Pop-in / absorption composite cold and power cogeneration system for cold chain cabin of medium and large hydrogen unmanned aerial vehicle

Abstract

The application provides a middle-large hydrogen unmanned aerial vehicle cold chain cabin elastic card / absorption composite cold and power supply system, which comprises a power system, an absorption cold and power supply module, an elastic card refrigeration module, an airborne refrigerator and an energy management module; the absorption cold and power supply module comprises an absorption refrigeration cycle loop and an expander power generation module; the power system outputs electric energy and waste heat cooling liquid; the power system delivers the generated waste heat cooling liquid to the absorption cold and power supply module through a pipeline, the absorption refrigeration cycle loop in the absorption cold and power supply module provides cold energy for the airborne refrigerator based on the waste heat cooling liquid; the expander power generation module in the absorption cold and power supply module generates electric energy based on the waste heat cooling liquid; the electric energy and the output electric energy of the power system are combined through the energy management module to jointly drive the elastic card refrigeration module to refrigerate.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) and refrigeration technology, specifically to a combined cooling and power supply system for the cold chain compartment of medium and large hydrogen-powered UAVs using a combination of spring-loaded and absorbent systems, and more specifically to a combined cooling and power supply system for the cold chain compartment of medium and large hydrogen-powered UAVs using a combination of spring-loaded and absorbent systems. Background Technology

[0002] Refrigeration technology is becoming increasingly important in the aerospace field, especially for devices like cold chain drones that have stringent requirements for system size, energy consumption, and response speed. Among the current mainstream refrigeration technologies, vapor compression refrigeration is difficult to adapt to the small size, lightweight, and environmental protection requirements of drones because it produces greenhouse gases and relies on core components such as compressors and throttling devices to form a closed loop.

[0003] Solid-state refrigeration and absorption refrigeration technologies have become important alternatives to traditional solutions. Among them, cartridge-based refrigeration, as one of the core types of solid-state refrigeration, achieves cooling by utilizing the reversible phase change and latent heat of phase change of shape memory alloys under uniaxial stress. Compared with magnetic and electronic cartridge refrigeration, it has advantages such as low cost, wide temperature range, and high energy efficiency. However, traditional cartridge-based refrigeration equipment mostly uses tubular or strip-shaped shape memory alloy structures, which require a large driving force during loading, resulting in high system energy consumption. In addition, the structural layout lacks flexibility and is difficult to adapt to the size of UAVs.

[0004] Absorption refrigeration technology consumes thermal energy and relies on the vaporization and heat absorption of liquid refrigerant within an evaporator, forcing heat to continuously transfer from a low temperature to a high temperature. It is particularly suitable for coupling with hydrogen hybrid power systems to form combined cooling and power systems, achieving cascaded energy utilization.

[0005] Patent document CN116678054A (application number: 202310479036.1) discloses a combined cooling, heating, and power (CCHP) system based on fuel cells and absorption refrigeration. It proposes a CCHP system that, based on an absorption refrigeration cycle, introduces a waste heat exchanger and an expander power generation module, achieving flexible supply of cooling, heat, and electricity. However, this patent only recovers waste heat from the fuel cell as the heat source for the absorption refrigeration cycle. If applied to drones, this approach has a limited scope for energy recovery, and there is still room for improvement in energy utilization.

[0006] Patent document CN118463419A (application number: 202410675470.1) discloses a parallel combined cooling and power generation system and method, which connects an absorption refrigeration system and a waste heat power generation system in parallel, allowing refrigeration and power generation to be regulated independently. However, the working fluid pressurization stage of its power generation module directly relies on the condensate from the absorption refrigeration, and the power generation is delayed due to the refrigerant phase change, making it difficult to generate stable power during the take-off and landing phases of UAVs.

[0007] Patent document CN118532844A (application number: 202410971626.0) discloses a spring-loaded refrigerator based on shape memory alloy helical spring tension and compression loading, which realizes the recovery of kinetic energy of the motor. However, its linear drive transmission device has large frictional losses and does not have the ability to be used for a long time under high speed conditions; at the same time, the patent does not mention the heat recovery design for the sensible heat of solid materials, resulting in a large amount of sensible heat being lost in each cycle due to the fluctuation of material temperature.

[0008] Patent document CN115031440A (application number: 202210906469.6) discloses an immersion heat exchange type water vapor energy heat pump air conditioning device, which absorbs water vapor energy from the air by immersing the heat exchanger in a heat exchange solution to achieve heating and cooling in winter and summer. However, this device relies on a fixed water vapor energy purification platform, is bulky, and needs to continuously exchange heat with the atmospheric environment. It cannot adapt to the low air pressure and variable temperature environment when UAVs fly at high altitudes. Furthermore, it does not involve combined cooling, heating, and power functions, and can only adjust the temperature, which cannot meet the combined cooling and power requirements of the cold chain cabin of medium and large UAVs.

[0009] For medium-to-large hydrogen-powered drones, existing refrigeration technologies suffer from limitations such as insufficient cooling capacity reserves, low efficiency, and difficulty in matching complex energy consumption conditions, and they also fail to effectively utilize system surplus energy. Therefore, there is an urgent need to develop a combined cooling and power system that can deeply recover surplus energy, achieve efficient cooling throughout the entire flight, and also provide power compensation during high-power consumption phases, in order to meet the cooling and energy consumption requirements of medium-to-large drones. Summary of the Invention

[0010] To address the shortcomings of existing technologies, the purpose of this invention is to provide a combined cooling and power supply system for the cold chain compartment of medium and large-sized hydrogen-powered unmanned aerial vehicles (UAVs) that integrates refrigeration and power supply with a combination of bomb and accumulator / absorption systems.

[0011] According to the present invention, a combined cooling and power system for a medium-to-large hydrogen-powered unmanned aerial vehicle (UAV) cold chain compartment includes: a power system 1, a combined cooling and power module for absorption, a cooling module for the airborne compartment, an airborne refrigerator 5, and an energy management module 7.

[0012] The absorption cooling and power generation module includes an absorption cooling cycle loop and an expander power generation module;

[0013] Based on the electrical energy and waste heat coolant output by the power system 1;

[0014] The power system 1 delivers the waste heat coolant it generates to the absorption cooling and power supply module through pipelines. The absorption cooling and power supply module provides cooling capacity to the airborne refrigerator 5 based on the waste heat coolant. The expander power generation module in the absorption cooling and power supply module generates electricity based on the waste heat coolant. The electricity and the output electricity of the power system 1 are combined through the energy management module 7 to jointly drive the cooling module of the airborne refrigerator.

[0015] Preferably, the absorption refrigeration cycle includes: a generator 211, a condenser 214, a first throttle valve 215, an evaporator 216, and an absorber 217; the generator 211, the condenser 214, the first throttle valve 215, the evaporator 216, and the absorber 217 are connected in sequence;

[0016] The expander power generation module includes: an expander 221 and a generator 222; the expander 221 is poweredly connected to the generator 222;

[0017] The refrigerant outlet of the generator 211 is connected to the working fluid inlet of the expander 221 and the refrigerant inlet of the condenser 214 via the first diverting three-way valve 61; the refrigerant inlet of the absorber 217 is connected to the working fluid outlet of the expander 221 and the refrigerant outlet of the evaporator 216.

[0018] A heat exchanger 218 and a solution pump 213 are provided between the absorber 217 and the generator 211, and a second throttle valve 212 is provided on the bypass pipeline between the generator 211 and the absorber 217.

[0019] Preferably, the combined cooling and power supply module includes: waste heat coolant generated by the power system 1 is transferred to the hot side of the generator 211 through a pipeline to heat the solution in the generator 211 and generate high-temperature refrigerant vapor; during the high-power operation phase of the UAV takeoff or landing that meets preset requirements, the refrigerant vapor enters the expander 221 through the first diverting three-way valve 61 to drive its operation; under the drive of the operating expander 221, the generator 222 generates electricity and transmits the electrical energy to the rotating electric motor in the bombardment cooling module. Machine 3; During the UAV's cruise operation, refrigerant vapor enters the condenser 214 through the first diverting three-way valve 61 and is condensed into liquid refrigerant. After being throttled and depressurized by the first throttling valve 215, it is sent to the evaporator 216 for heat exchange. After absorbing heat and evaporating, it returns to the absorber 217. The absorbent liquid in the absorber 217 is preheated by the heat exchanger 218 under the action of the solution pump 213 and then sent to the generator 211 for recycling. The second throttling valve 212 is used to adjust the bypass solution flow rate and stabilize the circulation pressure.

[0020] Preferably, the spring-loaded cooling module includes: a left-side housing 416, a right-side housing 426, a rotary motor 3, and an elliptical disk 44;

[0021] The left casing 416 and the right casing 426 are symmetrically arranged on both sides of the elliptical disk 44. The output shaft of the rotary motor 3 is coaxially fixed with the elliptical disk 44. The rotation of the rotary motor 3 drives the elliptical disk 44 to rotate synchronously. The rotation of the elliptical disk 44 drives the loading or unloading of the springs in the left casing 416 and the right casing 426. By controlling the springs to cause phase change, heat absorption and heat release are achieved, and cooling is realized in the process of heat absorption and heat release.

[0022] Preferably, the left casing 416 includes: a left inner water outlet 4151, a left outer water outlet 4152, a left inner water inlet 4141, a left outer water inlet 4142, a left inner spring 412, a left outer spring 411, and a left piston 413; wherein, the left piston 413 divides the heat exchange channel of the left casing 416 into an inner region and an outer region; the left inner spring 412 is provided in the inner region, and the left outer spring 411 is provided in the outer region;

[0023] The right-side casing 426 includes: a right-side outer water inlet 4251, a right-side inner water inlet 4252, a right-side inner water outlet 4241, a right-side outer water outlet 4242, a right-side inner spring 422, a right-side outer spring 421, and a right-side piston 423; wherein, the right-side piston 423 divides the heat exchange channel of the right-side casing 426 into an inner region and an outer region; a right-side inner spring 422 is provided in the inner region, and a right-side outer spring 421 is provided in the outer region;

[0024] The elliptical disk 44 rotates synchronously with the rotary motor 3, thereby driving the pistons in the two side housings to perform linear reciprocating motion, so that the inner and outer springs are alternately in the loading and unloading state; when the inner spring is loaded, the outer spring is unloaded; when the inner spring is unloaded, the outer spring is loaded.

[0025] The left inner outlet 4151 is connected to the right outer inlet 4251; the left outer outlet 4152 is connected to the right inner inlet 4252.

[0026] The right outer outlet 4242 and the right inner outlet 4241 are respectively connected to the two inlet ends of the right four-way reversing valve 65. The two outlet ends of the right four-way reversing valve 65 are respectively connected to the inlet end of the right three-way valve 64 and one end of the right natural convection cooler 432. The other end of the right natural convection cooler 432 is connected to the other inlet end of the right three-way valve 64. The outlet end of the right three-way valve 64 is connected to the inlet of the airborne refrigerator heat exchanger 51. The outlet of the airborne refrigerator heat exchanger 51 is connected to the inlet end of the left three-way valve 63. The two outlet ends of the left three-way valve 63 are respectively connected to the inlet end of the left four-way reversing valve 62 and one end of the left natural convection cooler 431. The other end of the left natural convection cooler 431 is connected to the other inlet end of the left four-way reversing valve 62. The two outlet ends of the left four-way reversing valve 62 are respectively connected to the left inner inlet 4141 and the left outer inlet 4142.

[0027] Preferably, the operation of the cartridge cooling module includes a high-power phase that meets preset requirements and a stable cruise phase that meets preset requirements;

[0028] During the high-power stage that meets the preset requirements, the generator 222 of the expander power generation module and the power system 1 are controlled by the first diversion three-way valve 61 to jointly provide power to the rotary motor 3 of the UAV rotor, while the absorption cooling cycle loop is closed.

[0029] During the stable cruise phase that meets the preset requirements, the power system 1 provides electrical energy to the rotary motor 3 of the UAV rotor by controlling the first diversion three-way valve 61, shuts down the expander power generation module, and simultaneously starts the absorption cooling cycle loop.

[0030] Preferably, the cartridge cooling module includes:

[0031] When the right inner spring 422 is unloaded and the right outer spring 421 is loaded, and the left inner spring 412 is unloaded and the left outer spring 411 is loaded, the hot water output from the onboard refrigerator heat exchanger 51 is connected to the left three-way valve 63, which distributes it into two equal streams. One stream flows into the left natural convection cooler 431 and is cooled into cold water. The other stream remains hot water and flows directly into the left four-way reversing valve 62. The left four-way reversing valve 62 sends the cold water into the left outer inlet 4142, and the cold water flows through the left... When the outer side spring 411 is in operation, it absorbs the heat released by the spring loading and heats up to become hot water. After flowing out from the outer left water outlet 4152, it is connected to the inner right water inlet 4252. At this time, the inner right spring 422 unloads and absorbs heat. After the hot water flows through the inner right spring 422, it is cooled to become cold water and flows out from the inner right water outlet 4241. Through the right four-way reversing valve 65 and the right three-way valve 64, the cold water is directly transported to the water inlet side of the airborne refrigerator heat exchanger 51 through the pipeline, where heat exchange and cooling are carried out.

[0032] The hot water supplied by the left four-way reversing valve 62 is sent into the left inner inlet 4141. When the hot water flows through the left inner spring 412, it is unloaded by the spring and cooled into cold water. It flows out from the left inner outlet 4151 and then into the right outer inlet 4251. The cold water flows through the right outer spring 421 and gains heat to become hot water. It flows out from the right outer outlet 4242. The hot water is cooled into cold water by the right four-way reversing valve 65 and the right natural convection cooler 432. Then, the cold water is delivered to the inlet side of the airborne refrigerator heat exchanger 51 by the right three-way valve 64, where it undergoes heat exchange and cooling.

[0033] When the inner spring switches to the loading state and the outer spring switches to the unloading state, the water flow distributed by the left three-way valve 63 remains equal. One stream is cooled by the left natural convection cooler 431 and then fed into the left inner inlet 4141 through the left four-way reversing valve 62. The cold water absorbs the heat released by the loading of the left inner spring 412 and heats up before flowing into the right outer spring 421, where it is cooled and flows out from the right outer outlet 4242. The cold water is then directly transported to the right side via pipeline through the right four-way reversing valve 65 and the right three-way valve 64. On the water inlet side of the airborne refrigerator heat exchanger 51, heat exchange and cooling are performed within the airborne refrigerator heat exchanger 51; another hot water, distributed by the left three-way valve 63, is directly sent to the left outer spring 411 via the left four-way reversing valve 62, and after cooling, flows into the right inner spring 422, where it gains heat and is heated to become hot water. It is then cooled to cold water via the right four-way reversing valve 65 and the right natural convection cooler 432, and then transported to the water inlet side of the airborne refrigerator heat exchanger 51 via the right three-way valve 64, where heat exchange and cooling are performed within the airborne refrigerator heat exchanger 51.

[0034] Preferably, the left outer spring 411, the left inner spring 412, the right outer spring 421, and the right inner spring 422 are all helical spring structures made of shape memory alloy and embedded in the heat exchange channel of the corresponding chassis area. The inner wall of the heat exchange channel is treated with anti-corrosion.

[0035] Preferably, the power system 1 uses hydrogen power and includes a hybrid power system consisting of an ammonia-hydrogen hybrid engine and a PEMFC stack.

[0036] Preferably, the system further includes a control module; the control module is used to adjust the valve group on / off and fluid flow distribution according to the loading / unloading state of the spring group and the operating conditions of the UAV, so as to realize the switching control of the operating conditions during the high-power stage and the stable cruise stage.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. This invention deeply couples the evaporator of the absorption refrigeration circuit with the heat exchanger of the spring-loaded refrigeration module, constructing a collaborative system in which the two refrigeration modules share the core heat exchange components. It abandons the redundant structure of the traditional separate design, greatly reduces the system volume, and adapts to the space compactness and lightweight requirements of the cold chain compartment of medium and large hydrogen-powered UAVs. At the same time, it adopts an elliptical disk transmission structure to replace the traditional linear drive device. The rotation of the elliptical disk synchronously drives the pistons and spring groups on both sides to alternately complete the loading and unloading actions. While simplifying the transmission link, it effectively avoids the jamming and wear problems of linear drive under high-speed operation, ensures the dynamic balance stability of the system under the vibration conditions of UAV high-speed flight, and improves the long-term operational reliability of the spring-loaded refrigeration cycle.

[0039] 2. This invention designs a linkage control logic between the left-side three-way valve, the right-side three-way valve, and the four-way reversing valve, which, together with the natural convection cooler, forms a closed-loop liquid flow distribution system. The liquid flow direction can be dynamically switched according to the reverse working conditions of the spring assembly loading / unloading, realizing reversible interchange of the left and right side cooling conditions. This design precisely matches the phase change heat characteristics of the shape memory alloy spring, effectively avoiding sensible heat loss under a single working condition, and significantly improving the stability of system operation, cooling continuity, and energy utilization efficiency.

[0040] 3. This invention constructs a dual-power drive rotary motor supply mode of "power system + generator", which is precisely adapted to the different working conditions of UAVs, such as high power consumption during take-off and landing and low energy consumption during cruise. Specifically, during take-off and landing, the power generation module of the expander compensates for the high power consumption of the rotor motor, and during cruise, the power generation module is turned off to ensure cooling efficiency. At the same time, it also recovers the waste heat of the power system and the kinetic energy of the rotor, and constructs a dual waste energy cascade conversion path of "waste heat-electric energy-cooling energy" and "kinetic energy-mechanical work-cooling energy". This solves the core problems of poor adaptability of traditional systems, high energy consumption and slow cooling response, and achieves the goal of efficient cooling throughout the entire flight. It can also adapt to various working conditions from refrigeration to freezing, and has a wide range of cooling needs.

[0041] 4. This invention introduces a novel cartridge-type refrigeration module with dual-power drive and refrigerant interactive circulation. By adjusting the drive source of the UAV rotor motor and the refrigeration mode of the UAV at different flight stages, it fully recovers the UAV's residual energy, achieves power compensation during high power consumption stages and efficient refrigeration throughout the flight, and has a high energy utilization rate.

[0042] 5. This invention utilizes the waste heat and rotor kinetic energy recovered from the power system as the main driving source for the system, aiming to solve problems such as the large cooling capacity requirements of the cold chain compartment in medium and large UAVs, the difficulty in reusing rotor kinetic energy, and the waste of waste heat in the power system. The rotor motor is mainly driven by the power system and a generator connected to the expander in the absorption refrigeration system. During takeoff and landing, the generator assists the power system in powering the rotor, with cooling provided solely by the cartridge cooling module; during cruise, the power system powers the rotor, with cooling provided collaboratively by the absorption and cartridge cooling modules. The cartridge cooling module is equipped with a rotating elliptical disk, a symmetrical chassis, and partitioned spring assemblies. Through valve groups and natural convection coolers, it achieves refrigerant circulation and precisely matches the spring loading / unloading conditions. This system fully recovers the waste energy of the UAV, enabling power compensation during high-power phases and efficient cooling throughout the flight, with wide adaptability to cooling needs and high energy utilization. Attached Figure Description

[0043] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0044] Figure 1This is a schematic diagram of a combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen-powered UAV, consisting of a bomb-cart / absorption module.

[0045] Figure 2 This is a schematic diagram of the cooling module structure.

[0046] Figure 3 A cross-sectional view of the spring-loaded cooling module with the inner spring loading to release heat and the outer spring unloading to absorb heat.

[0047] Figure 4 A cross-sectional view of the spring-loaded cooling module with the inner spring unloading and absorbing heat, and the outer spring loading and releasing heat.

[0048] Figure 5 This is a schematic diagram of the structure of a cartridge-type refrigeration unit.

[0049] Among them, 1-Power system; 211-Generator; 212-Second throttle valve; 213-Solution pump; 214-Condenser; 215-First throttle valve; 216-Evaporator; 217-Absorber; 218-Heat exchanger; 221-Expander; 222-Generator; 3-Rotating motor; 411-Left outer spring; 412-Left inner spring; 413-Left piston; 4141-Left inner inlet; 4142-Left outer inlet; 4151-Left inner outlet; 4152-Left outer outlet; 416-Left chassis; 421-Right... 422-Right inner spring; 423-Right piston; 4241-Right inner outlet; 4242-Right outer outlet; 4251-Right outer inlet; 4252-Right inner inlet; 426-Right chassis; 431-Left natural convection cooler; 432-Right natural convection cooler; 44-Oval disc; 5-Onboard refrigerator; 51-Onboard refrigerator heat exchanger; 61-First diversion three-way valve; 62-Left four-way reversing valve; 63-Left three-way valve; 64-Right three-way valve; 65-Right four-way reversing valve; 7-Energy management module. Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0051] Example 1

[0052] According to the present invention, a combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen-powered unmanned aerial vehicle (UAV) is provided, such as... Figures 1 to 5As shown, it includes: a power system 1, an absorption cooling and power generation module, a spring-loaded refrigeration module, an onboard refrigerator 5, and an energy management module 7; wherein, the absorption cooling and power generation module includes an absorption cooling cycle loop and an expander power generation module; each module forms a collaborative working system through pipelines, circuits, and transmission structures, wherein the absorption cooling and power generation module is coupled with the power system 1, and the spring-loaded refrigeration module forms a dual-power drive and energy interaction relationship with the absorption cooling and power generation module and the power system 1 respectively;

[0053] Specifically, the power system 1 transports the waste heat coolant it generates to the absorption cooling and power supply module through pipelines. The absorption cooling cycle loop in the absorption cooling and power supply module provides cooling capacity to the airborne refrigerator 5 based on the waste heat coolant. The expander power generation module in the absorption cooling and power supply module generates electricity based on the waste heat coolant. The electricity and the output electricity of the power system 1 are combined through the energy management module 7 to jointly drive the cooling module of the air-launched vehicle.

[0054] Specifically, the power system 1 uses hydrogen power, such as a hybrid power system consisting of an ammonia-hydrogen hybrid engine and a PEMFC stack.

[0055] The power system 1 and the absorption cooling and power supply module work together to form a basic cooling and power supply unit. The absorption cooling and power supply module includes an absorption refrigeration cycle loop and an expander power generation module. The absorption refrigeration cycle loop is composed of a generator 211, a condenser 214, a first throttle valve 215, an evaporator 216, and an absorber 217 connected in sequence. The expander power generation module includes an expander 221 and a generator 222 connected to it. The refrigerant outlet of the generator 211 is connected to the working fluid inlet of the expander 221 and the refrigerant inlet of the condenser 214 through a first diversion three-way valve 61. The refrigerant inlet of the absorber 217 is connected to the working fluid outlet of the expander 221 and the refrigerant outlet of the evaporator 216. By controlling the opening and closing of the first diversion three-way valve 61, the absorption refrigeration independent cooling, the expander 221 power generation independent power supply, or the cooling and power supply mode can be switched. A heat exchanger 218 is installed between the absorber 217 and the generator 211 to recover waste heat during the solution circulation process. A solution pump 213 is installed on the solution pipeline between the absorber 217 and the generator 211 to provide power for solution circulation. A second throttle valve 212 is installed on the bypass pipeline between the generator 211 and the absorber 217 to regulate the solution circulation flow rate and pressure. The waste heat coolant generated by the power system 1 is connected to the hot side of the generator 211 through a pipeline to realize waste heat utilization.

[0056] More specifically, the combined cooling and power (CCHP) module includes: waste heat coolant generated by the power system 1 is transferred to the hot side of the generator 211 through pipelines to heat the solution inside the generator 211 and generate high-temperature refrigerant vapor; during the high-power operation phase of the UAV takeoff or landing that meets preset requirements, the refrigerant vapor enters the expander 221 through the first diverting three-way valve 61 to drive its operation; under the drive of the operating expander 221, the generator 222 generates electricity and transmits the electrical energy to the rotating part of the refrigeration module. Motor 3; During the drone's cruise operation, refrigerant vapor enters the condenser 214 through the first diverting three-way valve 61 and is condensed into liquid refrigerant. After being throttled and depressurized by the first throttling valve 215, it is sent to the evaporator 216 for heat exchange. After absorbing heat and evaporating, it returns to the absorber 217. The absorbent liquid in the absorber 217 is preheated by the heat exchanger 218 under the action of the solution pump 213 and then sent to the generator 211 for recycling. The second throttling valve 212 is used to adjust the bypass solution flow rate and stabilize the circulation pressure.

[0057] The spring-loaded cooling module is the core cooling execution unit, including the left chassis 416, the right chassis 426, the rotary motor 3, and the elliptical disk 44;

[0058] The left casing 416 and the right casing 426 are symmetrically arranged on both sides of the elliptical disk 44. The output shaft of the rotary motor 3 is coaxially fixed with the elliptical disk 44. The rotation of the rotary motor 3 drives the elliptical disk 44 to rotate synchronously. The rotation of the elliptical disk 44 drives the loading or unloading of the springs in the left casing 416 and the right casing 426. By controlling the springs to cause phase change, heat absorption and heat release are achieved, and cooling is realized in the process of heat absorption and heat release.

[0059] The rotary motor 3 drives the UAV rotor to rotate, employing a dual-power drive system. It receives electrical energy from the power system 1 and the generator 222 via the energy management module 7. During takeoff and landing, the generator 222 operates, working together with the power system 1 to power the rotary motor 3, compensating for the high power consumption of the rotor motor. During cruise, the expander generator module is shut down, and only the power system 1 powers the rotary motor 3 to ensure cooling efficiency.

[0060] The left casing 416 includes: a left inner water outlet 4151, a left outer water outlet 4152, a left inner water inlet 4141, a left outer water inlet 4142, a left inner spring 412, a left outer spring 411, and a left piston 413; wherein the left piston 413 divides the heat exchange channel of the left casing 416 into an inner region and an outer region; the left inner spring 412 is provided in the inner region, and the left outer spring 411 is provided in the outer region;

[0061] The right-side casing 426 includes: a right-side outer water inlet 4251, a right-side inner water inlet 4252, a right-side inner water outlet 4241, a right-side outer water outlet 4242, a right-side inner spring 422, a right-side outer spring 421, and a right-side piston 423; wherein, the right-side piston 423 divides the heat exchange channel of the right-side casing 426 into an inner region and an outer region; a right-side inner spring 422 is provided in the inner region, and a right-side outer spring 421 is provided in the outer region;

[0062] The elliptical disk 44 rotates synchronously with the rotary motor 3, thereby driving the pistons in the two side housings to perform linear reciprocating motion, so that the inner and outer springs are alternately in the loading and unloading state; when the inner spring is loaded, the outer spring is unloaded; when the inner spring is unloaded, the outer spring is loaded.

[0063] The left inner outlet 4151 is connected to the right outer inlet 4251; the left outer outlet 4152 is connected to the right inner inlet 4252.

[0064] The right outer outlet 4242 and the right inner outlet 4241 are respectively connected to the two inlet ends of the right four-way reversing valve 65. The two outlet ends of the right four-way reversing valve 65 are respectively connected to the inlet end of the right three-way valve 64 and one end of the right natural convection cooler 432. The other end of the right natural convection cooler 432 is connected to the other inlet end of the right three-way valve 64. The outlet end of the right three-way valve 64 is connected to the inlet of the airborne refrigerator heat exchanger 51. The outlet of the airborne refrigerator heat exchanger 51 is connected to the inlet end of the left three-way valve 63. The two outlet ends of the left three-way valve 63 are respectively connected to the inlet end of the left four-way reversing valve 62 and one end of the left natural convection cooler 431. The other end of the left natural convection cooler 431 is connected to the other inlet end of the left four-way reversing valve 62. The two outlet ends of the left four-way reversing valve 62 are respectively connected to the left inner inlet 4141 and the left outer inlet 4142. In this embodiment, the left and right spring assemblies are fixedly connected. The valve assembly on / off and liquid flow distribution ratio are adjusted according to the loading / unloading conditions of the spring assembly and the operating status of the drone to ensure precise matching between the liquid flow and the spring phase change state, thereby achieving continuous cooling.

[0065] The left outer spring 411, the left inner spring 412, the right outer spring 421, and the right inner spring 422 are all helical springs made of shape memory alloy and embedded in the heat exchange channels of the corresponding chassis areas. The inner walls of the heat exchange channels are treated with anti-corrosion coating to reduce the erosion of the springs by the liquid flow. The original length of the springs is not fixed; the loading or unloading state of the springs is related to the set original length. For example, when the structure moves to… Figure 3 At the position shown, the inner spring is at its original length. In the instant of the next movement, the inner spring undergoes a phase change due to the tensile loading, releasing heat, while the outer spring returns to its original length, unloading and absorbing heat. Conversely, assuming the structure moves to... Figure 4 At the position shown, the inner spring is at its original length. In the instant of the next movement, the inner spring undergoes a phase change due to compression and releases heat, while the outer spring returns to its original length and absorbs heat. However, to ensure that the working states of the inner and outer springs are opposite, the original length of the spring must be one of the two cases mentioned above, and all springs must have the same original length.

[0066] In addition, to ensure that the structure moves to Figure 4 In the instant after positioning, the piston can be forced to move tightly against the elliptical disk, which also places certain requirements on the elastic coefficients of the springs in the inner and outer regions: if this structure moves to... Figure 3 At the position shown, the inner spring is at its original length, requiring the spring constant of the inner spring to be greater than that of the outer spring. This can be achieved by connecting multiple springs in parallel on the inner side. If the structure moves to... Figure 4 When the position shown is such that the length of the inner spring is the original length, the elastic coefficient of the outer spring must be greater than that of the inner spring.

[0067] The operation of the cartridge cooling module includes a high-power phase that meets preset requirements and a stable cruise phase that meets preset requirements.

[0068] During the high-power stage that meets the preset requirements, the generator 222 of the expander power generation module and the power system 1 are controlled by the first diversion three-way valve 61 to jointly provide power to the rotary motor 3 of the UAV rotor, while the absorption cooling cycle loop is closed.

[0069] During the stable cruise phase that meets the preset requirements, the power system 1 provides electrical energy to the rotary motor 3 of the UAV rotor by controlling the first diversion three-way valve 61, shuts down the expander power generation module, and simultaneously starts the absorption cooling cycle loop.

[0070] When the inner right spring 422 is unloaded (absorbing heat and cooling) and the outer right spring 421 is loaded (releasing heat and generating heat), and the inner left spring 412 is unloaded (absorbing heat and cooling) and the outer left spring 411 is loaded (releasing heat and generating heat), the control module regulating valve group is in the first working state. In this embodiment, for ease of description, water is used as the refrigerant; using other working fluids such as ammonia may have a better cooling effect: the hot water output from the onboard refrigerator heat exchanger 51 is connected to the left three-way valve 63, which distributes it into two water flows. One flow flows into the right natural convection cooler 432 and is cooled into cold water, while the other flow remains hot water and flows directly into the left four-way reversing valve 62. The left four-way reversing valve 62 sends the cold water into the left outer area inlet (left inner inlet 4141 and left outer inlet 4142). When the cold water flows through the left outer spring 411, it absorbs the heat from the spring. The heat released by the spring loading is heated to hot water, which flows out from the outlet on the left outer side (left inner outlet 4151 and left outer outlet 4152) and then into the inlet on the right inner side (right outer inlet 4251 and right inner inlet 4252). At this time, the right inner spring 422 unloads and absorbs heat (it is assumed that the flow velocity of the fluid in the pipeline is much greater than the angular velocity of the elliptical disk rotation, and the loading / unloading state of the spring remains unchanged during the process of the fluid flowing from the outlet to the inlet at the other end). After the hot water flows through the right inner spring 422, it is cooled to cold water and flows out from the outlet (right inner outlet 4241 and right outer outlet 4242). Through the right four-way reversing valve 65 and the right three-way valve 64, the cold water is directly transported to the inlet side of the airborne refrigerator heat exchanger 51 through the pipeline, where heat exchange and cooling are carried out.

[0071] Hot water supplied by the left four-way reversing valve 62 is sent to the inlet in the left inner area (left inner inlet 4141 and left outer inlet 4142). When the hot water flows through the left inner spring 412, it is unloaded by the spring and cooled into cold water. It then flows out from the outlet (left inner outlet 4151 and left outer outlet 4152) and into the inlet in the right outer area (right outer inlet 4251 and right inner inlet 4252). The cold water flows through the right outer spring 421 and gains heat, becoming hot water. It then flows out from the outlet (right inner outlet 4241 and right outer outlet 4242). The hot water is cooled into cold water by the right four-way reversing valve 65 and the right natural convection cooler 432. The cold water is then transported to the inlet side of the onboard refrigerator heat exchanger 51 by the right three-way valve 64, where it undergoes heat exchange and cooling.

[0072] When the inner spring switches to the loading state and the outer spring switches to the unloading state, the control module adjusts the valve group to the second working state: the water flow distributed by the left three-way valve 63 remains equal. After being cooled by the left natural convection cooler 431, it is sent to the water inlet of the left inner area (left inner water inlet 4141 and left outer water inlet 4142) through the left four-way reversing valve 62. After the cold water absorbs the heat released by the loading of the left inner spring 412 and rises in temperature, it flows into the right outer spring 421 (which is in the unloading heat absorption state at this time) and is cooled into cold water. It flows out from the outlet (right inner outlet 4241 and right outer outlet 4242) and is directly transported to the water inlet side of the airborne refrigerator heat exchanger 51 through the pipeline via the right four-way reversing valve 65 and the right three-way valve 64, where heat exchange and cooling are carried out. The other hot water, distributed by the left three-way valve 63, is directly sent to the left outer spring 411 (which is in the unloading and heat absorption state at this time) through the left four-way reversing valve 62. After cooling, it flows into the right inner spring 422 (which is in the loading and heat release state at this time), and gains heat to become hot water. It is then cooled into cold water by the right natural convection cooler 432 through the right four-way reversing valve 65. The cold water is then transported to the inlet side of the airborne refrigerator heat exchanger 51 through the right three-way valve 64, where it undergoes heat exchange and cooling.

[0073] The left and right valve groups are symmetrical in structure and have the same working logic. In actual operation, the cooling conditions of the left and right sides can be interchanged. The control module monitors the spring loading / unloading status and the heat dissipation requirements of the drone in real time through the working condition detection unit, and dynamically adjusts the valve group opening and closing and water flow distribution to ensure continuous and stable cooling.

[0074] The refrigerant in the tubing of the refrigeration module is in a closed system and does not exchange substances with other modules.

[0075] The cooling function of the airborne refrigerator 5 described in this embodiment is achieved by the evaporator 216 of the absorption refrigeration cycle loop and the airborne refrigerator heat exchanger 51 of the spring-loaded refrigeration module jointly providing cooling capacity.

[0076] This invention utilizes a dual-power drive design with three rotating motors to ensure a stable power supply for the motor throughout its entire flight range. The partitioned design of the left and right casings (416 and 426) of the spring-loaded refrigeration module, along with the fixed connection structure of the spring assembly, combined with the coordinated control of the valve assembly and the natural convection cooler, ensures precise matching between the loading / unloading states of the springs on both sides and the liquid flow temperature requirements. This achieves interactive circulation of hot and cold flow, improving refrigeration efficiency while reducing energy consumption.

[0077] The system also includes a control module; the control module is used to adjust the valve group opening and closing and fluid flow distribution according to the loading / unloading status of the spring group and the operating conditions of the UAV, so as to realize the switching control between the high-power stage and the stable cruise stage.

[0078] The combined cooling and power system of this embodiment is suitable for installation on medium and large UAVs. The overall structure adopts a modular design, with each component integrated into a preset installation position inside the UAV fuselage. The left chassis 416 and the right chassis 426 are symmetrically fixed on the base, and the elliptical disk 44 is set in the middle of the two chassis. The rotary motor 3 is fixed by a bracket, and the output shaft is rigidly connected to the elliptical disk 44 to ensure the accuracy of rotational transmission.

[0079] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen-powered unmanned aerial vehicle (UAV) with a combination of bomb and truck / absorption cooling, characterized in that, include: Power system (1), absorption cooling and power supply module, spring-loaded refrigeration module, airborne refrigerator (5) and energy management module (7); The absorption cooling and power generation module includes an absorption cooling cycle loop and an expander power generation module; Based on the output electrical energy and waste heat coolant of the power system (1); The power system (1) delivers the waste heat coolant it generates to the absorption cooling and power supply module through pipelines. The absorption cooling and power supply module provides cooling capacity to the airborne refrigerator (5) based on the waste heat coolant. The expander power generation module in the absorption cooling and power supply module generates electricity based on the waste heat coolant. The electricity and the output electricity of the power system (1) are combined through the energy management module (7) to jointly drive the cooling of the cartridge cooling module. The absorption refrigeration cycle includes: a generator (211), a condenser (214), a first throttle valve (215), an evaporator (216), and an absorber (217); the generator (211), the condenser (214), the first throttle valve (215), the evaporator (216), and the absorber (217) are connected in sequence; The expander power generation module includes: an expander (221) and a generator (222); the expander (221) and the generator (222) are poweredly connected; The refrigerant outlet of the generator (211) is connected to the working fluid inlet of the expander (221) and the refrigerant inlet of the condenser (214) via the first diverting three-way valve (61); the refrigerant inlet of the absorber (217) is connected to the working fluid outlet of the expander (221) and the refrigerant outlet of the evaporator (216). A heat exchanger (218) and a solution pump (213) are provided between the absorber (217) and the generator (211), and a second throttle valve (212) is provided on the bypass pipeline between the generator (211) and the absorber (217). The spring-loaded cooling module includes: a left-side casing (416), a right-side casing (426), a rotary motor (3), and an elliptical disk (44). The left casing (416) and the right casing (426) are symmetrically arranged on both sides of the elliptical disk (44). The output shaft of the rotary motor (3) is fixed coaxially with the elliptical disk (44). The rotation of the rotary motor (3) drives the elliptical disk (44) to rotate synchronously. The rotation of the elliptical disk (44) drives the loading or unloading of the springs in the left casing (416) and the right casing (426). By controlling the springs, the springs undergo phase change to achieve heat absorption and heat release. Cooling is achieved during the heat absorption and heat release process.

2. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 1, characterized in that, The combined cooling and power supply module includes: waste heat coolant generated by the power system (1) is transmitted to the hot side of the generator (211) through pipelines to heat the solution in the generator (211) and generate high-temperature refrigerant vapor; during the high-power operation phase of the UAV takeoff or landing that meets preset requirements, the refrigerant vapor enters the expander (221) through the first diversion three-way valve (61) to drive its operation; under the drive of the operating expander (221), the generator (222) generates electricity and transmits the electrical energy to the rotary motor (3) in the refrigeration module; During the drone's cruise operation, refrigerant vapor enters the condenser (214) through the first diverting three-way valve (61) and is condensed into liquid refrigerant. After being throttled and depressurized by the first throttling valve (215), it is sent to the evaporator (216) for heat exchange. After absorbing heat and evaporating, it returns to the absorber (217). The absorbent liquid in the absorber (217) is preheated by the heat exchanger (218) under the action of the solution pump (213) and then sent to the generator (211) for recycling. The second throttling valve (212) is used to adjust the bypass solution flow rate and stabilize the circulation pressure.

3. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 1, characterized in that, The left side casing (416) includes: a left inner water outlet (4151), a left outer water outlet (4152), a left inner water inlet (4141), a left outer water inlet (4142), a left inner spring (412), a left outer spring (411), and a left piston (413); wherein, the left piston (413) divides the heat exchange channel of the left side casing (416) into an inner region and an outer region; a left inner spring (412) is provided in the inner region, and a left outer spring (411) is provided in the outer region. The right-side casing (426) includes: a right-side outer water inlet (4251), a right-side inner water inlet (4252), a right-side inner water outlet (4241), a right-side outer water outlet (4242), a right-side inner spring (422), a right-side outer spring (421), and a right-side piston (423); wherein, the right-side piston (423) divides the heat exchange channel of the right-side casing (426) into an inner region and an outer region; a right-side inner spring (422) is provided in the inner region, and a right-side outer spring (421) is provided in the outer region. The elliptical disk (44) rotates synchronously with the rotary motor (3), thereby driving the pistons in the two side housings to perform linear reciprocating motion, so that the inner and outer springs alternately enter the loading and unloading state; when the inner spring is loaded, the outer spring is unloaded; when the inner spring is unloaded, the outer spring is loaded. The left inner outlet (4151) is connected to the right outer inlet (4251); the left outer outlet (4152) is connected to the right inner inlet (4252); The right outer outlet (4242) and the right inner outlet (4241) are respectively connected to the two inlet ends of the right four-way reversing valve (65). The two outlet ends of the right four-way reversing valve (65) are respectively connected to the inlet end of the right three-way valve (64) and one end of the right natural convection cooler (432). The other end of the right natural convection cooler (432) is connected to the other inlet end of the right three-way valve (64). The outlet end of the right three-way valve (64) is connected to the inlet of the airborne refrigerator heat exchanger (51). Connect the outlet of the airborne refrigerator heat exchanger (51) to the inlet of the left three-way valve (63); connect the two outlets of the left three-way valve (63) to the inlet of the left four-way reversing valve (62) and one end of the left natural convection cooler (431); connect the other end of the left natural convection cooler (431) to the other inlet of the left four-way reversing valve (62); connect the two outlets of the left four-way reversing valve (62) to the left inner inlet (4141) and the left outer inlet (4142) respectively.

4. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 3, characterized in that, The operation of the cartridge cooling module includes a high-power phase that meets preset requirements and a stable cruise phase that meets preset requirements. During the high-power stage that meets the preset requirements, the generator (222) of the expander power generation module and the power system (1) are controlled by the first diversion three-way valve (61) to provide power to the rotary motor (3) of the UAV rotor, while the absorption cooling cycle loop is closed. During the stable cruise phase that meets the preset requirements, the power system (1) provides electrical energy to the rotary motor (3) of the UAV rotor by controlling the first diversion three-way valve (61), shuts down the expander power generation module, and simultaneously opens the absorption cooling cycle loop.

5. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 3, characterized in that, The cartridge cooling module includes: When the right inner spring (422) is unloaded and the right outer spring (421) is loaded, and the left inner spring (412) is unloaded and the left outer spring (411) is loaded, the hot water output from the airborne refrigerator heat exchanger (51) is connected to the left three-way valve (63), and is equally distributed into two water flows. One flow flows into the left natural convection cooler (431) to be cooled into cold water, and the other flow remains hot water and flows directly into the left four-way reversing valve (62). The left four-way reversing valve (62) sends the cold water into the left outer inlet (4142), and the cold water flows through the left When the outer side spring (411) is applied, it absorbs the heat released by the spring loading and heats up to become hot water. After flowing out from the outer left outlet (4152), it is connected to the inner right inlet (4252). At this time, the inner right spring (422) unloads and absorbs heat. After the hot water flows through the inner right spring (422), it is cooled to become cold water and flows out from the inner right outlet (4241). Through the right four-way reversing valve (65) and the right three-way valve (64), the cold water is directly transported to the inlet side of the airborne refrigerator heat exchanger (51) through the pipeline, and heat exchange and cooling are carried out in the airborne refrigerator heat exchanger (51). The hot water supplied by the left four-way reversing valve (62) is sent into the left inner inlet (4141). When the hot water flows through the left inner spring (412), it is unloaded by the spring and cooled into cold water. It flows out from the left inner outlet (4151) and then into the right outer inlet (4251). The cold water flows through the right outer spring (421) and gets heated into hot water. It flows out from the right outer outlet (4242). The hot water is cooled into cold water by the right natural convection cooler (432) through the right four-way reversing valve (65). Then, the cold water is delivered to the inlet side of the airborne refrigerator heat exchanger (51) through the right three-way valve (64) for heat exchange and cooling in the airborne refrigerator heat exchanger (51). When the inner spring switches to the loading state and the outer spring switches to the unloading state, the water flow distributed by the left three-way valve (63) remains equal. One stream is cooled by the left natural convection cooler (431) and then sent to the left inner inlet (4141) through the left four-way reversing valve (62). After absorbing the heat released by the loading of the left inner spring (412) and heating up, the water flows into the right outer spring (421) and is cooled into cold water. It then flows out from the right outer outlet (4242) and is directly transported to the airframe through the pipeline via the right four-way reversing valve (65) and the right three-way valve (64). The water inlet side of the refrigerator heat exchanger (51) is used for heat exchange and cooling in the airborne refrigerator heat exchanger (51); another hot water distributed by the left three-way valve (63) is directly sent to the left outer spring (411) through the left four-way reversing valve (62), and after cooling, it flows into the right inner spring (422), where it is heated to become hot water. It is then cooled to cold water by the right natural convection cooler (432) through the right four-way reversing valve (65), and then transported to the water inlet side of the airborne refrigerator heat exchanger (51) through the right three-way valve (64) for heat exchange and cooling in the airborne refrigerator heat exchanger (51).

6. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 3, characterized in that, The left outer spring (411), the left inner spring (412), the right outer spring (421), and the right inner spring (422) are all helical spring structures made of shape memory alloy and embedded in the heat exchange channel of the corresponding chassis area. The inner wall of the heat exchange channel is treated with anti-corrosion.

7. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 1, characterized in that, The power system (1) uses hydrogen power and includes a hybrid power system consisting of an ammonia-hydrogen hybrid engine and a PEMFC stack.

8. The combined cooling and power supply system for the cold chain compartment of a medium-to-large hydrogen UAV according to claim 1, characterized in that, The system also includes a control module; the control module is used to adjust the valve group opening and closing and fluid flow distribution according to the loading / unloading status of the spring group and the operating conditions of the UAV, so as to realize the switching control between the high-power stage and the stable cruise stage.

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