An inertial instrument temperature control structure for a fiber-optic gyroscope inertial platform

Abstract

This invention discloses a temperature control structure for an inertial instrument used in a fiber optic gyroscope inertial platform, comprising: an inner upper spherical cover, an outer upper spherical cover, a platform assembly, an inner lower spherical cover, an outer lower spherical cover, a ring frame, a perforated baffle, and a fan. The outer upper spherical cover is connected to the outer lower spherical cover via the ring frame; the inner upper spherical cover is connected to the inner lower spherical cover via the ring frame; fans are respectively disposed on the inner surface of the outer upper spherical cover, the inner surface of the outer lower spherical cover, and the outer surface of the inner upper spherical cover; the perforated baffle is installed inside the fan mounting surface of the inner upper spherical cover; the platform assembly is disposed within the space formed by the inner upper and inner lower spherical covers; and the ring frame is connected to the platform assembly. This invention reduces the impact of external environmental temperature changes and complex internal thermal fields on the temperature control accuracy of the inertial instrument, and improves the uniformity and stability of the temperature field near the platform.

Description

Technical Field

[0001] This invention belongs to the field of temperature control technology for inertial instruments used in inertial measurement devices, and particularly relates to a temperature control structure for inertial instruments used in fiber optic gyroscope inertial platforms. Background Technology

[0002] A fiber optic gyroscope inertial platform is an inertial measurement device that uses a fiber optic gyroscope as the angular motion sensing element, primarily used in high-precision inertial navigation systems. The platform mainly consists of a platform assembly (fiber optic gyroscope, accelerometer, etc.), a stabilization loop, a ring frame assembly, a precision shaft system, a base, and vibration dampers. Its working principle involves using the fiber optic gyroscope to sense changes in the angular velocity of the carrier, which is then controlled by the stabilization loop to maintain the platform assembly stable in inertial space, providing a favorable dynamic environment for the inertial instruments (accelerometer and fiber optic gyroscope).

[0003] The inertial platform has a relatively compact structure with numerous internal heat sources, including circuit boards, torque motors, heating elements, and inertial instruments. Furthermore, the frame's corner positions change in real-time with operating conditions, creating a complex thermal environment. The performance of the inertial instruments on the platform is significantly affected by temperature; temperature fluctuations within the platform system can impact the measurement and installation accuracy of the instruments. Different instruments, installed at different locations on the platform, have varying optimal operating temperatures. Strong coupling exists between the temperature control loops of individual instruments, necessitating the development of heat transfer models between the heating elements of different instruments on the platform to improve the temperature control accuracy of the instruments.

[0004] During operation, the external temperature environment of a fiber optic gyroscope inertial platform undergoes significant changes. When the external temperature is high, heat is transferred through the base to the ring frame assembly and then to the platform itself. The fan on the base dissipates heat through convection, altering the internal thermal environment. Generally, the airflow velocity is higher near the fan and almost unaffected further away, resulting in an uneven distribution of the internal airflow field, making it difficult to provide suitable environmental conditions for the temperature control system. The relative angular positions of the ring frames change with the movement of the platform, leading to variations in heat conduction, radiation, and convection between the ring frames. These internal and external environmental factors prevent the platform system from maintaining a constant state of thermal equilibrium. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform, which reduces the impact of external environmental temperature changes and internal complex thermal fields on the temperature control accuracy of inertial instruments and improves the uniformity and stability of the temperature field near the platform.

[0006] The objective of this invention is achieved through the following technical solution: a temperature control structure for an inertial instrument used in a fiber optic gyroscope inertial platform, comprising: an inner upper spherical cover, an outer upper spherical cover, a platform assembly, an inner lower spherical cover, an outer lower spherical cover, a ring frame, a perforated baffle, and a fan; wherein, the outer upper spherical cover is connected to the outer lower spherical cover via the ring frame; the inner upper spherical cover is connected to the inner lower spherical cover via the ring frame; the fan is respectively disposed on the inner surface of the outer upper spherical cover, the inner surface of the outer lower spherical cover, and the outer surface of the inner upper spherical cover; the perforated baffle is installed inside the fan mounting surface of the inner upper spherical cover; the platform assembly is disposed within the space formed by the inner upper spherical cover and the inner lower spherical cover; the ring frame is connected to the platform assembly.

[0007] In the above-mentioned temperature control structure for inertial instruments in the fiber optic gyroscope inertial platform, the outer surfaces of the upper outer spherical cover and the lower outer spherical cover are both finned heat dissipation structures, and the inner surfaces of the upper outer spherical cover and the lower outer spherical cover are coated with a high thermal conductivity material.

[0008] In the above-mentioned temperature control structure for inertial instruments used in fiber optic gyroscope inertial platforms, both the upper inner spherical cover and the lower inner spherical cover are provided with slots.

[0009] In the temperature control structure of the inertial instrument for the aforementioned fiber optic gyroscope inertial platform, the perforated baffle has circular holes of different diameters distributed radially to prevent the fan from blowing directly onto the platform components and causing local temperature changes, thus ensuring uniform gas flow in all directions at the fan inlet.

[0010] The temperature control structure for the inertial instrument of the aforementioned fiber optic gyroscope inertial platform further includes a temperature sensor; wherein the temperature sensor is respectively installed on the platform assembly, the ring frame, the inner upper spherical cover, the inner lower spherical cover, the outer upper spherical cover, and the outer lower spherical cover.

[0011] The above-mentioned temperature control structure for inertial instruments in the fiber optic gyroscope inertial platform also includes: a window cover; wherein, both the outer upper spherical cover and the outer lower spherical cover are uniformly provided with heat dissipation windows, and the window cover is installed on the heat dissipation windows by a sealing ring.

[0012] In the temperature control structure of the inertial instrument for the aforementioned fiber optic gyroscope inertial platform, a multi-level temperature conduction model is established by collecting temperature data from temperature sensors. Based on the multi-level temperature conduction model, the fan speed and the duty cycle of the heating element of the platform components are controlled in real time to achieve the stability of the inertial instrument's equilibrium temperature.

[0013] In the above-mentioned temperature control structure for inertial instruments in the fiber optic gyroscope inertial platform, the multi-stage temperature conduction model is obtained through the following formula:

[0014] T = T0 + Λ·Δ;

[0015] Where T is the temperature vector at a temperature point, T0 is the temperature vector at each temperature point at room temperature, Δ is the duty cycle vector, and Λ is the temperature field influence factor matrix.

[0016] In the temperature control structure of the inertial instrument used in the aforementioned fiber optic gyroscope inertial platform, the temperature field influence factor matrix is ​​obtained through the following method: The heating element of the platform is energized and heated until equilibrium is reached, at which point the temperature T of the first x-gyroscope is measured. gx1 First y-gyroscope temperature T gy1 First z-gyroscope temperature T gz1 First quartz body temperature T a1 The heating element of the X gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the second X gyroscope is measured. gx2 The second y-gyroscope temperature T gy2 The second z-gyroscope temperature T gz2 The temperature T of the second quartz body a3 The heating element of the Y-gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the third x-gyroscope is measured. gx3 The third y-top temperature T gy3 The third z-gyroscope temperature T gz3 The temperature of the third quartz body, T a3 The heating element of the Z-gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the fourth x-gyroscope is measured. gx4 The fourth y-top temperature T gy4 The fourth gyroscope temperature T gz4 Fourth quartz body temperature T a4 The quartz watch heating element is energized and heated until equilibrium is reached, at which point the temperature T of the fifth gyroscope is measured. gx5 Fifth y-top temperature T gy5 Fifth gyroscope temperature T gz5 Fifth quartz body temperature T a5 According to the second x-gyroscope temperature T gx2 and the first x-gyroscope temperature T gx1 The first x-shaped gyroscope temperature difference is obtained by subtracting the first x-shaped gyroscope temperature difference, and then the second y-shaped gyroscope temperature T is obtained. gy2 and the first y-gyroscope temperature T gy1 The first y-top temperature difference is obtained by subtracting the first y-top temperature difference, based on the second z-top temperature T. gz2 and the first z-gyroscope temperature T gz1 The temperature difference of the first gyroscope is obtained by subtracting the difference, based on the temperature T of the second quartz watch body. a2 and the temperature T of the first quartz body a1 The difference is obtained by subtracting the temperature difference of the first quartz watch body; based on the temperature T of the third x-gyroscope... gx3 Second x gyroscope temperature T gx2 The difference is used to obtain the second x-type gyroscope temperature difference, based on the third y-type gyroscope temperature T. gy3Second y-gyroscope temperature T gy2 The second y-top temperature difference is obtained by subtracting the values, and then the third z-top temperature T is used as the basis. gz3 Second z-gyroscope temperature T gz2 The second gyroscope temperature difference is obtained by subtracting the values, based on the third quartz watch body temperature T. a3 Second quartz body temperature T a2 The difference is used to obtain the temperature difference of the second quartz watch body; based on the fourth x-gyroscope temperature T gx4 and the third x-gyroscope temperature T gx3 The difference is used to obtain the third x-type gyroscope temperature difference, based on the fourth y-type gyroscope temperature T. gy4 and the third y-gyroscope temperature T gy3 The third y-top temperature difference is obtained by subtracting the values, and the fourth z-top temperature T is used as the basis. gz4 and the third z-gyroscope temperature T gz3 The third gyroscope temperature difference is obtained by subtracting the values ​​from the fourth quartz watch body temperature T. a4 and the temperature T of the third quartz body a3 The difference is used to obtain the third quartz watch body temperature difference; based on the fifth x gyroscope temperature T gx5 and the fourth x gyroscope temperature T gx4 The difference is used to obtain the fourth x-type gyroscope temperature difference, based on the fifth y-type gyroscope temperature T. gy5 and the fourth y-gyroscope temperature T gy4 The fourth y-top temperature difference is obtained by subtracting the values, and the fifth z-top temperature T is used as the basis for this. gz5 and the fourth z-gyroscope temperature T gz4 The fourth gyroscope temperature difference is obtained by subtracting the values, based on the fifth quartz watch body temperature T. a5 and the fourth quartz body temperature T a4 The difference is used to obtain the fourth quartz watch body temperature difference; the temperature field influence factor matrix is ​​obtained based on the first x gyroscope temperature difference, the second x gyroscope temperature difference, the third x gyroscope temperature difference, the fourth x gyroscope temperature difference, the first y gyroscope temperature difference, the second y gyroscope temperature difference, the third y gyroscope temperature difference, the fourth y gyroscope temperature difference, the first z gyroscope temperature difference, the second z gyroscope temperature difference, the third z gyroscope temperature difference, the fourth z gyroscope temperature difference, the first quartz watch body temperature difference, the second quartz watch body temperature difference, the third quartz watch body temperature difference, and the fourth quartz watch body temperature difference.

[0017] In the temperature control structure of the inertial instrument for the aforementioned fiber optic gyroscope inertial platform, the internal space formed by the outer upper spherical cover and the outer lower spherical cover is closed, isolating the natural convection of internal and external air.

[0018] Compared with the prior art, the present invention has the following advantages:

[0019] (1) The present invention optimizes the double-layer spherical cover structure to form a multi-level circulating flow field, which is beneficial to enhance the heat dissipation of the inertial platform;

[0020] (2) This invention reduces the impact of external environmental temperature changes and internal complex thermal fields on the temperature control accuracy of inertial instruments. By optimizing the thermal structure design, it improves the uniformity and stability of the temperature field near the platform. Attached Figure Description

[0021] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0022] Figure 1 This is a schematic diagram of the temperature control structure for an inertial instrument used in a fiber optic gyroscope inertial platform provided in an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the outer spherical cover structure provided in an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the inner spherical cover structure provided in an embodiment of the present invention. Detailed Implementation

[0025] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0026] Optimizing the heat transfer structure within the platform system, isolating the impact of external ambient temperature changes on the operating temperature of the instruments on the platform, improving the heat dissipation efficiency and temperature gradient stability within the platform, and achieving high-precision temperature field control of the inertial instruments have become urgent problems to be solved in the engineering of fiber optic gyroscope inertial platforms.

[0027] To improve the temperature control accuracy of inertial instruments used in fiber optic gyroscope inertial platforms, a structure and method for temperature field control of these instruments needs to be designed. This involves using a double-layer spherical dome structure for graded temperature control within the platform system, implementing multi-level temperature control measures from the source, conduction structure, and heat dissipation conditions to achieve uniform and stable temperatures across different levels. Optimizing the thermal structure design effectively isolates the platform from external temperature variations while improving heat dissipation efficiency. Furthermore, establishing a heat transfer model between the instruments and the platform's heating elements enhances temperature control accuracy, thereby improving the inertial platform's navigation accuracy and its ability to cope with complex environments.

[0028] Figure 1 This is a schematic diagram of the temperature control structure for an inertial instrument used in a fiber optic gyroscope inertial platform provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the outer spherical cover structure provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the inner spherical cover structure provided in an embodiment of the present invention. Figure 2 The outer shroud fin features 2-1, the outer shroud window and window cover 2-2, and the plane inside the outer shroud where the temperature sensor is installed 2-3 are shown.

[0029] like Figure 1 , Figure 2 and Figure 3 As shown, the temperature control structure for the inertial instrument of the fiber optic gyroscope inertial platform includes: an inner upper spherical cover 1, an outer upper spherical cover 2, a platform assembly 3, an inner lower spherical cover 4, an outer lower spherical cover 5, a ring frame 6, a perforated baffle 7, and a fan 8. The outer upper spherical cover 2 is connected to the outer lower spherical cover 5 via the ring frame 6; the inner upper spherical cover 1 is connected to the inner lower spherical cover 4 via the ring frame 6; the fan 8 is respectively disposed on the inner surface of the outer upper spherical cover 2, the inner surface of the outer lower spherical cover 5, the outer surface of the inner upper spherical cover 1, and the outer surface of the inner lower spherical cover 4; the perforated baffle 7 is installed inside the fan mounting surface of the inner upper spherical cover 1; the platform assembly 3 is disposed inside the space formed by the inner upper spherical cover 1 and the inner lower spherical cover 4; and the ring frame 6 is connected to the platform assembly 3.

[0030] The outer surfaces of the upper outer spherical cover 2 and the lower outer spherical cover 5 are both finned heat dissipation structures, and the inner surfaces of the upper outer spherical cover 2 and the lower outer spherical cover 5 are coated with a high thermal conductivity material.

[0031] Both the inner upper spherical cover 1 and the inner lower spherical cover 4 are provided with slots.

[0032] The perforated baffle 7 has circular holes of different diameters distributed radially to prevent the fan from blowing directly onto the platform assembly 3 and causing local temperature changes, thus ensuring uniform airflow in all directions at the fan inlet.

[0033] The temperature control structure for the inertial instrument of the fiber optic gyroscope inertial platform also includes: a temperature sensor; wherein the temperature sensor is respectively installed on the platform assembly 3, the ring frame 6, the inner upper spherical cover 1, the inner lower spherical cover 4, the outer upper spherical cover 2, and the outer lower spherical cover 5.

[0034] The temperature control structure for the inertial instrument of the fiber optic gyroscope inertial platform also includes a window cover; wherein, the outer upper spherical cover 2 and the outer lower spherical cover 5 are evenly provided with heat dissipation windows, and the window cover is installed on the heat dissipation windows by a sealing ring.

[0035] A multi-level temperature conduction model is established by collecting temperature data from temperature sensors. Based on the multi-level temperature conduction model, the speed of fan 8 and the duty cycle of heating element of platform component 3 are controlled in real time to achieve the stability of the inertial instrument's balanced temperature.

[0036] The multi-stage temperature conduction model is obtained through the following formula:

[0037] T = T0 + Λ·Δ;

[0038] Where T is the temperature vector at a temperature point, T0 is the temperature vector at each temperature point at room temperature, Δ is the duty cycle vector, and Λ is the temperature field influence factor matrix.

[0039] The temperature field influence factor matrix is ​​obtained through the following method:

[0040] The heating element of the platform is energized and heated until equilibrium is reached, at which point the temperature T of the first x-gyroscope is measured. gx1 First y-gyroscope temperature T gy1 First z-gyroscope temperature T gz1 First quartz body temperature T a1 ;

[0041] The heating element of the X gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the second X gyroscope is measured. gx2 The second y-gyroscope temperature T gy2 The second z-gyroscope temperature T gz2 The temperature T of the second quartz body a2 ;

[0042] The heating element of the Y-gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the third x-gyroscope is measured. gx3 The third y-top temperature T gy3 The third z-gyroscope temperature T gz3 The temperature of the third quartz body, T a3 ;

[0043] The heating element of the Z-gyroscope is energized and heated until equilibrium is reached. The temperature T of the fourth x-gyroscope is then measured. gx4 The fourth y-top temperature T gy4 The fourth gyroscope temperature T gz4 Fourth quartz body temperature T a4 ;

[0044] The quartz watch heating element is energized and heated until equilibrium is reached, at which point the temperature T of the fifth gyroscope is measured. gx5 Fifth y-top temperature T gy5 Fifth gyroscope temperature T gz5 Fifth quartz body temperature T a5 ;

[0045] According to the second x-gyroscope temperature Tgx2 and the first x-gyroscope temperature T gx1 The first x-shaped gyroscope temperature difference is obtained by subtracting the first x-shaped gyroscope temperature difference, and then the second y-shaped gyroscope temperature T is obtained. gy2 and the first y-gyroscope temperature T gy1 The first y-top temperature difference is obtained by subtracting the first y-top temperature difference, based on the second z-top temperature T. gz2 and the first z-gyroscope temperature T gz1 The temperature difference of the first gyroscope is obtained by subtracting the difference, based on the temperature T of the second quartz watch body. a2 and the temperature T of the first quartz body a1 The difference was obtained by subtracting the temperature difference of the first quartz watch body;

[0046] According to the third x gyroscope temperature T gx3 Second x gyroscope temperature T gx2 The difference is used to obtain the second x-type gyroscope temperature difference, based on the third y-type gyroscope temperature T. gy3 Second y-gyroscope temperature T gy2 The second y-top temperature difference is obtained by subtracting the values, and then the third z-top temperature T is used as the basis. gz3 Second z-gyroscope temperature T gz2 The second gyroscope temperature difference is obtained by subtracting the values, based on the third quartz watch body temperature T. a3 Second quartz body temperature T a2 The difference was used to obtain the temperature difference of the second quartz watch body.

[0047] According to the fourth gyroscope temperature T gx4 and the third x-gyroscope temperature T gx3 The difference is used to obtain the third x-type gyroscope temperature difference, based on the fourth y-type gyroscope temperature T. gy4 and the third y-gyroscope temperature T gy3 The third y-top temperature difference is obtained by subtracting the values, and the fourth z-top temperature T is used as the basis. gz4 and the third z-gyroscope temperature T gz3 The third gyroscope temperature difference is obtained by subtracting the values ​​from the fourth quartz watch body temperature T. a4 and the temperature T of the third quartz body a3 The difference is used to obtain the third temperature difference of the quartz watch body;

[0048] According to the fifth x gyroscope temperature T gx5 and the fourth x gyroscope temperature T gx4 The difference is used to obtain the fourth x-type gyroscope temperature difference, based on the fifth y-type gyroscope temperature T. gy5 and the fourth y-gyroscope temperature T gy4 The fourth y-top temperature difference is obtained by subtracting the values, and the fifth z-top temperature T is used as the basis for this. gz5 and the fourth z-gyroscope temperature T gz4 The fourth gyroscope temperature difference is obtained by subtracting the values, based on the fifth quartz watch body temperature T. a5 and the fourth quartz body temperature T a4 The difference was obtained by subtracting the temperature difference of the fourth quartz watch body.

[0049] The temperature field influence factor matrix is ​​obtained based on the temperature differences of the first x-gyroscope, the second x-gyroscope, the third x-gyroscope, the fourth x-gyroscope, the first y-gyroscope, the second y-gyroscope, the third y-gyroscope, the fourth y-gyroscope, the first z-gyroscope, the second z-gyroscope, the third z-gyroscope, the fourth z-gyroscope, the first quartz watch body temperature difference, the second quartz watch body temperature difference, the third quartz watch body temperature difference, and the fourth quartz watch body temperature difference.

[0050] The internal space formed by the outer upper spherical cover 2 and the outer lower spherical cover 5 is closed, isolating the natural convection of internal and external air.

[0051] The outer surface of the outer spherical cover has a finned heat dissipation structure, and the inner surface is coated with a high thermal conductivity material and a fan 8 is installed for convection cooling. The outer upper spherical cover 2 and the outer lower spherical cover 5 are mounted on the ring frame 6 with screws. The inner upper spherical cover 1 and the inner lower spherical cover 4 have regularly distributed slots, and the outer surface is equipped with a fan 8 for convection cooling. The upper and lower spherical covers are connected by screws. The perforated baffle 7 is installed on the inner side of the fan mounting surface of the inner upper spherical cover 1 with screws. The above thermal structure is optimized using the thermal-fluid-structure interaction finite element method. The temperature control method is as follows: temperature sensors are installed on the inner and outer sides of the platform assembly 3, the inner upper spherical cover 1, the inner lower spherical cover 4, the outer upper spherical cover 2, and the outer lower spherical cover 5. Multi-channel temperature data is collected to establish a multi-level temperature conduction model, and the fan speed 8 and the duty cycle of the heating element of the platform assembly 3 are controlled in real time to achieve the stability of the inertial instrument balance temperature.

[0052] In the double-layer spherical structure, the outer spherical cover and the inner spherical cover are two independent components. The outer spherical cover is a closed structure that isolates the natural convection of the inner and outer air, while the inner spherical cover is an open structure that uses a fan 8 installed on the inner spherical cover 1 to achieve the air circulation field between the inner and outer sides.

[0053] The perforated baffle 7 has circular holes of different diameters distributed radially to prevent the fan from blowing directly onto the platform assembly 3 and causing local temperature changes, thus ensuring uniform airflow in all directions at the fan inlet.

[0054] Temperature sensors are evenly distributed on platform component 3, ring frame 6, and inner and outer spherical covers, which can fully reflect the temperature distribution of each component and air zone, facilitating the establishment of multi-level heat transfer models. The double-layer spherical cover structure divides the interior of the inertial platform into multi-level temperature fields for multi-level temperature control.

[0055] The outer spherical cover has a uniform long arc-shaped fin structure on its outer surface, with consistent fin thickness and radial distribution; both the inner and outer spherical covers have small planar structures distributed on their inner and outer sides, which facilitates the installation of temperature sensors.

[0056] The outer spherical cover structure has uniformly distributed heat dissipation windows, and the window covers and sealing rings are installed on the heat dissipation windows by screws; the inner surface of the outer spherical cover has a flexible material coating with a high thermal conductivity.

[0057] By optimizing the thermal structure design through thermal-fluid-structure interaction finite element simulation and rationally arranging the fan positions to form a circulating flow field, a double-layer spherical structure was obtained. This structure mainly consists of an inner upper spherical cover 1, an outer upper spherical cover 2, a platform assembly 3, an inner lower spherical cover 4, an outer lower spherical cover 5, a ring frame 6, a perforated baffle 7, and a fan 8. The outer surfaces of the outer upper spherical cover 2 and the outer lower spherical cover 5 are finned heat dissipation structures, and the inner surfaces are coated with high thermal conductivity material and equipped with fans 8 for convection heat dissipation. The outer upper spherical cover 2 and the outer lower spherical cover 5 are mounted on the ring frame 6 with screws. The inner upper spherical cover 1 and the inner lower spherical cover 4 have regularly distributed slots, and the outer surfaces are equipped with fans 8 for convection heat dissipation. The inner upper spherical cover 1 and the inner lower spherical cover 4 are connected by screws. The perforated baffle 7 is installed on the inner side of the fan mounting surface of the inner upper spherical cover 1 with screws. By employing the thermal-fluid-structure interaction finite element method to obtain the internal temperature and flow field distribution of the platform, inner spherical cover, and outer spherical cover, the number, location, and flow rate of fans, as well as the structure of structural components, can be optimized to improve heat dissipation efficiency and temperature distribution uniformity.

[0058] The temperature control method based on the above structure is as follows: temperature sensors are installed on the inner and outer sides of the platform assembly 3, the inner upper spherical cover 1, the inner lower spherical cover 4, the outer upper spherical cover 2, and the outer lower spherical cover 5. Multi-level temperature conduction models are established by collecting temperature data through multiple channels, and the speed of fan 8 and the duty cycle of heating element of platform assembly 3 are controlled in real time to achieve the stability of the inertial instrument balance temperature.

[0059] A heat transfer model was established between the instruments and the heating elements of the platform. By cumulatively heating at different stages, with different platforms and heating elements of each instrument, the temperatures at various measuring points after the heating elements stabilized were obtained. Specifically, the platform heating elements were first energized and heated, and the temperatures T of each instrument after equilibrium was measured. gx1 T gy1 T gz1 T a1 Then, the heating element of the platform is kept energized, and the heating elements of the X gyroscope, Y gyroscope, and Z gyroscope are energized and heated in sequence. The temperature T of each instrument after reaching equilibrium is measured. gxi T gyi T gzi T ai Finally, the heating element of the quartz watch is energized and heated, and the temperature T of each instrument after thermal equilibrium is measured. gxi+1 T gyi+1 T gzi+1 T ai+1 By processing the above temperature measurement data, T is calculated sequentially. gxi-T gxi-1 T gyi -T gyi-1 T gzi -T gzi-1 T ai -T ai-1 This allows us to obtain the influence factors of different heating elements on each temperature measuring point. Each instrument's heating element has a primary temperature gradient influence on its corresponding instrument, but it also affects all other instruments. Based on the previously obtained temperature field influence factor matrix, we can obtain the temperature control model for this temperature field configuration according to the temperature vector corresponding to this matrix. Let the temperature vector at each temperature point be T, the temperature vector at each temperature point at room temperature be T0, and the duty cycle vector be Δ.

[0060] T=T0+Λ·Δ

[0061] in,

[0062]

[0063] If it is necessary to obtain a specific temperature field of each instrument on the platform, that is, the temperature combination of the measuring points, the required heating element duty cycle combination can be obtained through algebraic calculations.

[0064] In the double-layer spherical structure, the outer spherical cover and the inner spherical cover are two independent components. The outer spherical cover is a closed structure that isolates the natural convection of the inner and outer air, while the inner spherical cover is an open structure that uses a fan 8 installed on the inner spherical cover 1 to achieve the air circulation field between the inner and outer sides.

[0065] Specifically, by optimizing the thermal structure design through thermal-fluid-structure interaction finite element simulation and rationally arranging the fan positions to form a circulating flow field, a double-layer spherical cover structure for a fiber optic gyroscope inertial platform was obtained. This structure mainly consists of an inner upper spherical cover 1, an outer upper spherical cover 2, a platform assembly 3, an inner lower spherical cover 4, an outer lower spherical cover 5, a ring frame 6, a perforated baffle 7, and a fan 8. The outer surfaces of the outer upper spherical cover 2 and the outer lower spherical cover 5 are finned heat dissipation structures, and the inner surfaces are coated with high thermal conductivity material and fitted with fans 8 for convection cooling. The outer upper spherical cover 2 and the outer lower spherical cover 5 are mounted on the ring frame 6 with screws. The inner upper spherical cover 1 and the inner lower spherical cover 4 have regularly distributed slots, and the outer surfaces are fitted with fans 8 for convection cooling. The inner upper spherical cover 1 and the inner lower spherical cover 4 are connected by screws. The perforated baffle 7 is mounted to the inner side of the fan mounting surface of the inner upper spherical cover 1 with screws to prevent the fan from blowing directly onto the platform.

[0066] A heat transfer model was established between the instruments and the heating elements of the platform. By cumulatively heating at different stages, with different platforms and heating elements of each instrument, the temperatures at various measuring points after the heating elements stabilized were obtained. Specifically, the platform heating elements were first energized and heated, and the temperatures T of each instrument after equilibrium was measured. gx1 T gy1 Tgz1 T a1 Then, the heating element of the platform is kept energized, and the heating elements of the X gyroscope, Y gyroscope, and Z gyroscope are energized and heated in sequence. The temperature T of each instrument after reaching equilibrium is measured. gxi T gyi T gzi T ai Finally, the heating element of the quartz watch is energized and heated, and the temperature T of each instrument after thermal equilibrium is measured. gxi+1 T gyi+1 T gzi+1 T ai+1 By processing the above temperature measurement data, T is calculated sequentially. gxi -T gxi-1 T gyi -T gyi-1 T gzi -T gzi-1 T ai -T ai-1 This allows us to obtain the influence factors of different heating elements on each temperature measuring point. Each instrument's heating element has a primary temperature gradient influence on its corresponding instrument, but it also affects all other instruments. Based on the previously obtained temperature field influence factor matrix, we can obtain the temperature control model for this temperature field configuration according to the temperature vector corresponding to this matrix. Let the temperature vector at each temperature point be T, the temperature vector at each temperature point at room temperature be T0, and the duty cycle vector be Δ.

[0067] Table 1 Instrument Temperature at Steady State

[0068]

[0069]

[0070] By subtracting the temperatures from the previous row, we can obtain the influence factors of different heating elements on each temperature point. These influence factors show that each heating element has a primary temperature gradient effect on its corresponding heating element, but also affects all other heating elements. Table 1 provides a temperature field influence factor matrix Λ.

[0071]

[0072] Based on the temperature field influence factor matrix obtained earlier, the temperature control model for this temperature field configuration can be obtained according to the temperature vector corresponding to the matrix. Let the temperature vector at each temperature point be T, the temperature vector at each temperature point at room temperature be T0, and the duty cycle vector be Δ.

[0073] T=T0+Λ·Δ

[0074] If it is necessary to obtain a specific temperature field of each instrument on the platform, that is, the temperature combination of the measuring points, the required heating element duty cycle combination can be obtained through algebraic calculations.

[0075] The temperature control method based on the above structure is as follows: temperature sensors are installed on the inner and outer sides of the platform assembly 3, the inner upper spherical cover 1, the inner lower spherical cover 4, the outer upper spherical cover 2, and the outer lower spherical cover 5. Multi-level temperature conduction models are established by collecting temperature data through multiple channels, and the speed of fan 8 and the duty cycle of heating element of platform assembly 3 are controlled in real time to achieve the stability of the inertial instrument balance temperature.

[0076] This embodiment employs the finite element method to optimize the acquisition of internal temperature and airflow distribution within the inertial platform, optimizing the double-layer spherical cover structure to form a multi-stage circulating flow field, which is beneficial for enhancing heat dissipation of the inertial platform. By controlling the multi-stage temperature fields between the outer and inner spherical covers, between the inner spherical cover and the platform cover, and among the various instruments on the platform, the impact of external environmental temperature changes on the inertial instruments can be reduced, providing a favorable external environment for instrument-level temperature control.

[0077] This embodiment establishes a heat transfer model for the heating elements of each instrument inside the platform assembly, thereby obtaining the influence of each instrument's heating element on the temperature gradient, which facilitates the establishment of a temperature control model.

[0078] The dome model in this embodiment is not limited to a double-layer structure. It can be adjusted according to the number of rings in the actual fiber optic platform, and has a certain degree of versatility and universality.

[0079] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A temperature control structure for an inertial instrument used in a fiber optic gyroscope inertial platform, characterized in that... include: The inner upper ball cover (1), the outer upper ball cover (2), the table assembly (3), the inner lower ball cover (4), the outer lower ball cover (5), the ring frame (6), the perforated baffle (7), and the fan (8); among which, The outer upper spherical cover (2) is connected to the outer lower spherical cover (5) through the ring frame (6); The inner upper spherical cover (1) is connected to the inner lower spherical cover (4) through the ring frame (6); The fan (8) is respectively disposed on the inner surface of the outer upper spherical cover (2), the inner surface of the outer lower spherical cover (5) and the outer surface of the inner upper spherical cover (1); The perforated baffle (7) is installed on the inside of the fan mounting surface of the inner upper spherical cover (1); The platform assembly (3) is disposed inside the space formed by the inner upper spherical cover (1) and the inner lower spherical cover (4); The ring frame (6) is connected to the platform assembly (3); A multi-level temperature conduction model is established by collecting temperature data from temperature sensors. The speed of the fan (8) and the duty cycle of the heating element of the platform assembly (3) are controlled in real time according to the multi-level temperature conduction model to achieve the stability of the inertial instrument balance temperature. The multi-stage temperature conduction model is obtained through the following formula: ； Where T is the temperature vector at a given temperature point, T0 is the temperature vector at each temperature point at room temperature, and Δ is the duty cycle vector. This is the temperature field influence factor matrix; The temperature field influence factor matrix is ​​obtained through the following method: The heating element of the platform is energized and heated until equilibrium is reached, at which point the temperature T of the first x-gyroscope is measured. gx1 First y-gyroscope temperature T gy1 First z-gyroscope temperature T gz1 First quartz body temperature T a1 ; The heating element of the X gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the second X gyroscope is measured. gx2 The second y-gyroscope temperature T gy2 The second z-gyroscope temperature T gz2 The temperature T of the second quartz body a2 ; The heating element of the Y-gyroscope is energized and heated until equilibrium is reached, at which point the temperature T of the third x-gyroscope is measured. gx3 The third y-top temperature T gy3 The third z-gyroscope temperature T gz3 The temperature of the third quartz body, T a3 ; The heating element of the Z-gyroscope is energized and heated until equilibrium is reached. The temperature T of the fourth x-gyroscope is then measured. gx4 The fourth y-top temperature T gy4 The fourth gyroscope temperature T gz4 Fourth quartz body temperature T a4 ; The quartz watch heating element is energized and heated until equilibrium is reached, at which point the temperature T of the fifth gyroscope is measured. gx5 Fifth y-top temperature T gy5 Fifth gyroscope temperature T gz5 Fifth quartz body temperature T a5 ; According to the second x-gyroscope temperature T gx2 and the first x-gyroscope temperature T gx1 The first x-shaped gyroscope temperature difference is obtained by subtracting the first x-shaped gyroscope temperature difference, and then the second y-shaped gyroscope temperature T is obtained. gy2 and the first y-gyroscope temperature T gy1 The first y-top temperature difference is obtained by subtracting the first y-top temperature difference, based on the second z-top temperature T. gz2 and the first z-gyroscope temperature T gz1 The temperature difference of the first gyroscope is obtained by subtracting the difference, based on the temperature T of the second quartz watch body. a2 and the temperature T of the first quartz body a1 The difference was obtained by subtracting the temperature difference of the first quartz watch body; According to the third x gyroscope temperature T gx3 Second x gyroscope temperature T gx2 The difference is used to obtain the second x-type gyroscope temperature difference, based on the third y-type gyroscope temperature T. gy3 Second y-gyroscope temperature T gy2 The second y-top temperature difference is obtained by subtracting the values, and then the third z-top temperature T is used as the basis. gz3 Second z-gyroscope temperature T gz2 The second gyroscope temperature difference is obtained by subtracting the values, based on the third quartz watch body temperature T. a3 Second quartz body temperature T a2 The difference is used to obtain the second temperature difference of the quartz watch body; According to the fourth gyroscope temperature T gx4 and the third x-gyroscope temperature T gx3 The difference is used to obtain the third x-type gyroscope temperature difference, based on the fourth y-type gyroscope temperature T. gy4 and the third y-gyroscope temperature T gy3 The third y-top temperature difference is obtained by subtracting the values, and the fourth z-top temperature T is used as the basis. gz4 and the third z-gyroscope temperature T gz3 The third gyroscope temperature difference is obtained by subtracting the values ​​from the fourth quartz watch body temperature T. a4 and the temperature T of the third quartz body a3 The difference is used to obtain the third temperature difference of the quartz watch body; According to the fifth x gyroscope temperature T gx5 and the fourth x gyroscope temperature T gx4 The difference is used to obtain the fourth x-type gyroscope temperature difference, based on the fifth y-type gyroscope temperature T. gy5 and the fourth y-gyroscope temperature T gy4 The fourth y-top temperature difference is obtained by subtracting the values, and the fifth z-top temperature T is used as the basis for this. gz5 and the fourth z-gyroscope temperature T gz4 The fourth gyroscope temperature difference is obtained by subtracting the values, based on the fifth quartz watch body temperature T. a5 and the fourth quartz body temperature T a4 The difference was obtained by subtracting the temperature difference of the fourth quartz watch body. The temperature field influence factor matrix is ​​obtained based on the temperature differences of the first x-gyroscope, the second x-gyroscope, the third x-gyroscope, the fourth x-gyroscope, the first y-gyroscope, the second y-gyroscope, the third y-gyroscope, the fourth y-gyroscope, the first z-gyroscope, the second z-gyroscope, the third z-gyroscope, the fourth z-gyroscope, the first quartz watch body temperature difference, the second quartz watch body temperature difference, the third quartz watch body temperature difference, and the fourth quartz watch body temperature difference.

2. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that: The outer surfaces of the upper outer spherical cover (2) and the lower outer spherical cover (5) are both finned heat dissipation structures, and the inner surfaces of the upper outer spherical cover (2) and the lower outer spherical cover (5) are coated with a high thermal conductivity material.

3. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that: Both the inner upper spherical cover (1) and the inner lower spherical cover (4) are provided with slots.

4. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that: The perforated baffle (7) has circular holes of different diameters distributed radially to prevent the fan from blowing directly onto the platform assembly (3) and causing local temperature changes, thus ensuring uniform gas flow in all directions at the fan inlet.

5. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that... Also includes: Temperature sensors; wherein the temperature sensors are respectively installed on the platform assembly (3), the ring frame (6), the inner upper spherical cover (1), the inner lower spherical cover (4), the outer upper spherical cover (2) and the outer lower spherical cover (5).

6. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that... It also includes: a window cover; wherein the outer upper spherical cover (2) and the outer lower spherical cover (5) are both uniformly provided with heat dissipation windows, and the window cover is installed on the heat dissipation windows by a sealing ring.

7. The temperature control structure for inertial instruments in a fiber optic gyroscope inertial platform according to claim 1, characterized in that: The internal space formed by the outer upper spherical cover (2) and the outer lower spherical cover (5) is closed, isolating the natural convection of internal and external air.

Images