Calibration structure for rudder shaft dynamic thermal test and calibration system thereof

Abstract

The embodiment of the invention provides a calibration structure for a rudder shaft dynamic thermal test and a calibration system thereof, and relates to the technical field of aircraft thermal tests, the calibration structure comprises a base body, a measuring block, a sensor and a heatproof ring, the top of the base body is provided with a mounting groove, the interior of the base body is provided with a vertically through accommodating cavity, and the mounting groove is communicated with the accommodating cavity; the measuring block is arranged in the mounting groove and partially protrudes out of the mounting groove upwards, a measuring channel extending in the horizontal direction is formed in the protruding part of the measuring block, and the measuring channel is communicated with the containing cavity; the sensor is mounted in the measuring channel, and a sensing head of the sensor faces one end, close to the accommodating cavity, of the measuring channel; the heat-proof ring is arranged on the base body and surrounds the periphery of the protruding part of the measuring block, and a gap communicated with the external environment and the containing cavity is formed between the heat-proof ring and the protruding part of the measuring block. According to the embodiment of the invention, the direct measurement of the real heat flow in the narrow rudder shaft gap is realized, and the simulation authenticity and measurement safety of the ground dynamic thermal test are ensured.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft thermal testing, and in particular to a calibration structure and calibration system for dynamic thermal testing of control shafts. Background Technology

[0002] As a critical aerodynamic control component of hypersonic aircraft, the narrow gap formed at the connection between the rudder shaft and the fuselage creates an extremely harsh aerodynamic thermal environment under the impact of high-speed airflow, posing a challenge to thermal protection design. To verify the ablation resistance, heat insulation, and thermal sealing performance of the thermal protection structure at the rudder shaft gap, ground dynamic thermal tests must be conducted.

[0003] In existing technologies, the space in such gaps is extremely limited in experimental measurements, and traditional heat flow sensors are too large to be directly installed at effective measurement locations, making it difficult to obtain accurate local heat flow data. Summary of the Invention

[0004] This invention provides a calibration structure and calibration system for dynamic thermal testing of rudder shafts, to solve the technical problem that existing calibration structures in related technologies are difficult to directly measure heat flow within narrow rudder shaft gaps.

[0005] In a first aspect, embodiments of the present invention provide a calibration structure for dynamic thermal testing of a rudder shaft, comprising: The base has a mounting groove at its top and a through-cavity inside, with the mounting groove connected to the through-cavity. A measuring block is disposed in the mounting groove, and a portion of the measuring block protrudes upward from the mounting groove. The protruding portion of the measuring block is provided with a measuring channel extending in a horizontal direction, and the measuring channel communicates with the receiving cavity. A sensor is installed in the measurement channel, with the sensor head facing the end of the measurement channel near the receiving cavity; A heat-resistant ring is disposed on the substrate and is surrounded around the protrusion of the measuring block. A gap is formed between the heat-resistant ring and the protrusion of the measuring block to communicate with the external environment and the receiving cavity.

[0006] In some embodiments, The measuring block has an L-shaped structure, with at least a portion of its horizontal section protruding from the mounting groove to form the protrusion, and its vertical section used to mate with the bottom of the simulated rudder.

[0007] In some embodiments, the outer edge of the vertical segment of the L-shaped structure is a rounded corner structure.

[0008] In some embodiments, the heat shield ring has a radially penetrating opening, and the protrusion of the measuring block passes through the opening.

[0009] In some embodiments, the measuring channel has a stepped structure with progressively increasing radial dimensions at one end near the receiving cavity.

[0010] In some embodiments, the corners of each of the stepped structures are rounded.

[0011] In some embodiments, the measuring block is detachably connected to the heat shield ring.

[0012] In some embodiments, the heat shield ring is made of fiberglass.

[0013] In some embodiments, an adapter flange is also included, which is disposed at the bottom of the base.

[0014] Secondly, embodiments of the present invention provide a calibration system for dynamic thermal testing of a rudder shaft, including the aforementioned calibration structure for dynamic thermal testing of a rudder shaft.

[0015] The beneficial effects of the technical solution provided by this invention include: This invention provides a calibration structure and system for dynamic thermal testing of a rudder shaft. The calibration structure includes a base, a measuring block, a sensor, and a heat shield ring. The base has a mounting groove on its top and a through-cavity inside, with the mounting groove communicating with the cavity. The measuring block is disposed within the mounting groove, with a portion protruding upwards from the groove. The protruding portion of the measuring block has a horizontally extending measuring channel communicating with the cavity. The sensor is mounted within the measuring channel, with its sensor head facing the end of the measuring channel closest to the cavity. The heat shield ring is disposed on the base and surrounds the protruding portion of the measuring block, with a gap forming between the heat shield ring and the protruding portion of the measuring block, allowing communication between the external environment and the cavity. In this embodiment of the invention, the measuring block protrudes from the mounting groove, and the measuring channel within the protrusion provides a horizontal mounting space for the sensor, allowing the sensor head to extend directly to the simulated gap formed by the heat shield ring and the protruding portion of the measuring block. This enables direct measurement of the real heat flow within the narrow rudder shaft gap, ensuring the simulation realism and measurement safety of the ground dynamic thermal test. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A cross-sectional schematic diagram of a calibration structure for dynamic thermal testing of a rudder shaft provided in an embodiment of the present invention; Figure 2 A schematic diagram of an overall structure for a calibration structure used in dynamic thermal testing of a rudder shaft, provided in an embodiment of the present invention; Figure 3 This is another overall structural schematic diagram of a calibration structure for dynamic thermal testing of a rudder shaft provided in an embodiment of the present invention; Figure 4 This invention provides a schematic diagram of the measuring block and heat shield ring of a calibration structure for dynamic thermal testing of a rudder shaft, as provided in an embodiment of the invention. Figure label: 1. Base; 11. Mounting groove; 12. Receiving cavity; 2. Measuring block; 21. Protrusion; 211. Measuring channel; 3. Adapter flange; 4. Heat shield; 5. Simulated rudder. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] This invention provides a calibration structure and calibration system for dynamic thermal testing of rudder shafts, which can solve the technical problem that existing calibration structures in related technologies are difficult to directly measure heat flow in narrow rudder shaft gaps.

[0020] See Figure 1 , Figure 2 and Figure 3As shown in the figure, an embodiment of the present invention provides a calibration structure for dynamic thermal testing of a rudder shaft. The calibration structure includes a base 1, a measuring block 2, a sensor, and a heat shield ring 4. The base 1 has a mounting groove 11 on its top and a through-cavity 12 inside, which is connected to the cavity 12. The measuring block 2 is disposed in the mounting groove 11, and part of the measuring block 2 protrudes upward from the mounting groove 11. The protruding part 21 of the measuring block 2 has a measuring channel 211 extending horizontally, which is connected to the cavity 12. The sensor is installed in the measuring channel 211, with the sensor head facing the end of the measuring channel 211 near the cavity 12. The heat shield ring 4 is disposed on the base 1 and surrounds the protruding part 21 of the measuring block 2. A gap is formed between the heat shield ring 4 and the protruding part 21 of the measuring block 2, which communicates with the external environment and the cavity 12. In this embodiment of the invention, the measuring block 2 protrudes from the mounting groove 11, and the measuring channel 211 within its protrusion 21 provides a horizontal mounting space for the sensor. The sensor is disposed within the measuring channel 211 (not shown in the figure), allowing the sensor head to extend directly to the simulated gap formed by the heat shield ring 4 and the protrusion 21 of the measuring block 2. This enables direct measurement of the real heat flow within the narrow rudder shaft gap, ensuring the simulation realism and measurement safety of the ground dynamic thermal test.

[0021] This invention provides a calibration structure for dynamic thermal testing of a steering shaft. The calibration structure includes a base, a measuring block, a sensor, and a heat shield ring. The base has a mounting groove on its top and a through-cavity inside, with the mounting groove communicating with the cavity. The measuring block is disposed within the mounting groove, with a portion protruding upwards from the groove. The protruding portion of the measuring block has a horizontally extending measuring channel communicating with the cavity. The sensor is mounted within the measuring channel, with its sensor head facing the end of the measuring channel closest to the cavity. The heat shield ring is disposed on the base and surrounds the protruding portion of the measuring block, with a gap forming between the heat shield ring and the protruding portion of the measuring block, allowing communication between the external environment and the cavity. In this embodiment of the invention, the measuring block protrudes from the mounting groove, and the measuring channel within the protrusion provides a horizontal mounting space for the sensor, allowing the sensor head to extend directly to the simulated gap formed by the heat shield ring and the protruding portion of the measuring block. This enables direct measurement of the real heat flow within the narrow rudder shaft gap, ensuring the simulation realism and measurement safety of the ground dynamic thermal test.

[0022] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 4As shown, the measuring block 2 has an L-shaped structure, with at least a portion of its horizontal section protruding from the mounting groove 11 to form the protrusion 21, and its vertical section used to mate with the bottom of the simulated rudder 5. In this embodiment of the invention, the measuring block 2 adopts an L-shaped structure, with its horizontal section protruding from the mounting groove 11 to form the protrusion 21, allowing the sensor to be closer to the heat source area of ​​the simulated gap, improving measurement sensitivity and accuracy; at the same time, its vertical section provides a stable and reliable mounting interface for mating with the bottom of the simulated rudder 5, ensuring the structural rigidity and sealing of the entire calibration structure during the dynamic thermal test, thereby maintaining a stable measurement environment under complex thermal loads and improving the reliability and repeatability of the test data.

[0023] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 4 As shown, the outer edge of the vertical section of the L-shaped structure is rounded. In this embodiment of the invention, the rounded outer edge of the vertical section of the L-shaped structure can effectively reduce the local aerodynamic heating effect of this part in high-speed airflow, reduce thermal stress concentration, and thus improve the structural durability and long-term measurement stability of the measuring block 2 under extreme thermal environments; at the same time, the rounded transition also facilitates cooperation with the simulated rudder 5, improving practicality.

[0024] As an optional implementation, in one embodiment of the invention, as shown in Figure *, the heat shield ring 4 has a radially penetrating opening, and the protrusion 21 of the measuring block 2 passes through the opening. In this embodiment of the invention, the heat shield ring 4 adopts a ring-shaped structure with a radially penetrating opening, allowing the protrusion 21 of the measuring block 2 to pass through it, ensuring that the heat shield ring 4 provides effective thermal protection for the main body of the measuring block 2. On the other hand, a gap is formed between its opening and the protrusion 21, accurately simulating the geometric characteristics of a real rudder shaft gap. This allows the sensor to directly measure the local heat flow within the gap, which is closer to the actual flight conditions, improving the realism of the experimental simulation and the reliability of the data.

[0025] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the measuring channel 211 has a stepped structure with progressively increasing radial dimensions at one end near the receiving cavity 12. In this embodiment of the invention, the stepped structure with progressively increasing radial dimensions at one end of the measuring channel 211 near the receiving cavity 12 allows for the installation of sensors or their accessories of different sizes. The stepped transition facilitates the laying and fixing of sensor leads, reduces signal interference or damage caused by lead bending or compression, thereby improving structural stability and data accuracy.

[0026] As an optional implementation, in one embodiment of the invention, the corners of each of the stepped structures are rounded. In this embodiment, the rounded corners of each stepped structure effectively eliminate stress concentration caused by sharp angles, improving the thermal fatigue resistance and structural integrity of the measurement channel 211 under repeated thermal cycling. Simultaneously, the rounded corner transition facilitates sensor alignment and insertion during installation, reducing the risk of damage due to impacts, and further enhancing the accuracy and reliability of the measurement results.

[0027] As an optional implementation, in one embodiment of the invention, the measuring block 2 and the heat shield ring 4 are detachably connected. In this embodiment, the measuring block 2 and the heat shield ring 4 are detachably connected, allowing for independent replacement or combined adjustment, greatly enhancing the flexibility of the calibration structure, facilitating individual maintenance of the measuring block 2 and the heat shield ring 4, and improving the flexibility and efficiency of the calibration structure.

[0028] As an optional implementation, in one embodiment of the invention, the heat shield ring 4 is made of fiberglass. In this embodiment, the heat shield ring 4 is made of fiberglass, which is lightweight and high-strength. This characteristic allows the heat shield ring 4 to reduce the weight of the entire calibration structure while maintaining its supporting function, facilitating test installation and operation. Simultaneously, fiberglass has low thermal conductivity and good molding properties, effectively blocking heat transfer to the substrate 1 and the sensor, stabilizing the measurement environment, and ensuring structural reliability and measurement accuracy during the test process.

[0029] As an optional implementation, in one embodiment of the invention, the calibration structure further includes a transition flange 3, which is disposed at the bottom of the base 1. In this embodiment of the invention, by adding the transition flange 3, standardization and rapid docking between the calibration structure and different ground test equipment interfaces are achieved, significantly improving the modularity and compatibility of the entire test system. At the same time, the transition flange 3 provides the base 1 with a stable installation reference and load transfer path, ensuring the connection rigidity and reliability of the calibration structure as a whole, and guaranteeing the safety and stability of the test process.

[0030] This invention also provides a calibration system for dynamic thermal testing of a rudder shaft. The calibration system includes the aforementioned calibration structure, which comprises a base 1, a measuring block 2, a sensor, and a heat shield 4. The base 1 has a mounting groove 11 at its top and a through-cavity 12 inside, the mounting groove 11 communicating with the cavity 12. The measuring block 2 is disposed within the mounting groove 11, with a portion protruding upwards from the mounting groove 11. The protruding portion 21 of the measuring block 2 has a [missing information - likely a feature or design]. A horizontally extending measurement channel 211 communicates with the receiving cavity 12. A sensor is installed within the measurement channel 211, with its sensing head facing the end of the measurement channel 211 closest to the receiving cavity 12. A heat shield ring 4 is disposed on the base 1, surrounding the protrusion 21 of the measuring block 2, and a gap is formed between the heat shield ring 4 and the protrusion 21 of the measuring block 2, connecting the external environment to the receiving cavity 12. In this embodiment, the measuring block 2 partially protrudes from the mounting groove 11, and the measurement channel 211 within its protrusion 21 provides a horizontal mounting space for the sensor, allowing the sensor head to directly extend to the simulated gap formed by the heat shield ring 4 and the protrusion 21 of the measuring block 2. This enables direct measurement of the actual heat flow within the narrow rudder shaft gap, ensuring the simulation realism and measurement safety of the ground dynamic thermal test.

[0031] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 4 As shown, the measuring block 2 has an L-shaped structure, with at least a portion of its horizontal section protruding from the mounting groove 11 to form the protrusion 21, and its vertical section used to mate with the bottom of the simulated rudder 5. In this embodiment of the invention, the measuring block 2 adopts an L-shaped structure, with its horizontal section protruding from the mounting groove 11 to form the protrusion 21, allowing the sensor to be closer to the heat source area of ​​the simulated gap, improving measurement sensitivity and accuracy; at the same time, its vertical section provides a stable and reliable mounting interface for mating with the bottom of the simulated rudder 5, ensuring the structural rigidity and sealing of the entire calibration system during dynamic thermal testing, thereby maintaining a stable measurement environment under complex thermal loads and improving the reliability and repeatability of test data.

[0032] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 4 As shown, the outer edge of the vertical section of the L-shaped structure is rounded. In this embodiment of the invention, the rounded outer edge of the vertical section of the L-shaped structure can effectively reduce the local aerodynamic heating effect of this part in high-speed airflow, reduce thermal stress concentration, and thus improve the durability and long-term measurement stability of the calibration system under extreme thermal environment; at the same time, the rounded transition also facilitates cooperation with the simulated rudder 5, improving practicality.

[0033] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 3 and Figure 4 As shown, the heat shield ring 4 has a radially penetrating opening, and the protrusion 21 of the measuring block 2 passes through the opening. In this embodiment of the invention, the heat shield ring 4 adopts a ring-shaped structure with a radially penetrating opening, allowing the protrusion 21 of the measuring block 2 to pass through it, ensuring that the heat shield ring 4 provides effective thermal protection for the main body of the measuring block 2. On the other hand, a gap is formed between its opening and the protrusion 21, accurately simulating the geometric characteristics of the real rudder shaft gap. This allows the sensor to directly measure the local heat flow within the gap, which is closer to the actual flight conditions, improving the realism of the experimental simulation and the reliability of the data.

[0034] In the description of this invention, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0035] It should be noted that in this invention, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0036] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features of the invention herein.

Claims

1. A calibration structure for dynamic thermal testing of a rudder shaft, characterized in that, include: The base (1) has a mounting groove (11) on its top and a receiving cavity (12) that runs vertically through it. The mounting groove (11) is connected to the receiving cavity (12). Measuring block (2), the measuring block (2) is disposed in the mounting groove (11), and part of the measuring block (2) protrudes upward from the mounting groove (11). The protruding part (21) of the measuring block (2) is provided with a measuring channel (211) extending in the horizontal direction. The measuring channel (211) is connected to the receiving cavity (12). A sensor is installed in the measurement channel (211), with the sensor head facing the end of the measurement channel (211) near the receiving cavity (12); A heat shield ring (4) is disposed on the substrate (1). The heat shield ring is disposed around the periphery of the protrusion (21) of the measuring block (2). A gap is formed between the heat shield ring (4) and the protrusion (21) of the measuring block (2) to communicate with the external environment and the receiving cavity (12).

2. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that: The measuring block (2) has an L-shaped structure, with at least a portion of its horizontal section protruding from the mounting groove (11) to form the protrusion (21), and its vertical section is used to cooperate with the bottom of the simulated rudder (5).

3. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 2, characterized in that: The outer edge of the vertical section of the L-shaped structure is rounded.

4. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that: The heat shield ring (4) has a radially penetrating opening, and the protrusion (21) of the measuring block (2) passes through the opening.

5. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that: The measuring channel (211) has a stepped structure with progressively increasing radial dimensions at one end near the receiving cavity (12).

6. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 5, characterized in that: The corners of each of the stepped structures are rounded.

7. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that: The measuring block (2) is detachably connected to the heat protection ring (4).

8. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that: The heat shield (4) is made of fiberglass.

9. The calibration structure for dynamic thermal testing of a rudder shaft according to claim 1, characterized in that, Also includes: The adapter flange (3) is located at the bottom of the base (1).

10. A calibration system for dynamic thermal testing of a rudder shaft, characterized in that, The invention includes a calibration structure for dynamic thermal testing of a rudder shaft as described in any one of claims 1-9.

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