapted to the shape of a tool.

7. The temperature sensor assembly according to claim 1, characterized in that: The outer peripheral surface (120a) of the seat portion (120) of the mounting seat (100) is at least partially cylindrical, and the seat portion (120) has a thread (121) on the outer peripheral surface (120a) near the temperature transfer portion (110), and The temperature sensor assembly (1) further comprises a nut (300), wherein the nut (300) cooperates with the thread (121).

8. The temperature sensor assembly according to claim 7, characterized in that: The temperature sensor assembly (1) further comprises a gasket (310), wherein the gasket (310) is arranged between the nut (300) and the housing inner surface (2b) of the housing (2).

9. The temperature sensor assembly according to claim 1, characterized in that: The seat portion (120) of the mounting seat (100) includes an open cavity (120b) that accommodates the temperature sensor (200).

10. The temperature sensor assembly according to claim 9, characterized in that The sensor cable (210) of the temperature sensor (200) extends away from the mounting base (100).

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