An extraterrestrial planet atmosphere collection control device and method for high-speed flight

Abstract

The embodiment of the application discloses a kind of extraterrestrial planet atmosphere collection control devices and methods for high-speed flight, it is related to the control or regulation technical field of non-electric variable in aerospace equipment.The sampling port of the present application is connected to the air inlet, and the air inlet is connected to each gas storage channel;The gas storage valve is installed at the front end of the gas storage channel to control the opening and closing of the gas storage channel;The gas storage channel is connected to the corresponding gas storage tank, a total of six gas storage channels and gas storage tanks are provided, and the adjusting device is arranged in the gas storage tank and controlled based on temperature, pressure and wind speed and other non-electric quantities.The present application is suitable for extraterrestrial planet atmosphere collection task under high-speed flight state, with the help of planetary spacecraft multiple intrusion into the planet atmosphere, the sub-collection of different target gases is completed and stored separately, which can cope with the extreme temperature and pressure brought by hypersonic flight, and the state of gas collection can be maintained, which is beneficial to the detection and utilization of gas after being brought back to the ground.

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment technology, and in particular to a device and method for collecting and controlling the atmosphere of exoplanets during high-speed flight. Background Technology

[0002] Compared to Earth's atmosphere, the internal environment of exoplanet atmospheres is more complex. Faced with issues such as variable conditions and communication delays, traditional airbag-based sampling methods that intrude into the atmosphere cannot achieve the goal of storing and recovering exoplanet gases. Multiple in-orbit intrusions of planetary spacecraft into the atmosphere to collect and store gases is an effective means of achieving this goal.

[0003] In this collection method, the gas collection device needs to deal with the complex environment of exoplanets and the high-speed flight state within the atmosphere, so as to efficiently and safely collect, store and encapsulate the target gas.

[0004] Therefore, how to achieve multiple atmospheric intrusions and sampling during hypersonic flight has become a technical challenge that needs to be studied and overcome. Summary of the Invention

[0005] The embodiments of the present invention provide a control device and method for atmospheric collection from exoplanets in high-speed flight, which can repeatedly enter the atmosphere and collect samples in hypersonic flight, and realize the collection, storage and encapsulation of gases in stages.

[0006] To achieve the above objectives, the embodiments of the present invention adopt the following technical solutions:

[0007] In a first aspect, the apparatus provided by embodiments of the present invention includes:

[0008] An atmospheric collection and control device for exoplanets in high-speed flight, wherein an air inlet is opened at the front end of the outer shell (1) of the spacecraft, and a sampling port (3) is opened at the front end of the gas storage tank (2). The gas storage tank (2) is installed inside the outer shell (1), and the outer surface of the sampling port (3) is closely fitted with the inner surface of the air inlet of the outer shell (1). The outer shell (1) is bullet-shaped and adopts a streamlined design.

[0009] The sampling port (3) is connected to the air inlet (4), and the air inlet (4) is connected to each air storage channel (7). During the sampling process, the gas enters the sampling port (3) from the air inlet of the outer shell (1) and enters the air inlet (4) from the sampling port (3). The air storage valve (6) is installed at the front end of the air storage channel (7) to control the opening and closing of the air storage channel (7). The air storage channel (7) is connected to the corresponding air storage tank (8).

[0010] The gas storage box (2) is equipped with six gas storage tanks (8), and the air inlet (4) is connected to the six gas storage channels (7). Each gas storage channel (7) is connected to one gas storage tank (8). Multiple samples are taken during the sampling process, and the samples are stored separately in each gas storage tank (8) for sealing. A ball screw drive mechanism (5) is installed in the air inlet (4). One end of the ball screw drive mechanism (5) is connected to the drive mechanism of the ball screw drive mechanism (5), and the other end is connected to the wind deflector slider (3-1). The ball screw drive mechanism (5) drives the wind deflector slider (3-1) to move back and forth to adjust the opening degree of the sampling port (3).

[0011] Secondly, the method provided by the embodiments of the present invention includes:

[0012] S1. The gas storage sensing system (10) collects measurement data inside the gas storage tank (8). The gas storage sensing system (10) includes a temperature sensor, a pressure sensor and a wind speed sensor.

[0013] S2. The control system operates a multi-source sensing information processing stage, which includes a front-end preprocessing stage and a back-end processing stage.

[0014] S3. The data processed by the multi-source sensing information processing stage is input into the sensing information consistency expression model. The information consistency expression model includes: consistency expression models for non-electrical sensing information such as temperature, pressure, and wind speed; S4. Bayesian estimation is performed on the output results of the sensing information consistency expression model to obtain comprehensive sensing information;

[0015] S5. Control the exoplanet atmosphere acquisition and control device based on the comprehensive sensing information.

[0016] This invention provides a control device and method for collecting atmospheric data from exoplanets during high-speed flight. The sampling port is connected to an air intake, which in turn connects to various gas storage channels. A gas storage valve is installed at the front end of each storage channel to control its opening and closing. Each storage channel connects to a corresponding gas storage tank, with a total of six storage channels and tanks. An adjustment device is located within each storage tank. A multi-source sensing and hierarchical sampling control system is employed for multi-layered coordinated control of sampling, encapsulation, and storage, based on non-electrical parameters such as temperature, pressure, and wind speed. This invention is applicable to exoplanetary atmospheric data collection missions during high-speed flight. By repeatedly penetrating the planetary atmosphere using a planetary spacecraft, it collects and stores different target gases in stages. This method can withstand the extreme temperatures and pressures of hypersonic flight and maintains the gas in its original state during collection, facilitating gas detection and utilization upon return to Earth. This embodiment enables multiple atmospheric intrusions during hypersonic flight and achieves staged gas collection, storage, and encapsulation. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is an overall appearance view provided for an embodiment of the present invention;

[0019] Figure 2 A cross-sectional view of the overall structure provided in an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of a single atmospheric sampling process provided in an embodiment of the present invention;

[0021] Figure 4 A flowchart of exoplanet atmospheric acquisition control based on multi-source sensing provided in this embodiment of the invention;

[0022] Figure 5 The sampling-encapsulation-storage hierarchical coordination control structure of the acquisition device provided in the embodiments of the present invention is described. Detailed Implementation

[0023] To enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. Embodiments of the present invention will be described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention. Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in the specification of the present invention means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. It should be understood that when we say an element is “connected” or “coupled” to another element, it can be directly connected or coupled to the other element, or there may be intermediate elements. Furthermore, “connected” or “coupled” as used herein can include wireless connections or couplings. The term "and / or" as used herein includes any unit and all combinations of one or more of the associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein, including technical and scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the meaning consistent with their meaning in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0024] This invention provides a control device for collecting and controlling the atmosphere of exoplanets in high-speed flight, such as... Figure 1-3 As shown, an air inlet is located at the front of the spacecraft's outer shell 1, and a sampling port 3 is located at the front of the air storage tank 2. The air storage tank 2 is installed inside the outer shell 1. The sampling port 3 is connected to the air inlet 4, and the air inlet 4 is connected to each air storage channel 7. (Specific details are as follows...) Figure 2 As shown, an air inlet is provided at the top of the outer casing 1; the air inlet 4 is also installed inside the outer casing 1, and the opening at the outward end of the air inlet 4 serves as the sampling port 3. The outward end of the air inlet 4 is inserted into the air inlet of the air inlet 4 from the inside out, and the outer surface of the sampling port 3 is tightly fitted with the inner surface of the air inlet of the outer casing 1. During the sampling process, gas enters the sampling port 3 from the air inlet of the outer casing 1 and is input into the air inlet 4 from the sampling port 3; the gas storage valve 6 is installed at the front end of the gas storage channel 7 and is used to control the opening and closing of the gas storage channel 7; the gas storage channel 7 is connected to the corresponding gas storage tank 8.

[0025] The system includes six gas storage tanks 8 within the gas storage box 2, with an air inlet 4 connecting to six gas storage channels 7. Each gas storage channel 7 is connected to one gas storage tank 8. Multiple samples are taken during the sampling process, and the samples are stored separately in each gas storage tank 8 and sealed. A ball screw drive mechanism 5 is installed inside the air inlet 4. One end of the ball screw drive mechanism 5 is connected to the transmission mechanism of the ball screw drive mechanism 5, and the other end is connected to the wind deflector slider 3-1. The ball screw drive mechanism 5 moves the wind deflector slider 3-1 back and forth to adjust the opening degree of the sampling port 3.

[0026] In this embodiment, as Figure 1 As shown, the outer shell 1 is bullet-shaped and features a streamlined design. This shape results in low air resistance and stability during high-speed flight. The entire assembly employs a non-exhaust system to avoid interference with other onboard systems or disrupting overall aerodynamics, thus improving the spacecraft's stability.

[0027] The sampling port designed in this scheme is adjustable, employing a ball screw drive mechanism for forward and backward movement. It remains closed before entering the atmosphere of an exoplanet. After the spacecraft enters the atmosphere, the sampling port adjusts its opening size and shape to adapt to atmospheric sampling requirements at different flight speeds, enabling efficient gas collection and storage under various flight conditions. The ball screw drive mechanism allows for precise positioning and stable movement of the sampling port, improving its flexibility and adaptability, as well as the stability and reliability of the sampling process. This is beneficial for capturing high-quality gas samples at high speeds. Furthermore, the ball screw drive mechanism allows for dynamic adjustment of the sampling port during flight based on real-time monitoring data, thereby optimizing sampling results.

[0028] In this embodiment, the sampling port 3 is integrated into the upstream part of the air intake duct 4 through an integrated design. The sampling port 3 is designed to be adjustable, and a ball screw drive mechanism 5 is used to move it back and forth to adjust the shape and size of the sampling port 3. Multi-stage compression and isentropic compression technologies are employed, combined with Busemann air intake design and streamline tracing methods, to integrate the sampling port 3 into the upstream part of the air intake duct 4.

[0029] In this design, the sampling port is integrated into the upstream part of the air intake and employs multi-stage compression and isentropic compression techniques. The sampling port acts as an inducer of leading-edge shock waves, establishing an initial basic flow field for the fuselage outflow and air intake, improving the air intake's compressibility with the sampled atmosphere, and enhancing the overall efficiency of the air intake. The inner wall of the flow tube is designed using a combination of Busemann air intake design and streamline tracing, preserving the baseline flow field characteristics of the air intake. This facilitates effective reduction of the incoming Mach number at different flight speeds, improving gas density, static pressure, and static temperature. The streamline tracing Busemann air intake design parameter relationships are as follows:

[0030] F(Ma1,CR)=G(σ,Cx,φ,η), where Ma1 is the design Mach number, referring to the isentropic compression start Mach number defined during the inlet design process; CR is the contraction ratio, referring to the ratio of the inlet area to the outlet area of ​​the inlet. If the inlet shape is irregular, it is defined as the ratio of the projected area of ​​the inlet to the vertical plane of the incoming flow to the outlet area; the performance parameter σ is the total pressure recovery coefficient, referring to the ratio of the mass-average total pressure at the inlet outlet to the total pressure of the incoming flow; Cx is the drag coefficient, used to measure the drag characteristics of the inlet; φ is the flow coefficient, measuring the inlet's ability to capture the incoming flow; η is the pressure ratio, referring to the ratio of the mass-average static pressure at the outlet section to the static pressure of the incoming flow; F and G represent two intermediate functions in the design process, belonging to the intermediate function tools in the calculation process, which can be called the first function and the second function. In the design process, the parameters in G() determine the parameter design in F().

[0031] Each gas storage tank 8 is equipped with a gas storage sensing system 10, a regulating device, and a control system. The regulating device includes a temperature control device 9 and a pressure regulating device. Specifically, the gas storage sensing system 10 monitors parameters such as pressure and temperature within the gas storage tank in real time, ensuring the tank operates within a safe and stable range. It collects pressure and temperature data from the tank and transmits it to the control system for analysis and processing, thereby achieving real-time monitoring and early warning of the tank's status. The temperature control device 9 can specifically employ a composite aerospace equipment standard heating wire to maintain a stable gas temperature within the tank. Since the physical properties of gas change with temperature, the temperature control device regulates the internal temperature of the tank to maintain gas stability, avoiding safety issues and gas changes caused by temperature fluctuations. The pressure regulating device controls the pressure within the tank, ensuring it remains within a set safe range. By automatically adjusting the gas volume, the pressure regulating device prevents excessively high or low pressure, controlling the pressure within the set range, thus ensuring the stable operation and safe use of the entire system.

[0032] The control system inside the gas storage tank receives temperature and pressure data monitored in real time by the gas storage sensor system 10, analyzes and processes this data to ensure an accurate understanding of the internal environment of the gas storage tank 8, and precisely and intelligently controls the adjustment device to determine the triggering conditions and opening and closing times of the constant temperature device 9 and the pressure adjustment device.

[0033] For specific examples: combining Figure 1 and Figure 2As shown, this embodiment is an atmospheric sampling device for high-speed flying exoplanets, including a sampling port 3, an air inlet 4, a gas storage sensing system 10, a control system, a gas storage valve 6, gas storage channels 7, gas storage tanks 8, and a regulating device. The sampling port 3 is connected to the air inlet 4, and the air inlet 4 is connected to each gas storage channel 7; the gas storage valve 6 is installed at the front end of the gas storage channel 7 and is used to control the opening and closing of the gas storage channel 7; the gas storage channel 7 is connected to the corresponding gas storage tank 8, and the gas storage tank 8 is installed in the gas storage box 2; the gas storage sensing system 10 and the regulating device are arranged in the gas storage tank 8, and the regulating device includes a temperature control device 9 and a pressure regulating device.

[0034] Combination Figure 2 and Figure 3 As shown, the sampling port 3 in this embodiment is an adjustable sampling port, which uses a ball screw transmission mechanism 5 to move back and forth, adjusting the size and shape of the sampling port 3 to adapt to the atmospheric sampling requirements at different flight speeds, ensuring that the sampling port correctly induces the leading-edge shock wave and establishes the initial basic flow field for the air intake. Figure 3 As shown, the spacecraft is in standby mode before entering the atmosphere of an exoplanet, and the sampling port 3 remains closed. After the spacecraft enters the atmosphere of an exoplanet, it is in atmospheric intake and storage mode. The ball screw transmission mechanism 5 controls the sampling port 3 to open and adjust it to a size suitable for the current flight state. Then, the atmosphere rushes into the intake duct 4.

[0035] Combination Figure 2 and Figure 3 As shown, in this embodiment, the sampling port 3 and the air intake 4 are integrated into a single design. The inner wall of the flow tube is designed using a combination of Busemann air intake design and streamline tracing method, preserving the reference flow field characteristics of the air intake 4. Figure 3 As shown, the airflow is compressed during the process of the atmosphere passing through sampling port 3 and air inlet 4, which reduces the incoming Mach number, increases the gas density, static pressure and static temperature, and effectively guides and stores the gas.

[0036] Combination Figure 2 and Figure 3 As shown, the gas storage device in this embodiment has a total of six sets, including a gas storage channel 7, a gas storage valve 6, and a gas storage tank 8. The gas storage valve 6 is used to control the storage state of the device. When atmospheric storage is not required, the gas storage valve is closed, which is the standby state with atmospheric closure; when atmospheric storage is required, the corresponding gas storage valve is opened, which is the atmospheric intake storage state. Figure 3 As shown, multiple samples are taken during the atmospheric sampling process and stored separately, with different batches of target gases being classified, stored, and packaged.

[0037] Combination Figure 2 and Figure 3As shown, the gas storage tank 8 in this embodiment is equipped with a gas storage sensing system 10, a temperature control device 9, and a control system, which can realize multi-source sensing and autonomous adjustment of parameters such as temperature and pressure of the gas in the storage tank, ensuring the safety of atmospheric storage and sealing processes. Figure 3 As shown, during the sampling and storage process, the gas storage sensing system 10 in the gas storage tank provides feedback on the gas state, and the constant temperature device 9 completes gas encapsulation after ensuring the gas state is stable and safe by evaluating and analyzing the onboard multi-source sensing information such as temperature and pressure.

[0038] This embodiment also provides a control method applied to the exoplanet atmosphere acquisition control device, including:

[0039] S1. The gas storage sensing system 10 collects measurement data inside the gas storage tank 8. The gas storage sensing system 10 includes a temperature sensor, a pressure sensor, and a wind speed sensor.

[0040] S2. The control system operates a multi-source sensing information processing stage, which includes a front-end preprocessing stage and a back-end processing stage.

[0041] S3. Data input sensing information consistency expression model after processing through the multi-source sensing information processing stage, wherein the information consistency expression model includes: temperature sensing information consistency expression model, pressure sensing information consistency expression model and wind speed sensing information consistency expression model;

[0042] S4. Perform Bayesian estimation on the publication results of the consistent expression model of the perceived information to obtain the comprehensive perceived information;

[0043] S5. Control the exoplanet atmospheric acquisition control device based on the comprehensive sensing information. The comprehensive sensing information is received by the atmospheric sampling-packaging-storage control system and used to determine whether and when to perform atmospheric sampling, sampling port size adjustment, gas storage valve opening, atmospheric packaging, and gas state adjustment within the container.

[0044] This embodiment employs a gas acquisition scheme involving multiple atmospheric intrusions by a planetary spacecraft in orbit for gas collection and storage. A multi-source sensing and hierarchical sampling control system is used for multi-layered coordinated control of sampling, encapsulation, and storage. Through multi-source sensing and hierarchical control technology, a hybrid intelligent control structure is used to perform single-layer control and coordinated control between layers for sampling, encapsulation, and storage tasks. Combining Kalman filter-based sensing information fusion and dynamic detection methods, abnormal data is automatically detected and eliminated. Sensing information is weighted to ensure accuracy and reliability, and dynamic weighting is used to determine the optimal timing for operations. Before sampling, environmental conditions are sensed; after encapsulation, the gas state adjustment process within the storage tank is performed using an adaptive unscented Kalman filter algorithm with noise-adaptive nonlinear prediction estimation method to estimate time-varying parameters of the sensing information in real time. Then, based on Bayesian estimation theory, multi-source sensing information with consistent representation characteristics is fused to obtain the optimal comprehensive sensing solution, ensuring the accuracy of the acquired multi-source sensing information and adjustment operations.

[0045] For example: combining Figure 4 and Figure 5 As shown, this implementation employs multi-source sensing and hierarchical control technology. Based on a hybrid intelligent control structure, it performs single-layer control and coordinated control between layers for sampling, encapsulation, and storage tasks. Combining Kalman filtering-based sensing information fusion and dynamic detection methods, it automatically detects the reliability of sensing information and removes abnormal data. The sensing information is weighted to ensure accuracy and reliability, and dynamically weighted to determine the optimal timing for operations. Figure 4 This implementation method describes a process where, before sampling, environmental conditions are sensed, and after packaging, the gas state regulation process within the storage tank is performed. This is achieved through a noise-adaptive nonlinear prediction and estimation method, specifically an adaptive unscented Kalman filter algorithm, which estimates the time-varying parameters of the sensed information in real time. Then, based on Bayesian estimation theory, the multi-source sensed information with consistent representation characteristics is fused to obtain the optimal comprehensive sensed solution, ensuring the accuracy of the acquired multi-source sensed information and the regulation operation.

[0046] The front-end preprocessing stage includes: sequentially performing information filtering, data diagnosis, and filter performance evaluation on the measurement data; the front-end preprocessing stage ensures that the exoplanetary atmosphere acquisition and control device can provide accurate and reliable data, providing support for subsequent scientific analysis and precise control of the control system.

[0047] Specifically, information filtering is an estimation theory that uses a series of noisy measurement data to estimate the state of a dynamic system. In exoplanetary atmosphere acquisition and control devices, information filtering is used to extract useful information from sensor data and reduce the impact of noise and errors. In this embodiment, the information filtering stage can employ a Kalman filter, a commonly used information filtering technique that estimates the state of a linear dynamic system through a recursive algorithm. It can be used to estimate and correct sensor data to obtain more accurate system state information.

[0048] Data diagnostics refers to the process of quality control and anomaly detection of acquired data, including checking data consistency and identifying and handling outliers or erroneous data points. In exoplanetary atmosphere acquisition and control systems, data diagnostics ensures that only high-quality data is used for subsequent analysis. In this embodiment, the data diagnostic process includes multi-platform quality control and platform-specific quality control to ensure data accuracy and reliability. Specifically, Gaussian model-based data diagnostics can identify outlier data points by estimating the probability density function of the data and comparing it to a threshold.

[0049] Filter performance evaluation involves assessing the effectiveness of an applied filter to ensure it achieves the expected noise reduction and signal preservation effects. This includes evaluating the filter's stability, accuracy, and response time. In this embodiment, the filter performance evaluation includes: in Extended Information Filtering (EIF), performance evaluation can be performed by comparing data before and after filtering to assess the degree of signal improvement. Furthermore, filter performance can be evaluated by calculating the variance of the filtering error; in Kalman filters, calculating the error variance is a crucial part of performance evaluation.

[0050] Specifically, in the process of establishing the information consistency expression model, it includes: the sensor model of the gas storage sensing system 10 is x i =x ture +∈ i The sensing information comes from N sensors in the gas storage sensing system 10, and the initial observation value of the sensors is T. i x i Let represent the measured value of the i-th recorded sensor, and let be the measurement error of the sensor. i , i represents the sensor number, x ture The data used is real-world data, including temperature, pressure, and wind speed data; spatiotemporal constraints are established for the sensor model, wherein historical data {x} are utilized. t-1 ,x t ,x t+1 The established time consistency constraints include:

[0051] α+β+γ=1, xt This represents the actual measured value at time t. The estimated value at time t represents time, and α, β, and γ represent the first to third smoothing factors, used to combine historical and current sensor data to estimate the actual value at the current time; the data gradient is used to measure spatial consistency constraints. d i+1,i Given the sensor distance; establish the information consistency expression model: Where, λ t ,λ s ω represents the time consistency weighting factor and the spatial consistency weighting factor, respectively. i ω represents the confidence coefficient of the perceived information from the i-th sensor, used to reflect the sensor's reliability. i Represents the confidence coefficient. This represents the estimated value of the data after comprehensive consideration.

[0052] The back-end processing stage includes: assigning confidence coefficients to the measurement data after the front-end preprocessing stage, then estimating time-varying parameters and extracting key parameters.

[0053] Specifically, the process of assigning confidence coefficients to the measurement data after the aforementioned front-end preprocessing stage includes: based on the error variance σ i 2 The confidence coefficient ω of the sub-configuration i , σ i and σ j Let represent two standard deviations, and j represent a reference in the iterative calculation. In practical applications, Kalman filtering is used to recursively estimate the dynamic parameters, where the prediction steps are:

[0054] Update steps: x represents the state estimate, A is the state transition matrix, B is the control input matrix, u is the control input or external action, P is the error covariance matrix, Q is the process noise covariance matrix, K is the Daleman gain, H is the observation matrix, and z is the actual observed value. The subscript "k" indicates time, and the subscript "k|k-1" indicates a prediction made before time k based on information from time k-1. R represents the observation noise covariance matrix. Based on sensor observations...

[0055] Adjusting the system state Tracking time-varying parameters. The key parameter extraction and screening method utilizes Principal Component Analysis (PCA) to extract key parameters. Specifically, the covariance matrix is ​​calculated as follows: Find the eigenvalues ​​and eigenvectors, and select the eigenvectors V corresponding to the m largest eigenvalues. m , This represents the mean vector of the dataset, i.e., the average value of all samples. Dimensionality reduction extracts key information, reduces redundancy, and improves fusion efficiency.

[0056] For example, the acquisition device is equipped with a gas storage sensing system, a regulating device, and a control system. Through evaluation and analysis of onboard multi-source sensing information such as temperature and pressure, it can achieve precise control of each stage of atmospheric acquisition and storage under different flight conditions, and autonomous adjustment of parameters such as temperature and pressure of the gas in the storage tank, ensuring the efficiency and safety of the atmospheric encapsulation and storage process. The designed multi-source sensing and hierarchical control is based on a hybrid intelligent control structure to perform single-layer control and coordinated control between layers for sampling, encapsulation, and storage tasks. The system integrates multiple sensors to collect multi-dimensional information on the environment and the gas state in the storage tank, ensuring the diversity and accuracy of the information. Kalman filtering technology is used to perform real-time fusion and dynamic detection of the sensing information. When the system detects a sudden change in sensing information caused by a certain sensor, or when the data from a certain sensor differs significantly from that of other sensors, the system will issue an alarm. After identifying abnormal data, the system can automatically detect and remove the data from that sensor, ensuring that only reliable information is used for subsequent decisions. Based on the data from the remaining sensors, the system will use a weighted processing method to dynamically adjust the weights of each sensor to ensure the accuracy and reliability of the fused information. Simultaneously, through dynamic weighting, the system can determine the optimal operation timing, thereby optimizing the sampling, encapsulation, and storage processes. Close coordination between control modules at each layer ensures that control strategies at different levels work together to adapt to complex task requirements and dynamically changing environmental conditions. Through these mechanisms, this invention ensures the authenticity and reliability of the sensed information, improves the system's response to unexpected events, optimizes overall control performance, and enhances the efficiency and security of sampling, encapsulation, and storage tasks.

[0057] In practical applications, the environmental condition sensing before sampling and the gas state regulation process inside the gas storage tank after packaging are evaluated using the Adaptive Unscented Kalman Filter (AUKF) algorithm, a noise-adaptive nonlinear prediction and estimation method, to estimate the time-varying parameters of the sensing information in real time. Then, based on Bayesian estimation theory, the multi-source sensing information with consistent representation characteristics is fused to obtain the optimal integrated sensing solution, ensuring the accuracy of the acquired multi-source sensing information and regulation operations. The AUKF steps include initialization, Sigma point selection, prediction, and updating, dynamically updating the process noise covariance and observation noise covariance by observing the prediction error. Bayesian estimation obtains the optimal estimate of the parameters through Bayesian decision-making, minimizing the total expected risk. The steps include determining the prior distribution p(θ) of the parameter θ, obtaining the joint distribution p(D|θ) of the samples from the sample set D, obtaining the posterior distribution P(θ|D) of the parameters using the Bayesian formula, and finally obtaining the Bayesian estimate. The Bayesian formula is as follows:

[0058]

[0059] By using this modeling and fusion processing method, the accuracy of multi-source sensing information and the effectiveness of adjustment operations are ensured, thereby improving the performance and reliability of the entire system.

[0060] The data acquisition device in this embodiment employs a non-venting scheme, eliminating the need for an exhaust pipe and further simplifying the structural complexity. In this non-venting scheme, the gas storage channel structure incorporates a gas storage valve to enable segmented sampling and storage, accommodating both atmospheric intake storage and standby states. In atmospheric standby mode, atmospheric encapsulation storage is unnecessary; the gas storage valve is closed to prevent atmospheric entry into the storage channel. Closing the gas storage valve prevents external atmospheric air from entering the storage channel, protecting the internal system from external conditions and improving system stability and reliability. In atmospheric intake storage mode, the corresponding gas storage valve is opened, allowing gas to enter the appropriate storage tank. Multiple gas storage channels facilitate the safe and categorized storage and encapsulation of different batches of target gas, ensuring efficient sampling and safe storage by the acquisition device, which is beneficial for analysis and utilization after the gas is transmitted back to Earth.

[0061] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on its differences from other embodiments. In particular, the device embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. The above descriptions are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. An extraterrestrial planet atmosphere collection control device oriented toward high speed flight, characterized by, The front end of the outer shell (1) of the spacecraft is provided with an air inlet, and the front end of the gas storage tank (2) is provided with a sampling port (3). The gas storage tank (2) is installed in the outer shell (1); The air inlet channel (4) is also installed in the outer shell (1), and the opening at the outer end of the air inlet channel (4) serves as the sampling port (3), and the outer surface of the sampling port (3) is tightly attached to the inner surface of the air inlet of the outer shell (1). The air inlet channel (4) is connected to each gas storage channel (7). During sampling, the gas enters the sampling port (3) from the air inlet of the outer shell (1) and enters the air inlet channel (4) from the sampling port (3); The gas storage valve (6) is installed at the front end of the gas storage channel (7) to control the opening and closing of the gas storage channel (7); The gas storage channel (7) is connected to the corresponding gas storage tank (8); The air inlet channel (4) is provided with a ball screw transmission mechanism (5), one end of the screw rod of the ball screw transmission mechanism (5) is connected to the transmission mechanism of the ball screw transmission mechanism (5), and the other end is connected to the wind-blocking sliding block (3-1); The ball screw transmission mechanism (5) adjusts the opening degree of the sampling port (3) by driving the wind-blocking sliding block (3-1) to move forward and backward; The sampling port (3) is designed as part of the upstream of the air inlet channel (4) through integrated design; In the integrated design, the design parameters of the sampling port (3) are determined by a flow line tracking Busemann air inlet channel design parameter model, wherein F(Ma1, CR)=G(σ, Cx, φ, η), the parameter Ma1 is the design Mach number of the profile, which is the isentropic compression start Mach number defined in the air inlet channel design process; CR is the contraction ratio, which is the ratio of the inlet area to the outlet area of the air inlet channel. If the inlet shape is irregular, it is defined as the projection area of the inlet vertical to the incoming flow area and the outlet area; the performance parameter σ is the total pressure recovery coefficient, which is the ratio of the mass average total pressure at the outlet of the air inlet channel to the incoming flow total pressure; Cx is the resistance coefficient, which is used to measure the resistance characteristics of the air inlet channel; φ is the flow coefficient, which measures the ability of the air inlet channel to capture the incoming flow; η is the pressure ratio, which is the ratio of the mass average static pressure of the outlet section to the incoming flow static pressure; F and G represent two intermediate functions in the design process.

2. The extraterrestrial planet atmosphere collection control device oriented toward high-speed flight of claim 1, wherein, Six gas storage tanks (8) are arranged in the gas storage tank (2), and the air inlet channel (4) is connected to six gas storage channels (7), each of which is connected to one gas storage tank (8); Multiple sampling is performed during sampling, and the samples are stored separately in each gas storage tank (8).

3. The extraterrestrial planet atmosphere collection control device for high speed flight of claim 1, wherein, Each gas storage tank (8) is provided with a gas storage sensing system (10), an adjusting device and a control system, wherein the adjusting device includes a constant temperature device (9) and a pressure adjusting device; The control system in the gas storage tank receives the temperature and pressure data monitored by the gas storage sensing system (10) in real time, analyzes and processes these data; the control system is also used to determine the triggering conditions of the constant temperature device (9) and the pressure adjusting device and the opening and closing time of the constant temperature device (9) and the pressure adjusting device.

4. The extraterrestrial planet atmosphere collection control device for high speed flight of claim 1, wherein, The outer shell (1) is a bullet head type and adopts a streamlined design.

5. The atmospheric gas collection control method for the extraterrestrial planet atmospheric gas collection control device facing high-speed flight according to claim 3, characterized by, It includes: S1, the gas storage sensing system (10) collects the measurement data inside the gas storage tank (8), the gas storage sensing system (10) includes temperature sensor, pressure sensor and wind speed sensor; S2, the control system runs the multi-source perception information processing link, the multi-source perception information processing link includes front-end preprocessing link and rear-end processing link; S3, the data processed by the multi-source perception information processing link is input into the perception information consistency expression model; S4, the output result of the perception information consistency expression model is subjected to Bayesian estimation to obtain comprehensive perception information; S5, the extraterrestrial planet atmosphere collection control device is controlled according to the comprehensive perception information.

6. The method of claim 5, wherein, The front-end preprocessing link includes: sequentially performing information filtering, data diagnosis and filter performance evaluation on the measurement data; The rear-end processing link includes: confidence coefficient distribution is performed on the measurement data subjected to the front-end preprocessing link, then time-varying parameter estimation is performed and then key parameters are extracted.

7. The method of claim 5, wherein, In the established information consistency expression model, the sensor model of the gas storage sensing system (10) is x i =x ture +ϵ i , wherein the perception information comes from N sensors in the gas storage sensing system (10), the measurement error of the sensor is ϵ i , i represents the sensor number, and x ture is real data including temperature data, pressure data and wind speed data; establishing spatio-temporal constraints for the sensor model, wherein a temporal consistency constraint is established using historical data {x t-1 ,x t ,x t+1} includes: ,x , x t represents an actual measurement value at time t, represents an estimated value at time t, the parameter carrying the symbol "^" is the estimated value of the parameter not carrying the symbol, t represents time, and α, β, γ represent first to third smoothing factors for estimating the actual value at the current time by combining historical and current sensor data; the data gradient is used to measure the spatial consistency constraint: , d i+1,i is the sensor distance; The information consistency expression model is established: wherein λ t and λ s respectively represent a time consistency weight factor and a space consistency weight factor, ω i represents a confidence coefficient of the perception information of the i th sensor, and is used to reflect sensor reliability, represents a data estimation value after comprehensive consideration, represents a measurement value of the i th sensor.

8. The method of claim 5, wherein, In the process of confidence coefficient distribution on the measurement data subjected to the front-end preprocessing link, it includes: Based on the error variance σ i 2 The allocation coefficient ω i , , σ i and σ j denote two standard deviations, j denotes a reference in the loop calculation.

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