Multi-ion synergistic electrochromic window intelligent control system for manned spacecraft

Abstract

The present application relates to a multi-ion synergistic electrochromic window intelligent control system for manned spacecraft, belonging to the technical field of intelligent materials and aerospace control systems, solving the problems of control lag defects of traditional passive feedback, functional isolation of electrochromic control system, etc. The system constructs an intelligent control system with "feedforward prediction as the main, feedback fine-tuning as the auxiliary", realizes advance prediction type dimming based on the orbit and attitude data of manned spacecraft, perfectly adapts to the rapidly changing light environment of low earth orbit, and realizes "zero delay" anti-glare and heat load control.

Description

Technical Field

[0001] This invention belongs to the interdisciplinary field of smart materials and aerospace control systems, specifically relating to a multi-ion collaborative electrochromic porthole intelligent control system for manned spacecraft, which is particularly suitable for the intelligent dimming and system integration design of ultra-large portholes in manned spacecraft, space stations and other on-orbit manned spacecraft. Background Technology

[0002] During their operation in orbit, manned spacecraft face an extreme and rapidly changing space lighting environment. Low Earth orbit spacecraft complete a day-night cycle every 90 minutes. The direct sunlight, which is not filtered by the Earth's atmosphere, contains high-intensity ultraviolet, visible, and near-infrared radiation across the entire spectrum. This not only easily causes sunburn and visual glare for the occupants but also significantly increases the load on the cabin's thermal control system. Therefore, the windows of manned spacecraft must have a wide range and fast-response intelligent dimming capability.

[0003] Existing multi-ion synergistic electrochromic portholes, used in aviation, shipbuilding, and other fields, have several technical shortcomings when applied to the space environment, as follows: (1) The control logic is seriously lagging: the existing electrochromic porthole control system mostly adopts the passive feedback control mode based on the current illumination data, which cannot adapt to the drastic changes in the illumination conditions of near-Earth orbit space on the order of minutes or even seconds. It is easy to cause glare and sudden increase in heat load due to dimming lag, and cannot achieve active and predictive dimming control.

[0004] (2) Low system integration and isolated functions: The existing electrochromic window control system is mostly an independent functional unit and is not linked with the spacecraft power system and attitude and orbit control system, so it cannot achieve collaborative optimization; at the same time, it does not integrate auxiliary functions such as window film health status monitoring and window film temperature monitoring, resulting in insufficient overall performance and adaptability.

[0005] Based on the shortcomings of the existing technologies, there is an urgent need in this field to develop an overall solution for an electrochromic window control system that has a faster control response, higher system integration, stronger adaptability to the space environment, and can be deeply adapted to manned spacecraft. Summary of the Invention

[0006] The technical problem solved by this invention is to address the aforementioned deficiencies in the prior art by providing a multi-ion coordinated electrochromic porthole intelligent control system for manned spacecraft, mainly solving the following technical problems: (1) Abandoning the lag defect of traditional passive feedback control, constructing a feedforward master control loop based on spacecraft orbit attitude prediction, and combining feedback fine-tuning of multi-dimensional real-time sensing to achieve “zero-delay” intelligent dimming under space illumination changes; (2) Break the functional isolation problem of the electrochromic control system. By linking with the spacecraft attitude and orbit control system and power system, the temperature and health status of the window film layer are monitored at the same time, so as to achieve precise control of the electrochromic window and complete the functional optimization of the electrochromic window control system.

[0007] The solution of this invention is: a multi-ion coordinated electrochromic porthole intelligent control system for manned spacecraft, the system including a prediction feedforward main control module and a feedback fine-tuning control module; the porthole is set with N partitions, each partition is set with independent electrode leads and execution units, where N is a positive integer greater than 1; The prediction feedforward main control module predicts the solar incidence angle and irradiance for each section of the porthole based on the spacecraft's current orbital parameters, attitude data, and solar ephemeris data. It obtains the visible and near-infrared irradiance at the predicted time based on the energy proportions of different spectral bands. Based on these irradiances, it calculates the effective visible and near-infrared irradiance, determines the spacecraft's irradiance scenario, and finally calculates the target visible transmittance value for the predicted time. By comparing the current visible light transmittance with the target value of visible light transmittance at the predicted time, it is determined whether the porthole is about to enter the tinting or fading process. Substituting the pre-calibrated near-infrared blocking rate minus visible light transmittance function, determine the target value of the near-infrared blocking rate at the prediction time. Based on the target value of visible light transmittance at the predicted time and the target value of near-infrared blocking rate at the predicted time Calculate the base driving voltage for each partition coloring process at the prediction time. Or the basic driving voltage during the fading process ; The feedback fine-tuning control module acquires the window film temperature, the spacecraft's current remaining power, and the window film health status, and sets the base driving voltage for the coloring process of each window zone at the predicted time. Or the basic driving voltage of the fading process Correction yields the actual driving voltage for each zone coloring process of the porthole at the predicted time. Or the actual driving voltage during the fading process The actual driving voltage of each partition coloring process at the predicted time will be used. Or the actual driving voltage during the fading process Send it to the corresponding execution unit; The execution unit, based on the actual driving voltage during the coloring process Or the actual driving voltage during the fading process It generates independent drive voltages to independently control the dimming of each zone of the porthole.

[0008] Preferably, the angle of sunlight incidence for each section of the porthole is calculated using the following method: Extrapolate the spacecraft's position, velocity, and transformation matrix from the spacecraft's body coordinate system to the window coordinate system at the predicted time. ; Calculate the solar incident vector in the geocentric inertial coordinate system at the predicted time. ; Based on the spacecraft's position, velocity, and the transformation matrix from the spacecraft's body coordinate system to the window coordinate system at the predicted time. The solar incident vector in the geocentric inertial coordinate system Convert to solar incident vector in porthole coordinate system ; Calculate the solar incident vector in the porthole coordinate system at the predicted time. The angle between the angle and the normal vector of each section of the porthole is the angle of sunlight incident on each section of the porthole at the predicted time.

[0009] Preferably, the method for predicting the irradiance of each zone of the porthole is as follows: Determine whether the spacecraft is in the sunlit, penumbra, or umbra region at the predicted time, and output the ground shadow occlusion coefficient. ; Based on the angle of sunlight incidence in each section of the porthole Ground shadow occlusion coefficient Calculate the direct solar irradiance for each partition. In the formula, The standard solar constant outside the atmosphere. This is the correction factor for the Earth-Sun distance; Based on the energy proportions of different spectral bands, the visible and near-infrared irradiance at the predicted time are obtained, and the visible irradiance of each region at the predicted time is calculated. and near-infrared irradiance The following formula is used to calculate: In the formula, This represents the percentage of visible light energy. This represents the energy percentage coefficient in the near-infrared band. This indicates the angle of incidence of visible light. Incident to the Actual transmittance for each zone, Indicates the near-infrared band at the angle of incidence. Incident to the Actual transmittance for each zone.

[0010] Preferably, At that time, the spacecraft was in an anti-glare priority scenario; At that time, the spacecraft was in a scenario where thermal protection was the priority. At that time, the spacecraft was in a routine, dual-use scenario; At that time, the spacecraft was in a high-transparency standby scenario; in, Visible light effective irradiance, This refers to the effective near-infrared irradiance.

[0011] The basic driving voltage of the coloring process Determined using the following method: Based on the target value of visible light transmittance at the predicted time Coloring voltage-visible light transmittance function Combined with the incident angle correction factor To obtain a separate driver for Li + The coloring voltage, denoted as ; In the formula, Li + Embedded threshold voltage, Li + Saturation embedding voltage; Based on the target value of near-infrared blocking rate Coloring voltage-near-infrared blocking rate function Combined with the ion-coordinated voltage coupling coefficient To obtain a separate driving Na + The coloring voltage, denoted as Ensure Na + In Li + Embedded functionality will be implemented after startup; In the formula Na represents + Embedded threshold voltage, Na represents + Saturation embedding voltage; Pick and The larger value in the range is used as the basic driving voltage for the coloring process. .

[0012] Preferably, the basic driving voltage of the fading process Determined using the following method: Based on the target value of near-infrared blocking rate and fading voltage-near-infrared blocking rate function To obtain a separate driving Na + fading voltage ; In the formula, Na represents + De-intercalation threshold voltage Na represents + Complete de-intercalation saturation voltage; Based on the target value of visible light transmittance at the predicted time and fading voltage-visible light transmittance function To obtain a separate driver for Li + fading voltage ; In the formula , Li + De-intercalation threshold voltage Li + Complete de-intercalation saturation voltage; Pick and The larger value is used as the basic driving voltage for the fading process. .

[0013] Preferably, the actual driving voltage during the coloring process and the actual driving voltage during the fading process The calculation formula is: In the formula, This is the temperature correction factor for the porthole film. This is a correction factor for the spacecraft's electrical charge. This is a correction factor for the health status of the porthole film layer.

[0014] Preferably, the temperature correction coefficient of the porthole film layer for: In the formula This refers to the temperature of the porthole film layer.

[0015] Preferably, the spacecraft's electrical correction coefficient for: In the formula, This refers to the State of Charge (SOC) value of the power system of a manned spacecraft.

[0016] Preferably, the health correction coefficient of the porthole film layer Based on membrane health status values The value is determined.

[0017] The advantages of this invention compared to the prior art are: (1) Fundamental innovation in control logic: The intelligent control system constructed in this invention, which is based on "feedforward prediction as the main method and feedback fine-tuning as the auxiliary method", realizes advance prediction-based dimming based on the orbit and attitude data of manned spacecraft, fundamentally solving the problem of lag in traditional feedback control, perfectly adapting to the rapidly changing lighting environment in near-Earth orbit, and achieving "zero-delay" anti-glare and heat load control; at the same time, the zoned independent control strategy takes into account both the occupant observation needs and energy-saving and heat insulation needs, greatly improving the user experience.

[0018] (2) The system integration and synergy are greatly improved: This invention breaks the limitation of the independent unit of the electrochromic control system and is linked with the attitude and orbit control system and power system of the manned spacecraft to achieve system-level synergistic optimization. By monitoring the temperature and health status of the window film, the on-orbit dimming / heat insulation performance is improved while extending the service life of the window film, thus improving the overall system energy efficiency of the manned spacecraft. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the overall architecture and data flow of the intelligent control system according to an embodiment of the present invention; Figure 2 This is a schematic diagram illustrating a typical application scenario of the independent window zone control strategy according to an embodiment of the present invention. Detailed Implementation

[0020] The present invention will be further described below with reference to the embodiments.

[0021] This invention abandons the traditional passive feedback control mode and constructs a multi-ion collaborative electrochromic window intelligent control system for manned spacecraft. It belongs to the dual-loop intelligent control system of "predictive feedforward as the main method and real-time feedback as the auxiliary method". At the same time, it adopts a window full-domain zone independent control strategy to achieve intelligent dimming in all scenarios with zero delay.

[0022] like Figure 1 As shown, the multi-ion coordinated electrochromic porthole intelligent control system for manned spacecraft specifically includes: (1) Predictive feedforward master control module The predictive feedforward main control module is the core control unit of the dual-loop intelligent control system described in this invention. It is deeply integrated into the spacecraft's main control computer and interacts with the spacecraft's attitude and orbit control system and the onboard high-precision ephemeris in real time. The module has a built-in window illumination prediction algorithm. Based on the current orbital parameters and attitude data provided by the attitude and orbit control system and the solar ephemeris data provided by the onboard high-precision ephemeris, it predicts the solar incidence angle and irradiance of each window section in advance (1-3 minutes). Based on the energy ratio of each spectral band, it obtains the visible light irradiance and near-infrared irradiance at the predicted time. Based on the visible light irradiance and near-infrared irradiance at the predicted time, it calculates the effective visible light irradiance and effective near-infrared irradiance at the predicted time, thereby determining the irradiance scene where the spacecraft is located at the predicted time. Based on the irradiance scene where the spacecraft is located at the predicted time, it calculates the target value of visible light transmittance at the predicted time. By comparing the target values ​​of visible light transmittance at the current time and the predicted time, it is determined whether the porthole is about to enter the tinting or fading process. The target value of visible light transmittance at the predicted time is then used. Substituting the pre-calibrated near-infrared blocking rate minus visible light transmittance function, the target value of the near-infrared blocking rate at the prediction time is determined. Based on the target value of visible light transmittance at the predicted time and the target value of near-infrared blocking rate at the predicted time Calculate the base driving voltage for each partition coloring process at the prediction time. Or the basic driving voltage during the fading process .

[0023] (2) Feedback fine-tuning control module The feedback fine-tuning control module acquires real-time information on the window film temperature, the spacecraft's remaining power, and the window film's health status, and then uses the base driving voltage for the coloring process of each window zone at the predicted time. and the basic driving voltage of the fading process Correction yields the actual driving voltage for each zone coloring process of the porthole at the predicted time. and the actual driving voltage during the fading process The actual driving voltage of each partition coloring process at the predicted time. Or the actual driving voltage during the fading process Send it to the corresponding execution unit.

[0024] (3) Execution unit The porthole is divided into N independent areas, each with its own electrode leads and actuation unit. N is a positive integer greater than 1.

[0025] The execution unit, based on the actual driving voltage during the coloring process Or the actual driving voltage during the fading process It generates independent drive voltages to independently control the dimming of each zone of the porthole.

[0026] The main contents of this invention will be described in detail below: The onboard main control computer completes a full-process calculation every second, continuously updating the predicted parameters for the next 1-3 minutes to ensure the real-time performance of the predictions and the smoothness of the drive control. Using the solar incidence angle and wavelength-specific irradiance of each window zone at the predicted time, the drive voltage for the corresponding window zone is calculated. In a specific embodiment of this invention, the steps are as follows: S1, Prediction Algorithm S1.1 Extrapolation of spacecraft orbit and attitude in the next 1-3 minutes 1) Extrapolation of track position Using the SGP4 / SDP4 orbital model, which is commonly used in aerospace engineering, the predicted time is obtained by extrapolating the current TLE orbital elements. ( For the current moment, (With a lead time of 1-3 minutes), the spacecraft's center of mass position vector and velocity vector in the J2000 ECI geocentric inertial coordinate system are shown below: In the formula, This represents the position vector of the spacecraft's center of mass in the J2000 ECI geocentric inertial frame. This represents the spacecraft velocity vector in the J2000ECI geocentric inertial frame. This is an extrapolation function for the orbital position of a near-Earth orbit spacecraft, used to calculate the geometric position of the spacecraft in the J2000 ECI geocentric inertial frame at the predicted time. yes The velocity calculation function is used to calculate the spacecraft's velocity vector at the predicted time.

[0027] 2) Spacecraft attitude extrapolation Based on spacecraft rigid body attitude dynamics, a quaternion linear extrapolation method is used to extrapolate the spacecraft's attitude quaternion vector relative to the orbital coordinate system at the predicted time. Based on this quaternion vector, the attitude transformation matrix from the orbital coordinate system to the spacecraft's body coordinate system is calculated. : 1) Extrapolated attitude quaternion vector The attitude quaternion vector of the spacecraft body relative to the orbital coordinate system at the predicted time is shown in the following equation: In the formula, Indicates the current time The attitude quaternion vector of the spacecraft body relative to the orbital coordinate system. This represents the cosine value of the half-angle rotation at the current moment. Together, these three elements represent the direction information of the rotation axis at the current moment. Coupled with the sine value of the current rotation half-angle. Indicates the predicted time The attitude quaternion vector of the spacecraft body relative to the orbital coordinate system. This represents the cosine value of the half-angle of rotation at the predicted time. Together, these three elements represent the direction information of the rotation axis at the predicted time. It is coupled with the sine value of the half-angle of rotation at the predicted time. To represent quaternion multiplication, ,in This represents the X-axis attitude angular velocity of the spacecraft body relative to the orbital coordinate system; This represents the Y-axis attitude angular velocity of the spacecraft body relative to the orbital coordinate system; This represents the Z-axis attitude angular velocity of the spacecraft body relative to the orbital coordinate system. The antisymmetric matrix corresponding to the XYZ three-axis attitude angular velocities is expressed as: 2) Calculate the attitude transformation matrix from the orbital coordinate system to the spacecraft body coordinate system. The predicted time obtained after extrapolation attitude quaternion vector Convert to attitude transformation matrix As shown in the following formula: S1.2 Calculate the solar incident vector in the geocentric inertial coordinate system at the predicted time. 1) Calculate the predicted time of UTC to Julian Day conversion Using a simplified formula adapted for spaceborne operations from 1900 to 2100 (integer operations with no floating-point error), the predicted time and year are known. ,moon ,day ,hour ,point ,Second : In the formula, the function INT() represents rounding down.

[0028] 2) Calculate the Julian century number for the predicted time. T Julian Century TThis represents the time difference relative to the geocentric inertial coordinate system at the predicted time, expressed in Julian centuries (1 century = 36525 days), and is the core independent variable for all square roots. 3) Calculate the mean aperimeter angle of the sun at the predicted time. Sun's horizontal aperitoneal angle It describes the angle of the Sun relative to the perihelion in the Earth's orbit, and is a core parameter for correcting orbital perturbations and calculating the Earth-Sun distance.

[0029] 4) Calculate the solar mean ecliptic longitude at the predicted time. Sun longitude It is the mean longitude of the sun in the ecliptic coordinate system, and is the core reference for calculating the sun's apparent position and the ecliptic-to-equatorial coordinates.

[0030] 5) Calculate the obliquity of the ecliptic at the predicted time. obliquity of the ecliptic It is the angle between the ecliptic plane and the Earth's equatorial plane.

[0031] 6) Correct orbital perturbations and calculate the apparent ecliptic longitude at the predicted time. Sun longitude To obtain the average position, the center difference of the elliptical revolution needs to be corrected to get the apparent ecliptic longitude of the sun at the predicted time. As shown in the following formula: 7) Calculate the solar incident vector in the geocentric inertial coordinate system at the predicted time. : S1.3, the solar incident vector in the geocentric inertial coordinate system Convert to solar incident vector in porthole coordinate system This step maps the solar incidence vector in the geocentric inertial coordinate system to the single-span window coordinate system step by step, and then calculates the angle of incidence of sunlight relative to each section of the window, i.e., the angle of incidence of sunlight in each section of the window. The overall transformation link is: geocentric inertial coordinate system (J2000 ECL) → orbital coordinate system (LVLH) → spacecraft body coordinate system (BODY) → single-span window installation coordinate system (WIN).

[0032] 1) The solar incident vector in the geocentric inertial frame Convert to solar incidence vector in orbital coordinate system The orbital coordinate system has its origin at the spacecraft's center of mass, with the X-axis along the orbital velocity direction, the Z-axis pointing towards the Earth's center, and the Y-axis perpendicular to the orbital plane. The transformation matrix from the geocentric inertial frame to the orbital coordinate system is... for: The solar incidence vector in the transformed orbital coordinate system is: 2) The solar incident vector in the orbital coordinate system Converted to solar incident vector in spacecraft body coordinate system : Using attitude matrix The solar incident vector in the spacecraft's body coordinate system is obtained by transformation as follows: Origin of spacecraft body coordinate system For the spacecraft's center of mass, The axis runs along the longitudinal axis of the spacecraft body and points towards the head of the spacecraft (direction of travel). The axis is along the horizontal axis of the spacecraft body and points to the right side of the spacecraft, satisfying the right-hand orthogonal rule; The axis runs along the vertical axis of the spacecraft body, pointing towards the top of the spacecraft, and is... , This forms a right-handed orthogonal unit coordinate system.

[0033] 3) The solar incident vector in the spacecraft's body coordinate system Convert to solar incident vector in porthole coordinate system Based on the ZYX sequential moving axis Euler angle rotation rule, generate the transformation matrix from the spacecraft body coordinate system to the porthole coordinate system. As shown in the following formula: In the formula, the yaw angle is installed. For the body coordinate system The rotation angle of the axis determines the left and right orientation of the porthole in the circumference of the spacecraft. The installation yaw angle of the forward porthole of the spacecraft is 0°, the installation yaw angle of the porthole on the left side of the spacecraft is 90°, the installation yaw angle of the porthole on the right side of the spacecraft is 270°, the installation yaw angle of the porthole on the tail of the spacecraft is 180°, and the installation yaw angle of the porthole at the non-orthogonal point in the circumference is directly assigned according to the circumferential angle. Install pitch angle To yaw angle Newly generated after rotation The rotation angle of the shaft determines the fore-and-aft tilt of the porthole, and is a core parameter affecting the field of view and incident light; its value ranges from 15° to 30°. Installation roll angle... For pitch angle Newly generated after rotation The rotation angle of the axis determines the amount of rotation of the porthole around its own normal, ensuring that the porthole is horizontally / vertically aligned, and is fixed at 0°.

[0034] The solar incident vector in the porthole coordinate system is: S1.4 Constructing a local coordinate system for a single section of the porthole from the porthole coordinate system 1) Definition of coordinate system (1) Porthole coordinate system It is the global reference coordinate system for the porthole. The origin is the geometric center of the porthole glass; the coordinate axes The axis representing the overall normal of the porthole is perpendicular to the porthole reference plane and points inwards into the cabin; coordinate axis The horizontal axis is located in the reference plane of the porthole, and is horizontal to the right when viewed from inside the cabin; coordinate axis The vertical axis is located in the reference plane of the porthole, and is vertically upward when viewed from inside the cabin.

[0035] (2) Local coordinate system of the partition It is the local reference coordinate system for each section within the porthole. This is the partition number. The origin is the first The geometric center of each partition; coordinate axes For the first The local normal axis of each partition is perpendicular to the first... Each partition's local reference plane points outwards; coordinate axes For the first The horizontal axis within the local reference plane of each partition, and Parallel; coordinate axes For the first The vertical axis within the local reference plane of each partition, and parallel.

[0036] coordinate axes exist The unit vector in the coordinate system is For porthole glass of arbitrary shape, as long as the surface equation of the glass is known, it can be derived using the gradient method. The derivation process is as follows: Step 1: Definition of Surface Equation In the porthole coordinate system, the surface of the porthole glass can be described as: in Let the horizontal and vertical coordinates of the points on the glass surface be... The depth coordinates of this point (the Z-axis points inwards from the cabin, therefore...) (Direction is the negative Z-axis direction).

[0037] Step 2: Solve using the gradient method The implicit equation of the surface can be written as: Based on the properties of gradients, the gradient of an implicit function is a unit vector along the Z-axis of the surface. Therefore... The opposite direction of the implicit function gradient is expressed as follows: 2) Orthogonalization of local coordinate axes (1) Constructing a local X-axis Project the global X-axis of the porthole onto the local reference plane of the partition. coordinate system The X-axis unit vector.

[0038] (2) Constructing a local Y-axis The coordinate axes are automatically obtained through cross product. exist unit vector in coordinate system S1.5, Precise calculation of the solar incidence angle for each section of the porthole. The solar incidence angle of the single-zone porthole output in this step is the core parameter for calculating the electrochromic driving voltage.

[0039] Porthole Sun incidence angle in each zone For the predicted time, the solar incident vector and the first The angle between the normal vectors of each partition is only when At that time, the area was directly exposed to sunlight. The calculation formula is as follows: S1.6 Precise Calculation of Irradiance in a Single Zone of the Porthole at Predicted Time 1) Determining the boundary of the ground shadow Determine whether the spacecraft is in the sunlit, penumbra, or umbra region at the predicted time, and output the ground shadow occlusion coefficient. When the Earth is in its umbra, the sun is completely blocked by the Earth. When in a sunny area, the sun is unobstructed. When the Earth is in the penumbra, part of the sun is blocked by the Earth. Calculate according to the following steps Specific numerical values.

[0040] From the perspective of a spacecraft, the Earth and the Sun can be approximated as two circular planes on the celestial sphere.

[0041] (1) Calculate the apparent radius of the Earth And the apparent radius of the sun a. Earth's apparent radius Earth's apparent radius The formula for calculating the half-angle of Earth as observed from a spacecraft is as follows: In the formula, This represents the Earth's equatorial radius, with a value of 6378.13 km. The distance from the Earth's center to the spacecraft is represented by the following formula. In the formula, The position vector from the Earth's center to the spacecraft is represented by the following formula: Low Earth orbit The value is 6778.13km.

[0042] b. The apparent radius of the sun apparent radius of the sun The formula for calculating the half-angle of the sun as observed from a spacecraft is as follows: In the formula, This represents the radius of the sun, with a value of 695,700 km. The instantaneous Earth-Sun distance is expressed by the following formula: In the formula, The formula for calculating the angle of approach is shown below: In the formula, The orbital eccentricity is expressed by the following formula: (2) Calculate the angular distance σ between the centers of the two viewing planes. σ represents the angle between the direction of the Earth's center and the direction of the Sun as observed from the spacecraft, that is, the angular distance between the centers of the two planes of view.

[0043] a. Calculate the unit vector pointing from the spacecraft to the Earth's center. The calculation formula is as follows: b. Calculate the unit vector pointing from the spacecraft to the sun. In the formula The position vector from the Earth's center to the Sun is represented by the following formula: c. Calculate the cosine of the angle between two vectors by calculating the dot product of the two vectors. d. Calculate angular distance (3) Calculate the shading coefficient The occlusion relationship between two circular view planes is equivalent to the overlap problem of two circles on a plane. The occlusion coefficient is obtained by calculating the ratio of the overlapping areas. This is based on the Earth's apparent radius. The apparent radius of the sun Calculate the overlapping area of ​​the two circular viewing planes by the angular distance σ between their centers. The overlapping area of ​​two view planes The full apparent size of the sun Calculate the occlusion coefficient Specifically: (1) If No overlap It is believed that the spacecraft is in a sunlit area. ; (2) If The sun was completely blocked by the Earth. They believe the spacecraft is located in the umbra. ; (3) If : It is believed that the spacecraft is in the penumbra, because Therefore, the occlusion coefficient for: 2) Calculate the first Direct solar irradiance in each zone No. Direct solar irradiance in each zone The calculation formula is: In the formula, For a single zone, the solar incidence angle is only when There is direct radiation at times, otherwise The standard solar constant outside the atmosphere has a value of [value missing]. ; The Earth-Sun distance correction factor is calculated using the following formula: In the formula, The average distance between the Earth and the Sun is denoted as , and its value is . km.

[0044] S1.7 Calculate solar irradiance by wavelength. This step obtains the irradiance of the two core bands, visible light and near-infrared, based on the energy proportions of different spectral bands, directly corresponding to Li. + and Na + The drive control strategy.

[0045] Table 1 Energy percentage of AM0 standard solar spectrum outside the atmosphere by band irradiance by waveband The calculation formula is: In the formula, Indicates the first Each partition corresponds to a waveband. irradiance; Indicates the corresponding band The energy proportions of the AM0 spectrum are shown in Table 1; Indicates wavelength as The incident light, at the angle of incidence Incident to the The actual transmittance of the porthole glass in each zone The calculation consists of the following 5 steps: Step 1: Calculate the angle of refraction According to Snell's law, when incident light enters glass from a vacuum, the angle of refraction is... satisfy: Indicates wavelength The refractive index of the lower glass is a fixed value, and the refractive index of visible light is... =1.458, near-infrared =1.443, ultraviolet radiation =1.472.

[0046] Step 2: Calculate the interface reflectivity According to Fresnel's formula, the interface reflectivity of s-waves for: p-wave interface reflectivity for: Interface reflectivity for: Step 3: Calculate the reflectance and transmittance The glass has two interfaces (outside air-glass, inside glass-air). Ignoring the minor effects of multiple reflections, the reflectance transmittance... for: Step 4: Calculate the absorption transmittance According to Beer-Lambert's law, absorption transmittance... for: In the formula, This indicates the thickness of the porthole glass, and is taken as 10mm. Indicates wavelength The absorption coefficient of the lower glass is a fixed value, and the absorption coefficient of visible light is... Near-infrared ultraviolet rays .

[0047] Step 5: Calculate the actual transmittance Will and Combined, the actual transmittance is obtained. : S2, Pre-calibration core parameters In order to precisely adjust the visible light transmittance and near-infrared band blocking rate, it is necessary to calibrate the multi-ion synergistic electrochromic film structure to obtain the relationship between visible light transmittance and coloring voltage, near-infrared blocking rate and coloring voltage, visible light transmittance and fading voltage, and near-infrared blocking rate and fading voltage.

[0048] In a specific embodiment of the present invention, a polynomial fitting method is used to construct and solve the visible light transmittance-coloring voltage function, the near-infrared blocking rate-coloring voltage function, the near-infrared blocking rate-visible light transmittance function, the near-infrared blocking rate-fading voltage function, and the visible light transmittance-fading voltage function. Then, according to the definition of inverse functions, the coloring voltage-visible light transmittance function, the coloring voltage-near-infrared blocking rate function, the visible light transmittance-near-infrared blocking rate function, the fading voltage-near-infrared blocking rate function, and the fading voltage-visible light transmittance function are obtained. Specifically, as follows: 1) Visible light transmittance - coloring voltage function , Visible light transmittance-coloring voltage function Indicates the visible light transmittance of the electrochromic film layer. With Li + Coloring voltage The mapping relationship is such that the function is a monotonically decreasing function. Indicates that Li is driven separately + The coloring voltage, with a value range of Li + Embedded threshold voltage, with a value of 0.4V; Li + Saturation embedding voltage, taken as 0.9V. Visible light transmittance. The range of values ​​is express The highest light transmittance at that time was 85%. express The minimum transmittance at that time is set to 10%.

[0049] 2) Coloring voltage-visible light transmittance function Coloring voltage-visible light transmittance function It is a function of visible light transmittance and coloring voltage. The inverse function of is monotonically decreasing, and its analytical expression is shown below: 3) Near-infrared blocking rate - coloring voltage function , Near-infrared blocking rate - coloring voltage function Indicates the near-infrared blocking efficiency of the electrochromic film layer with Na + Coloring voltage The mapping relationship is such that the function is a monotonically increasing function. Indicates that Na is driven separately. + The coloring voltage, with a value range of ; Na represents + Embedded threshold voltage, with a value of 0.7V; Na represents + Saturation embedding voltage, taken as 1.4V. Near-infrared blocking rate. The range of values ​​is , express The minimum near-infrared blocking rate is set at 20%. express The highest near-infrared blocking rate was 92%.

[0050] 4) Coloring voltage-near-infrared blocking rate function Coloring voltage-near-infrared blocking rate function It is a function of near-infrared blocking rate and coloring voltage. The inverse function of is monotonically increasing, and its analytical expression is shown below: 5) Near-infrared blocking rate - visible light transmittance function Li + and Na + Driven by the same voltage, Li + First embedding, Na + Post-embedding. Only when Li + Coloring voltage greater than Li Shi + Activate embedded control of visible light transmittance , only if Na + Coloring voltage greater than And Li + After pre-embedding is completed, Na + Activate embedded modulation of near-infrared blocking rate .

[0051] Visible light transmittance As the color voltage increases, the near-infrared blocking rate decreases strictly and monotonically. The color voltage increases strictly monotonically with increasing color voltage. Therefore, by using the color voltage as an intermediate variable, the near-infrared blocking rate can be obtained. With visible light transmittance The functional relationship is shown in the following formula: Near-infrared blocking rate - Visible light transmittance function. It is a monotonically decreasing function.

[0052] 6) Visible light transmittance - near-infrared blocking rate function Visible light transmittance - near-infrared blocking rate function It is a function of near-infrared blocking rate and visible light transmittance. The inverse function of , which is monotonically decreasing, is shown in the following equation: 7) Near-infrared blocking rate - fading voltage function The calculation logic for the fading process is the same as that for the coloring process, only the voltage polarity is reversed; the fading process is driven by a positive DC voltage. Under the action of the positive driving voltage, Na+ ions with larger ionic radii... + The insertion / extraction barrier is lower, leading to earlier insertion / extraction and a corresponding decrease in near-infrared blocking efficiency; Li has a smaller ionic radius. + Post-deintercalation results in increased visible light transmittance. Near-infrared blocking rate decreases strictly monotonically with increasing fading voltage; the near-infrared blocking rate versus fading voltage function... The analytical expression is shown below.

[0053] Near-infrared blocking rate-fading voltage function Indicates the near-infrared blocking efficiency of the electrochromic film layer with Na + Fading voltage The mapping relationship, Indicates that Na is driven separately. + The fading voltage, with a value range of [value missing]. ; Na represents + The de-intercalation threshold voltage is set to 0.15V. Na represents + The complete deintercalation saturation voltage is set to 0.3V. Near-infrared blocking rate. The value range is [92%, 20%].

[0054] 8) Fading voltage-near-infrared blocking rate function Fading voltage-near-infrared blocking rate function It is a function of near-infrared blocking rate and fading voltage. The inverse function of is shown in the following expression.

[0055] 9) Visible light transmittance - fading voltage function Visible light transmittance-fading voltage function Indicates the visible light transmittance of the electrochromic film layer. With Li + Fading voltage The mapping relationship is such that the function is a monotonically increasing function. Indicates that Li is driven separately + The fading voltage, with a value range of [value missing]. ; Li + The de-intercalation threshold voltage is set to 0.2V. Li + The complete deintercalation saturation voltage is set to 0.5V. Visible light transmittance. The value range is [10%, 85%].

[0056] 10) Fading voltage-visible light transmittance function Fading voltage-visible light transmittance function It is a function of visible light transmittance and fading voltage. The inverse function of is shown in the following expression.

[0057] S3. Calculate the effective irradiance by band. By band irradiance The visible light irradiance is obtained by calculating the energy proportions of the AM0 spectrum by wavelength using the formula and in Table 1. for: Near-infrared irradiance for: Effective irradiance in the visible light band and effective irradiance in the near-infrared band for: In the formula, Correcting the attenuation of irradiance flux of obliquely incident light; This is an incident angle correction factor, used to correct the oblique optical properties of the porthole glass. The calculation formula is as follows: S4. Calculate the target value of visible light transmittance. and near-infrared blocking rate target value Visible light effective irradiance calculated based on S3 and near-infrared effective irradiance The scenarios are divided into four categories according to their priority from high to low, such as... Figure 2 As shown in Table 2: Table 2 Irradiance Scenarios The specific control measures are as follows: Scenario 1: Anti-glare priority scenario First, determine the target value of visible light transmittance using the following formula. : Then, based on the near-infrared blocking rate-visible light transmittance function pre-calibrated in step S2... Determine the target value for near-infrared blocking rate .

[0058] Scenario 2: Thermal Insulation Priority Scenario First, determine the target value of the near-infrared blocking rate according to the following formula. : Then, based on the visible light transmittance-near-infrared blocking rate function pre-calibrated in step S2... Determine the target value for visible light transmittance. .

[0059] Scenario 3: Conventional scenarios First, determine the target value of visible light transmittance using the following formula. : Then, based on the near-infrared blocking rate-visible light transmittance function pre-calibrated in step S2... Determine the target value for near-infrared blocking rate .

[0060] Scenario 4: High Transparency Standby Scenario First, determine the target value of visible light transmittance using the following formula. : Then, based on the near-infrared blocking rate-visible light transmittance function pre-calibrated in step S2... Determine the target value for near-infrared blocking rate .

[0061] S5. Calculate the basic driving voltage for the shading process. Basic driving voltage of the coloring process It is a unipolar DC negative voltage to realize Li + First embedding, Na +The embedded hierarchical collaborative control meets the design requirements of millisecond-level visible light dimming and second-level near-infrared heat insulation, and is divided into Li + Colored voltage calculation, Na + The process involves three steps: coloring voltage calculation and co-voltage fusion.

[0062] S5.1 Calculate Li + Coloring voltage (Visible light dimming) Based on the target value of visible light transmittance Coloring voltage-visible light transmittance function Combined with the incident angle correction factor To obtain a separate driver for Li + The coloring voltage, denoted as To ensure fast coloring in milliseconds, as shown below: In the formula , Li + Embedded threshold voltage, Li + Saturation embedding voltage; when During a sudden increase, the control system can output instantaneously. The above voltage enables Li + Millisecond-level embedding rapidly reduces visible light transmittance, fundamentally solving the glare problem and meeting the "zero-delay" dimming requirement.

[0063] S5.2 Calculate Na + Coloring voltage (Near-infrared heat insulation) Based on the target value of near-infrared blocking rate Coloring voltage-near-infrared blocking rate function Combined with the ion-coordinated voltage coupling coefficient To obtain a separate driving Na + The coloring voltage, denoted as Ensure Na + In Li + After startup, rapid embedding is achieved, realizing deep thermal insulation within seconds, as shown in the following formula: In the formula ,and (Guarantee Na) + In Li + (Pre-embedded startup); The value is 0.9, representing that when Li + After embedding, Na + The embedding barrier is lowered, eliminating the need for a separate high-voltage drive. Na represents + Embedded threshold voltage, Na represents + Saturation embedding voltage.

[0064] S5.3 Calculation of the basic driving voltage for multi-ion synergy in the coloring process Li + / Na + Driven by the same driving voltage, therefore and To merge, take and The larger value in the range is used as the basic driving voltage for the coloring process. This ensures that both types of ions can be embedded according to the target requirements, achieving synergistic regulation of visible light and near-infrared light, as shown in the following formula: In the formula ,when At that time, Li + First to embed and achieve visible light dimming; when When, Na + It can be embedded to achieve near-infrared thermal insulation; a single voltage can achieve hierarchical coordination, simplifying the design of spaceborne drive circuits and meeting the needs of engineering implementation.

[0065] S6. Calculate the basic driving voltage for the fading process. The fading process of electrochromic films (Li + / Na + (De-intercalation and restoration of high transmittance) is driven by a positive DC voltage. The calculation logic is consistent with the coloring process, only the voltage polarity is reversed, to achieve Na… + First, embedding, Li + The sequential synergistic fading after insertion / extraction ensures a smooth fading process and optical consistency, and is divided into Na... + Calculation of fading voltage, Li + The process involves three steps: fading voltage calculation and synergistic voltage fusion.

[0066] S6.1 Calculate Na + Fading voltage Based on the target value of near-infrared blocking rate and fading voltage-near-infrared blocking rate function To obtain a separate driving Na + fading voltage As shown in the following formula: In the formula Na represents +De-intercalation threshold voltage Na represents + Complete de-intercalation saturation voltage.

[0067] S6.2 Calculate Li + Fading voltage Based on the target value of visible light transmittance and fading voltage-visible light transmittance function To obtain a separate driver for Li + fading voltage As shown in the following formula: In the formula , Li + De-intercalation threshold voltage Li + Complete de-intercalation saturation voltage.

[0068] S6.3 Calculation of the basic driving voltage for multi-ion synergy in the fading process Li + / Na + Driven by the same driving voltage, therefore and To merge, take and The larger value is used as the basic driving voltage for the fading process. This ensures that both types of ions can be inserted and extracted according to the target requirements, achieving synergistic regulation of visible light and near-infrared light, as shown in the following formula: , In the formula ,when When, Na + First to disembed; when At that time, Li + Initiate de-embedding; single-channel voltage can achieve graded coordination, simplifying the design of spaceborne drive circuits and meeting the requirements for engineering implementation.

[0069] S7. Calculate the actual driving voltage during the coloring process (system-level function fusion). Basic driving voltage of the coloring process To meet only core dimming / heat insulation requirements, the electrochromic window intelligent control system proposed in this invention is linked with the spacecraft power system to achieve system-level collaborative optimization. Simultaneously, it improves on-orbit dimming performance and extends window lifespan by monitoring window film temperature and health status. Therefore, it is necessary to adjust the system based on window film temperature, the current remaining power of the spacecraft power system, and the window film health status. Make corrections to obtain Actual driving voltage As shown in the following formula In the formula This is the temperature correction factor for the porthole film. This is a correction factor for the spacecraft's electrical charge. This is a correction factor for the health status of the porthole film layer.

[0070] S7.1, Temperature Correction Factor for Porthole Film The porthole film is subjected to extreme high and low temperature environments in space, ranging from -180℃ to +120℃. + and Na + The ion migration rate changes with temperature and needs to be determined by... Correction As shown below: In the formula, This refers to the temperature of the porthole film layer.

[0071] S7.2, Spacecraft Electricity Correction Coefficient Based on the SOC value of the spacecraft power system Adaptive adjustment This represents the percentage of remaining power in the spacecraft's power system. When power is low, priority is given to safety-level dimming to reduce unnecessary energy consumption and meet energy-saving requirements. The expression is as follows: S7.3, Correction coefficient for the health status of porthole film layer By monitoring the health status values ​​of the port window membrane Adjust the correction factor for the health status of the porthole film. The adjustment strategy is shown in Table 3: Table 3 and Correspondence Port window film health status value The calculation uses a multi-feature parameter weighted normalization model, which not only ensures the health of the microstructure of the coating layer but also directly reflects the actual dimming performance. The calculation formula is as follows: In the formula, Weighting factor for ohmic impedance component, Weighting factor for charge transfer impedance component, The weighting coefficients for the electrochemical activity component, For the weighting coefficients of optical performance components, satisfying 1+ 2+ 3+ 4 = 1; For the health of the ohmic impedance sub-item, For the health of charge transfer impedance sub-item, For electrochemical activity sub-items of health, For the optical performance sub-items of health, all values ​​are normalized to the [0,1] interval. The weight coefficients for each sub-item are shown in Table 4. Table 4. Values ​​of Sub-item Weight Coefficients S8. Calculate the actual driving voltage during the fading process (system-level function integration) The voltage correction principle for the fading process is the same as that for the coloring process, adjusting the base voltage for the fading process based on the window film temperature, the current remaining power of the spacecraft's power system, and the health status of the window film. Dynamic correction is performed to obtain the actual driving voltage during the fading process. The corrected voltage ensures both dimming / heat insulation performance and meets the system-level requirements of manned spacecraft. The calculation formula is as follows: In the formula This is the temperature correction factor for the porthole film. This is a correction factor for the spacecraft's electrical charge. This is a correction factor for the health status of the porthole film layer. , , The calculation formula is consistent with step S7. A partitioned independent drive architecture is adopted, with each porthole divided into at least 4 independently controlled quadrant partitions, and each partition's electrochromic film layer is equipped with independent electrode leads and drive voltage.

[0072] Compared with the prior art, the present invention has the following outstanding substantive features and significant beneficial effects: (1) Fundamental innovation in control logic: The intelligent control system constructed in this invention, which is based on "feedforward prediction as the main method and feedback fine-tuning as the auxiliary method", realizes advance prediction-based dimming based on the orbit and attitude data of manned spacecraft, fundamentally solving the problem of lag in traditional feedback control, perfectly adapting to the rapidly changing lighting environment in near-Earth orbit, and achieving "zero-delay" anti-glare and heat load control; at the same time, the zoned independent control strategy takes into account both the occupant observation needs and energy-saving and heat insulation needs, greatly improving the user experience.

[0073] (2) The system integration and synergy are greatly improved: This invention breaks the limitation of the independent unit of the electrochromic control system and links with the attitude and orbit control system, power system and function of the manned spacecraft to achieve system-level synergistic optimization. By monitoring the temperature and health status of the window film, the on-orbit dimming / heat insulation performance is improved while extending the service life of the window film, thus improving the overall system energy efficiency of the manned spacecraft.

[0074] 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 multi-ion coordinated electrochromic porthole intelligent control system for manned spacecraft, characterized in that... It includes a predictive feedforward main control module and a feedback fine-tuning control module; the porthole is set with N partitions, each partition is set with independent electrode leads and execution units, where N is a positive integer greater than 1; The prediction feedforward main control module predicts the solar incidence angle and irradiance for each section of the porthole based on the spacecraft's current orbital parameters, attitude data, and solar ephemeris data. It obtains the visible and near-infrared irradiance at the predicted time based on the energy proportions of different spectral bands. Based on these irradiances, it calculates the effective visible and near-infrared irradiance, determines the spacecraft's irradiance scenario, and finally calculates the target visible transmittance value for the predicted time. By comparing the current visible light transmittance with the target value of visible light transmittance at the predicted time, it is determined whether the porthole is about to enter the tinting or fading process. Substitute the pre-calibrated near-infrared blocking rate - visible light transmittance function to determine the target value of the near-infrared blocking rate at the prediction time. Based on the target value of visible light transmittance at the predicted time and the target value of near-infrared blocking rate at the predicted time Calculate the base driving voltage for each partition coloring process at the prediction time. Or the basic driving voltage during the fading process ; The feedback fine-tuning control module acquires the window film temperature, the spacecraft's current remaining power, and the window film health status, and sets the base driving voltage for the coloring process of each window zone at the predicted time. Or the basic driving voltage of the fading process Correction yields the actual driving voltage for each zone coloring process of the porthole at the predicted time. Or the actual driving voltage during the fading process The actual driving voltage of each partition coloring process at the predicted time will be used. Or the actual driving voltage during the fading process Send it to the corresponding execution unit; The execution unit, based on the actual driving voltage during the coloring process Or the actual driving voltage during the fading process It generates independent drive voltages to independently control the dimming of each zone of the porthole.

2. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 1, characterized in that... The angle of sunlight incidence for each section of the porthole is calculated using the following method: Extrapolate the predicted spacecraft position, velocity, and transformation matrix from the spacecraft body coordinate system to the window coordinate system at the predicted time. ; Calculate the solar incident vector in the geocentric inertial coordinate system at the predicted time. ; Based on the spacecraft's position, velocity, and the transformation matrix from the spacecraft's body coordinate system to the window coordinate system at the predicted time. The solar incident vector in the geocentric inertial coordinate system Convert to solar incident vector in porthole coordinate system ; Calculate the solar incident vector in the porthole coordinate system at the predicted time. The angle between the angle and the normal vector of each section of the porthole is the angle of sunlight incident on each section of the porthole at the predicted time.

3. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 1, characterized in that, The prediction method for the irradiance of each zone of the porthole is as follows: Determine whether the spacecraft is in the sunlit, penumbra, or umbra region at the predicted time, and output the ground shadow occlusion coefficient. ; Based on the angle of sunlight incidence in each section of the porthole Ground shadow occlusion coefficient Calculate the direct solar irradiance for each partition. In the formula, The standard solar constant outside the atmosphere. This is the correction factor for the Earth-Sun distance; Based on the energy proportions of different spectral bands, the visible and near-infrared irradiance at the predicted time are obtained, and the visible irradiance of each region at the predicted time is calculated. and near-infrared irradiance In the formula, This represents the percentage of visible light energy. Indicates the energy proportion coefficient in the near-infrared band; This indicates the angle of incidence of visible light. Incident to the Actual transmittance for each zone, Indicates the near-infrared band at the angle of incidence. Incident to the Actual transmittance for each zone.

4. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 1, characterized in that: At that time, the spacecraft was in an anti-glare priority scenario; At that time, the spacecraft was in a scenario where thermal protection was the priority. At that time, the spacecraft was in a routine, dual-use scenario; At that time, the spacecraft was in a high-transparency standby scenario; in, Visible light effective irradiance, This refers to the effective near-infrared irradiance.

5. The intelligent control system for multi-ion synergistic electrochromic portholes for manned spacecraft according to claim 1, characterized in that, The basic driving voltage of the coloring process Determined using the following method: Based on the target value of visible light transmittance at the predicted time Coloring voltage-visible light transmittance function Combined with the incident angle correction factor To obtain a separate driver for Li + The coloring voltage, denoted as ; In the formula, Li + Embedded threshold voltage, Li + Saturation embedding voltage; Based on the target value of near-infrared blocking rate Coloring voltage-near-infrared blocking rate function Combined with the ion-coordinated voltage coupling coefficient To obtain a separate driving Na + The coloring voltage, denoted as Ensure Na + In Li + Embedded functionality will be implemented after startup; In the formula Na represents + Embedded threshold voltage, Na represents + Saturation embedding voltage; Pick and The larger value in the range is used as the basic driving voltage for the coloring process. .

6. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 1, characterized in that, The basic driving voltage of the fading process Determined using the following method: Based on the target value of near-infrared blocking rate and fading voltage-near-infrared blocking rate function To obtain a separate driving Na + fading voltage ; In the formula, Na represents + De-intercalation threshold voltage Na represents + Complete de-intercalation saturation voltage; Based on the target value of visible light transmittance at the predicted time and fading voltage-visible light transmittance function To obtain a separate driver for Li + fading voltage ; In the formula , Li + De-intercalation threshold voltage Li + Complete de-intercalation saturation voltage; Pick and The larger value is used as the basic driving voltage for the fading process. .

7. The intelligent control system for multi-ion synergistic electrochromic portholes for manned spacecraft according to claim 1, characterized in that, Actual driving voltage during coloring process and the actual driving voltage during the fading process The calculation formula is: In the formula, This is the temperature correction factor for the porthole film. This is a correction factor for the spacecraft's electrical charge. This is a correction factor for the health status of the porthole film layer.

8. The intelligent control system for multi-ion coordinated electrochromic portholes in manned spacecraft according to claim 7, characterized in that, The temperature correction coefficient of the porthole film layer for: In the formula This refers to the temperature of the porthole film layer.

9. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 7, characterized in that... The spacecraft's electrical correction coefficient for: In the formula, This refers to the State of Charge (SOC) value of the power system of a manned spacecraft.

10. The intelligent control system for multi-ion coordinated electrochromic portholes for manned spacecraft according to claim 7, characterized in that... The health correction coefficient of the porthole film layer Based on membrane health status values The value of is determined.

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