High altitude release system and method of operation thereof

Abstract

The application discloses a high-altitude launching system and a working method thereof, and belongs to the technical field of high-altitude launching and aerostation platform application, and aims to solve the problems of controllability and safety in the process of high-altitude ball launching. The application scheme comprises a rising platform, a launching separation control cabin and a recovery assembly, the rising platform is provided with an aerostation balloon, a positioning measurement unit and a balloon controllable treatment assembly for terminating balloon drift; the launching separation control cabin is connected with the task load assembly and the rising platform through a hanging connection structure with a primary separator and a secondary separator, and is internally provided with a positioning communication assembly and a control unit; wherein, the control unit combines health state information as a launching criterion related parameter to complete determination, and triggers an abnormal control strategy or a load separation strategy according to the determination result. The application realizes intelligent determination and controllable execution of high-altitude launching, and improves the safety and reliability of the launching process.

Description

Technical Field

[0001] This invention belongs to the field of high-altitude delivery and floating platform application technology, and specifically relates to a high-altitude delivery system and its working method. Background Technology

[0002] In recent years, to meet the needs of reconnaissance and surveillance, emergency communication relay, disaster relief, and environmental monitoring, high-altitude delivery / airborne deployment technologies have received widespread attention due to the demands for "rapid deployment, long-distance access, and low-cost delivery." Explain this by analogy: traditional fixed-wing or rotary-wing UAVs mostly rely on runway takeoff and landing, vehicle-mounted catapults, or runway takeoffs, which are limited by site conditions, airspace applications, ground wind fields, and support resources. In environments such as high altitudes, deserts, and islands, the organization of ground launches and recoveries becomes significantly more difficult and risky. In contrast, high-altitude helium balloons, as an ascent platform, have advantages such as low cost, simple equipment, and flexible deployment. They can raise the mission payload to a predetermined altitude before delivery. Furthermore, combined with ground station remote control, positioning links, and parachute recovery, a closed loop of "launch, delivery, and recovery" can be achieved to a certain extent. However, high-altitude balloon platforms exhibit significant wind drift characteristics. During takeoff and drift, issues such as deviations from the preset flight path and difficulty in accurately predicting the landing point of the mission payload are inevitable. In particular, if the balloon and pod (control module) continue to drift with the wind after deployment, they may cross safety barriers or enter no-fly / residential areas, posing safety hazards such as falling and injuring people or entanglement in power and communication facilities. If deployment conditions are not met or the mission is aborted, how to safely recover the payload and avoid resource waste during the high-altitude phase has also become a key challenge for engineering applications.

[0003] Currently, the industry has proposed solutions from two directions: "drone aerial delivery" and "high-altitude balloon self-destruction / recovery". However, these solutions are still insufficient to cover the system-level safety requirements of high-altitude delivery systems for "controllable delivery, balloon disposal, cabin recovery and abnormal redundancy".

[0004] For example, Chinese invention patent application CN119611839A discloses an aerial deployment system for a large-wingspan, curled-wing UAV. The technical concept involves mounting the UAV onto a deployment vehicle while its wings are curled, using a rope restraint system and a rope cutter to cascade the restraints, and releasing the UAV into autonomous flight after its attitude stabilizes, thereby improving the aerial deployment efficiency of large-wingspan UAVs. While this technical solution provides a relatively complete deployment control logic and constraint / cutting structure design for "how the UAV unties, unfolds, levels itself, and enters stable flight in the air," its focus is on the deployment and unfolding of the UAV itself. It does not adequately address system integrity issues such as balloon handling (e.g., controlled self-destruction / release) in scenarios involving "launching using a high-altitude helium balloon pod," pod recovery and reuse, and cascaded protection and recovery of the payload and pod in abnormal deployment conditions. Therefore, it is difficult to directly solve the safety risks caused by platform and control cabin drift after deployment and the safe recovery of aborted missions.

[0005] For example, Chinese invention patent application CN119551175A discloses a high-altitude balloon self-destruct device and a high-altitude balloon system. The system includes components such as a balloon, a parachute, a traction rope, and a self-destruct device. It achieves the self-destruction / disposal of the balloon through a specific structure, thereby serving the safe recovery or termination after the high-altitude balloon mission ends. This technical solution can improve the safety of the high-altitude balloon mission's end phase, but it mainly focuses on the balloon platform's own disposal and landing system. It does not address the two-stage (or multi-stage) separation sequence, pre-deployment deceleration / protection, and coordinated control issues of "successful deployment, platform self-destruction, and pod recovery" required for the "controllable deployment of UAV payloads under the pod." Especially in engineering practice, the deployment system often needs to make judgments based on multiple conditions such as altitude, position, ascent time, and communication status within a limited airspace, and switch to manual / automatic emergency strategies in abnormal situations. The balloon's self-destruct capability alone is not enough to constitute a complete high-altitude deployment safety closed loop.

[0006] Furthermore, Chinese invention patent application CN113844635A discloses a high-altitude balloon mission payload recovery device and its recovery method, focusing on the buffer protection and recovery process design of the mission payload (including the cabin) during descent and landing, which can improve the reliability of payload landing and the feasibility of recovery. Similar patents, such as Chinese invention patent application CN103630921A, disclose a device for high-altitude balloon payload recovery and positioning, which proposes improvements from the perspective of recovery and positioning, and improves the positioning and search efficiency of the payload after landing through satellite communication terminals and structural design. The above-mentioned recovery or positioning technologies mostly emphasize "landing recovery after the mission ends", and lack a system-level solution that is deeply coupled with the release control for "controllable separation of the payload within the high-altitude release window, safe abort of recovery when release conditions are not met, and safe handling of the balloon and control cabin after release (avoiding continuous drift)". Summary of the Invention

[0007] The purpose of this invention is to provide a high-altitude delivery system and its operating method to address the safety and system integrity deficiencies in existing technologies for delivering drones or mission payloads using high-altitude helium balloons with attached pods. Specifically, the technical solution disclosed in this invention is a complete high-altitude delivery system with features such as delivery window determination, tiered and controllable separation, controllable balloon self-destruction, trackable pod recovery, and anomaly redundancy emergency strategies. This system enables reliable deployment of mission payloads, safe disposal of the launch platform, and equipment reuse.

[0008] To achieve the above objectives, the present invention adopts the following technical solution: In a first aspect, the present invention provides a high-altitude delivery system, comprising: an launch platform, a delivery and separation control cabin, and a recovery assembly; wherein, The launch platform includes: a floating balloon, a positioning and measurement unit, and a balloon controllable disposal component; wherein, the balloon controllable disposal component is used to terminate the continuous drift of the floating balloon; The launch and separation control cabin is equipped with a first sling connection structure for connecting to the mission payload assembly and a second sling connection structure for connecting to the launch platform; wherein, the first sling connection structure is equipped with a primary separator and the second sling connection structure is equipped with a secondary separator; The recovery assembly is used to recover one or both of the launch separation control cabin and the mission payload assembly; The deployment separation control cabin is further equipped with a positioning and communication component and a control unit. The positioning and communication component acquires data output from the positioning measurement unit and transmits it to the control unit. The control unit uses the acquired health status information and the data transmitted by the positioning and communication component as deployment criteria parameters to determine the deployment result. If the determination result indicates that the deployment criteria parameters do not meet the requirements, an abnormal control strategy is triggered to achieve overall or tiered recovery of the deployment separation control cabin and the mission payload component. If the determination result indicates that the deployment criteria parameters meet the requirements, a payload separation strategy is triggered to achieve controllable deployment of the mission payload component and slow descent recovery of the deployment separation control cabin.

[0009] A further improvement to the technical solution of the present invention is that the controllable balloon handling component includes: an actuator and a triggering circuit; wherein, The triggering circuit is electrically connected to the control unit and is used to receive the disposal command sent by the control unit and trigger the actuator according to the disposal command; The actuator is a controllable venting mechanism, which is used to open the venting channel to release the gas inside the air balloon when triggered by the triggering circuit; or, the actuator is a controllable destructive venting mechanism, which is used to create a rupture in the skin of the air balloon to cause a loss of lift when triggered by the triggering circuit.

[0010] A further improvement of the technical solution of the present invention is that the controllable balloon disposal component, the first-stage separator, and the second-stage separator all adopt a dual-redundant configuration, which consists of two independent triggering circuits and two independent execution terminals.

[0011] A further improvement of the technical solution of the present invention is that the execution steps of the load separation strategy include: The separation of the mission payload assembly from the launch and separation control cabin is achieved by controlling the operation of the first-stage separator; After controlling the first-stage separator to act, the second-stage separator is controlled to act after a delay to separate the release and separation control cabin from the launch platform, and the balloon controllable disposal component is triggered simultaneously to terminate the continuous drift of the floating balloon. The recovery assembly enables the slow descent and recovery of the deployment separation control cabin.

[0012] A further improvement to the technical solution of the present invention is that, in the control unit, the steps of using the acquired health status information and the data transmitted by the positioning communication component as relevant parameters for deployment criteria to obtain the determination result specifically include: The determination is made based on altitude, location, time, and health criteria to obtain the determination result. Among them, the height criterion is reaching the target delivery height or the target height range; the position criterion is being within the safety fence range and the drift prediction landing point does not cross the boundary; the time criterion is that the ascent time does not exceed the preset threshold; and the health criterion is that the communication link heartbeat is normal and the high-altitude delivery system self-test is normal. When all or a preset combination of criteria are met, the judgment result is that the relevant parameters of the delivery criteria meet the requirements; otherwise, the judgment result is that the relevant parameters of the delivery criteria do not meet the requirements.

[0013] A further improvement of the technical solution of the present invention is that the anomaly control strategy includes one or more of the following: overall recovery strategy, deployment before disposal strategy, timeout or loss of contact disposal strategy, and separation failure retry strategy. The overall recovery strategy involves controlling only the secondary separator to perform secondary separation, and then using the recovery component to achieve a smooth descent and recovery of the deployment separation control module and the mission payload module. The "deploy first, then handle" strategy involves controlling the primary separator to perform primary separation and deploy the mission payload module when the risk of location exceeding the boundary is below a set threshold and the mission payload module is ready, followed by controlling the secondary separator to perform secondary separation and triggering the balloon's controllable disposal mechanism. The recovery component then enables a smooth descent and recovery of the deployment separation control module. The timeout or communication loss handling strategy involves controlling the secondary separator to perform secondary separation and using the recovery component to achieve a smooth descent and recovery of the deployment separation control module when the set requirements are met. The separation failure retry strategy involves retrying the system a preset number of times and at preset intervals when primary or secondary separation is detected as unsuccessful. Once the number of failures reaches a set threshold, the strategy switches to either the overall recovery strategy or a backup strategy that triggers the balloon's controllable disposal mechanism.

[0014] A further improvement of the technical solution of the present invention is that the target priority configuration of the anomaly control strategy is one or more combinations of balloon disposal priority, normal payload separation priority, abnormal payload recovery priority and control cabin recovery priority.

[0015] A further improvement to the technical solution of the present invention is that it also includes: a load protection chamber and a deceleration parachute system; The payload protection chamber is used to cover the mission payload components and provide shock and low temperature protection during the ascent phase; the deceleration parachute system is used to trigger after the first-stage separator performs the first-stage separation, so that the mission payload components enter a deceleration and stable descent state.

[0016] A further improvement of the technical solution of the present invention is that the load protection cabin is provided with a secondary release mechanism, which is used to release the mission load component when the load protection cabin descends to a preset height window.

[0017] In a second aspect, the present invention provides a method for operating a high-altitude delivery system, comprising the following steps: The air balloon in the launch platform carries the launch separation control cabin and mission payload components into the air. The positioning measurement unit acquires and outputs the relevant setting data of the air balloon in real time. The positioning communication component receives the data output by the positioning measurement unit and transmits it to the control unit of the launch separation control cabin. The control unit uses the acquired health status information and data transmitted by the positioning and communication components as parameters related to the deployment criteria to determine the deployment and obtain a determination result. If the determination result indicates that the parameters related to the deployment criteria do not meet the requirements, an abnormal control strategy is triggered to achieve the overall recovery or staged recovery of the deployment separation control cabin and the mission payload component. If the determination result indicates that the parameters related to the deployment criteria meet the requirements, a payload separation strategy is triggered to achieve the controllable deployment of the mission payload component and the slow descent recovery of the deployment separation control cabin.

[0018] Compared with the prior art, the present invention has the following beneficial effects: This invention discloses a high-altitude delivery system. If the parameters related to the delivery criteria are not met, an abnormal control strategy is triggered. The control unit then controls the primary and secondary separators and the recovery assembly to achieve overall or staged recovery of the delivery separation control cabin and the mission payload assembly. If the delivery criteria are met, a payload separation strategy is triggered. The control unit controls the primary and secondary separators to operate sequentially according to a preset time sequence, achieving controllable delivery of the mission payload assembly. Simultaneously, the controllable disposal component of the balloon is controlled to terminate the drift of the aerosol balloon, and the recovery assembly enables the slow descent and recovery of the delivery separation control cabin. This invention enables reliable deployment of mission payloads, safe disposal of the launch platform, and reuse of equipment.

[0019] Specifically, in the technical solution of this invention, relevant information (exemplarily, including the position, air pressure, altitude, and environmental parameters of the air balloon) is obtained through the positioning and measurement unit in the launch platform. This information is then transmitted to the control unit via the positioning and communication component of the launch separation control cabin. The control unit uses this parameter data, along with one or more parameters related to communication and system health status, as launch criteria to determine the launch window. This forms a scientific basis for launch decisions from a data perspective, solving the problems of traditional technologies lacking clear launch criteria, being prone to mislaunches, and launching beyond designated areas. It achieves accurate determination of launch timing and launch area, significantly improving the controllability of payload launch, ensuring that the payload is launched within a preset safe airspace, and effectively predicting the launch landing point. In this invention, a two-stage separator is installed to achieve graded separation between the launch separation control cabin and the mission payload components, and between the launch platform and the launch separation control cabin, respectively. The control unit triggers the separator action according to preset logic based on the judgment result. This solves the problems of existing technologies lacking graded separation design, where the handling action and payload release are prone to mutual interference, leading to attitude impact and launch failure. It ensures that the payload completes safe separation and enters a stable state before the platform and control cabin separation action is performed, avoiding link chaos and equipment damage, and significantly improving the success rate of payload launch and the safety margin of system operation. This invention also incorporates a controllable balloon handling component on the launch platform. Triggered according to the launch process or abnormal situations, it terminates the continuous drift of the aerosol balloon, solving the safety problems of traditional technologies such as balloons and pods drifting with the wind after launch, easily entering no-fly zones / residential areas, causing falls and injuries, and entanglement with facilities. It achieves proactive and controllable handling of the launch platform, eliminating various safety hazards caused by platform drift after launch from the source, and ensuring the safety of airspace and ground personnel and assets. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the structure of a high-altitude delivery system in an embodiment of the present invention; Figure 1 The explanations of the reference numerals in the attached figures are as follows: 1. Buoyancy balloon; 2. Bursting chamber device; 3. Bursting chamber communication cable; 4. Positioning and measurement unit; 5. First protective umbrella; 6. Suspended basket; 7. First-stage separator; 8. Mission load; 9. Ball rope; 10. Second protective umbrella; 11. Second-stage separator; 12. Suspension rope. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention; obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0023] Based on the technical solutions disclosed in the embodiments of this invention, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this invention. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to these processes, methods, products, or devices.

[0024] The high-altitude delivery system provided in this embodiment of the invention mainly includes the following components: An airlift platform, comprising: an air balloon, a positioning and measurement unit, and a balloon controllable disposal component; wherein, the air balloon is used to provide buoyancy; the positioning and measurement unit is used to acquire and output the position, air pressure altitude, and environmental parameters of the air balloon; the balloon controllable disposal component is used to terminate the continuous drift of the air balloon after deployment or in abnormal circumstances; The deployment and separation control cabin is equipped with a first sling connection structure for connecting to the mission payload assembly and a second sling connection structure for connecting to the launch platform. The first sling connection structure includes a primary separator for separating the deployment and separation control cabin from the mission payload assembly. The second sling connection structure includes a secondary separator for separating the launch platform from the deployment and separation control cabin. In a specific exemplary technical solution, the mission payload assembly may include a UAV or other mission payloads. Furthermore, both the first and second sling connection structures can be constructed using high-strength ropes, cables, or metal connectors, with a load-bearing safety margin meeting a preset multiple of the load weight. Additionally, the connection structure may be equipped with guide limits and anti-torsion structures to reduce the risk of swaying and entanglement during ascent, and to ensure a clear force path and reliable cutting or release actions when the separator operates. A recovery component is used to recover the launch separation control cabin and / or the mission payload component; The deployment and separation control cabin is equipped with a positioning and communication component, a control unit, and a power supply unit. The power supply unit provides power to the positioning and communication component and the control unit. The positioning and communication component acquires parameter data output by the positioning measurement unit and transmits it to the control unit. The control unit uses the parameter data transmitted by the positioning and communication component and the health status of the communication link as deployment criteria parameters and makes a determination. If the determination result indicates that the deployment criteria parameters do not meet the requirements, an abnormal control strategy is triggered, and one or both of the deployment and separation control cabin and the mission payload component are recovered through the balloon controllable disposal component, the first-stage separator, the second-stage separator, and the recovery component. If the determination result indicates that the deployment criteria are met, a payload separation strategy is triggered, and the mission payload component is deployed and the deployment and separation control cabin are recovered through the balloon controllable disposal component, the first-stage separator, the second-stage separator, and the recovery component.

[0025] This invention discloses a high-altitude delivery system, which constructs an integrated system architecture that integrates delivery window determination, graded and controllable separation, controllable self-destruction of balloons, trackable recovery of pods, and emergency strategies for abnormal redundancy. It solves the technical problems existing in the current high-altitude balloon delivery technology, such as uncontrollable delivery landing point, safety hazards caused by balloon drift, inability to safely recover the payload in abnormal situations, and insufficient overall system safety and integrity. It forms a closed-loop control of the entire process of "determination, delivery, disposal, recovery, and emergency response", and achieves significant improvements in delivery controllability, system safety, and equipment reusability. It can effectively avoid safety risks such as boundary crossing and falling. In the technical solution of this invention, when the control unit determines that the relevant parameters of the deployment criteria do not meet the requirements, it triggers the execution of an abnormal control strategy. Through the linkage of the two-stage separator and the recovery component, the deployment separation control cabin and the mission payload component are recovered in an overall or hierarchical manner. This solves the problem that existing technologies lack targeted emergency response plans in abnormal situations such as location out-of-bounds, communication abnormalities, and altitude failures, which can easily lead to deployment failures or safety accidents. It achieves full coverage of emergency backup for various abnormal working conditions, converging the deployment risk to a predictable landing area. This effectively avoids safety accidents, minimizes equipment losses, and ensures the safe operation of the system under complex working conditions.

[0026] Specifically, in the technical solutions of this invention, the deployment window determination strategy solves the problems of blind deployment decisions and uncontrollable landing points, achieving precise and controllable deployment results; the hierarchical controllable separation strategy solves the problems of mutual interference between deployment and platform handling actions and low deployment success rates, achieving stable and reliable payload deployment results; the balloon controllable self-destruction strategy solves the safety hazards of continuous balloon drift and easy boundary crossing / falling after deployment, achieving the technical effect of eliminating platform drift risks and ensuring airspace safety; the pod trackable recovery strategy solves the problems of untrackable control cabin / payload landing points and inability to recover and reuse equipment, achieving the technical effect of equipment recovery, reuse, and reduced usage costs; and the abnormal redundancy emergency strategy solves the technical problems of no effective handling means and inability to converge risks under abnormal operating conditions, achieving the technical effect of full-scenario safety protection and minimizing losses.

[0027] In this embodiment of the invention, the aerosol balloon can be a high-altitude helium balloon or other lightweight gas balloon. The aerosol balloon is connected to the deployment and separation control cabin via a balloon rope and a suspension rope. The balloon rope is equipped with bursting capsule devices as a controllable disposal component for the balloon. The number of bursting capsule devices can be set according to the specifications of the aerosol balloon and the reliability requirements of disposal. Each bursting capsule device is electrically connected to the control unit via a bursting capsule communication cable to achieve bidirectional transmission of control commands. The suspension rope is equipped with a positioning and measurement unit, specifically including a GNSS positioning module and / or a radiosonde positioning module, for real-time output of the balloon's position, pressure altitude, and environmental parameters. A secondary separator is also provided on the suspension rope.

[0028] In this embodiment of the invention, the launch platform is not limited to a high-altitude helium balloon; it can also be a hydrogen balloon, a hot air balloon, a tethered balloon, or other floating platforms. Provided that the load capacity and target height are met, the balloon material can be replaced by a composite membrane balloon instead of a latex balloon, or a combination of a latex balloon and an auxiliary dome can be used.

[0029] In a further preferred embodiment, the controllable balloon disposal component includes a controllable release mechanism and / or a controllable destructive deflation mechanism and its triggering circuit; the controllable release mechanism allows the gas inside the balloon to be quickly discharged by opening the release channel, and the controllable destructive deflation mechanism causes a loss of lift by quickly rupturing the balloon skin; the triggering circuit is electrically connected to the execution control board and executes the balloon disposal action after receiving the disposal command.

[0030] In a further preferred technical solution, the controllable balloon disposal component adopts dual-path trigger redundancy, including two independent trigger circuits and two independent execution terminals, and the two execution terminals are arranged at key positions on the balloon to improve the disposal success rate; when either path is successfully triggered, the balloon loss of ascent can be disposed of, thereby avoiding the risk of the balloon and platform drifting in the wind after deployment and causing the risk of crossing the boundary or falling.

[0031] In this embodiment of the invention, the power supply unit is a low-temperature resistant battery pack used to power the various components inside the launch and separation control cabin; the positioning and communication component is used to acquire launch criterion-related parameters such as altitude, position, and communication link health status, and to establish two-way communication with the ground command and control component; the control unit includes a control calculation unit and an execution control unit, the control calculation unit is used to make launch decisions based on the launch criterion-related parameters, and the execution control unit is used to output trigger signals to the various levels of separators and the balloon controllable disposal component; the data recording module is used to record key parameters throughout the launch process.

[0032] Specifically, the deployment and separation control cabin is a gondola, which includes a cabin structure, load-bearing attachment points, a flight / mission control computer, a cryogenic battery pack, an execution control board, a communication and data transmission module, a positioning module, and a data recording module. The cabin structure provides a windproof, cryogenic, and impact-resistant installation environment for the internal equipment. The load-bearing attachment points form a load-bearing path with the first and second suspension connection structures. The execution control board outputs trigger signals to the separation execution components (first-stage and second-stage separators) and the balloon controllable disposal component. The data recording module records altitude, position, speed, attitude, power supply status, and key action timestamps for verification and traceability of experimental criteria. The ground terminal receives data from the positioning and measurement unit via a matching receiving device and inputs the data into the ground command and control component for trajectory prediction and deployment point verification. The control unit is used to control the separation execution component to complete at least one level of payload separation action based on deployment criteria such as altitude, location, time and health status. Under the conditions of successful deployment or abnormal triggering, it controls the controllable disposal component and recovery component of the air balloon to achieve safe disposal of the launch platform and safe recovery of the control cabin / payload, thus forming a closed-loop system of "controllable deployment, controllable disposal and redundant recovery".

[0033] In a specific exemplary technical solution, the primary separator and the secondary separator are independently controlled by the execution control board, and they have a preset timing relationship to ensure the completion of the system action closed loop under the strategy of safe departure of the mission load first and safe disposal of the platform later. Specifically, the primary separator and / or the secondary separator adopt a structure of cutting the load-bearing rope / cable, or a structure of releasing the lock / disconnecting the locking pin; when the cutting method is used, the separator cuts the load-bearing rope or load-bearing connector to achieve separation; when the release method is used, the separator releases the restraint mechanism to release the load-bearing connection; the above separation methods can be used individually or in combination to adapt to different load-bearing weights, different ambient temperatures, and different reliability requirements. Furthermore, the separators at each level can adopt pyrotechnic rope cutting, or methods such as electrothermal cutting, mechanical blade cutting, explosive bolt disconnection, release lock / unlocking buckle, and shearing pin disconnection; the separation object can be replaced by cutting the polyethylene rope with cutting the steel cable, webbing, or releasing the ferrule / hook connection, specifically selected according to the load-bearing and reliability requirements.

[0034] In the preferred technical solution, the primary separator and / or the secondary separator adopt a dual-redundant configuration, forming two parallel separation channels or two independent separation actuators. The execution control board triggers the two redundant separation channels simultaneously or sequentially, and determines the separation result through current / voltage detection, limit signals, tension changes, attitude / acceleration abrupt changes, or load-side feedback confirmation, thereby reducing the risk of deployment failure due to single-point failure. Dual redundancy can be achieved by having two separators connected in parallel acting on the same load-bearing path, or by having two independent load-bearing paths controlled by independent separators. Trigger redundancy can be achieved by dual-circuit ignition / dual power supply / dual command links (main data transmission combined with backup links), and the redundancy level can be increased or decreased according to the mission risk level.

[0035] In this embodiment of the invention, the power supply unit for the deployment and separation control cabin is a low-temperature resistant battery pack, which, together with the insulation structure and power management module, ensures that it can still provide stable power to the control unit, communication module, and actuators in low-temperature environments. The execution control board can be equipped with action interlocking and anti-mistriggering mechanisms, including at least one or more of the following: power-on self-test, unlock authorization, secondary confirmation, and post-action status readback, to prevent unexpected separation caused by ground misoperation or electromagnetic interference. The system supports two workflows: pre-test and formal test. The pre-test is used to verify the balloon disposal, separation, and recovery link; the formal test is used to verify the UAV deployment and return recovery. The two workflows can reuse the same system hardware, and the deployment sequence, parachute type selection, and trigger threshold can be switched through ground station parameter configuration, thereby reducing development costs and improving verification efficiency. This invention can also be extended to a multi-payload delivery system, where multiple payload attachment points and multiple first-stage separators are connected in series below the first sling connection structure to achieve multiple deliveries based on time or altitude. It can also be extended to airdrop applications on different platforms, including airborne, missile-borne, rocket-borne, submarine-borne, or ball-borne delivery, requiring only equivalent replacements and adaptations in the launch platform and delivery criteria parameters. Through the above structure and control logic, this invention integrates "controllable delivery, controllable platform handling, recoverable pod, and fallback mechanism" into a unified system under the unavoidable objective condition of high-altitude drift, thereby improving the safety, reliability, and reusability of high-altitude delivery missions.

[0036] In this embodiment of the invention, the positioning and communication component includes at least one or more of a primary positioning module, a backup positioning module, and a search and rescue beacon. The primary positioning module outputs position and altitude throughout the flight / deployment process, while the backup positioning module provides compensatory positioning when the primary positioning fails. The search and rescue beacon continuously transmits positioning / identification signals after landing to assist ground search and rescue vehicles in quickly reaching the landing point for recovery. In a further preferred embodiment, the ground command and control component includes ground station software and a human-machine interface for displaying altitude, position, vertical velocity, system health status, action status, and alarm information, and supports mode switching. The modes include an automatic deployment mode and a manual deployment mode: in automatic deployment mode, the system automatically executes the deployment sequence based on deployment criteria; in manual deployment mode, the operator can issue separation and disposal commands based on the information displayed on the ground station to form a backup emergency control capability.

[0037] The technical solution of this invention achieves full-process positioning and tracking of the deployment and separation control cabin through a positioning measurement unit and a positioning communication component. It works in conjunction with a recovery component to complete the recovery of the control cabin and / or mission payload components. This solves the problems of difficulty in tracking and recovery of the cabin / payload after deployment, which leads to waste of equipment resources in the prior art. It achieves accurate tracking and slow descent recovery of core equipment such as the deployment and separation control cabin, greatly improves the reuse rate of equipment, and reduces the equipment investment and usage costs of high-altitude deployment missions.

[0038] In this embodiment of the invention, the deployment criteria include at least: height criteria, location criteria, time criteria, and communication health criteria; wherein, the height criteria is reaching the target deployment height or target height range, the location criteria is being within the safety fence range and the drift prediction landing point does not cross the boundary, the time criteria is the rise time not exceeding a preset threshold, and the communication health criteria are that the main link heartbeat is normal and the key power supply voltage and the actuator self-test results meet the requirements; when all or a preset combination of criteria are met, first-level separation is allowed; when any key criterion is not met, the system enters an abnormal strategy.

[0039] In a further preferred technical solution, the anomaly strategy includes at least one of the following: A) Overall recovery strategy: When the deployment conditions are not met, the first-level separation is not performed. Instead, the second-level separation is performed directly and the payload recovery parachute is opened, so that the control cabin and the payload are recovered as a whole through slow descent. B) Deployment-then-disposal strategy: When the risk of the location going out of bounds is low and the payload is ready, first perform the first-level separation to deploy the payload, then perform the second-level separation and trigger the controllable disposal of the balloon, while the control cabin opens its parachute for recovery. C) Timeout / Loss of Contact Handling Strategy: When the ascent timeout or communication loss continues for more than the threshold, the second-level separation will be automatically executed and the parachute will be deployed to recover the control cabin. If necessary, the balloon disposal will be triggered at the same time to limit the drift distance. D) Separation failure retry strategy: When the first-level separation or second-level separation fails, the retry is triggered according to the preset number of times and intervals, and after multiple failures, the strategy is switched to overall recovery or balloon disposal as a backup.

[0040] In the technical solution of this invention embodiment, the target priority can be configured as one or more combinations of "balloon disposal priority, normal payload separation priority, abnormal payload recovery priority, and control module recovery priority". By pre-setting parameters and priority tables at the ground station, the system can be adapted to different test airspaces, different payload values, and different risk constraint scenarios.

[0041] In a specific exemplary technical solution, the recovery component includes a control cabin recovery parachute system and / or a payload recovery parachute system; the control cabin recovery parachute system is installed on the launch separation control cabin and automatically deploys the parachute after secondary separation to allow the control cabin to descend stably and slowly; the payload recovery parachute system is used to recover the mission payload when the launch conditions are not met or the launch is abnormal, so that the mission payload can land slowly within a controllable landing point range; each of the above recovery parachute systems can be equipped with a parachute line separation mechanism so that the parachute breaks after landing to avoid dragging, thereby improving recovery efficiency and equipment integrity.

[0042] In this embodiment of the invention, the deployment separation control cabin is further provided with a load protection and deceleration component, which covers the outside of the mission payload component and is used to provide high-altitude protection for the mission payload component and achieve deceleration and stabilization after deployment; the mission payload component is one of a foldable UAV, an emergency monitoring payload, or a communication relay payload.

[0043] Specifically, the load protection and deceleration assembly includes a load protection cabin and a deceleration parachute system. The load protection cabin covers the UAV or mission load assembly, providing shock and low-temperature protection during the ascent phase, and triggers the deceleration parachute system after the first separation, allowing the load to enter a decelerated and stable descent state. The deceleration parachute system may include at least one of a stabilizing parachute and a main parachute, used to reduce descent speed, improve attitude stability, and provide a window for subsequent release of the UAV or safe recovery.

[0044] In a further preferred technical solution, when the mission payload is a high-altitude unmanned aerial vehicle (UAV), the payload protection cabin is equipped with a secondary release mechanism to release the UAV when the payload descends to a preset altitude window; the UAV has a foldable or rapidly deployable configuration, and after the UAV leaves the protection cabin, it completes deployment and enters autonomous flight mode, and flies to the recovery point or mission area according to a preset route; the UAV recovery can adopt net-crashing recovery, parachute recovery or other equivalent recovery methods.

[0045] This invention proposes a closed-loop system architecture for high-altitude balloon deployment, encompassing "deployment, disposal, and recovery." It integrates deployment window determination, controllable separation, controlled balloon self-destruction, control cabin / payload recovery, and landing point tracking into a complete system, rather than focusing solely on a single separation or recovery stage. After deployment, it proactively eliminates the risk of continuous drift between the balloon and platform, significantly reducing the risk of overrunning and impact, while simultaneously improving system integrity and engineering feasibility. By establishing a multi-criteria deployment window determination mechanism and supporting automatic / manual dual-mode switching, this invention reduces the probability of misdeployment and overrunning, making deployment decisions traceable and improving mission controllability and safety. Through at least two levels of hierarchical timing control, this invention ensures the payload enters a controllable state first, avoiding interference between disposal actions and payload release that could lead to attitude shocks or link disruptions, thus improving deployment success rate and system safety margin. This invention employs a dual-redundancy design for key execution stages, coupled with closed-loop action determination. Separation and disposal status determination is achieved through current readback, limit / tension changes, sudden attitude / acceleration changes, or load-side feedback signals. This significantly reduces the risk of separation failure, disposal failure, or unrecoverable failure due to single-point failures, improving system reliability and mission success probability. Furthermore, this invention sets up strategies for various scenarios such as out-of-bounds location, communication loss, ascent timeout, abnormal load status, and separator malfunction. These strategies include overall recovery (direct recovery without deployment), deployment followed by disposal, timeout / loss self-protection, separation failure retry, and backup disposal. These strategies can be configured according to mission priority. Even in abnormal situations, the risk can be converged to a predictable landing area, maximizing the safety of personnel and ground assets while minimizing equipment loss and resource waste. The control cabin of this invention is trackable, retrievable, and reusable. It integrates a recovery parachute system, a search and rescue beacon / positioning module, and a data recording module. When necessary, it can be equipped with a landing parachute breakage or anti-drag structure to improve the predictability of the control cabin's landing point and search and recovery efficiency. It supports repeated use in multiple tests and ensures the complete collection of key data, which is conducive to the rapid iteration and engineering application of the system.

[0046] In this embodiment of the invention, the deployment window determination and control method can be determined and executed automatically by the control cabin, or determined by the ground station and then issued a command. The criteria can be replaced by a combination of altitude, position, time, and communication health, such as altitude, drift prediction landing point, and wind field threshold. The abnormal strategy can be replaced by a fully automatic mode combined with automatic triggering and manual secondary confirmation, or conversely, a mode of manual control combined with automatic backup. Positioning can be replaced by Beidou or GPS / Beidou dual-mode, or additional methods such as radiosonde positioning, satellite short message positioning, VHF / UHF search and rescue beacons, and buzzer / flash can be added. The communication link can be replaced by conventional data transmission, such as satellite link, mobile public network link, or spread spectrum radio link, and can be combined according to the coverage conditions of the test site. Control cabin recovery can be carried out using single parachute recovery, double parachute (guide parachute combined with main parachute) recovery, or controllable parachute recovery. Payload recovery can be carried out using parachutes of different specifications or airbag cushioning recovery. Parachute line separation after landing can be omitted, or replaced by electric heating cut-off / release locks, etc., instead of mechanical shearing. Alternative solutions for payload protection and deceleration include: for UAVs, a combination of a protective cabin and a deceleration parachute for secondary release, or a direct descent using a deceleration parachute without a protective cabin; the secondary release altitude window can be adjusted according to the UAV model and mission; for non-UAV payloads, a drop container / supply compartment can be used for direct parachute delivery, or a multi-stage deceleration parachute can be used to reduce impact. Alternative solutions for the controllable disposal of balloons include: self-destruction using a burst capsule igniter, depressurization and de-elevation using a controllable release valve / rapid deflation valve, or creating a breach in the balloon using a cutting mechanism, a tear rope, or a fuse; disposal triggering can be replaced by pyrotechnic triggering with solenoid valve triggering or mechanical triggering, and the disposal execution end can be replaced by a multi-point deployment.

[0047] Please see Figure 1 The high-altitude delivery system provided in this embodiment of the invention mainly includes: a floating balloon 1, a detonation capsule device 2, a detonation capsule communication cable 3, a positioning and measurement unit 4, a first protective umbrella 5, a basket 6, a first-stage separator 7, a mission payload 8, a ball rope 9, a second protective umbrella 10, a second-stage separator 11, and a suspension rope 12. The air-bearing balloon 1 is a high-altitude helium balloon. After being filled with helium, the balloon provides lift, carrying the deployment and separation control module and mission payload components into the air. Air-bearing balloon 1 is equipped with a bursting capsule 2, a bursting capsule communication cable 3 (for transmitting commands), and a positioning and measurement unit 4. As a specific example, air-bearing balloon 1 can be inflated under environmental conditions of approximately -20°C at the ground and an altitude of approximately 150 m at the takeoff point, with a target altitude of approximately 8000 m and a temperature of approximately -50°C. The system can use an empirical formula for balloon buoyancy to verify the inflation volume, resulting in an initial inflation volume of approximately 157 m³ (corresponding to a diameter of approximately 6.70 m), expanding to approximately 429 m³ (corresponding to a diameter of approximately 9.36 m) during ascent. These values ​​are preferred examples and can be adjusted according to payload weight, target altitude, and weather conditions.

[0048] The launch separation control cabin (i.e., basket 6) is connected to the air balloon 1 via ball rope 9 and suspension rope 12, which serve as the first suspension connection structure, and is connected to the mission payload assembly via a second suspension connection structure. Both the first and second suspension connection structures are constructed using high-strength load-bearing ropes and metal connectors. For example, ultra-high molecular weight polyethylene rope with a diameter of approximately 5 mm can be used as the load-bearing rope, and 304 stainless steel snap rings / connecting rings with a diameter of approximately 0.8 mm can be used as connectors to form a clear and reliable load-bearing path. This load-bearing path should ensure sufficient safety margin for the target load (e.g., on the order of 100 kg) to withstand ascent oscillation, cryogenic embrittlement, and transient impacts during separation.

[0049] The launch and separation control cabin is equipped with a control computing unit, a power supply unit, an execution control unit, a positioning and communication unit, and a data recording unit. The control computing unit receives information such as altitude, position, speed, and link status from the positioning and communication components, and executes launch and emergency logic based on preset launch criteria. The power supply unit is preferably a low-temperature resistant battery pack, which, in conjunction with an insulation structure and power management circuit, ensures stable power supply in low-temperature environments. The execution control unit outputs trigger signals to the separation execution component and the balloon controllable disposal component. The positioning and communication unit establishes two-way communication with the ground command and control component and transmits key telemetry data back. The data recording unit records key parameters such as action sequence, position and altitude, power supply voltage, and trigger current, facilitating verification of test criteria and post-event traceability.

[0050] The mission payload assembly can be a high-altitude unmanned aerial vehicle (UAV) (preferably a foldable, rapidly deployable fixed-wing UAV) or a simulated payload bay / mission weapons bay, etc. Taking a UAV as an example, the UAV can adopt a folding electric configuration, with wings and tail fins having rapid deployment and retraction capabilities: the wings can be telescopically and rotatably retracted, and after release, the outer wings automatically extend and rotate to the working angle to complete deployment; the tail fin can automatically rotate and deploy after being released from restraint; the power system can use a brushless motor and a high-efficiency folding propeller, and the control system can use servo motors for drive. The above are preferred examples and do not limit the specific layout of the UAV.

[0051] The payload protection and deceleration assembly preferably includes a UAV protective cabin and a deceleration parachute system. The UAV protective cabin encloses the UAV and provides protection and restraint during takeoff; the deceleration parachute system is mounted on the protective cabin and can deploy immediately upon release to decelerate the payload, allowing the UAV to fall stably under the action of the deceleration parachute. Preferably, the protective cabin also has a secondary release mechanism for releasing the UAV when the payload descends to a preset altitude window (e.g., 5 km to 6 km), allowing the UAV to break free from the influence of the deceleration parachute, enter autonomous flight mode, and execute a loitering flight path.

[0052] The separation execution assembly includes at least a primary separator 7 and a secondary separator 11. The primary separator 7 separates the mission payload assembly from the deployment and separation control cabin (payload separation); the secondary separator 11 separates the deployment and separation control cabin from the launch platform (basket separation). Preferably, both the primary separator 7 and the secondary separator 11 are cutting-type separators, meaning they cut and release the load-bearing rope / cable using a flame-driven blade or equivalent cutting structure. More preferably, both the primary separator 7 and the secondary separator 11 employ a dual-redundancy configuration: two separators can be configured in parallel to act on the same load-bearing connection within the same separation stage, or two parallel load-bearing ropes can be controlled by independent separators to reduce the risk of separation failure due to single-point failure. The trigger signal for the separator is issued by the execution control unit, and the action can be completed by outputting an ignition pulse through the ignition controller.

[0053] The balloon controllable disposal component is used to terminate the safety hazards caused by the balloon's continued drift after deployment or under abnormal conditions. Preferably, the balloon controllable disposal component includes a burst igniter and its triggering circuit. The burst igniter is installed on the balloon handle or near a critical position on the balloon body, with the flame directed towards the balloon skin to achieve self-destruction / rapid deflation of the burst igniter. More preferably, the burst igniter has dual-redundancy: two sets of igniters or two independent triggering circuits operate independently, and successful triggering of either circuit completes the balloon's failure to ascend. It should be noted that the balloon disposal method is not limited to burst ignition; it can also be replaced with a controllable relief valve, a cutting mechanism, or other equivalent solutions.

[0054] The positioning and communication component is used to achieve full-process tracking and recovery. Preferably, the positioning methods can be combined as follows: GNSS positioning (GPS / BeiDou), radiosonde-assisted positioning (BeiDou), search and rescue beacons, etc.; the ground-based receiving equipment is used to receive and display the balloon / control module trajectory information in real time. Furthermore, the positioning and communication component can transmit information such as altitude, position, vertical velocity, and link quality back to the ground command and control component for route prediction, deployment window determination, and emergency response decisions.

[0055] The ground command and control component consists of a ground station and an operating interface, used to display system altitude, location, communication status, and action status, and supports switching between automatic and manual control modes. Preferably, the ground station is pre-loaded with deployment criteria and safety fence parameters, including target altitude (e.g., 8 km), tolerance range, geofence range, ascent time threshold (e.g., 30 min), etc. The ground station can combine pre-launch weather balloon wind measurement data and historical wind field data to perform drift simulation, provide launch point and drop point suggestions, and update landing point predictions during the test.

[0056] In one specific implementation, pre-test preparation includes at least: meteorological confirmation, equipment confirmation, and pre-test rehearsal. During the meteorological confirmation phase, a weather balloon is launched at the test site to acquire upper-air meteorological data from the day before and one hour prior to launch, focusing on analyzing wind speed and direction changes with altitude to preliminarily determine the balloon's high-altitude drift trajectory and flight distance. During the equipment confirmation phase, the complete set of equipment, including the high-altitude helium balloon, launch and separation control cabin, separator, igniter, recovery parachute, positioning and communication equipment, is verified. During the pre-test rehearsal phase, a process drill is conducted according to the division of responsibilities to ensure no omissions in on-site operation.

[0057] Furthermore, a high-altitude simulated payload pre-test can be conducted before the formal deployment: deploying a simulated payload, verifying the balloon's self-destruction, recovering the simulated payload compartment and control compartment, and collecting key parameters. The formal UAV deployment test can only proceed after the pre-test verifies the reliability of the separation, disposal, and recovery link.

[0058] During the ascent phase, the launch platform, carrying the delivery separation control module and mission payload components, ascends vertically. The ground station continuously receives altitude and position data and performs drift prediction based on wind field data. Preferably, the delivery window determination includes at least the following criteria: reaching the target altitude (e.g., approximately 8 km), being within the safety fence, having normal communication feedback, and the ascent time not exceeding a threshold. When normal delivery conditions are met, the automatic delivery process begins; when delivery conditions are abnormal (e.g., location exceeding boundaries, communication failures, etc.), abnormal delivery logic is activated, and the ground station can switch to manual delivery mode.

[0059] When the normal delivery conditions are met, the delivery process is preferably executed automatically, and the following actions are performed sequentially according to the trigger conditions: First-stage separator separation (payload separation): The execution control unit sends a trigger signal to the first-stage separator (preferably one ignition controller signal, simultaneously controlling the operation of two redundant separators) to complete the separation of the control cabin from the mission payload assembly. After separation, the deceleration parachute system in the payload protection and deceleration assembly immediately deploys to decelerate the UAV / payload and stabilize its descent attitude.

[0060] Secondary separator separation (basket separation) and balloon disposal linkage: In a preferred embodiment, the system can be set with timing control: after a delay Δt (e.g., 20 s) after the mission payload sends back the "normal deployment signal", the execution control unit sends a trigger signal to the secondary separator (which can also control the operation of the two redundant separators) to complete the separation of the control cabin from the balloon; at the same time, a trigger signal is sent to the balloon controllable disposal component to ignite the burst bladder igniter to realize the balloon self-destruction / loss of ascent disposal, thereby terminating the continued drift of the balloon.

[0061] Basket / Control Module Recovery: After the secondary separation and balloon disposal are completed, the control module activates the recovery parachute system (preferably a protective parachute). After a set delay (e.g., 1.5 s), the parachute opens, allowing the control module to fall at a constant speed. After landing, the rescue vehicle is guided to the recovery site via search and rescue beacons and positioning information, enabling the control module to be reused.

[0062] Secondary release and flight recovery of the UAV: ​​During the stable descent of the deceleration parachute, when the payload reaches a preset altitude window (e.g., 5 km to 6 km), the protective cabin executes the secondary release mechanism, releasing the UAV to enter autonomous flight. After deployment, the UAV enters a loitering / return route and is finally recovered at the recovery point using methods such as net-based recovery. This completes the closed-loop process of payload deployment—platform disposal—pod recovery—UAV recovery.

[0063] When abnormal deployment conditions occur, the system can automatically execute abnormal commands, or the ground station can manually execute deployment / retrieval commands. Abnormal handling process: Altitude not met and communication abnormal: If the ground control station determines that the altitude has not reached the target altitude (e.g., 8 km) and there is an anomaly in the communication feedback status, it will switch to manual deployment mode. The operator can choose based on the risk assessment: manually perform the first-level separation to separate the payload and enter the parachute descent / stabilization process, or directly perform the second-level separation and recovery (without deployment) to reduce the risk of overrunning.

[0064] Reaching target height but position exceeding safety fence: When the target height is reached but the position is determined to be beyond the safety fence, the ground control console can manually execute the first-stage separator separation (load separation). Subsequent branching processing is based on the load feedback status. If the mission payload transmits a normal deployment signal, the second-stage separation will be performed and the balloon disposal will be triggered according to the normal timing delay (e.g., 20 s), and the control module will open its parachute for recovery. If the mission payload transmits an abnormal deployment signal, the ground control console can directly execute the secondary separation and trigger balloon disposal. At the same time, it can select a recovery parachute configuration with greater drag / stronger descent capability (such as the T200-200 model) to protect the basket and payload, and after landing, it can execute the recovery parachute separator to disconnect the deceleration parachute for easy recovery by the rescue vehicle.

[0065] Other abnormal triggering conditions: When the specified upper limit of altitude is not reached (e.g., 8.5 km) but the position has exceeded the safety fence or the ascent time exceeds the threshold (e.g., 30 min), the system can automatically execute the secondary separator separation and open the recovery parachute, so that the basket and mission load can be recovered as a whole. After landing, the parachute is disconnected by the recovery parachute separator, and the rescue vehicle goes to retrieve it, thereby avoiding continued drifting or misdeployment in unsafe airspace.

[0066] Through the aforementioned normal / abnormal processes, this invention prioritizes objectives into an executable chain of actions at the engineering implementation level: firstly, ensuring controllable balloon handling (eliminating drift risks); secondly, ensuring controllable payload separation and deployment; thirdly, achieving payload recovery in abnormal situations; and finally, achieving the recovery and reuse of the deployment separation control cabin. Each action can be enhanced in reliability through dual-redundant separation and dual-redundant handling triggers; simultaneously, GPS / BeiDou / sondesktop and search and rescue beacons enable full-process tracking and landing point recovery, significantly improving the safety, controllability, and system integrity of high-altitude deployment missions.

[0067] In summary, the problems include uncertainties in the deployment and landing points due to wind drift, risks of overshooting and falling due to the continuous drifting of the balloon and pod after deployment; inability to safely recover the payload when deployment conditions are not met or the mission is aborted; and single-point failures in key execution stages such as separation / ignition leading to deployment or recovery failures. This invention provides a high-altitude deployment system with deployment window determination, graded and controllable separation, controllable self-destruction of the balloon, trackable recovery of the pod, and anomaly redundancy emergency strategy to achieve reliable payload deployment, safe platform handling, and equipment reusability. For UAV (or other mission payload) deployment applications using high-altitude helium balloons combined with pod platforms, a systematic high-altitude deployment solution is still urgently needed: one that can achieve deployment window determination and controllable separation under limited airspace and wind drift constraints; controllable handling of the balloon platform after successful deployment to eliminate drift hazards; trackable, recoverable, and reusable control cabin / pod; and graded emergency and redundancy protection mechanisms in cases of communication anomalies, location overshooting, ascent timeouts, and abnormal payload status, thereby simultaneously meeting the requirements of safety, controllability, and economy.

[0068] In scenarios such as earthquakes, floods, wildfires, and maritime accidents, high-altitude balloons are used to launch the separation control cabin and UAVs / payloads to a preset altitude. After meeting the safety fencing and delivery window criteria, a controlled delivery is executed. The UAVs quickly deploy and enter the mission route to conduct reconnaissance and mapping of the disaster area, personnel search and rescue, and disaster information transmission. After the mission, the system's controllable balloon disposal and control cabin parachute recovery mechanism ensures the platform's safe termination of drift and reuse. In situations such as large-scale event support, remote communication blind spots, and sudden network outages, this high-altitude delivery system deploys communication relay payloads or UAVs carrying relay payloads to the target airspace. Ground stations determine the delivery window and implement tiered separation control to ensure stable deployment of the relay platform within a defined area. Simultaneously, relying on positioning beacons and recovery parachute systems, the relay payload / control cabin can be quickly recovered and reused, reducing deployment costs and improving response efficiency. This invention can be used for missions such as reconnaissance and jamming, area patrol flights, and delivery of special materials. It can carry foldable drones or special payloads into the air via a balloon and achieve controlled separation and delivery when preset altitude and position conditions are met. In case of abnormal or boundary risks, it can switch to overall recovery or emergency response strategies to ensure safety and controllability. After delivery, the balloon can be self-destructed in a controlled manner and the control cabin can be tracked and recovered to reduce exposure risks and improve equipment reuse rate.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A high-altitude delivery system, characterized in that, include: The launch platform, the deployment and separation control module, and the recovery components; among them, The launch platform includes: a floating balloon, a positioning and measurement unit, and a balloon controllable disposal component; wherein, the balloon controllable disposal component is used to terminate the continuous drift of the floating balloon; The launch and separation control cabin is equipped with a first sling connection structure for connecting to the mission payload assembly and a second sling connection structure for connecting to the launch platform; wherein, the first sling connection structure is equipped with a primary separator and the second sling connection structure is equipped with a secondary separator; The recovery assembly is used to recover one or both of the launch separation control cabin and the mission payload assembly; The deployment separation control cabin is further equipped with a positioning and communication component and a control unit. The positioning and communication component acquires data output from the positioning measurement unit and transmits it to the control unit. The control unit uses the acquired health status information and the data transmitted by the positioning and communication component as deployment criteria parameters to determine the deployment result. If the determination result indicates that the deployment criteria parameters do not meet the requirements, an abnormal control strategy is triggered to achieve overall or tiered recovery of the deployment separation control cabin and the mission payload component. If the determination result indicates that the deployment criteria parameters meet the requirements, a payload separation strategy is triggered to achieve controllable deployment of the mission payload component and slow descent recovery of the deployment separation control cabin.

2. The high-altitude delivery system according to claim 1, characterized in that, The controllable balloon handling component includes: an actuator and a triggering circuit; wherein... The triggering circuit is electrically connected to the control unit and is used to receive the disposal command sent by the control unit and trigger the actuator according to the disposal command; The actuator is a controllable venting mechanism, which is used to open the venting channel to release the gas inside the air balloon when triggered by the triggering circuit; or, the actuator is a controllable destructive venting mechanism, which is used to create a rupture in the skin of the air balloon to cause a loss of lift when triggered by the triggering circuit.

3. The high-altitude delivery system according to claim 1, characterized in that, The controllable balloon disposal component, the first-stage separator, and the second-stage separator all adopt a dual-redundancy configuration, which consists of two independent trigger circuits and two independent execution terminals.

4. The high-altitude delivery system according to claim 1, characterized in that, The execution steps of the load separation strategy include: The separation of the mission payload assembly from the launch and separation control cabin is achieved by controlling the operation of the first-stage separator; After controlling the first-stage separator to act, the second-stage separator is controlled to act after a delay to separate the release and separation control cabin from the launch platform, and the balloon controllable disposal component is triggered simultaneously to terminate the continuous drift of the floating balloon. The recovery assembly enables the slow descent and recovery of the deployment separation control cabin.

5. The high-altitude delivery system according to claim 1, characterized in that, In the control unit, the steps of using the acquired health status information and the data transmitted by the positioning communication component as relevant parameters for deployment criteria to obtain the determination result specifically include: The determination is made based on altitude, location, time, and health criteria to obtain the determination result. Among them, the height criterion is reaching the target delivery height or the target height range; the position criterion is being within the safety fence range and the drift prediction landing point does not cross the boundary; the time criterion is that the ascent time does not exceed the preset threshold; and the health criterion is that the communication link heartbeat is normal and the high-altitude delivery system self-test is normal. When all or a preset combination of criteria are met, the judgment result is that the relevant parameters of the delivery criteria meet the requirements; otherwise, the judgment result is that the relevant parameters of the delivery criteria do not meet the requirements.

6. The high-altitude delivery system according to claim 5, characterized in that, The anomaly control strategy includes one or more of the following: overall recovery strategy, deployment before disposal strategy, timeout or loss of contact disposal strategy, and separation failure retry strategy. The overall recovery strategy involves controlling only the secondary separator to perform secondary separation, and then using the recovery component to achieve a smooth descent and recovery of the deployment separation control module and the mission payload module. The "deploy first, then handle" strategy involves controlling the primary separator to perform primary separation and deploy the mission payload module when the risk of location exceeding the boundary is below a set threshold and the mission payload module is ready, followed by controlling the secondary separator to perform secondary separation and triggering the balloon's controllable disposal mechanism. The recovery component then enables a smooth descent and recovery of the deployment separation control module. The timeout or communication loss handling strategy involves controlling the secondary separator to perform secondary separation and using the recovery component to achieve a smooth descent and recovery of the deployment separation control module when the set requirements are met. The separation failure retry strategy involves retrying the system a preset number of times and at preset intervals when primary or secondary separation is detected as unsuccessful. Once the number of failures reaches a set threshold, the strategy switches to either the overall recovery strategy or a backup strategy that triggers the balloon's controllable disposal mechanism.

7. A high-altitude delivery system according to claim 5, characterized in that, The target priority configuration of the anomaly control strategy is one or more combinations of balloon disposal priority, normal payload separation priority, abnormal payload recovery priority, and control module recovery priority.

8. The high-altitude delivery system according to claim 1, characterized in that, Also includes: Load protection chamber and deceleration parachute system; The payload protection chamber is used to cover the mission payload components and provide shock and low temperature protection during the ascent phase; the deceleration parachute system is used to trigger after the first-stage separator performs the first-stage separation, so that the mission payload components enter a deceleration and stable descent state.

9. A high-altitude delivery system according to claim 8, characterized in that, The load protection cabin is equipped with a secondary release mechanism, which is used to release the mission load components when the load protection cabin descends to a preset height window.

10. A method for operating the high-altitude delivery system according to claim 1, characterized in that, Includes the following steps: The air balloon in the launch platform carries the launch separation control cabin and mission payload components into the air. The positioning measurement unit acquires and outputs the relevant setting data of the air balloon in real time. The positioning communication component receives the data output by the positioning measurement unit and transmits it to the control unit of the launch separation control cabin. The control unit uses the acquired health status information and data transmitted by the positioning and communication components as parameters related to the deployment criteria to determine the deployment and obtain a determination result. If the determination result indicates that the parameters related to the deployment criteria do not meet the requirements, an abnormal control strategy is triggered to achieve the overall recovery or staged recovery of the deployment separation control cabin and the mission payload component. If the determination result indicates that the parameters related to the deployment criteria meet the requirements, a payload separation strategy is triggered to achieve the controllable deployment of the mission payload component and the slow descent recovery of the deployment separation control cabin.

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