Inertia instrument temperature control structure for fiber-optic gyroscope inertial platform

Abstract

The invention discloses an inertial instrument temperature control structure for a fiber-optic gyroscope inertial platform. The inertial instrument temperature control structure comprises an inner-layer upper spherical cover, an outer-layer upper spherical cover, a platform body assembly, an inner-layer lower spherical cover, an outer-layer lower spherical cover, an annular frame, a baffle with holes and a fan, wherein the outer-layer upper ball cover is connected with the outer-layer lower ball cover through the ring frame; the inner-layer upper ball cover is connected with the inner-layer lower ball cover through the ring frame; the fans are respectively arranged on the inner surface of the outer-layer upper dome cover, the inner surface of the outer-layer lower dome cover and the outer surface of the inner-layer upper dome cover; the perforated baffle is mounted on the inner side of the fan mounting surface of the inner-layer upper spherical cover; the table body assembly is arranged in a space formed by the inner-layer upper ball cover and the inner-layer lower ball cover; and the ring frame is connected with the table body assembly. The influence of external environment temperature change and an internal complex thermal field on the temperature control precision of the inertia instrument is reduced, and the uniformity and stability of the temperature field near the table body are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of temperature control of inertial instruments used in inertial measurement devices, and in particular relates to a temperature control structure of an inertial instrument used in a fiber optic gyro inertial platform. Background Art

[0002] Fiber optic gyro inertial platform is an inertial measurement device that uses fiber optic gyro as an angular motion sensitive element, and is mainly used in high-precision inertial navigation systems. Fiber optic gyro inertial platform is mainly composed of platform components (fiber optic gyro, accelerometer, etc.), stabilization loop, ring frame components, precision shaft system, base and vibration absorber. Its working principle is to control the platform components in the inertial space through the angular velocity change of the fiber optic gyro sensitive carrier through the stabilization loop, providing a good dynamic environment for inertial instruments (accelerometer and fiber optic gyro).

[0003] The inertial platform has a relatively compact structure, and has many internal heat sources including circuit boards, torque motors, heaters, inertial instruments, etc. At the same time, the frame angle position changes in real time with the working conditions, and has a complex thermal field environment. The performance indicators of the inertial instruments on the platform are significantly affected by temperature, and the temperature fluctuations in the platform system will affect the measurement accuracy and installation accuracy of the inertial instruments. Different instruments are installed at different positions on the platform, and their optimal temperature operating points are not the same. There is a strong coupling relationship between the temperature control circuits of a single meter. It is necessary to establish a heat transfer model between the heaters of different instruments on the platform to improve the temperature control accuracy of the instrument.

[0004] During the operation of the fiber optic gyro inertial platform, the external temperature environment will change greatly. When the external temperature is high, the heat is transferred to the ring frame assembly through the base, and then to the platform body. The fan on the base dissipates heat by convection, changing the internal thermal field environment. Generally, the air flow rate is higher near the fan, and it is almost unaffected away from the fan, resulting in uneven distribution of the internal air flow field, making it difficult to provide good environmental conditions for the temperature control system. The relative angular position relationship between the ring frames changes with the movement of the carrier, resulting in changes in the heat conduction, heat radiation, and thermal convection of the gas between the ring frames. The above-mentioned internal and external environmental factors cause the internal temperature field of the platform system to not always be in a thermal equilibrium state. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide an inertial instrument temperature control structure for a fiber optic gyro inertial platform, to reduce the influence of external environmental temperature changes and internal complex thermal fields on the temperature control accuracy of the inertial instrument, and to improve the uniformity and stability of the temperature field near the platform body.

[0006] The object of the present invention is achieved through the following technical solutions: an inertial instrument temperature control structure for a fiber optic gyro inertial platform, comprising: an inner upper ball cover, an outer upper ball cover, a platform assembly, an inner lower ball cover, an outer lower ball cover, a ring frame, a baffle with holes and a fan; wherein the outer upper ball cover is connected to the outer lower ball cover through the ring frame; the inner upper ball cover is connected to the inner lower ball cover through the ring frame; the fan is respectively arranged on the inner surface of the outer upper ball cover, the inner surface of the outer lower ball cover and the outer surface of the inner upper ball cover; the baffle with holes is installed on the inner side of the fan installation surface of the inner upper ball cover; the platform assembly is arranged inside the space formed by the inner upper ball cover and the inner lower ball cover; the ring frame is connected to the platform assembly.

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

[0008] In the above-mentioned inertial instrument temperature control structure for the fiber optic gyro inertial platform, both the inner upper spherical cover and the inner lower spherical cover are provided with slots.

[0009] In the temperature control structure of the inertial instrument for the fiber optic gyro inertial platform, the perforated baffle is provided with circular holes of different diameters, which are distributed radially to avoid the fan directly blowing the platform assembly and causing local temperature changes, thereby ensuring uniform gas flow in all directions at the fan inlet.

[0010] The above-mentioned inertial instrument temperature control structure for the fiber optic gyro inertial platform also includes: a temperature sensor; wherein the temperature sensors are respectively installed on the platform body assembly, the ring frame, the inner upper ball cover, the inner lower ball cover, the outer upper ball cover and the outer lower ball cover.

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

[0012] In the temperature control structure of the inertial instrument for the above-mentioned fiber optic gyro inertial platform, a multi-level temperature conduction model is established through the temperature data collected by the temperature sensor, and the fan speed and the duty cycle of the platform component heating plate are controlled in real time according to the multi-level temperature conduction model to achieve the stability of the inertial instrument balance temperature.

[0013] In the temperature control structure of the inertial instrument for the above-mentioned fiber optic gyro inertial platform, the multi-stage temperature conduction model is obtained by the following formula:

[0014] T = T0 + Λ·Δ;

[0015] Among them, T is the temperature vector of the temperature point, T0 is the temperature vector of each temperature point at room temperature, Δ is the duty cycle vector, and Λ is the temperature field influencing factor matrix.

[0016] In the temperature control structure of the inertial instrument for the fiber optic gyro inertial platform, the temperature field influencing factor matrix is ​​obtained by the following method: the platform heating plate is powered on to heat up, and after reaching equilibrium, the first x gyro temperature T is measured. gx1 , the first y-gyro temperature T gy1 , the first z gyro temperature T gz1 , the first quartz body temperature T a1 ; The X gyro heating plate is powered on to heat up, and after reaching equilibrium, the second X gyro temperature T is measured. gx2 , the second y gyro temperature T gy2 , the second z gyro temperature T gz2 , the second quartz body temperature T a3 ; The Y gyro heating plate is powered on to heat up, and after reaching equilibrium, the third x gyro temperature T is measured. gx3 、The third y gyro temperature T gy3 、Third z gyro temperature T gz3 、The third quartz body temperature T a3 ; The Z gyro heating plate is powered on to heat up, and after reaching equilibrium, the fourth x gyro temperature T is measured gx4 , the fourth y gyro temperature T gy4 , Fourth z gyro temperature T gz4 , Fourth quartz body temperature T a4 ; The quartz watch heater is powered on to heat up, and after reaching equilibrium, the fifth x gyro temperature T is measured gx5 、Fifth y gyro temperature T gy5 、Fifth z gyro temperature T gz5 、5. Quartz body temperature T a5 ; According to the second x gyro temperature T gx2 and the first x gyro temperature T gx1 The temperature difference of the first x gyro is obtained by subtracting the temperature of the second y gyro. gy2 and the first y-gyro temperature T gy1 The temperature difference of the first y gyro is obtained by subtracting the temperature of the second z gyro T gz2 and the first z gyro temperature T gz1 The temperature difference of the first z gyro is obtained by subtracting the temperature of the second quartz table T a2 and the first quartz body temperature T a1 The temperature difference of the first quartz watch is obtained by subtraction; according to the temperature T of the third gyro gx3 and the second x gyro temperature T gx2 The temperature difference of the second x gyro is obtained by subtracting it, and according to the temperature T of the third y gyro gy3and the second y-gyro temperature T gy2 The temperature difference of the second y gyro is obtained by subtracting the temperature of the third z gyro. gz3 and the second z gyro temperature T gz2 The temperature difference of the second z gyro is obtained by subtraction, and the temperature of the third quartz table body T a3 and the second quartz body temperature T a2 The temperature difference of the second quartz watch is obtained by subtraction; according to the temperature T of the fourth gyro gx4 and the third x gyro temperature T gx3 The temperature difference of the third x gyro is obtained by subtracting, and according to the temperature T of the fourth y gyro gy4 and the third y gyro temperature T gy3 The temperature difference of the third y gyro is obtained by subtracting, and according to the temperature T of the fourth z gyro gz4 and the third z gyro temperature T gz3 The temperature difference of the third z gyro is obtained by subtraction, and according to the temperature T of the fourth quartz table a4 and the third quartz body temperature T a3 The temperature difference of the third quartz watch is obtained by subtraction; according to the fifth x gyro temperature T gx5 and the fourth x gyro temperature T gx4 The temperature difference of the fourth x gyro is obtained by subtracting the temperature of the fifth y gyro T gy5 and the fourth y-gyro temperature T gy4 The temperature difference of the fourth y gyro is obtained by subtracting, and according to the temperature T of the fifth z gyro gz5 and the fourth z gyro temperature T gz4 The temperature difference of the fourth z gyro is obtained by subtraction, and according to the fifth quartz table body temperature T a5 and the fourth quartz body temperature T a4 The fourth quartz watch body temperature difference is obtained by difference; the temperature field influencing factor matrix is ​​obtained according to the first x gyro temperature difference, the second x gyro temperature difference, the third x gyro temperature difference, the fourth x gyro temperature difference, the first y gyro temperature difference, the second y gyro temperature difference, the third y gyro temperature difference, the fourth y gyro temperature difference, the first z gyro temperature difference, the second z gyro temperature difference, the third z gyro temperature difference, the fourth z gyro 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 fiber optic gyro inertial platform, the inner space formed by the outer upper spherical cover and the outer lower spherical cover is closed, isolating the natural convection of the inner and outer air.

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

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

[0020] (2) The present invention reduces the influence 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 by optimizing the thermal structure design. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0022] Figure 1 Schematic diagram of a temperature control structure of an inertial instrument for a fiber optic gyro inertial platform provided by an embodiment of the present invention;

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

[0024] Figure 3 It is a schematic diagram of the structure of the inner ball cover provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0025] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0026] How to optimize the heat transfer structure within the platform system, isolate the impact of external environmental temperature changes on the operating temperature of the platform instruments, improve the internal heat dissipation efficiency and temperature gradient stability of the platform, and achieve high-precision temperature field control of inertial instruments has become an urgent problem to be solved in fiber optic gyro inertial platform engineering.

[0027] In order to improve the temperature control accuracy of inertial instruments used in fiber optic gyro inertial platforms, it is necessary to design a structure and method for temperature field control of inertial instruments used in fiber optic gyro inertial platforms. The temperature in the platform system is controlled in stages through a double-layer ball cover structure, and multi-level temperature control measures are implemented from the source, conduction structure, and heat dissipation conditions to form a uniform and stable temperature between different levels. By optimizing the thermal structure design, the heat dissipation efficiency is improved while effectively isolating the temperature changes of the external environment. By establishing a heat transfer model between the instrument and the platform heating plate, the temperature control accuracy is improved, thereby improving the navigation accuracy of the inertial platform and its ability to cope with complex environments.

[0028] Figure 1 Schematic diagram of a temperature control structure of an inertial instrument for a fiber optic gyro inertial platform provided by an embodiment of the present invention; Figure 2 is a schematic diagram of the structure of the outer ball cover provided by an embodiment of the present invention; Figure 3 It is a schematic diagram of the structure of the inner ball cover provided by an embodiment of the present invention. Figure 2 The outer ball cover fin feature 2-1, the outer ball cover window and window cover 2-2, and the temperature sensor plane 2-3 installed inside the outer ball cover are shown.

[0029] like Figure 1 , Figure 2 and Figure 3 As shown, the inertial instrument temperature control structure for the fiber optic gyro inertial platform includes: an inner upper ball cover 1, an outer upper ball cover 2, a platform assembly 3, an inner lower ball cover 4, an outer lower ball cover 5, a ring frame 6, a baffle plate with holes 7 and a fan 8; wherein, the outer upper ball cover 2 is connected to the outer lower ball cover 5 through the ring frame 6; the inner upper ball cover 1 is connected to the inner lower ball cover 4 through the ring frame 6; the fan 8 is respectively arranged on the inner surface of the outer upper ball cover 2, the inner surface of the outer lower ball cover 5, the outer surface of the inner upper ball cover 1 and the outer surface of the inner lower ball cover 4; the baffle plate with holes is installed on the inner side of the fan installation surface of the inner upper ball cover 1; the platform assembly 3 is arranged inside the space formed by the inner upper ball cover 1 and the inner lower ball cover 4; the ring frame 6 is connected to the platform assembly 3.

[0030] The outer surfaces of the outer upper ball cover 2 and the outer lower ball cover 5 are both fin heat dissipation structures, and the inner surfaces of the outer upper ball cover 2 and the outer lower ball cover 5 are coated with high thermal conductivity materials.

[0031] The inner upper ball cover 1 and the inner lower ball cover 4 are both provided with slots.

[0032] The perforated baffle 7 is provided with circular holes of different diameters, which are distributed radially, so as to avoid the fan directly blowing the platform assembly 3 and causing local temperature changes, and ensure uniform gas flow in all directions at the fan air inlet.

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

[0034] The inertial instrument temperature control structure for the fiber optic gyro 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 window through a sealing ring.

[0035] A multi-stage temperature conduction model is established based on the temperature data collected by the temperature sensor. The rotation speed of the fan 8 and the duty cycle of the heating plate of the platform component 3 are controlled in real time according to the multi-stage temperature conduction model to achieve the stability of the inertial instrument balance temperature.

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

[0037] T = T0 + Λ·Δ;

[0038] Among them, T is the temperature vector of the temperature point, T0 is the temperature vector of each temperature point at room temperature, Δ is the duty cycle vector, and Λ is the temperature field influencing factor matrix.

[0039] The temperature field influencing factor matrix is ​​obtained by the following method:

[0040] The stage heating plate is powered on to heat up, and after reaching equilibrium, the first x gyro temperature T is measured. gx1 , the first y-gyro temperature T gy1 , the first z gyro temperature T gz1 , the first quartz body temperature T a1 ;

[0041] The X gyro heating plate is powered on to heat up, and after reaching equilibrium, the second X gyro temperature T is measured. gx2 , the second y gyro temperature T gy2 , the second z gyro temperature T gz2 , the second quartz body temperature T a2 ;

[0042] The Y gyro heating plate is powered on to heat up, and after reaching equilibrium, the temperature of the third x gyro T is measured. gx3 、The third y gyro temperature T gy3 、Third z gyro temperature T gz3 、The third quartz body temperature T a3 ;

[0043] The Z gyro heating plate is powered on to heat up, and after reaching equilibrium, the temperature of the fourth gyro T is measured. gx4 , the fourth y gyro temperature T gy4 , Fourth z gyro temperature T gz4 , Fourth quartz body temperature T a4 ;

[0044] The quartz watch heater is powered on to heat up, and after reaching equilibrium, the fifth x gyro temperature T is measured. gx5 、Fifth y gyro temperature T gy5 、Fifth z gyro temperature T gz5 、5. Quartz body temperature T a5 ;

[0045] According to the second x gyro temperature Tgx2 and the first x gyro temperature T gx1 The temperature difference of the first x gyro is obtained by subtracting the temperature of the second y gyro. gy2 and the first y-gyro temperature T gy1 The temperature difference of the first y gyro is obtained by subtracting the temperature of the second z gyro T gz2 and the first z gyro temperature T gz1 The temperature difference of the first z gyro is obtained by subtracting the temperature of the second quartz table T a2 and the first quartz body temperature T a1 Make a difference to get the temperature difference of the first quartz watch;

[0046] According to the third x gyro temperature T gx3 and the second x gyro temperature T gx2 The temperature difference of the second x gyro is obtained by subtracting it, and according to the temperature T of the third y gyro gy3 and the second y-gyro temperature T gy2 The temperature difference of the second y gyro is obtained by subtracting the temperature of the third z gyro. gz3 and the second z gyro temperature T gz2 The temperature difference of the second z gyro is obtained by subtraction, and the temperature of the third quartz table body T a3 and the second quartz body temperature T a2 The temperature difference of the second quartz watch is obtained by subtracting the temperature.

[0047] According to the fourth x gyro temperature T gx4 and the third x gyro temperature T gx3 The temperature difference of the third x gyro is obtained by subtracting, and according to the temperature T of the fourth y gyro gy4 and the third y gyro temperature T gy3 The temperature difference of the third y gyro is obtained by subtracting, and according to the temperature T of the fourth z gyro gz4 and the third z gyro temperature T gz3 The temperature difference of the third z gyro is obtained by subtraction, and according to the temperature T of the fourth quartz table a4 and the third quartz body temperature T a3 The temperature difference of the third quartz watch is obtained by making a difference;

[0048] According to the fifth x gyro temperature T gx5 and the fourth x gyro temperature T gx4 The temperature difference of the fourth x gyro is obtained by subtracting the temperature of the fifth y gyro T gy5 and the fourth y-gyro temperature T gy4 The temperature difference of the fourth y gyro is obtained by subtracting, and according to the temperature T of the fifth z gyro gz5 and the fourth z gyro temperature T gz4 The temperature difference of the fourth z gyro is obtained by subtraction, and according to the fifth quartz table body temperature T a5 and the fourth quartz body temperature T a4 Make the difference to get the temperature difference of the fourth quartz watch;

[0049] A temperature field influencing factor matrix is ​​obtained according to the first x gyro temperature difference, the second x gyro temperature difference, the third x gyro temperature difference, the fourth x gyro temperature difference, the first y gyro temperature difference, the second y gyro temperature difference, the third y gyro temperature difference, the fourth y gyro temperature difference, the first z gyro temperature difference, the second z gyro temperature difference, the third z gyro temperature difference, the fourth z gyro 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.

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

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

[0052] The outer spherical cover and the inner spherical cover in the double-layer spherical cover structure are two independent components, wherein the outer spherical cover is a closed structure that isolates the natural convection of the inner and outer air, and the inner spherical cover is an open structure that uses a fan 8 installed on the inner upper spherical cover 1 to realize the inner and outer air circulation flow fields.

[0053] The perforated baffle 7 is provided with circular holes of different diameters, which are distributed radially, so as to avoid the fan directly blowing the platform assembly 3 and causing local temperature changes, and ensure uniform gas flow in all directions at the fan air inlet.

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

[0055] The outer surface of the outer ball cover has a uniform long arc fin structure with uniform fin thickness and radial distribution; the inner and outer sides of the inner and outer ball covers are both distributed with small plane structures to facilitate the installation of temperature sensors.

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

[0057] The thermal structure design is optimized by thermal-fluid-solid coupling finite element simulation, the fan position is reasonably arranged, a circulating flow field is formed, and a double-layer ball cover structure is obtained. The structure is mainly composed of an inner upper ball cover 1, an outer upper ball cover 2, a platform assembly 3, an inner lower ball cover 4, an outer lower ball cover 5, a ring frame 6, a baffle plate with holes 7, a fan 8 and other components. The outer surfaces of the outer upper ball cover 2 and the outer lower ball cover 5 are fin heat dissipation structures, and the inner surfaces are coated with high thermal conductivity materials and installed with fans 8 for convection heat dissipation. The outer upper ball cover 2 and the outer lower ball cover 5 are installed on the ring frame 6 by screws; the inner upper ball cover 1 and the inner lower ball cover 4 parts are regularly distributed with slots, and the outer surfaces are installed with fans 8 for convection heat dissipation. The inner upper ball cover 1 and the inner lower ball cover 4 are connected by screws; the baffle plate with holes 7 is installed to the inner side of the fan installation surface of the inner upper ball cover 1 by screws. By adopting the thermal-fluid-solid coupling finite element method to obtain the internal temperature and flow field distribution of the platform, inner spherical cover and outer spherical cover, the number, position and flow rate of the fans and the structure of the structural parts are optimized to improve the heat dissipation efficiency and the uniformity of temperature distribution.

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

[0059] Establish a heat transfer model between the instrument and the table heating plate. Through cumulative heating at different stages, different tables and each instrument heating plate, obtain the temperature of each temperature measuring point after multiple groups of heating plates are stabilized. That is, firstly, power on the table heating plate to heat it, and measure the temperature T of each instrument after reaching equilibrium. gx1 , T gy1 , T gz1 , T a1 Then the stage heating plate is powered on, and the heating plates of the X-gyro, Y-gyro, and Z-gyro are powered on and heated in turn. Similarly, the temperature T of each instrument is measured after reaching equilibrium. gxi , T gyi , T gzi , T ai Finally, the quartz watch heater is powered on to heat up, 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 gxi-T gxi-1 , T gyi -T gyi-1 , T gzi -T gzi-1 , T ai -T ai-1 , we can get the influence factors of different heating plates on each temperature measurement point. Among them, each instrument heating plate will have a major temperature gradient influence on the corresponding instrument, but will also affect all other instruments. According to the temperature field influence factor matrix obtained above, we can obtain the temperature control model of the temperature field configuration according to the temperature vector corresponding to the matrix. Let the temperature vector of the temperature point be T, the temperature vector of 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 plate duty cycle combination can be obtained through algebraic calculation.

[0064] The outer spherical cover and the inner spherical cover in the double-layer spherical cover structure are two independent components, wherein the outer spherical cover is a closed structure that isolates the natural convection of the inner and outer air, and the inner spherical cover is an open structure that uses a fan 8 installed on the inner upper spherical cover 1 to realize the inner and outer air circulation flow fields.

[0065] Specifically, the thermal structure design is optimized through thermal-fluid-solid coupling finite element simulation, the fan position is reasonably arranged, and a circulating flow field is formed to obtain a double-layer ball cover structure for a fiber optic gyroscope inertial platform. The structure is mainly composed of an inner upper ball cover 1, an outer upper ball cover 2, a platform assembly 3, an inner lower ball cover 4, an outer lower ball cover 5, a ring frame 6, a baffle plate with holes 7, a fan 8 and other components. The outer surfaces of the outer upper ball cover 2 and the outer lower ball cover 5 are fin heat dissipation structures, the inner surfaces are coated with high thermal conductivity materials and a fan 8 is installed for convection heat dissipation, the outer upper ball cover 2 and the outer lower ball cover 5 are installed on the ring frame 6 by screws; slots are regularly distributed on the inner upper ball cover 1 and the inner lower ball cover 4, and a fan 8 is installed on the outer surface for convection heat dissipation, and the inner upper ball cover 1 and the inner lower ball cover 4 are connected by screws; the baffle plate with holes 7 is installed to the inner side of the fan installation surface of the inner upper ball cover 1 by screws to prevent the fan from blowing directly onto the platform.

[0066] Establish a heat transfer model between the instrument and the table heating plate. Through cumulative heating at different stages, different tables and each instrument heating plate, obtain the temperature of each temperature measuring point after multiple groups of heating plates are stabilized. That is, firstly, power on the table heating plate to heat it, and measure the temperature T of each instrument after reaching equilibrium. gx1 , T gy1 , Tgz1 , T a1 Then the stage heating plate is powered on, and the heating plates of the X-gyro, Y-gyro, and Z-gyro are powered on and heated in turn. Similarly, the temperature T of each instrument is measured after reaching equilibrium. gxi , T gyi , T gzi , T ai Finally, the quartz watch heater is powered on to heat up, 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 gxi -T gxi-1 , T gyi -T gyi-1 , T gzi -T gzi-1 , T ai -T ai-1 , we can get the influence factors of different heating plates on each temperature measurement point. Among them, each instrument heating plate will have a major temperature gradient influence on the corresponding instrument, but will also affect all other instruments. According to the temperature field influence factor matrix obtained above, we can obtain the temperature control model of the temperature field configuration according to the temperature vector corresponding to the matrix. Let the temperature vector of the temperature point be T, the temperature vector of 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 temperature of the next row from that of the previous row, we can get the influence factors of different heaters on each temperature point. From the influence factors, we can see that each heater will have a major influence on the temperature gradient of the corresponding heater, but will also affect all other heaters. From Table 1, we can get a temperature field influence factor matrix Λ.

[0071]

[0072] According to the temperature field influencing factor matrix obtained above, the temperature control model of the temperature field configuration can be obtained according to the temperature vector corresponding to the matrix. Let the temperature vector of the temperature point be T, the temperature vector of 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 plate duty cycle combination can be obtained through algebraic calculation.

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

[0076] This embodiment uses the finite element method to optimize the internal temperature and air flow field distribution of the inertial platform, optimizes the double-layer ball cover structure, forms a multi-level circulation flow field, and is conducive to enhancing the heat dissipation of the inertial platform. By controlling the multi-level temperature field between the outer ball cover and the inner ball cover, between the inner ball cover and the platform cover, and each instrument on the platform, the influence of the external environment temperature change on the inertial instrument can be reduced, providing a good external environment for instrument-level temperature control.

[0077] In this embodiment, a heat transfer model is established for the heating plates of each instrument inside the platform assembly to obtain the influence of the heating plates of each instrument on the temperature gradient, so that a temperature control model can be easily established.

[0078] The ball cover model of this embodiment is not limited to a double-layer structure, and can be adjusted accordingly according to the number of rings of an actual optical fiber platform, and has certain versatility and universality.

[0079] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A temperature control structure for an inertial instrument for a fiber optic gyro inertial platform, characterized in that include: An inner upper ball cover (1), an outer upper ball cover (2), a platform assembly (3), an inner lower ball cover (4), an outer lower ball cover (5), a ring frame (6), a baffle with holes (7) and a fan (8); wherein: The outer upper spherical cover (2) is connected to the outer lower spherical cover (5) via the ring frame (6); The inner upper ball cover (1) is connected to the inner lower ball cover (4) via the ring frame (6); The fans (8) are respectively arranged on the inner surface of the outer upper ball cover (2), the inner surface of the outer lower ball cover (5) and the outer surface of the inner upper ball cover (1); The perforated baffle plate (7) is installed on the inner side of the fan installation surface of the inner upper ball cover (1); The platform assembly (3) is arranged 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).

2. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 1, characterized in that: The outer surfaces of the outer upper ball cover (2) and the outer lower ball cover (5) are both fin heat dissipation structures, and the inner surfaces of the outer upper ball cover (2) and the outer lower ball cover (5) are coated with high thermal conductivity materials.

3. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 1, characterized in that: The inner upper ball cover (1) and the inner lower ball cover (4) are both provided with slot holes.

4. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 1, characterized in that: The perforated baffle (7) is provided with circular holes of different diameters, which are distributed radially, so as to avoid the fan directly blowing the platform assembly (3) and causing local temperature changes, and ensure that the gas flow in all directions at the fan inlet is uniform.

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

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

7. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 5, characterized in that: A multi-stage temperature conduction model is established by using temperature data collected by a temperature sensor, and the rotation speed of a fan (8) and the duty cycle of a heating plate of a platform component (3) are controlled in real time according to the multi-stage temperature conduction model to achieve stability of the inertial instrument balance temperature.

8. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 7, characterized in that: The multi-stage temperature conduction model is obtained by the following formula: T = T0 + Λ·Δ; Among them, T is the temperature vector of the temperature point, T0 is the temperature vector of each temperature point at room temperature, Δ is the duty cycle vector, and Λ is the temperature field influencing factor matrix.

9. The inertial instrument temperature control structure for the fiber optic gyro inertial platform according to claim 8, characterized in that: The temperature field influencing factor matrix is ​​obtained by the following method: The stage heating plate is powered on to heat up, and after reaching equilibrium, the first x gyro temperature T is measured. gx1 , the first y-gyro temperature T gy1 , the first z gyro temperature T gz1 , the first quartz body temperature T a1 ; The X gyro heating plate is powered on to heat up, and after reaching equilibrium, the second X gyro temperature T is measured. gx2 , the second y gyro temperature T gy2 , the second z gyro temperature T gz2 , the second quartz body temperature T a2 ; The Y gyro heating plate is powered on to heat up, and after reaching equilibrium, the temperature of the third x gyro T is measured. gx3 、The third y gyro temperature T gy3 、Third z gyro temperature T gz3 、The third quartz body temperature T a3 ; The Z gyro heating plate is powered on to heat up, and after reaching equilibrium, the temperature of the fourth gyro T is measured. gx4 , the fourth y gyro temperature T gy4 , Fourth z gyro temperature T gz4 , Fourth quartz body temperature T a4 ; The quartz watch heater is powered on to heat up, and after reaching equilibrium, the fifth x gyro temperature T is measured. gx5 、Fifth y gyro temperature T gy5 、Fifth z gyro temperature T gz5 、5. Quartz body temperature T a5 ; According to the second x gyro temperature T gx2 and the first x gyro temperature T gx1 The temperature difference of the first x gyro is obtained by subtracting the temperature of the second y gyro. gy2 and the first y-gyro temperature T gy1 The temperature difference of the first y gyro is obtained by subtracting the temperature of the second z gyro. gz2 and the first z gyro temperature T gz1 The temperature difference of the first z gyro is obtained by subtracting the temperature of the second quartz table T a2 and the first quartz body temperature T a1 Make a difference to get the temperature difference of the first quartz watch; According to the third x gyro temperature T gx3 and the second x gyro temperature T gx2 The temperature difference of the second x gyro is obtained by subtracting it, and according to the temperature T of the third y gyro gy3 and the second y-gyro temperature T gy2 The temperature difference of the second y gyro is obtained by subtracting the temperature of the third z gyro. gz3 and the second z gyro temperature T gz2 The temperature difference of the second z gyro is obtained by subtraction, and the temperature of the third quartz table body T a3 and the second quartz body temperature T a2 Make a difference to get the temperature difference of the second quartz watch; According to the fourth x gyro temperature T gx4 and the third x gyro temperature T gx3 The temperature difference of the third x gyro is obtained by subtracting, and according to the temperature T of the fourth y gyro gy4 and the third y gyro temperature T gy3 The temperature difference of the third y gyro is obtained by subtracting, and according to the temperature T of the fourth z gyro gz4 and the third z gyro temperature T gz3 The third z gyro temperature difference is obtained by subtraction, and according to the fourth quartz table body temperature T a4 and the third quartz body temperature T a3 The temperature difference of the third quartz watch is obtained by making a difference; According to the fifth x gyro temperature T gx5 and the fourth x gyro temperature T gx4 The temperature difference of the fourth x gyro is obtained by subtracting the temperature of the fifth y gyro T gy5 and the fourth y-gyro temperature T gy4 The temperature difference of the fourth y gyro is obtained by subtracting, and according to the temperature T of the fifth z gyro gz5 and the fourth z gyro temperature T gz4 The temperature difference of the fourth z gyro is obtained by subtraction, and according to the fifth quartz table body temperature T a5 and the fourth quartz body temperature T a4 Make the difference to get the temperature difference of the fourth quartz watch; A temperature field influencing factor matrix is ​​obtained according to the first x gyro temperature difference, the second x gyro temperature difference, the third x gyro temperature difference, the fourth x gyro temperature difference, the first y gyro temperature difference, the second y gyro temperature difference, the third y gyro temperature difference, the fourth y gyro temperature difference, the first z gyro temperature difference, the second z gyro temperature difference, the third z gyro temperature difference, the fourth z gyro 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.

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

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