Space test load safety discrimination method

Abstract

The invention relates to the field of spacecraft loads, in particular to a space test load safety judgment method, which comprises the following steps: acquiring multi-dimensional parameters of spacecraft loads in real time, including six dimensional parameters of electrical, fluid, biological, medical, energy storage and vacuum exhaust gas; respectively calculating a dynamic threshold value of each dimension parameter, marking the dimension parameters which do not exceed the dynamic threshold values as a normal state, and marking the dimension parameters which exceed the dynamic threshold values as an abnormal state; constructing a multi-dimensional parameter fusion security model, and inputting the dimension parameters of the abnormal state into the multi-dimensional parameter fusion security model to calculate a comprehensive risk index R; and risk grades are divided according to the R value, and the safety of the spacecraft load is divided into three grades. According to the method, the multi-dimensional parameter fusion security model is established, dynamic quantitative risk assessment is realized based on weight distribution, severity level, control effectiveness, time decay factor and inter-dimension coupling effect, and the problems of parameter splitting and high subjectivity in a traditional method are solved.

Description

Technical Field

[0001] This invention relates to the field of spacecraft payload technology, and in particular to a method for determining the safety of space test payloads. Background Technology

[0002] The payload safety of a spacecraft is a core element in ensuring the stable operation of the spacecraft platform. It encompasses multiple key dimensions, each with clearly defined safety requirements and standards: I. Power Supply Interface Safety The payload typically relies on the spacecraft platform's power bus for energy. To ensure the safety of power supply to both sides, several stringent requirements must be imposed on the payload: Surge current limits: For example, a spacecraft stipulates that the load start-up current must not exceed 4 times the maximum rated current and must not exceed 12A, and the duration must be less than 4ms.

[0003] Power supply voltage deviation adaptation: For example, a certain spacecraft specifies that the safe voltage range of the platform's primary bus is 80V~120V, and all electrical loads must operate normally within this range (performance indicators are allowed to be appropriately reduced).

[0004] Overcurrent protection design: Generally, a dual-fuse scheme is adopted. The selected fuses must have the ability to resist transient overload and must not blow when the equipment experiences a transient overload that does not endanger the busbar.

[0005] II. Safety of Fluid Circuit Connection For payloads connected to the spacecraft's fluid loop, safety must be ensured through multi-layered design and verification, including: Material selection: Material compatibility of components such as cold-rolled steel plates, pipes, valves, and quick-break components.

[0006] Experimental verification: compatibility test of contact materials, and effect of foreign matter control.

[0007] Structural design: Pipeline strength and margin design, sealing design and verification results, etc.

[0008] III. Safety of Biomaterials When using biomaterials (mostly polymers) as loads, it is necessary to address the issue of material performance degradation over time, therefore, the following characteristics are required: Biocompatibility verification of selected biological materials.

[0009] Protective design and long-term validation for key performance aspects such as sealing.

[0010] IV. Medical Safety The potential impact of payloads operating in orbit on astronauts must be strictly controlled. Noise control: For example, a spacecraft requires noise levels not to exceed 65 dB.

[0011] In-cabin pressure control: must comply with spacecraft medical safety standards.

[0012] V. Safety of Energy Storage Batteries For loads using energy storage batteries, the battery system must have multiple protection functions, including overcurrent protection, overvoltage protection, short circuit protection, overtemperature protection, and equalization control of battery cells.

[0013] VI. Safety of Vacuum Exhaust Gas Pipeline Connection For loads connected to vacuum exhaust gas pipelines, it is necessary to conduct verification of key aspects such as the compatibility design of experimental exhaust gas and pipeline materials, structural strength and margin design, and sealing design.

[0014] Existing security assessment methods have the following technical shortcomings: (1) Highly subjective and lacking quantitative analysis: The judgment of load safety relies heavily on experience and has not formed a standardized quantitative evaluation system; (2) Parameters are fragmented and lack collaborative analysis: each safety element is mainly assessed independently, ignoring the correlation between dimensions (such as electrical fluctuations may affect the stability of fluid circuits). (3) Insufficient dynamic response: It is difficult to adapt to the dynamic changes of the complex space environment. For example, traditional fuse protection cannot adapt to the fluctuation of bus voltage (80-120V) of the space station; when the pipeline pressure changes by 20%, the fluid control system with a fixed flow threshold cannot automatically adjust the leakage detection sensitivity, resulting in the failure to detect minor leaks, etc. Summary of the Invention

[0015] This invention aims to provide a method for judging the safety of space test payloads. By establishing a multi-parameter fusion safety model, integrating parameters from six dimensions—electrical, fluid, biological, medical, energy storage, and vacuum exhaust—it achieves dynamic quantitative risk assessment through weight allocation, severity level, control effectiveness, time decay factor, and inter-dimensional coupling effect. This solves the problems of parameter fragmentation and strong subjectivity in traditional methods.

[0016] To achieve the above objectives, the technical solution created by this invention is implemented as follows: A method for determining the safety of space test loads includes the following steps: S1: Real-time acquisition of multi-dimensional parameters of spacecraft payloads; these multi-dimensional parameters include six dimensions: electrical, fluid, biological, medical, energy storage, and vacuum exhaust gas. S2: Calculate the dynamic threshold for each dimension parameter, mark the dimension parameters that do not exceed the dynamic threshold as normal, and mark the dimension parameters that exceed the dynamic threshold as abnormal. S3: Construct a multi-dimensional parameter fusion security model, input the dimension parameters of abnormal states into the multi-dimensional parameter fusion security model to calculate the comprehensive risk index R; S4: Based on the R-value, the safety of spacecraft payloads is divided into three levels; among them, When R < 0.3, the safety of the spacecraft payload is determined to be low risk; When 0.3 ≤ R < 0.6, the safety of the spacecraft payload is determined to be of medium risk. When R ≥ 0.6, the safety of the spacecraft payload is determined to be high risk.

[0017] Furthermore, the formula for calculating the dynamic threshold of the electrical dimension parameters is as follows: ; in, The protection time threshold of the electrical system, where V is the bus voltage. This is the insulation resistance value. This is the reference value for insulation resistance.

[0018] Furthermore, the formula for calculating the dynamic threshold of the fluid dimension parameter is as follows: ; in, The leakage rate threshold of the fluid system. This represents the nominal leakage rate of the fluid system. The working pressure of the fluid in the spacecraft payload fluid circuit. The reference pressure for the fluid in the spacecraft payload fluid loop. This represents the actual temperature of the fluid in the spacecraft payload fluid loop.

[0019] Furthermore, the formula for calculating the dynamic threshold of the biological dimension parameter is as follows: ; in, The biological activity threshold, This is the initial threshold for the bioactivity threshold. Let be the material attenuation constant. This refers to the time spent in orbit.

[0020] Furthermore, the formula for calculating the dynamic threshold of the medical dimension parameters is as follows: ) M ; in, The dynamic noise safety threshold (dB(A)); is the baseline noise safety threshold (dB(A)); P is the current cabin pressure (kPa); The reference cabin pressure (kPa); The pressure influence coefficient is dimensionless. The continuous working time of astronauts in orbit (days); This serves as the baseline for the work cycle (days). The period of influence (days) is denoted by M; M is the cumulative fatigue penalty coefficient (dB(A)).

[0021] Furthermore, the formula for calculating the dynamic threshold of the energy storage dimensional parameters is as follows: ; in, The dynamic protection time threshold (s); The maximum allowable protection time; This is the real-time discharge current; For safe discharge current; This is the current penalty coefficient; Real-time battery temperature; The safe temperature threshold; This represents the temperature penalty coefficient.

[0022] Furthermore, the formula for calculating the dynamic threshold of the vacuum exhaust gas dimensional parameters is as follows: ; in, The emission rate threshold for the vacuum exhaust system. This represents the maximum emission rate of the vacuum exhaust system. The actual pressure of the pipeline in the vacuum exhaust system. The optimal working pressure for the vacuum exhaust system. For pressure tolerance zone, The concentration of toxic gases, This refers to the safe concentration threshold for toxic gases.

[0023] Furthermore, the constructed multi-dimensional parameter fusion security model is as follows: ; in, The weights of each dimension parameter, The severity level for each dimension parameter, The effectiveness of controlling parameters for each dimension, The attenuation coefficient for each dimension parameter, Let be the on-orbit time, and β be the coupling coefficient for each dimension parameter. These are the interaction coefficients between dimensional parameters.

[0024] Furthermore, the weights of the parameters in each dimension. as follows: The electrical dimension parameter is 0.3; The fluid dimension parameter is 0.25; The biological dimension parameter is 0.15; The medical dimension parameter is 0.1; The energy storage dimension parameter is 0.1; The vacuum exhaust gas dimension parameter is 0.1; Severity levels of each dimension parameter as follows: The electrical dimension parameters are level 8; The fluid dimension parameter is level 7; The biological dimension parameters are at level 6; The medical dimension parameters are at level 5; The energy storage dimension parameters are level 4; The vacuum exhaust gas dimensional parameters are level 3; Effectiveness of control over parameters in each dimension as follows: The electrical dimension parameters are 90%; The fluid dimension parameter is 85%; The biological dimension parameter is 80%; The medical dimension parameter is 75%; The energy storage dimension parameter is 70%; The vacuum exhaust gas dimension parameter is 65%.

[0025] Compared with the prior art, the present invention can achieve the following beneficial effects: (1) Multi-dimensional collaborative quantitative assessment For the first time, a safety parameter fusion model integrating six dimensions—electrical, fluid, biological, medical, energy storage, and vacuum exhaust—was established. This model utilizes weighted allocation and severity level quantification, transforming traditional isolated assessments into dynamic correlation analysis. For example, the electrical surge protection threshold is linked to the fluid leakage rate threshold, resolving the issue of missed detections caused by fragmented parameters in traditional methods.

[0026] (2) Adaptive dynamic threshold system A dynamic compensation mechanism was developed to address the complex environment of space.

[0027] Electrical system: Surge protection time is automatically adjusted according to bus voltage fluctuations, breaking through the limitations of traditional fixed thresholds.

[0028] Fluid systems: The leakage rate threshold is exponentially corrected as pressure and temperature change, solving the problem of leak detection during sudden changes in pipeline pressure.

[0029] Biomaterials: Combining material decay constants with diurnal periodic functions to achieve time-varying prediction of activity thresholds.

[0030] (3) Risk evolution prediction and intelligent decision-making By introducing a time decay factor and a coupling adjustment factor, the on-orbit aging effect and cross-dimensional interaction risks can be quantified. A three-level early warning system is achieved through a comprehensive risk index R. Attached Figure Description

[0031] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic flowchart of the space test load safety determination method described in the embodiments of the present invention. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not constitute a limitation thereof.

[0033] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0034] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0035] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0036] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0037] like Figure 1 As shown in the figure, an embodiment of the present invention provides a method for determining the safety of space test loads, which includes the following steps: S1: Real-time acquisition of multi-dimensional parameters of spacecraft payloads; among which, the multi-dimensional parameters include six dimensions: electrical, fluid, biological, medical, energy storage, and vacuum exhaust gas.

[0038] The spacecraft payload acquires six key parameters through an onboard sensor network and dedicated measurement equipment, including: Electrical: The bus voltage V provided by the spacecraft platform (typically 100V), the insulation resistance of the load ( ); Fluid: Working pressure of the fluid in the load fluid circuit (Measured by pressure sensor), actual fluid temperature T (measured by temperature sensor), leakage rate L of fluid pipeline (detected by pressure drop method, vacuum leak detection method, etc.). Biological: Microbial activity CFU of the payload device; sealing condition of the payload device materials; Medical: Noise level N during payload operation (measured by noise sensor), current cabin pressure (measured by pressure sensor), and astronaut working hours (recorded in flight log). Energy storage: real-time discharge current (measured by a current sensor), real-time battery temperature (measured by a temperature sensor); Vacuum exhaust: Load-assisted vacuum exhaust pipeline pressure (Measured by pressure sensor), exhaust flow rate Q (measured by flow sensor), toxic gas concentration (Gas sensor measurement).

[0039] The onboard system performs front-end preprocessing on the raw data of the six dimensions of parameters collected, including rationality verification (determining whether the data is within the physically possible range), redundancy management (cross-comparing key parameters with redundant sensor data), and data compression and packaging, and then transmits it to the ground operation and control center through the telemetry link.

[0040] S2: Calculate the dynamic threshold for each dimension parameter, mark the dimension parameters that do not exceed the dynamic threshold as normal, and mark the dimension parameters that exceed the dynamic threshold as abnormal.

[0041] After receiving and verifying the data, the ground control center calculates the dynamic safety threshold for each dimension parameter. Dimension parameters that do not exceed the dynamic threshold are marked as normal, while those that exceed the dynamic threshold are marked as abnormal.

[0042] The formula for calculating the dynamic threshold of electrical dimension parameters is: ; in, The dynamic protection time threshold (ms) for the electrical system; V represents the insulation resistance value; V is the bus voltage (80-120V). The insulation reference resistance is 100MΩ.

[0043] Insulation resistance value A higher threshold indicates better insulation performance and stronger system fault tolerance, thus allowing for a more lenient dynamic protection time threshold to be set. .

[0044] The formula for calculating the dynamic threshold of the fluid dimension parameter is: ; in, The allowable leakage rate threshold (cc / min) for the fluid system. The nominal leakage rate of the fluid system; The working pressure of the fluid in the spacecraft payload fluid circuit; The reference pressure for the fluid in the spacecraft payload fluid loop; This represents the actual temperature of the fluid in the spacecraft payload fluid loop.

[0045] The formula for calculating the dynamic threshold of biological dimension parameters is: ; in, The dynamic bioactivity threshold (CFU) is used. The initial threshold for the bioactivity threshold is 100 CFU. The material attenuation constant (polymer) =72h, metal = ); The time spent in orbit (h).

[0046] Bioactivity threshold It is the maximum permissible microbial load in a closed ecosystem of a spacecraft, measured in CFUs (Colony Forming Units), representing the upper limit of tolerance for microbial proliferation in the spacecraft's internal environment. Generally, as the materials used inside a spacecraft increase in on-orbit operation time, they will experience a certain degree of degradation and microcrack formation. Therefore, we need to gradually reduce the permissible microbial concentration standard.

[0047] The formula for calculating the dynamic threshold of medical dimension parameters is: ) M ; where is the dynamic noise safety threshold (dB(A)); is the reference noise safety threshold (dB(A)); P is the current cabin pressure (kPa); is the reference cabin pressure (kPa); is the pressure influence coefficient, dimensionless; is the continuous working time of astronauts in orbit (days); is the working cycle baseline (days); is the influence period (days); M is the fatigue accumulation penalty coefficient (dB(A)).

[0048] Note: Pressure compensation term: ), in a low-pressure environment, the tolerance of the human auditory system to noise will decrease. This is because the pressure balance inside and outside the middle ear tympanic cavity is broken, the sound transmission efficiency changes, making the noise appear louder and more likely to cause auditory discomfort and damage. When the cabin pressure P is lower than the reference pressure , that is, in a low-pressure environment, the system will automatically tighten the noise safety limit to provide stricter protection for astronauts. Using the natural logarithm ln makes the change smooth and conforms to the physiological perception characteristics.

[0049] Fatigue accumulation compensation term: M , long-term exposure to microgravity, confined spaces and high-pressure work loads will cause physiological and psychological fatigue to accumulate in astronauts, increase sensory sensitivity, and decrease the tolerance to environmental stressors such as noise. This item simulates this "fatigue effect". At the beginning of the mission (T < T0), this item is 0 and does not affect the threshold. When the continuous working time exceeds the baseline T0 (e.g., 30 days), the system starts to consider the fatigue effect to appear, and over time, it gradually tightens the noise limit at a rate of decreasing M dB(A) every ΔT days (e.g.,  10 days).

[0050] The calculation formula for the dynamic threshold of the energy storage dimension parameter is: ; where is the dynamic protection time threshold (s); is the maximum allowable protection time; is the real-time discharge current; is the safe discharge current; is the current penalty coefficient; is the real-time battery temperature; is the safe temperature threshold; is the temperature penalty coefficient.

[0051] The formula for calculating the dynamic threshold of the dimensional parameters of vacuum exhaust gas is: ; in, The allowable emission rate threshold (L / min) for the vacuum exhaust system. The maximum emission rate (L / min) of the vacuum exhaust system. The actual pressure (kPa) in the pipeline of the vacuum exhaust system. The optimal working pressure (kPa) for the vacuum exhaust system. Pressure tolerance zone (kPa); The concentration of toxic gases is expressed in ppm. The safe concentration threshold (ppm) for toxic gases.

[0052] S3: Construct a multi-dimensional parameter fusion security model, and input the dimension parameters of abnormal states into the multi-dimensional parameter fusion security model to calculate the comprehensive risk index R.

[0053] The constructed multi-dimensional parameter fusion security model is as follows: ; in, The weights for each dimension parameter range from 0 to 1; The severity level for each dimension parameter was determined using the Analytic Hierarchy Process (AHP). The control effectiveness of each dimension parameter is determined through Failure Mode and Effect Analysis (FMEA). The attenuation coefficient for each dimension parameter; For on-orbit time; β is the coupling coefficient for each dimension parameter; These are the interaction coefficients between dimensional parameters; Main risk item This is a coupling term.

[0054] Because the dynamic thresholds for each dimension parameter can be dynamically adjusted, the dimension parameters marked as abnormal will also change. Therefore, the calculated comprehensive risk index R will also change each time. For example, in the first data collection, if the medical dimension parameter and the energy storage dimension parameter exceed the threshold, the risk indices for the medical dimension parameter and the energy storage dimension parameter are calculated separately and then added together to obtain the comprehensive risk index R. In the second data collection, if the medical dimension parameter and the electrical dimension parameter exceed the threshold, the risk indices for the medical dimension parameter and the electrical dimension parameter are calculated separately and then added together to obtain the comprehensive risk index R.

[0055] The key parameters of the multi-dimensional parameter fusion security model are calculated as follows: (1) Dimension weight allocation

[0056] Using the Analytic Hierarchy Process (AHP) and historical fault data, the weights of the six dimensions of parameters were determined. The weights of the six dimensions of parameters are shown in the table below.

[0057] (2) Severity level

[0058] The severity of failure consequences is quantified using FMEA (Failure Mode and Effects Analysis). The severity levels of the six parameters are shown in the table below:

[0059] (3) Control effectiveness

[0060] The effectiveness score (0%~100%) of the current load protection measures is based on the load. The effectiveness scores for the six dimensions are shown in the table below:

[0061] (4) Time decay factor

[0062] Attenuation coefficient (α): set according to material properties, for example, α=0.01 / h for polymer materials and α=0.001 / h for metals.

[0063] Cumulative effect over time: The longer the on-orbit time t, the more parameters such as control effectiveness and biological activity will decay over time.

[0064] (5) Coupling adjustment factor

[0065] Interaction coefficient Used to quantify the synergistic effects between dimensions, for example: Biomedical coupling: Degradation of biomaterials may release microparticles, increasing medical noise. =0.1).

[0066] Coupling coefficient β=0.1, used to balance multidimensional coupling effects.

[0067] S4: Based on the R value, the safety of spacecraft payloads is divided into three levels.

[0068] When R < 0.3, the safety of the spacecraft payload is determined to be low-risk, and continuous monitoring is performed. When 0.3 ≤ R < 0.6, the safety of the spacecraft payload is determined to be of medium risk, and local protection measures are initiated. When R≥0.6, the safety of the spacecraft payload is determined to be high-risk, and a forced power-off is performed and the on-orbit working mode is optimized.

[0069] A medium-risk status (0.3 ≤ R < 0.6) indicates the existence of a systemic bias requiring proactive intervention, but it has not yet reached the critical point that jeopardizes mission safety. Typical scenarios and corresponding response strategies are categorized according to six dimensions: (1) Risks in electrical safety These include: bus voltage continuously deviating from the reference band (e.g., dropping to 75V or rising to 125V); surge current approaching the threshold (e.g., reaching 3 times the rated value but not exceeding 12A); insulation resistance dropping to 90MΩ (reference 100MΩ), etc.

[0070] Protection measures: dynamic voltage compensation + transient overcurrent suppression.

[0071] Implementation method: Activate the voltage compensation module to stabilize the bus voltage within the range of 80±5V by adjusting the power supply parameters in real time; Using on-orbit spare parts, the astronauts upgraded the power module to a three-level fuse + solid-state relay composite protection, and used gate turn-off technology to quickly divert transient overcurrents, limiting the surge current to within 2.5 times the rated value.

[0072] (2) Risks in fluid loops This includes: pipeline pressure fluctuations exceeding ±10% of the nominal value (e.g., a sudden drop from 3MPa to 2.7MPa); leakage rate rising to 0.3cc / min (nominal 0.1cc / min); Slight corrosion in contact materials (compatibility index decreased by 15%).

[0073] Protective measures: Intelligent pressure regulation + rapid isolation.

[0074] Implementation method: The liquid supply rate of the cold plate is dynamically adjusted by solenoid valve to maintain stable pressure; the distributed fiber optic sensor array already deployed in the pipeline is used to locate minor leaks and trigger a fast circuit breaker to isolate the faulty section. If necessary, the on-orbit test is stopped, and the astronauts switch the redundant pipeline on-orbit through space-ground coordination.

[0075] (3) Risks in biological materials This includes: the number of bioactive units (CFU) increases to 90 (baseline 100), microcracks appear in the seal; and the surface degradation rate of polymer materials reaches 5% (design life ≥ 2 years).

[0076] Protective measures: Targeted UV sterilization + sealing repair.

[0077] Implementation method: Activate the ultraviolet lamp group and irradiate a cumulative dose of ≥10kJ / m² per day to inhibit microbial proliferation; use nano-silver ion infiltration technology to strengthen the sealing interface and monitor the change in dielectric constant simultaneously (>10% triggers an early warning).

[0078] (4) Risk in medical parameters This includes: cabin noise increasing to 63dB (baseline 65dB).

[0079] Protection measures: Acoustic damping optimization Implementation method: Install gradient porous sound-absorbing material (NRC≥0.8) at the vibration source. If necessary, optimize and reconstruct the equipment support structure by replacing the equipment at the upstream position to reduce resonance noise.

[0080] (5) Medium-term risks of energy storage systems This includes: individual cell temperature differences exceeding 2℃ (design ≤1.5℃).

[0081] Protection measures: balanced charging management + forced heat sink cooling.

[0082] Implementation method: The bidirectional Buck-Boost circuit is activated to realize energy transfer between batteries; the liquid-cooled heat sink system is activated to maintain the average temperature of the battery pack at 25-30°C through phase change material (PCM).

[0083] (6) Risks in vacuum exhaust gas This includes: actual pipeline pressure exceeding 45 kPa (upper limit 50 kPa); CO2 concentration rising to 8 ppm (baseline 10 ppm).

[0084] Protective measures: emergency exhaust pressure relief + catalytic oxidation treatment.

[0085] Implementation: Open the pulse-type pressure relief valve (single release volume ≤ 5L / min) and use the membrane separation device to remove overpressure gas; if necessary, replace with spare parts or deploy a catalyst bed (reaction temperature 300℃) to increase CO2 conversion rate to 95%. High risk: Force power failure and optimize on-orbit operation mode.

[0086] For high-risk conditions (R≥0.6), in addition to forced power outages, "optimizing on-orbit operating modes" will be implemented from three levels: system reconfiguration, resource scheduling, and fault-tolerant design, as detailed below: (1) System-level refactoring strategy The core objective of achieving functional degradation or mode switching through hardware / software architecture adjustments is to ensure the continuity of core tasks.

[0087] ① Electrical safety Load priority redistribution is implemented, activating a dynamic load balancing algorithm. Devices are prioritized based on real-time power consumption (obtained via a sensor network), ensuring power supply to core loads while non-critical devices enter low-power sleep mode. For example, when the bus voltage is <75V, branches below 3A for non-essential devices are automatically disconnected.

[0088] ② Fluid circuit safety Redundancy switching activates the pre-embedded second cold plate circuit (duplex design), and the fluid is switched to the backup pipeline through a three-way valve. Quick-connect flanges are pre-embedded at pipeline nodes to support partial replacement of contaminated components during emergency maintenance.

[0089] ③Biosafety Use the polymer alternative as a backup module. Contact compatibility must be re-verified after load transfer.

[0090] ④ Medical safety The layout of noise sources was redesigned, and high-vibration equipment was moved to non-habitable compartments.

[0091] ⑤ Energy storage security Remove the faulty battery module and maintain the total capacity by connecting a healthy battery pack in parallel; activate the electrolyte circulation pump to accelerate thermal equilibrium. Safety thresholds: after removal, the voltage difference between individual cells ≤0.5V, and the temperature difference ≤2℃.

[0092] ⑥ Vacuum exhaust gas safety The membrane separation device was activated to filter toxic gases.

[0093] (2) Dynamic resource scheduling mechanism The core objective of optimizing resource allocation through dynamic algorithms is to minimize energy or material consumption.

[0094] ① Electrical safety Based on real-time power consumption data, a fuzzy logic algorithm is used to prioritize devices; non-critical devices are powered by pulses (e.g., 30% duty cycle), while core loads are guaranteed to have continuous power.

[0095] ② Fluid circuit safety The liquid supply flow rate is dynamically adjusted according to the needs of each cold plate (the flow rate is controlled by valves); the heat prediction model is activated to prioritize cooling of high-heat-generating equipment (such as components with power > 500W).

[0096] ③Biosafety For highly active areas (CFU>80), activate the enhanced UV sterilization mode (irradiation dose ≥15kJ / m² / day); reduce the sterilization frequency of low-risk areas to save energy consumption.

[0097] ④ Medical safety The noise reduction strategy is dynamically adjusted according to the astronauts' activity area: full-band noise reduction is activated during sleep, while low-frequency noise suppression is emphasized during work.

[0098] ⑤ Energy storage security Dynamic staggered power supply to the load reduces load consumption, thereby reducing current and battery temperature.

[0099] ⑥ Vacuum exhaust gas safety Based on the fluctuation of air pressure inside the cabin, the exhaust gas emission is predicted, and the turbine speed is adjusted in advance; inert gas is recovered and reused (purity ≥99.9%).

[0100] (3) Fault-tolerant design Reduce the impact of failures through redundancy / self-healing mechanisms.

[0101] ① Electrical safety Replace the circuit boards such as fuses in the equipment with spare parts and upgrade them to positive temperature coefficient components, which automatically limit current instead of hard disconnection when overloaded; configure fault arc detectors (response time <2ms) at key nodes to trigger microsecond-level circuit breaker isolation.

[0102] ② Fluid safety Pipeline nodes use clamp-type quick-break joints (withstanding differential pressure ≥1MPa); by deploying a distributed fiber optic sensor network (positioning accuracy ±0.5m), even minor leaks automatically trigger isolation valves.

[0103] ③Biosafety When CFU levels exceed the limit, an antimicrobial peptide solution (concentration 10 ppm) is automatically injected to inhibit proliferation.

[0104] ④ Medical safety The noise sensor array is redundantly configured (≥3 measurement points), and automatically switches to the backup channel if any one fails; the radiation shielding layer adopts a multi-layer composite structure, and the damage to a single layer does not affect the overall performance.

[0105] ⑤ Energy storage security Configure a backup battery so that it switches to operation when the temperature gets too high.

[0106] ⑥ Vacuum exhaust gas safety When the CO2 concentration exceeds the standard, chemical adsorption is initiated (capacity ≥10g / mol).

[0107] Example 1 Taking the calculation of the comprehensive risk index of a spacecraft payload from a medical dimension as an example, and taking the operational status of the spacecraft payload at a certain moment as an example, assume the following parameters: The actual noise level is N=68dB, the on-orbit time is t=100h, the control effectiveness is C=75% (active noise reduction system), the coupling adjustment factor is F=0.2, and the noise is related to fluid pressure fluctuations. Fluid system pressure fluctuations (such as leakage causing turbulence) may induce mechanical vibrations, thereby increasing the noise level. At this time, the two are positively correlated, so a positive value is taken.

[0108] N0 = 65 dB(A); K = 2.5; P0 = 101.3 kPa; M = 1.0 dB(A); T0 = 30 days; ΔT = 10 days; P = 101.3 kPa, T = 65 days; then:

[0109] Explanation: Due to the on-orbit working time far exceeding the baseline, the fatigue accumulation effect is significant. The system has reduced the noise safety threshold by 3.5 dB(A), providing additional protection for astronauts in the fatigue period.

[0110] but It is possible to determine the actual noise. This triggers anomalies in the medical dimension.

[0111] Calculate the values ​​of medical dimension parameters

[0112] The risk index for the medical dimension parameters is:

[0113] Excessive noise levels significantly increase medical risks.

[0114] Insufficient control effectiveness (75%) indicates a need to strengthen noise reduction measures (such as upgrading active noise reduction algorithms or adding shielding layers).

[0115] Coupling effect ( =0.2) This indicates that attention should be paid to the combined risks of noise and fluid pressure.

[0116] For example, if the risk indices for each dimension parameter are: electrical (0.25), fluid (0.6), biological (0.1), medical (0.2292), energy storage (0.03), and vacuum exhaust gas (0.02), then: R=0.25+0.6+0.1+0.2292+0.03+0.02=1.2292.

[0117] According to the risk level classification, R > 0.6 indicates high risk, in which case the load should be powered off and the on-orbit working mode should be optimized.

[0118] The foregoing details the space test load safety assessment method provided by the embodiments of the present invention. Using this assessment method can achieve the following technical effects: 1. Cross-dimensional dynamic coupling model Traditional approach: Each safety dimension (such as electrical and fluid) is assessed independently, and static thresholds are used for determination.

[0119] This invention quantifies the interactions between dimensions through coupling terms; The dynamic threshold formula incorporates real-time compensation for environmental parameters (such as voltage fluctuations to correct surge thresholds and pressure changes to adjust leakage sensitivity) to adapt to the complex space environment.

[0120] 2. Time-varying biological activity control Conventional approach: Biomaterial safety is verified based on fixed thresholds.

[0121] This invention combines the material decay constant and the diurnal cycle function to dynamically adjust the bioactivity threshold, thereby solving the problem of polymer material performance degradation over time.

[0122] 4. Real-time decision-making based on multi-parameter fusion Conventional techniques rely on human experience or single-dimensional thresholds to trigger responses.

[0123] This invention is superior to automatic graded response based on comprehensive risk index, combined with prediction of long-term risks by control effectiveness decay, thereby improving on-orbit autonomous decision-making capability.

[0124] It should be understood that the various forms of processes shown above can be used to reorder, add, or delete steps. For example, the steps described in this invention disclosure can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this invention can be achieved, and this is not limited herein.

[0125] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A method for determining the safety of space test loads, characterized in that, Includes the following steps: S1: Real-time acquisition of multi-dimensional parameters of spacecraft payloads; these multi-dimensional parameters include six dimensions: electrical, fluid, biological, medical, energy storage, and vacuum exhaust gas. S2: Calculate the dynamic threshold for each dimension parameter, mark the dimension parameters that do not exceed the dynamic threshold as normal, and mark the dimension parameters that exceed the dynamic threshold as abnormal. S3: Construct a multi-dimensional parameter fusion security model, input the dimension parameters of abnormal states into the multi-dimensional parameter fusion security model to calculate the comprehensive risk index R; S4: Based on the R-value, the safety of spacecraft payloads is divided into three levels; among them, When R < 0.3, the safety of the spacecraft payload is determined to be low risk; When 0.3 ≤ R < 0.6, the safety of the spacecraft payload is determined to be of medium risk. When R ≥ 0.6, the safety of the spacecraft payload is determined to be high risk.

2. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of electrical dimension parameters is: ； in, The protection time threshold of the electrical system, where V is the bus voltage. This is the insulation resistance value. This is the reference value for insulation resistance.

3. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of the fluid dimension parameter is: ； in, The leakage rate threshold of the fluid system. This represents the nominal leakage rate of the fluid system. The working pressure of the fluid in the spacecraft payload fluid circuit. The reference pressure for the fluid in the spacecraft payload fluid loop. This represents the actual temperature of the fluid in the spacecraft payload fluid loop.

4. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of biological dimension parameters is: ； in, The biological activity threshold, This is the initial threshold for the bioactivity threshold. Let be the material attenuation constant. This refers to the time spent in orbit.

5. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of medical dimension parameters is: )- M ； in, The dynamic noise safety threshold; The reference noise safety threshold is P; P is the current cabin air pressure. The reference cabin pressure; This is the air pressure influence coefficient; For the continuous working time of astronauts in orbit; As a baseline for the work cycle; The period is the influence period; M is the fatigue cumulative penalty coefficient.

6. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of energy storage dimensional parameters is as follows: ； in, For dynamic protection time threshold; The maximum allowable protection time; This is the real-time discharge current; For safe discharge current; This is the current penalty coefficient; Real-time battery temperature; The safe temperature threshold; This represents the temperature penalty coefficient.

7. The method for determining the safety of space test loads according to claim 1, characterized in that, The formula for calculating the dynamic threshold of the dimensional parameters of vacuum exhaust gas is: ； in, The emission rate threshold for the vacuum exhaust system. This represents the maximum emission rate of the vacuum exhaust system. The actual pressure of the pipeline in the vacuum exhaust system. The optimal working pressure for the vacuum exhaust system. For pressure tolerance zone, The concentration of toxic gases, This refers to the safe concentration threshold for toxic gases.

8. The method for determining the safety of space test loads according to claim 1, characterized in that, The constructed multi-dimensional parameter fusion security model is as follows: ； in, The weights of each dimension parameter, The severity level for each dimension parameter, The effectiveness of controlling parameters for each dimension, The attenuation coefficient for each dimension parameter, Let be the on-orbit time, and β be the coupling coefficient for each dimension parameter. These are the interaction coefficients between dimensional parameters.

9. The method for determining the safety of space test loads according to claim 8, characterized in that, Weights of parameters in each dimension as follows: The electrical dimension parameter is 0.3; The fluid dimension parameter is 0.25; The biological dimension parameter is 0.15; The medical dimension parameter is 0.1; The energy storage dimension parameter is 0.1; The vacuum exhaust gas dimension parameter is 0.1; Severity levels of each dimension parameter as follows: The electrical dimension parameters are level 8; The fluid dimension parameter is level 7; The biological dimension parameters are at level 6; The medical dimension parameters are at level 5; The energy storage dimension parameters are level 4; The vacuum exhaust gas dimensional parameters are level 3; Effectiveness of control over parameters in each dimension as follows: The electrical dimension parameters are 90%; The fluid dimension parameter is 85%; The biological dimension parameter is 80%; The medical dimension parameter is 75%; The energy storage dimension parameter is 70%; The vacuum exhaust gas dimension parameter is 65%.

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