Rocket fairing environment temperature and humidity control system and method

Abstract

The application discloses a rocket fairing environment temperature and humidity control system and method. The method comprises the following steps: fixing a movable integrated platform with a bearing surface, wherein the integrated platform comprises a heat preservation cabin and a temperature and humidity adjusting device; butting the heat preservation cabin with the rocket fairing to form a closed temperature control space; starting the temperature and humidity adjusting device to make the air flow in the temperature control space circulate through an air flow channel; collecting three-dimensional temperature and humidity distribution data in the temperature control space in real time through a multi-node temperature and humidity sensor network arranged at different spatial positions in the heat preservation cabin; sending the three-dimensional temperature and humidity distribution data to a controller; the controller runs an adaptive control algorithm to generate a control instruction according to the deviation between preset target parameters and the three-dimensional temperature and humidity distribution data; and the temperature and humidity adjusting device adjusts its output according to the control instruction to realize closed-loop regulation and control of the temperature and humidity distribution in the temperature control space. The application is suitable for the internal environment guarantee of the fairing under complex environments such as offshore launching.

Description

Technical Field

[0001] This invention relates to the field of spacecraft launch support system technology, and in particular to a rocket fairing environmental temperature and humidity control system and method. Background Technology

[0002] The stability of the internal environment of a spacecraft fairing, especially the precise control of temperature and humidity, is crucial to ensuring the safety and functional reliability of internal payloads (such as satellites and precision instruments).

[0003] Currently, several system solutions exist for fairing environmental control. For example, these solutions incorporate gas flow control, air environment detection, circulating air drive, air conditioning, and rapid cooling within the fairing. Through the coordination of a semiconductor cooler, heating chamber, water storage chamber, and related airflow piping, these systems can humidify, dehumidify, heat, and cool the airflow inside the fairing, thereby maintaining a stable internal environment to a certain extent and preventing equipment damage due to environmental fluctuations. This system represents a typical technical approach based on closed-loop airflow circulation and active thermal and humidity control.

[0004] However, existing technologies were primarily designed for land-based or conventional space launch sites. These applications typically feature a stable ground base, a continuous and reliable power supply, and a relatively mild external environment. When applied to complex and variable launch missions, especially sea-based launch scenarios, they suffer from the inability to maintain stability in high-humidity, high-salt-spray environments and the inability to adaptively regulate temperature and humidity. Summary of the Invention

[0005] To address the aforementioned technical problems, the technical solution adopted by this invention is as follows: According to a first aspect of the present invention, a method for controlling the ambient temperature and humidity of a rocket fairing is provided, the method comprising the following steps: A movable integrated platform is fixed to a bearing surface. The movable integrated platform includes an insulated chamber and a temperature and humidity control device. The insulated chamber is docked with the rocket fairing to be serviced to form a closed temperature-controlled space.

[0006] The temperature and humidity control device is activated, and the airflow is circulated within the temperature-controlled space through the airflow channel connected to the insulated chamber.

[0007] A network of multi-node temperature and humidity sensors deployed at different locations within the insulated chamber is used to collect real-time three-dimensional temperature and humidity distribution data within the temperature-controlled space.

[0008] The three-dimensional temperature and humidity distribution data is sent to a controller, which runs an adaptive control algorithm to generate control commands based on the deviation between the preset target parameters and the three-dimensional temperature and humidity distribution data.

[0009] The temperature and humidity regulating device adjusts its output according to the control command to achieve closed-loop control of the temperature and humidity distribution within the temperature-controlled space.

[0010] According to a second aspect of the present invention, a rocket fairing environmental temperature and humidity control system for implementing the method described in the first aspect is provided, comprising: The mobile integrated platform includes a carrier unit and an insulated cabin fixed to the carrier unit. The insulated cabin is used to dock with the rocket fairing to be serviced to form a closed temperature-controlled space.

[0011] The temperature and humidity control device is connected to the insulated chamber through an airflow channel to form a circulating airflow loop.

[0012] A multi-node temperature and humidity sensor network is deployed at different locations within the insulated chamber to collect three-dimensional temperature and humidity distribution data.

[0013] The controller is connected to the sensor network and the temperature and humidity control device, and runs an adaptive control algorithm to dynamically control the operation of the temperature and humidity control device.

[0014] The present invention has at least the following beneficial effects: This method creates a closed temperature-controlled space by fixing a movable integrated platform to the support surface and docking it with the fairing. This allows airflow to circulate completely isolated from the external environment, preventing the intrusion of high-humidity, high-salt-spray air. A multi-node temperature and humidity sensor network is deployed to collect three-dimensional temperature and humidity distribution data in real time, identifying temperature gradients and humidity hotspots within the controlled space. The controller runs an adaptive control algorithm, generating control commands based on the deviation between preset target parameters and the collected data. This drives the temperature and humidity regulating device to adjust its output in a closed loop, dynamically maintaining the temperature and humidity distribution within the controlled space within the preset target parameter range. Compared to existing technologies, this method achieves mobile deployment, refined spatial perception, and adaptive closed-loop control, making it particularly suitable for controlling the internal environment of the fairing in harsh environments such as launch ship decks.

[0015] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying 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.

[0017] Figure 1 This is a structural block diagram of the rocket fairing environmental temperature and humidity control system provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of a temperature and humidity control device. Figure 3 A flowchart of a method for controlling the ambient temperature and humidity of a rocket fairing provided in an embodiment of the present invention.

[0018] (Explanation of reference numerals in the attached image) 1. Transport and launch vehicle; 2. Insulated chamber; 3. Air inlet duct; 4. Temperature and humidity control device; 5. Return air duct; 41. Electrical control box; 42. Compressor; 43. Electric heater; 44. Humidifier; 45. Air inlet valve; 46. Return air inlet valve; 47. Operation display screen; 48. Centrifugal fan; 49. Humidifying water tank; 410. Axial flow fan; 412. Evaporator. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0021] It should be noted that some exemplary embodiments are described as processes or methods depicted as flowcharts. Although the flowcharts describe the steps as sequential processes, many of these steps can be performed in parallel, concurrently, or simultaneously. Furthermore, the order of the steps can be rearranged. A process can be terminated when its operation is complete, but it may also have additional steps not included in the figures. A process can correspond to a method, function, procedure, subroutine, subroutine, etc.

[0022] When existing technical solutions are applied to complex and ever-changing special launch missions, especially in maritime launch scenarios, the following shortcomings are exposed: First, existing systems are mostly embedded or integrated structures within the fairing, lacking a rapidly deployable, mobile, and deeply coupled integrated platform that can be coupled with the launch platform (such as a transport launch vehicle). In sea-based launch missions, rockets need to remain on the launch ship's deck for extended periods, in environments characterized by high humidity, high salt spray, and ship swaying. Existing fixed or embedded systems struggle to achieve rapid positioning, flexible adaptation to different fairing models, and overall dismantling and reuse after the mission.

[0023] Second, the environmental control strategies of existing systems are relatively basic, mainly relying on single or limited temperature and humidity sensors (such as ejector temperature and humidity sensors and internal temperature and humidity sensors) for data acquisition, and controlling the airflow path through simple valve switching. This control architecture cannot detect significant temperature gradients and humidity hotspots that may exist in the three-dimensional space inside the fairing, making it difficult to achieve precise, zoned, and differentiated control. It is prone to local overheating, overcooling, or condensation, and the control accuracy and response speed are insufficient to meet the stringent requirements of high-value payloads.

[0024] Third, existing systems generally lack remote intelligent monitoring and multi-energy redundant power supply designs. Under the harsh conditions of sea launches, on-site personnel face high risks, and the ship's electrical grid is susceptible to fluctuations or interruptions. If the main power supply fails, the existing system, lacking effective backup, will immediately shut down, leading to environmental chaos and directly threatening mission success or failure. Furthermore, the inability to conduct remote, unmanned monitoring and intervention reduces the safety and flexibility of the launch organization.

[0025] Therefore, there is an urgent need to develop a new type of fairing temperature and humidity control system and method that can adapt to the special conditions of sea launches and integrate mobile deployment, high-precision adaptive control, remote intelligent monitoring and high-reliability power supply.

[0026] Example 1 I. Application Scenarios The rocket fairing environmental temperature and humidity control system provided in this embodiment is specifically designed to ensure the internal environment of the fairing during the long-term stay of the launch vehicle on the deck of the launch ship in a sea launch mission.

[0027] In sea-based launch scenarios, after completing technical preparations, the launch vehicle typically remains erect on the launch ship's deck for over 24 hours, awaiting a suitable launch window. During this period, the rocket fairing and its internal payloads (such as satellites, optical equipment, and precision electronic instruments) are exposed to the complex marine environment, facing the following significant challenges: High humidity environment: The relative humidity of the sea surface is above 80% year-round, and can reach over 95% at night. High humidity can cause condensation on the mirrors of optical payloads, short circuits in electronic equipment due to moisture, and corrosion of metal components.

[0028] High salt spray environment: Salt spray particles generated by breaking waves are suspended in the air, which can accelerate material corrosion, reduce insulation performance, and cause poor contact of connectors.

[0029] Dramatic temperature fluctuations: Large temperature differences between day and night, and solar radiation can cause the surface temperature of the fairing to rise rapidly, thereby causing changes in thermal stress and performance drift of internal equipment.

[0030] Hull swaying: Swaying can cause traditional airflow organization schemes to fail, and can easily lead to local overheating or overhumidification.

[0031] Unstable power supply: The ship's electrical grid is affected by factors such as main engine start-up and shutdown, load changes, etc., and there is a risk of voltage fluctuations or even temporary interruptions. Once the environmental control system shuts down due to power supply problems, it will directly lead to uncontrolled temperature and humidity inside the fairing, seriously threatening the safety of the payload.

[0032] The existing fixed air conditioning systems at land-based launch sites cannot be directly applied to sea-based launch scenarios: on the one hand, the launch ship deck does not have ground-based fixed air conditioning rooms and air duct infrastructure; on the other hand, the open air supply scheme cannot resist the erosion of the payload by the high humidity and high salt spray environment.

[0033] The system in this embodiment is designed to solve the technical challenges of the special conditions of sea launch. Its core application scenario is to provide a microclimate protection environment for the vertical launch vehicle fairing on the launch ship deck, which can be quickly deployed, completely sealed and autonomously controlled, to ensure that the payload is always within a safe temperature and humidity range throughout the entire process before launch.

[0034] II. System Overall Architecture and Technical Solution like Figure 1 As shown, the rocket fairing environmental temperature and humidity control system in this embodiment is installed on the transport launch vehicle 1. The transport launch vehicle 1 itself has a vehicle-ship connection and fixing mechanism, which can maintain a stable attitude under the swaying conditions of the launch ship deck. The system mainly includes: a mobile integrated platform, a temperature and humidity regulating device 4, a multi-node temperature and humidity sensor network, a central controller (integrated in the electrical control box 41), a remote telemetry monitoring module, and a multi-energy power supply module.

[0035] (i) Mobile integration platform: Enables modular rapid deployment and task reuse. This embodiment constructs an integrated, mobile platform based on a transport and launch vehicle. Specifically: A steel-structured insulated cabin 2 is integrated above the transport and launch vehicle 1. The insulated cabin 2 adopts a frame-skin structure with an insulation layer, which is filled with polyurethane foam material (or high-performance insulation materials such as aerogel felt). The external dimensions of the insulated cabin 2 are adapted to the typical rocket fairing dimensions, and it consists of two semi-cones, which are fixed on two sets of fairing docking brackets respectively.

[0036] After the insulated chamber 2 is docked with the fairing, it forms a sealed temperature-controlled space through a mechanical locking device and an annular sealing strip, completely isolating it from the external high-humidity, high-salt-fog marine environment.

[0037] The front center of the insulation chamber 2 is provided with a circular air inlet, which is connected to the air outlet of the temperature and humidity control device 4 through a flexible air duct (i.e., air inlet duct 3); the front bottom of the insulation chamber 2 is provided with a return air inlet, which is connected to the return air end of the temperature and humidity control device 4 through a rigid return air duct plus a flexible air duct (i.e., return air duct 5), forming a complete internal circulation ventilation system.

[0038] Based on the above structure, since the entire system is integrated on the transport and launch vehicle, it can be quickly deployed and withdrawn after the mission, and reused between different launch missions, thereby reducing launch costs. Because the thermal insulation chamber and fairing form a sealed temperature-controlled space through mechanical locking devices and annular sealing strips, and the air intake and return ducts form a completely internal circulation, external high-humidity and high-salt-spray air cannot penetrate, thus effectively preventing condensation on optical payloads and moisture damage to electronic equipment. Because the thermal insulation layer has good thermal insulation performance, it can reduce the transfer of external heat and reduce the cooling load of temperature and humidity control devices. Because the air intake duct uses flexible ducts, it can absorb the hull sway and vibration of the ship, avoid leakage or damage at the duct connection, and ensure stable operation of the system under swaying conditions at sea.

[0039] (ii) Temperature and humidity control device: to achieve precise temperature and humidity control. The temperature and humidity control device 4 (i.e., the integrated air conditioning unit) is connected to the insulation chamber 2 through an airflow channel, forming a circulating airflow loop. This device integrates cooling, heating, humidification, air supply, and electrical control functions, adopting a modular frame structure with functional units arranged in layers for ease of manufacturing, maintenance, and repair. Specifically, such as... Figure 2 As shown, the temperature and humidity control device 4 includes a compressor 42, an axial flow fan 411, an evaporator 412, an electric heater 43, a humidifier 44, a centrifugal fan 48, an air inlet valve 45, an air return valve 46, a humidifying water tank 49, and an operation display screen 47. The above components are integrated and installed in the electrical control box 41 and multiple functional frames.

[0040] (1) Airflow circuit and circulation drive The airflow channels include an inlet duct 3 and a return duct 5: one end of the inlet duct 3 is connected to the outlet of the temperature and humidity control device 4, and the other end is connected to the air inlet at the lower center of the front of the insulation chamber 2; one end of the return duct 5 is connected to the return air outlet of the temperature and humidity control device 4, and the other end is connected to the return air inlet at the bottom front of the insulation chamber 2. Driven by the centrifugal fan 48, the airflow circulates between the temperature-controlled space and the temperature and humidity control device 4, completely isolating it from the external ambient air, thereby preventing the intrusion of high-humidity, high-salt-spray marine air into the temperature-controlled space.

[0041] (2) Modular frame structure The temperature and humidity control device 4 adopts a modular frame structure with upper and lower layers and independent functions, specifically including: First frame: Located in the middle of the device, it houses an electric heater 43 and a humidifier 44 for heating or humidifying the circulating airflow. Air inlet valve 45 is connected to the side of the first frame and is used to adjust the proportion of fresh air entering the device (allowing for the introduction of external air when supplementary air is needed).

[0042] The second frame is located above the first frame and houses the centrifugal fan 48. A return air valve 46 is connected to the outlet of the centrifugal fan 48 to regulate the return air flow. An operation display screen 47 is also located on the outside of the second frame to display system operating parameters, temperature and humidity data, and equipment status, and supports local parameter setting and manual control.

[0043] The third frame is connected to the first frame (it can be located on the side or rear of the first frame), and the electrical control box 41 and compressor 42 are fixedly installed inside. The electrical control box 41 integrates a central controller, drive circuit and power management module, which is used to receive sensor signals and control various actuators; the compressor 42 is used to drive the refrigerant circulation to achieve the cooling and dehumidification functions.

[0044] The fourth frame 410 is located on top of the third frame and has an axial fan 411 and an evaporator 412 fixedly installed inside. The evaporator 412, together with the compressor 42 and the condenser (not shown in the figure), forms a refrigeration cycle to cool and dehumidify the circulating airflow; the axial fan 411 is used to enhance the heat exchange between the evaporator 412 and the air, thereby improving the refrigeration efficiency.

[0045] Humidifying water tank 49: Located on the upper part of the fourth frame 410, it stores pure water and is connected to the humidifier 44 through a pipe to supply water to the humidifier 44.

[0046] (3) Working principle of each functional unit Cooling and dehumidification mode: When the central controller determines that cooling or dehumidification is needed, it starts the compressor 42. The refrigerant evaporates and absorbs heat in the evaporator 412, and the air flowing through the evaporator 412 is cooled. Water vapor in the air condenses and is discharged through the drain pipe, thereby achieving cooling and dehumidification. The axial fan 411 accelerates the airflow through the evaporator 412, improving heat exchange efficiency.

[0047] Heating mode: When the central controller determines that heating is needed, it activates the electric heater 43, and the air flowing through the electric heater 43 is heated. The electric heater 43 can use a PTC thermistor heating element, which has self-limiting temperature characteristics and is safe and reliable.

[0048] Humidification mode: When the central controller determines that humidification is needed, it starts the humidifier 44. The humidifier 44 atomizes or evaporates the water in the humidification water tank 49 and sends it into the airflow to increase the air humidity. The humidifier 44 can use ultrasonic atomization humidification or electrode steam humidification.

[0049] Air supply mode: The centrifugal fan 48 adjusts its speed according to the instructions of the central controller, thereby controlling the circulating air volume to meet the air supply requirements under different operating conditions. The inlet damper 45 and the return damper 46 can be used together to adjust the airflow distribution.

[0050] Based on the above structure, the device is compact and easy to install and deploy on a transport and launch vehicle because each functional unit is arranged in a modular frame structure and integrated into one unit. It integrates cooling, dehumidification, heating, humidification and air supply functions, and can adapt to various working conditions of sea launch from high temperature and humidity to low temperature and dryness without the need for additional independent equipment. Since each functional unit can be disassembled and assembled independently, when a module fails, it can be replaced individually, thereby shortening the on-site maintenance time and meeting the rapid support requirements of sea missions. Since the frames are rigidly connected and the internal components are fixed by vibration damping brackets, it can still maintain stable operation under the condition of hull swaying, avoiding pipeline loosening or component falling off. Since the airflow circulates completely between the temperature control space and the temperature and humidity regulation device without exchanging with the external environment, it can effectively isolate the external high humidity and high salt spray air, preventing salt spray corrosion and condensation on the optical payload.

[0051] (III) Multi-node temperature and humidity sensor network: realizing three-dimensional spatial distribution sensing A multi-node temperature and humidity sensor network is arranged inside the thermal chamber 2: the chamber is divided into three sections along its axial direction: upper, middle, and lower. Multiple sensing units are evenly distributed circumferentially in each layer, with a total of no fewer than six sensing units, covering the entire space along the axial and circumferential directions of the fairing. Each sensing unit uses a digital temperature and humidity sensor (e.g., SHT30, HDC1080, or equivalent precision element) to collect temperature and humidity data at that point in real time. All sensors are connected to the central controller via shielded cables. Based on this arrangement, since the sensor network is layered and evenly distributed circumferentially in three-dimensional space, it can collect temperature and humidity data from multiple locations within the temperature-controlled space, thereby identifying temperature gradients and humidity hotspots (e.g., when the humidity in the area where the optical payload is located is significantly higher than in other areas, the controller can determine that there is localized moisture accumulation), providing a spatial distribution basis for subsequent zoned differentiated control.

[0052] (iv) Central controller and adaptive control algorithm: to achieve high-precision closed-loop regulation The controller (e.g., an industrial PLC or embedded industrial computer, integrated within the electrical control box 41) is connected to both the multi-node temperature and humidity sensor network and the temperature and humidity control device 4. The controller has a pre-installed adaptive control algorithm. Based on this connection, the controller can receive real-time three-dimensional temperature and humidity distribution data collected by the multi-node temperature and humidity sensor network, and calculate the deviation between the current temperature and humidity and the preset target parameters using the adaptive control algorithm. Based on this, it dynamically generates adjustment commands and sends them to the temperature and humidity control device 4. The temperature and humidity control device 4 adjusts its cooling, heating, dehumidification, or humidification output according to the commands, thus forming a closed-loop control chain of "sensing-decision-execution," achieving high-precision control of the temperature and humidity distribution within the temperature-controlled space. The specific implementation steps of the adaptive control algorithm will be described in detail in the following method embodiments.

[0053] (v) Remote telemetry and monitoring module: Enables unattended operation The system is equipped with a remote telemetry and monitoring module, which integrates a dual-channel communication interface for 4G public network communication and BeiDou short message communication, and connects to the central controller. Based on this configuration, the remote telemetry and monitoring module can upload the system's operating status (including the operating mode of the temperature and humidity control device, fan speed, valve opening, fault codes, etc.), environmental parameters (including real-time temperature and humidity data collected by various sensors, and temperature and humidity change sequences within a preset time period), and fault alarm information to a shore-based or shipborne remote command center via the communication network. Simultaneously, it receives control commands from the remote command center (including starting or stopping the temperature and humidity control device, modifying temperature and humidity setpoints, switching operating modes, querying historical data, triggering emergency plans, etc.), allowing operators to monitor and intervene in the system without being physically present, achieving unattended operation. The remote command center displays temperature curves, humidity trends, equipment status, and energy consumption statistics in real time through a customized monitoring software interface. Authorized users can remotely access the system via an encrypted link, further enhancing the remote control capabilities for environmental support during maritime launch missions.

[0054] (vi) Multi-energy power supply module: to achieve highly reliable uninterrupted power supply The power supply system consists of three parts: Main power supply: AC220V / 50Hz input, from the launch ship's power distribution cabinet; Backup power: Lithium iron phosphate battery pack, which can support the system to operate at full load for ≥8 hours; Auxiliary power supply: The monocrystalline silicon solar photovoltaic panel array installed on the top of the insulated chamber can replenish the battery pack with power during the day.

[0055] The three power sources mentioned above are connected to the Battery Management System (BMS). Based on this configuration, the BMS monitors the voltage and current status of each power source in real time and automatically selects the optimal power supply path according to preset priorities. When the main power supply is interrupted, it can seamlessly switch to the backup battery pack for power supply. Experimental tests show that, under no-light conditions, the system can maintain full-load operation for more than 8 hours relying solely on battery power, thereby ensuring that the temperature and humidity control device can continue to operate when the ship's power grid fluctuates or is interrupted, providing highly reliable uninterrupted power support for maritime launch missions.

[0056] (vii) Cooling device In another preferred embodiment, the system also includes a cooling device. This device is a liquid nitrogen cylinder, the output of which is connected to the airflow duct via a control valve and piping. Based on this configuration, when the central controller detects that the rate of temperature rise in the temperature-controlled space exceeds a preset threshold and the temperature and humidity control devices have reached their maximum cooling capacity but are still unable to suppress the temperature rise (e.g., the rectifier's temperature rises sharply due to sun exposure or abnormal heating of internal equipment), the controller opens the liquid nitrogen cylinder control valve, releasing liquid nitrogen into the circulating airflow. The liquid nitrogen's vaporization absorbs heat, achieving rapid auxiliary cooling. This design provides a last line of defense for emergency protection under extreme conditions.

[0057] It should be noted that the above embodiments can be adapted to specific needs in actual missions. For example, for fairings with larger diameters (e.g., 6m or more), a segmented modular thermal insulation cabin structure can be adopted, dividing the thermal insulation cabin into multiple independently transportable and assembleable modules to improve transportation convenience and on-site assembly efficiency. The adaptive control algorithm can also be upgraded to a predictive control model based on machine learning, using historical environmental data and weather forecast data to predict temperature and humidity change trends in advance, thereby providing feedforward intervention to the operating status of the temperature and humidity regulation device and further reducing control lag. In addition, high-efficiency salt mist filters can be added to the air intake or return air ducts to filter salt mist particles in the circulating airflow, further improving the protection level against marine corrosive particles. This embodiment, through the synergistic effect of a mobile integrated platform, multi-node three-dimensional perception, fuzzy PID adaptive control, remote telemetry monitoring, and multi-energy redundant power supply, achieves the following comprehensive technical effects for the special working conditions of a sea launch scenario: Environmental stability: The temperature and humidity inside the temperature-controlled space can be kept within the preset target parameter range, effectively ensuring the safety of the payload. Deployment efficiency: The system moves as a whole with the transport launch vehicle, and can be deployed and docked in a short time. After the mission, it can be completely withdrawn, enabling reuse for multiple missions.

[0058] Operational reliability: The multi-energy redundant power supply can maintain system operation for more than 8 hours after the main power supply is interrupted; remote telemetry monitoring supports unattended operation.

[0059] Protection capabilities: The fully enclosed internal circulation system can isolate the external high humidity and high salt spray environment, reducing the risk of condensation on optical loads and moisture damage to electronic equipment.

[0060] Energy efficiency optimization: Differentiated regional control can avoid excessive overall dehumidification or cooling; solar photovoltaic auxiliary power supply can reduce dependence on the ship's power grid.

[0061] This embodiment utilizes a modular, mobile, and integrated platform design, enabling the system to be reused across different launch missions. It improves control response speed and accuracy through an adaptive temperature control algorithm based on multi-node sensing. Remote telemetry monitoring reduces the need for on-site personnel operation. A multi-energy power supply architecture enhances the system's continuous operation capability in harsh sea conditions. Therefore, this invention provides a fairing environment temperature and humidity control solution suitable for maritime launch scenarios.

[0062] The control method of the present invention will be described in detail below with reference to the specific working process.

[0063] Example 2 This embodiment provides a method for controlling the ambient temperature and humidity of a rocket fairing, which can preferably be implemented using the system described in Embodiment 1. Figure 3 As shown, the method includes the following steps: The S100 system secures a movable integrated platform to a load-bearing surface and docks the insulated chamber with the rocket fairing to be serviced, forming a closed, temperature-controlled space.

[0064] In this specification, the term "bearing surface" uniformly refers to the physical structure used to support and fix the movable integrated platform, including but not limited to the launch ship deck, the carrier base for the transfer launch vehicle, or a dedicated fixed base pre-installed on the deck. The fixing method between the movable integrated platform and the bearing surface includes at least one of mechanical locking, bolted connection, quick clamping, or hydraulic locking. In this embodiment, the bearing surface is the launch ship deck, or a dedicated fixed base installed on the launch ship deck, or the carrier base of the transfer launch vehicle 1 itself.

[0065] Specifically, after the transfer launch vehicle 1 is driven to the designated launch position on the deck of the launch ship, the hydraulic locking mechanism or mechanical clamping device on the transfer launch vehicle 1 is activated to rigidly connect and lock the frame of the transfer launch vehicle 1 to the bearing surface (i.e., the preset fixed base on the deck), ensuring that there is no relative displacement between the transfer launch vehicle 1 and the bearing surface under the condition of ship swaying. If the transfer launch vehicle is not used, the bearing unit (e.g., the steel structure base) of the insulated compartment 2 can also be directly fixed to the bearing surface (i.e., the deck base) with bolts or quick-locking pins.

[0066] The mobile integrated platform includes a thermal insulation chamber 2 and a temperature and humidity control device 4. The thermal insulation chamber 2 consists of two semi-conical sections, mounted on the left and right sides above the transport launch vehicle 1 via hinges or sliding rails. After the rocket is erected and positioned at the launch location, the operator (or automatically via an electric push rod) brings the two semi-conical sections together, aligning the front end of the thermal insulation chamber 2 with the outline of the rocket fairing. Mechanical locking devices (such as quick clamps or cam locking mechanisms) installed at the mating edges of the thermal insulation chamber 2 lock the two semi-conical sections together, while simultaneously compressing the annular sealing strip between the thermal insulation chamber 2 and the fairing to create an airtight contact, thus forming a closed, temperature-controlled space between the thermal insulation chamber 2 and the fairing. This temperature-controlled space is completely isolated from the external high-humidity, high-salt-spray marine environment, providing a sealed physical boundary for subsequent internal airflow.

[0067] This step ensures that subsequent airflow circulation will not introduce external polluted air, laying the foundation for maintaining a stable temperature and humidity environment inside the fairing.

[0068] S200, the temperature and humidity control device is activated, and the airflow is circulated within the temperature-controlled space through the airflow channel connected to the heat preservation chamber.

[0069] Specifically, after the insulated chamber 2 and the rectifier cover are docked to form a closed temperature-controlled space, the temperature and humidity control device 4 is activated. The centrifugal fan 48 inside the temperature and humidity control device 4 starts operating, generating negative pressure to draw air from the temperature-controlled space into the device via the return air duct 5. The drawn-in air first flows through the evaporator 412 (if cooling and dehumidification are required, the refrigeration cycle is activated, the air is cooled and condensate is released), the electric heater 43 (if heating is required, it is powered on to raise the temperature), and the humidifier 44 (if humidification is required, it sprays humidification), etc., and the temperature and humidity are adjusted accordingly according to control commands. The treated air is then sent back to the temperature-controlled space of the insulated chamber 2 via the inlet air duct 3. In this way, a closed circulation path is formed between the temperature-controlled space and the temperature and humidity control device 4. Throughout the entire circulation process, the air always flows in a closed loop consisting of the insulation chamber 2, the air inlet duct 3, the temperature and humidity control device 4, and the return air duct 5, without exchanging with the external ambient air, thus effectively isolating the high humidity and high salt spray environment from the outside from interfering with the temperature-controlled space.

[0070] The S300 uses a network of multi-node temperature and humidity sensors deployed at different locations within the insulated chamber to collect real-time three-dimensional temperature and humidity distribution data within the temperature-controlled space.

[0071] Specifically, each sensing unit in the multi-node temperature and humidity sensor network, evenly distributed circumferentially in the upper, middle, and lower parts of the insulated chamber 2, reads the temperature and humidity values ​​at its location in real time according to a preset sampling frequency. Data from all sensing units is transmitted to the central controller via shielded cables. After receiving data from all sensing units, the controller generates a three-dimensional data matrix based on the spatial coordinates of each sensor. This matrix comprehensively reflects the real-time temperature and humidity distribution at different axial and circumferential positions within the temperature-controlled space. This three-dimensional distribution data provides input parameters for subsequent adaptive control algorithms, enabling the controller to identify temperature gradients and humidity hotspots, thereby supporting differentiated zone control decisions.

[0072] S400, the three-dimensional temperature and humidity distribution data is sent to a controller, which runs an adaptive control algorithm to generate control commands based on the deviation between the preset target parameters and the three-dimensional temperature and humidity distribution data.

[0073] Specifically, the central controller receives three-dimensional temperature and humidity distribution data sent by a multi-node temperature and humidity sensor network and calls an internally preset adaptive control algorithm for processing. The core of this algorithm is to calculate the deviation between the current temperature and humidity state and the preset target parameters (such as the temperature setpoint and its allowable fluctuation range, the relative humidity setpoint and its allowable fluctuation range), and generate control commands based on the deviation to drive the various actuators of the temperature and humidity regulating device.

[0074] (I) Feedback control algorithm based on fuzzy PID In a preferred embodiment, the adaptive control algorithm is a fuzzy PID control algorithm, and the specific execution steps are as follows: Weighted averaging: The readings of all sensing units in the multi-node temperature and humidity sensor network are weighted and averaged to obtain the current average temperature and humidity. The weighting coefficients are set based on the fact that the payload is usually located in the upper part of the fairing, so sensors in the upper and middle parts are given higher weights, and sensors in the lower parts are given lower weights. For example, upper sensors can be given higher weights, middle sensors medium weights, and lower sensors lower weights (the specific weights can be adjusted according to the actual task through historical data fitting or on-site calibration).

[0075] Calculate the deviation and rate of change: Calculate the deviation *e* between the current average temperature and humidity and the preset target values, and the rate of change of the deviation *ec* = *de* / dt. Here, the sign of the deviation *e* indicates whether the current value is higher or lower than the preset target value, and the rate of change *ec* represents the trend of the deviation over time.

[0076] Fuzzy inference adjusts PID parameters: Using deviation e and the rate of change of deviation ec as the two input variables for fuzzy inference, the PID parameters (Kp, Ki, Kd) are dynamically adjusted through a pre-set fuzzy rule table in the controller (e.g., when |e| is large, increase the proportional coefficient Kp to improve response speed; when |e| is small, increase the integral coefficient Ki to eliminate steady-state error; when |ec| is large, increase the derivative coefficient Kd to suppress overshoot). The fuzzy rule table uses the Mamdani inference method, dividing the input variables e and ec into seven fuzzy subsets: "negative large, negative medium, negative small, zero, positive small, positive medium, and positive large." The output variables ΔKp, ΔKi, and ΔKd also use a similar fuzzy partitioning. The precise PID parameter adjustment is obtained by defuzzification (e.g., using the centroid method), and then superimposed with the initial values ​​to obtain the PID parameters at the current moment.

[0077] In this embodiment, increasing a certain PID parameter (e.g., proportional coefficient Kp, integral coefficient Ki, or derivative coefficient Kd) means adding a positive offset (incremental value) to the current value of the parameter, or multiplying it by a coefficient greater than 1 (proportional factor). This embodiment preferably uses the incremental value method because it is more intuitive and easier to be compatible with the numerical interface of the standard PID controller.

[0078] Specifically, the output variables ΔKp, ΔKi, and ΔKd of the fuzzy inference are defined as incremental values. The adjusted PID parameters are calculated according to the following formula: Kp new =Kp current +ΔKp; Ki new =Ki current +ΔKi; Kd new =Kd current +ΔKd.

[0079] Among them, Kp current Ki current Kd current The values ​​are the PID parameters at the current moment; ΔKp, ΔKi, and ΔKd are the incremental values ​​output by fuzzy inference based on the input variables (deviation e and rate of change of deviation ec); Kp new Ki new Kd new These are the adjusted PID parameter values, used for calculating the control input at the next time step.

[0080] When a fuzzy rule requires increasing Kp, the corresponding ΔKp is positive, and its specific value is determined by the membership function and rule table of the fuzzy inference. Similarly, decreasing ΔKp corresponds to a negative value, while keeping it unchanged results in ΔKp being 0.

[0081] The specific values ​​of ΔKp, ΔKi, and ΔKd are preset through offline optimization or expert experience and stored as a fuzzy rule lookup table.

[0082] Output control command: Based on the adjusted PID parameters, the control quantity is calculated, and the corresponding control command is generated. This control command controls the actuators of the temperature and humidity regulating device 4 through the drive circuit in the electrical control box 41, including but not limited to: the start and stop and frequency of the compressor, the opening degree of the electronic expansion valve, the heating power of the electric heater, the spray volume of the humidifier, and the speed of the centrifugal fan.

[0083] (II) Composite control scheme based on predictive models In another embodiment, the adaptive control algorithm further includes a predictive control module for generating feedforward control commands, which are then superimposed with the aforementioned fuzzy PID feedback control commands to form a feedforward-feedback composite control. The predictive control module is implemented as follows: Input parameters: The controller internally maintains a historical temperature and humidity data sequence for a time window (e.g., a period of time in the past, such as 30 minutes), and can also receive real-time meteorological parameters (e.g., ambient temperature, ambient humidity, solar radiation intensity, wind speed, etc.) collected by external environmental sensors, as well as the ship's sway acceleration detected by the inertial measurement unit (IMU) installed on the mobile integrated platform.

[0084] Predictive Model: The controller is pre-loaded with an autoregressive moving average (ARMA) model or an exponential smoothing model based on time series analysis. This model uses current and historical input parameters to predict the temperature and humidity trends over a future time period through linear regression or exponentially weighted moving average. Specifically, for temperature prediction, a first-order or second-order autoregressive model can be established: T(t+Δt)=a0+a1·T(t)+a2·T(t-Δt)+…+b1·S1(t)+b2·S2(t)+…. Where: T(t) is the temperature value at the current moment, T(t-Δt) is the temperature value at the previous moment; S1(t), S2(t),… are external influencing factors, including but not limited to ambient temperature, ambient humidity, solar radiation intensity, wind speed, ship rolling acceleration, etc.; a0, a1, a2,…, b1, b2… are the regression coefficients of the model, which are obtained offline by collecting historical operating data under typical marine environments and using regression algorithms such as least squares. For humidity prediction, a similar multiple linear regression model can be established, using historical humidity data and external factors as input, to output the predicted humidity value for future times.

[0085] Feedforward control command generation: The predicted temperature and humidity change trend is compared with the preset target parameters. If a deviation is predicted to occur in the future (e.g., the temperature is predicted to rise above the threshold), a feedforward compensation command is generated in advance. This command is then superimposed on the fuzzy PID feedback control command and output to the temperature and humidity control device to form a feedforward-feedback composite control.

[0086] In this invention, the preset target parameters refer to the desired environmental parameters that are pre-set and stored in the controller based on the temperature and humidity tolerance range of the payload (such as a satellite, optical equipment, etc.). These parameters include the target temperature value (e.g., 20°C) and its allowable fluctuation range (e.g., ±1°C), and the target relative humidity value (e.g., 40%RH) and its allowable fluctuation range (e.g., ±3%RH). During operation, the controller consistently aims to maintain the temperature and humidity of the temperature-controlled space within the preset target parameter range.

[0087] Feedforward compensation commands do not rely on current feedback deviations, but rather act in advance based on prediction results to offset or mitigate the impact of anticipated disturbances. For example, when it is predicted that the temperature will rise above a preset threshold in the future, the feedforward compensation command could be "start the compressor in advance" or "appropriately increase the fan speed," thereby intervening before the disturbance actually occurs and reducing control lag.

[0088] The superposition of the feedforward compensation command and the fuzzy PID feedback control command refers to: combining the control quantity corresponding to the feedforward compensation command (e.g., the incremental value Δf of the compressor frequency) with the control quantity corresponding to the feedforward compensation command. ff The incremental value of fan speed Δn ff The control quantity corresponding to the fuzzy PID feedback control command (e.g., the current required compressor frequency f) fb Fan speed n fb The values ​​are algebraically added together to obtain the final control command value, which is then output to the actuator of the temperature and humidity control device.

[0089] Specifically: For compressor frequency: f cmd =f fb +Δf ff ; For the fan speed: n cmd =n fb +Δn ff .

[0090] Among them, f fb and n fb Δf is calculated by the fuzzy PID algorithm based on the current deviation. ff and Δn ffThe value is generated by the predictive model based on future deviation trends (it can be positive or negative, representing increase or decrease, respectively). To prevent control commands from exceeding the physical limits of the actuator, the controller also includes amplitude limiting: if f cmd Exceeding the compressor's maximum permissible frequency f max Then f cmd Take f max If it is below the minimum frequency f min Then take f min The same applies to fan speed.

[0091] By using the above superposition method, feedforward control can pre-adjust the control quantity before the disturbance occurs, while feedback control is responsible for eliminating residual steady-state error. The two work together to achieve better control performance.

[0092] The specific parameters of the prediction model (such as order, coefficients, and smoothing constant) can be determined through offline training using historical data collected in typical marine environments, and then fine-tuned after on-site deployment. Because it uses a linear model rather than a black-box neural network, it has low computational cost, strong interpretability, and is easy to run in real-time on industrial PLCs.

[0093] (III) Issuance and execution of control commands Regardless of which algorithm is used, the adjustment commands ultimately generated by the controller are converted into specific electrical signals by the drive circuit within the electrical control box 41, controlling the corresponding actuators of the temperature and humidity regulating device 4. After responding to the command, the temperature and humidity of the delivered airflow change accordingly, thus affecting the environmental conditions within the temperature-controlled space. The newly acquired three-dimensional temperature and humidity distribution data is then fed back to the controller, forming a closed-loop control to ensure that the temperature and humidity always fluctuate around the preset target parameters.

[0094] S500, the temperature and humidity regulating device adjusts its own output according to the control command to realize closed-loop control of the temperature and humidity distribution in the temperature-controlled space.

[0095] Specifically, the adjustment commands generated by the central controller are converted into control signals for each actuator of the temperature and humidity control device 4 via the drive circuit within the electrical control box 41. Based on the received control signals, the temperature and humidity control device 4 dynamically adjusts its output parameters, including the cooling power of the compressor, the heating power of the electric heater, the humidification capacity of the humidifier, the airflow of the centrifugal fan, and the opening degree of each air valve. The adjusted airflow is then delivered into the temperature-controlled space of the insulation chamber 2 via the air inlet duct 3, changing the temperature and humidity distribution of that space. The multi-node temperature and humidity sensor network then collects the updated three-dimensional temperature and humidity distribution data again and transmits it back to the controller. The controller recalculates the deviation based on the new data and generates the next round of control commands. This cycle forms a closed-loop control link of "acquisition—decision—execution—reacquisition," ensuring that the temperature and humidity within the temperature-controlled space are always dynamically adjusted around the preset target parameters, thereby achieving continuous closed-loop control of the temperature and humidity distribution.

[0096] Furthermore, the method provided by the present invention also includes a zoned differential control step: when the multi-node sensor network identifies a temperature gradient or humidity hotspot area exceeding a preset threshold in the temperature control space, the controller performs zoned differential control based on the identified temperature gradient and humidity hotspot area.

[0097] Based on the aforementioned fuzzy PID control, if the system is configured with multi-branch air supply ducts, further differentiated control by zone can be achieved. Specifically: Hardware configuration: After entering the insulation chamber 2, the air inlet duct 3 is divided into at least two independent air supply branches by a distributor. Each branch extends to different areas within the temperature-controlled space (e.g., corresponding to the upper, middle, and lower parts of the shroud, respectively). Each air supply branch is equipped with an electrically adjustable damper and an airflow sensor to independently control the airflow of that branch.

[0098] Control Logic: The controller independently sets air supply parameters for each region based on the temperature gradient and humidity hotspots identified by the multi-node temperature and humidity sensor network. For example, if the humidity in the upper region is high while the humidity in the lower region is normal, the controller increases the opening of the electric regulating damper in the corresponding upper region's air supply branch while keeping the opening of the lower branch unchanged. This allows more dry, cool air to be delivered to the humidity hotspots without changing the total air supply volume, achieving on-demand distribution and precise control.

[0099] Furthermore, the method provided by the present invention also includes a remote telemetry and monitoring step: through a remote monitoring module integrated on a mobile integrated platform, the operating status, environmental parameters and fault alarm information of the mobile integrated platform and the temperature and humidity control device are uploaded to a remote command center via a wireless communication network such as 4G / 5G or Beidou message communication, and control commands issued by the remote command center, such as remotely modifying the target temperature and humidity parameters or performing an emergency shutdown, are received.

[0100] Furthermore, the method provided by this invention also includes a multi-energy redundant power supply step: configuring a multi-energy power supply architecture for the mobile integrated platform, the architecture including at least a ship power input interface and a battery pack input interface, and incorporating a built-in battery management system. The battery management system monitors the power status of the ship power input interface and the battery pack input interface in real time, and automatically selects the power supply path according to a preset priority (ship power takes precedence over battery). When a ship power interruption is detected, the battery management system automatically switches to backup battery pack power supply within a preset time, for example, 0.5 seconds, to ensure the continuous operation of the temperature control system.

[0101] Furthermore, the method provided by the present invention also includes an auxiliary temperature regulation step: when the rate of temperature change in the temperature-controlled space exceeds a preset threshold and the temperature and humidity regulating device has reached its maximum regulating capacity (i.e., it cannot further cool or heat), the auxiliary medium injection device connected to the airflow channel is controlled to release the auxiliary medium. The auxiliary medium injection device includes a storage tank, a control valve, and a delivery pipeline. One end of the delivery pipeline is connected to the control valve, and the other end is connected to the airflow channel. The control valve is electrically connected to the controller, which opens or closes it according to the detection result. In this embodiment, the auxiliary medium is liquid nitrogen for rapid cooling; in other embodiments, the auxiliary medium can also be a hot gas or hot fluid for rapid heating.

[0102] Example 3 This embodiment provides another rocket fairing environmental temperature and humidity control system, which differs from the previous embodiment in that: an inertial measurement unit is added, and the airflow disturbance caused by the hull sway is actively compensated by a preset swaying airflow coupling model.

[0103] The system in this embodiment includes the same mobile integrated platform, temperature and humidity control device, multi-node temperature and humidity sensor network, controller, and multi-energy power supply module as in Embodiment 1. The difference lies in the addition of the following components: Inertial Measurement Unit: A six-axis inertial measurement unit (IMU), such as an MPU6050 or an industrial-grade fiber optic gyroscope IMU, is installed on a mobile integrated platform (e.g., the chassis of the transport launch vehicle 1 or the base of the insulated cabin 2). This IMU can output the ship's acceleration, angular velocity, roll angle, pitch angle, bow angle, and sway frequency and phase in three axes in real time. The IMU's sampling frequency is higher than the control frequency to ensure timely capture of sway dynamics.

[0104] Feedforward perturbation model in the controller: A pre-built swaying airflow coupling model is incorporated into the controller. This model is established through offline CFD simulation or fitting of actual ship test data, establishing the transfer function between swaying parameters (amplitude, frequency, phase, direction) and airflow velocity perturbation and temperature gradient perturbation at specific locations within the temperature control space. For example, when the hull rolls at frequency f and amplitude A, the model can predict that an upward-directed induced airflow with a velocity of v will be generated in a certain region at the top of the fairing. This induced airflow will carry cold air upwards, causing the top temperature to decrease and the bottom temperature to increase. The model parameters are extracted from simulation or experimental data using system identification methods (such as least squares or subspace identification) and simplified into low-order linear difference equations.

[0105] Adjustable actuator: Same as in Embodiment 1, including a variable-speed centrifugal fan and an electrically adjustable damper (or an oscillating nozzle). The feedforward compensation command will adjust the fan speed or damper opening to generate an airflow compensation amount equal to the magnitude and opposite to the expected disturbance.

[0106] Example 4 This embodiment provides another method for controlling the ambient temperature and humidity of a rocket fairing. The method provided in this embodiment includes the following steps: S20, Deployment and docking: The docking steps are the same as in Example 2. The movable integrated platform is fixed and docked with the fairing to form a closed temperature-controlled space.

[0107] S21, Start the internal circulation airflow: The same as the start-up steps in Example 2, start the temperature and humidity control device to make the airflow circulate.

[0108] S22, Real-time detection of sway parameters: An inertial measurement unit (IMU) mounted on a movable integrated platform collects raw motion data of the hull in real time. This raw data includes three-axis acceleration, three-axis angular velocity, and attitude quaternions or Euler angles. After receiving the raw data, the controller performs noise reduction processing on the raw data using a well-known filtering algorithm (e.g., Kalman filtering) to obtain filtered acceleration and angular velocity data. The controller further calculates and derives parameters based on the filtered data, including roll angle, pitch angle, sway frequency, and sway phase. The filtered acceleration and angular velocity, along with the calculated roll angle, pitch angle, sway frequency, and sway phase, together constitute the sway parameters.

[0109] S23, Predicting Airflow Disturbances: The controller inputs the filtered sway parameters (i.e., the filtered acceleration, angular velocity, attitude angle, frequency, phase, etc.) into a preset sway airflow coupling model. Based on the current sway parameters and historical sway parameters (i.e., the sequence of sway parameters stored over a past time period, such as sway parameters over the past few seconds), the sway airflow coupling model predicts the development trend of airflow disturbances within the temperature-controlled space over a future time period (e.g., from a fraction of a second to several seconds), and outputs the expected predicted airflow disturbance value. The predicted airflow disturbance value includes the additional velocity field change and additional pressure field change caused by the sway, as well as the resulting airflow and direction compensation required for each air supply area.

[0110] S24, Generate Feedforward Compensation Command: The controller generates a feedforward compensation command in advance based on the predicted airflow disturbance value. For example, if the model predicts that an upward induced airflow will appear in the top region (this airflow will carry cold air upwards, causing overheating at the bottom), the controller will reduce the opening of the electric damper in the top air supply branch in advance (reducing upward airflow), while increasing the opening of the bottom air supply branch or increasing the total speed of the centrifugal fan to generate a downward compensating airflow. This feedforward compensation command is algebraically superimposed with the feedback control command based on temperature and humidity deviation in Embodiment 2 to jointly drive the actuator.

[0111] S25, Execution and Adaptive Adjustment: The temperature and humidity control device and the air valve / nozzle execute the superimposed commands. The system simultaneously monitors the actual temperature changes fed back by the temperature and humidity sensors and compares them with the predicted results. The controller uses an online recursive least squares method or Kalman filter algorithm to continuously update the parameters of the sloshing airflow coupling model to adapt to changes in different sea states and load conditions.

[0112] Examples three and four utilize an inertial measurement unit to detect hull rolling in real time and employ a pre-set rolling-airflow coupling model to predict airflow disturbances caused by the rolling. This generates feedforward compensation commands, proactively adjusting the air supply system before the disturbances actually affect temperature and humidity, effectively suppressing temperature and humidity fluctuations caused by hull rolling. Compared to simple feedback control, this embodiment exhibits less control lag and stronger disturbance resistance, making it particularly suitable for sea launch missions in sea states 3-5. Furthermore, the online adaptive learning mechanism enables the system to adapt to different sea states and load variations, demonstrating high robustness.

[0113] 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 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.

[0114] 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 controlling the ambient temperature and humidity of a rocket fairing, characterized in that, The method includes the following steps: A movable integrated platform is fixed to a bearing surface, the movable integrated platform including an insulated chamber and a temperature and humidity control device; the insulated chamber is docked with the rocket fairing to be serviced to form a closed temperature-controlled space. The temperature and humidity control device is activated, and the airflow is circulated within the temperature-controlled space through the airflow channel connected to the heat preservation chamber. A network of multi-node temperature and humidity sensors deployed at different locations within the insulated chamber is used to collect real-time three-dimensional temperature and humidity distribution data within the temperature-controlled space. The three-dimensional temperature and humidity distribution data is sent to a controller, which runs an adaptive control algorithm to generate control commands based on the deviation between the preset target parameters and the three-dimensional temperature and humidity distribution data. The temperature and humidity regulating device adjusts its output according to the control command to achieve closed-loop control of the temperature and humidity distribution within the temperature-controlled space.

2. The method according to claim 1, characterized in that, The adaptive control algorithm is a fuzzy PID control algorithm; The fuzzy PID control algorithm includes: The readings of the multi-node temperature and humidity sensor network are weighted and averaged to obtain the current average temperature and humidity. Calculate the deviation between the current average temperature and humidity and the target values, as well as the rate of change of the deviation; The deviation and the rate of change of the deviation are used as inputs for fuzzy inference, and the PID parameters are dynamically adjusted through fuzzy inference. The control command is generated based on the adjusted PID parameters.

3. The method according to claim 1, characterized in that, The multi-node temperature and humidity sensor network is arranged in layers along the axial and radial directions of the insulation chamber. The multi-node temperature and humidity sensor network includes multiple sensing units for identifying temperature gradients and humidity hotspots within the temperature-controlled space. The controller performs zoned differentiated control based on the identified temperature gradients and humidity hotspots.

4. The method according to claim 1, characterized in that, It also includes a multi-energy redundant power supply step: configuring a multi-energy power supply architecture for the mobile integrated platform, the multi-energy power supply architecture including at least a ship power input interface and a battery pack input interface, and having a built-in battery management system; the power status of the ship power input interface and the battery pack input interface is monitored in real time through the battery management system, and automatically switched to backup battery pack power supply when the main power is interrupted.

5. The method according to claim 1, characterized in that, It also includes an auxiliary temperature regulation step: when the temperature change rate of the temperature-controlled space exceeds a preset threshold and the temperature and humidity regulation device has reached its maximum regulation capacity, the auxiliary medium injection device connected to the airflow channel is controlled to release the auxiliary medium.

6. The method according to claim 1, characterized in that, The thermal insulation chamber has a modular structure, and its interior is filled with an insulation layer. The external dimensions of the insulation layer are adapted to the rocket fairing to be serviced. The bottom of the mobile integrated platform is equipped with a connection mechanism for fixing to the transport launch vehicle or launch ship deck.

7. The method according to claim 1, characterized in that, It also includes a predictive control step: using a predictive model pre-installed in the controller to predict the temperature and humidity change trend of the temperature-controlled space in the future time period, the predictive model being trained based on historical environmental data and weather forecast data; the controller generating a feedforward control command based on the output of the predictive model, and superimposing the feedforward control command with the feedback control command generated by the adaptive control algorithm and outputting it to the temperature and humidity regulating device.

8. The method according to claim 1, characterized in that, It also includes an anti-sway feedforward compensation step: an inertial measurement unit is installed on the movable integrated platform to detect the hull sway parameters in real time; the hull sway parameters are input into the sway airflow coupling model built into the controller, and the expected airflow disturbance prediction value is output; the controller adjusts the air volume or airflow direction of the temperature and humidity control device in advance before the temperature fluctuation caused by sway occurs, based on the disturbance prediction value.

9. A rocket fairing environmental temperature and humidity control system for implementing the method of any one of claims 1-8, characterized in that, include: A mobile integrated platform includes a support unit and an insulated cabin fixed to the support unit. The insulated cabin is used to dock with the rocket fairing to be serviced to form a closed temperature-controlled space. The temperature and humidity control device is connected to the heat preservation chamber through an airflow channel, forming a circulating airflow loop; A multi-node temperature and humidity sensor network is deployed in different spatial locations within the insulated chamber to collect three-dimensional temperature and humidity distribution data. The controller is connected to the sensor network and the temperature and humidity control device, and runs an adaptive control algorithm to dynamically control the operation of the temperature and humidity control device.

Images