A manned spacecraft multi-type micro-nano satellite on-orbit release method and device

Abstract

The present application relates to aerospace vehicle technical field, provide a kind of manned spacecraft multi-type micro-nano satellite on-orbit release method, comprising: S1: micro-nano satellite is sent up to manned spacecraft with cargo spaceship;S2: according to task demand, release device component is assembled into micro-satellite release device configuration or cubic star release device configuration on workbench, micro-nano satellite is filled into release device;S3: release device filled with micro-nano satellite is installed to load transfer mechanism, executes cargo automatic egress procedure, and release device is transferred to cabin outside by load transfer mechanism along with micro-nano satellite through airlock cabin;S4: mechanical arm is grabbed release device from airlock cabin egress opening and makes it separate from load transfer mechanism, and micro-nano satellite is released into orbit after release device receives instruction;S5: after release is completed, mechanical arm sends release device back to airlock cabin egress position and is reconnected after load transfer mechanism, and withdraws;S6: astronaut separates release device from load transfer mechanism.

Description

Technical Field

[0001] This invention relates to the technical field of aerospace vehicles, and in particular to a method and apparatus for on-orbit release of multiple types of micro-nano satellites from a manned spacecraft. Background Technology

[0002] With the continuous breakthroughs in global aerospace technology and the deepening of commercialization, significant progress has been made in commercial-grade space components, new materials, and satellite miniaturization technology. Driven by this technological evolution, microsatellites and nanosatellites (typically referring to satellites weighing less than 100 kg) have rapidly emerged due to their unique advantages, with increasingly widespread on-orbit applications and a significant increase in their number. Compared to traditional large satellites, microsatellites and nanosatellites have outstanding characteristics such as lower development costs, shorter development cycles, ease of standardization and modular design, and rapid technological updates. Leveraging these advantages, microsatellites and nanosatellites have become important carriers for space science experiments and technology verification, widely serving multidisciplinary research and cutting-edge technology exploration. Specific applications cover key areas such as space situational awareness, space environment monitoring and detection, high-resolution Earth observation, on-orbit verification of new space materials, and research on the biological effects of space radiation. In particular, the gradual maturation of commercial-grade space components and materials has further lowered the development threshold for microsatellites and nanosatellites, laying a solid material and technological foundation for their large-scale constellation deployment and routine on-orbit application.

[0003] Currently, while there are numerous methods for launching and deploying microsatellites and nanosatellites, they can be broadly categorized into two main types. The first type utilizes a launch vehicle and its accompanying upper stage to directly transport the microsatellite or nanosatellite as the primary or secondary payload to a predetermined target orbit, achieving a one-time deployment. The second type employs space transportation platforms such as cargo spacecraft, releasing the microsatellite or nanosatellite into orbit at a specific altitude during docking with a space station or target spacecraft via a release mechanism carried by the spacecraft or by astronauts. These two methods constitute the primary technological means for microsatellites and nanosatellites to enter space, and to a certain extent, meet the growing demand for satellite launches.

[0004] However, in-depth analysis reveals that the existing methods for launching and deploying microsatellites and nanosatellites still suffer from numerous deep-seated technical flaws and application limitations. Firstly, in terms of cost and resource utilization, both rocket-borne launches and cargo spacecraft releases are typical "one-off" missions. The release adapters or dedicated deployment devices used are usually discarded upon mission termination, making them difficult to recover and reuse, resulting in high per-launch costs. Simultaneously, existing methods fail to fully leverage the comprehensive resource advantages of manned spacecraft, a scarce space platform. In particular, advanced equipment such as airlocks, extravehicular robotic arms, and payload transfer mechanisms, which are equipped on manned spacecraft, have low participation rates in routine launch missions, and the efficiency of onboard resource utilization needs improvement. Secondly, regarding mission flexibility and adaptability, existing launch schemes typically employ fixed adapter interfaces and release mechanisms. When facing different types (such as microsatellites and CubeSats) and different sizes (such as 1U to 6U) of microsatellites and nanosatellites, it is often necessary to redevelop dedicated interfaces or replace the entire release device, making it difficult to achieve "one machine for multiple uses" and rapid mission switching, significantly limiting the response speed and adaptability of launch missions. Furthermore, from the perspective of microsatellite design, in existing launch methods, satellites must withstand extremely harsh dynamic environments (including severe vibrations, shocks, and overloads) during the ascent phase. To ensure structural integrity, microsatellites must incorporate additional reinforcing structures and mechanically resistant components. This directly leads to an unnecessary increase in the satellite's mass and volume, encroaching on already limited payload mass and installation space, thus weakening the economic viability and payload capacity of microsatellites. In addition, existing launch methods typically solidify all satellite states before launch. Once the satellite enters orbit and malfunctions or components fail, ground control systems often struggle to provide on-orbit intervention and hardware-level repairs, increasing the risk of mission failure.

[0005] In summary, given the significant shortcomings of existing microsatellite launch methods in terms of cost control, mission flexibility, resource utilization, and satellite mass optimization, there is an urgent need to propose a novel on-orbit release method for microsatellites that can fully leverage the advantages of manned spacecraft platforms and the on-orbit operational capabilities of astronauts. This method should possess reusable release devices, allowing astronauts to flexibly assemble and modify the satellite into either a microsatellite or CubeSat configuration on-orbit according to specific mission requirements. It should also support the transfer of microsatellites to manned spacecraft via cargo spacecraft, where astronauts can complete satellite loading, status setup, and self-testing operations within the sealed cabin. Through this systematic innovation, the aim is to significantly reduce the cost of a single on-orbit release of microsatellites, lower the economic and technological barriers to entry for microsatellites into space, and leverage the unique on-orbit environment provided by manned spacecraft, including long-term microgravity, extreme high and low temperature alternation, and space radiation, to provide a space flight verification platform closer to real-world application scenarios for novel devices, materials, and processes carried on microsatellites. This will powerfully promote the efficient, low-cost, and sustainable development of microsatellite technology. Summary of the Invention

[0006] To address the aforementioned problems, the present invention aims to provide a method and apparatus for on-orbit release of various types of micro- and nano-satellites from manned spacecraft.

[0007] The above-mentioned objective of this invention is achieved through the following technical solutions: A method for on-orbit release of multiple types of micro-nano satellites from a manned spacecraft includes the following steps: S1: Ascent and Preparation: The micro-nano satellite will be ascended to the manned spacecraft aboard the cargo spacecraft, where the astronauts will transfer the micro-nano satellite into the sealed cabin and perform a self-test. S2: Release device self-inspection and assembly: Astronauts take out the scattered release device components, perform a self-inspection on the release device, and assemble the release device components into a microsatellite release device configuration or a CubeSat release device configuration on the workbench according to mission requirements. Then, they fill the microsatellite and nanosatellite into the release device and set its status. S3: Install and exit the cabin: The astronauts install the release device containing the micro-nano satellite onto the payload transfer mechanism, execute the automatic cargo exit procedure, and the payload transfer mechanism transfers the release device along with the micro-nano satellite to the outside of the cabin through the airlock. S4: Robotic arm release: The robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism. The release device is transferred outside the cabin and its position is adjusted to meet the release and launch orientation. After receiving the command, the release device releases the micro-nano satellite into orbit. S5: Recovery into the cabin: After the release is completed, the robotic arm will send the release device back to the airlock exit position and reconnect it with the load transfer mechanism before withdrawing. The automatic cargo entry procedure will be executed, and the release device will return to the sealed cabin through the airlock. S6: Disassembly and Storage: The astronauts separate the release device from the payload transfer mechanism and disassemble the release device into its components, storing them in a storage box for future reuse.

[0008] Furthermore, in step S1, the specific method by which the micro-nano satellite is transported to the manned spacecraft aboard the cargo spacecraft is as follows: Microsatellites are loaded into standard cargo bags during cargo spacecraft launch and secured securely inside the cargo bags to reduce the impact of vibration and shock during launch. This allows microsatellites to eliminate the need for reinforcement structures to resist mechanical environments, saving the mass and volume of the microsatellite itself. The specific method for the microsatellite to perform self-check is as follows: the astronauts transport the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, and perform a self-check on the microsatellite inside the sealed cabin to ensure that all functions and performance of the microsatellite are in good working order before release. If necessary, the astronauts can perform on-orbit repairs or replace parts of the microsatellite.

[0009] Furthermore, in step S2, the specific method for the self-test of the release device is as follows: after the astronaut takes out the release device component on the workbench inside the cabin, he performs a self-test on the release device through the release device controller to confirm that all functions of the release device are normal. The specific method for assembling the microsatellite release device configuration according to mission requirements is as follows: the astronauts take out the release device back plate, release device base plate, base plate connecting mechanism active end and microsatellite release unit stored separately in the sealed cabin, and complete the assembly to form the microsatellite release device configuration on the workbench in the cabin. After assembly, the astronauts transfer the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the microsatellite installation tool to connect the microsatellite to the microsatellite release unit, and set the status of the microsatellite through the operation interface on the release device. The specific method for assembling the CubeSat release device configuration according to mission requirements is as follows: astronauts take out the release device backplate, release device base plate, base plate connecting mechanism active end, and CubeSat release unit, which are stored separately in the sealed cabin, and assemble them on the workbench inside the cabin to form the CubeSat release device configuration. After assembly, the astronauts transfer the CubeSat from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the CubeSat installation tool to fill the CubeSat release unit and press it tightly, and set the status of the CubeSat through the operation interface on the release device.

[0010] Furthermore, in step S3, the specific method by which the astronaut installs the release device containing the micro-nano satellite onto the payload transfer mechanism is as follows: The astronauts opened the airlock cabin door, and the ground requested the payload transfer mechanism to extend into the sealed cabin. The astronauts installed the passive end of the base plate connection mechanism on the payload transfer mechanism and installed the release device containing the micro-nano satellites onto the passive end of the payload transfer mechanism. The specific method for executing the automatic cargo exit procedure is as follows: the payload transfer mechanism retracts into the airlock, the astronauts close the inner hatch and check for leaks in the inner hatch, after the leak check is normal, the airlock is reused and depressurized, after the airlock is depressurized, the outer hatch is opened, and the payload transfer mechanism carrying the release device extends to the position of the outer hatch of the airlock, realizing the exit of the micro-nano satellite together with the release device.

[0011] Further, in step S4, the specific method by which the robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism is as follows: the robotic arm moves to the position to be grabbed outside the cabin through path planning; after the load transfer mechanism extends, the robotic arm grabs the release device through the robotic arm target adapter, thereby separating the release device from the load transfer mechanism. The specific method for transferring the release device to the outside of the cabin and adjusting its position is as follows: the robotic arm transfers the release device to a designated position outside the cabin and adjusts the position of the robotic arm so that the release device meets the release and launch orientation. The specific method by which the release device releases the microsatellite into orbit after receiving the command is as follows: the command is sent by ground request or by the astronaut, the controller of the microsatellite release device or CubeSat release device receives the telemetry and control command, drives the microsatellite release unit or CubeSat release unit to perform the release action, and completes the on-orbit separation of the microsatellite or CubeSat.

[0012] Furthermore, in step S5, the specific method of recycling into the chamber is as follows: After the microsatellite or CubeSat is released, the robotic arm grabs the release device and transfers it back to the airlock exit position. The release device is then installed on the payload transfer mechanism and connected. The robotic arm releases the release device at its end and withdraws. The outer hatch of the airlock is closed and leaks are checked. After the leaks are detected and approved, the airlock is repressurized. After repressurization, the astronauts open the inner hatch, and the payload transfer mechanism rotates 90° and extends into the sealed cabin, allowing the release device to return to the sealed cabin via the airlock.

[0013] Furthermore, in step S6, the specific method of disassembling and storing is as follows: Inside the sealed cabin, the astronauts remove the microsatellite release device or CubeSat release device from the payload transfer mechanism. They then disassemble the release device backplate, release device base plate, microsatellite release unit or CubeSat release unit, and the active end of the base plate connection mechanism. The disassembled components are placed in storage boxes to save storage space. The storage boxes are then placed in the designated storage location within the manned spacecraft's sealed cabin for reassembly and reuse during the next on-orbit release mission.

[0014] An on-orbit release device for manned spacecraft multi-type micro-nano satellites for performing the on-orbit release method for manned spacecraft as described above, comprising: The sealed cabin of a manned spacecraft serves as the mounting base for all its components; An airlock, connected to the sealed compartment, is used to provide a transition passage for cargo to enter and exit the compartment. It has an openable and closable inner and outer hatch and is capable of leak detection, depressurization and repressurization operations. A load transfer mechanism, located inside the airlock, can extend into the sealed compartment or out of the airlock to carry and transfer the release device; The release device includes a detachable and assembleable release device back plate, a release device base plate, an active end of the base plate connecting mechanism, a passive end of the base plate connecting mechanism, a release device controller, and a robotic arm target adapter. The release device can be assembled into a microsatellite release device configuration or a CubeSat release device configuration according to mission requirements. The workbench, located inside the sealed cabin of the manned spacecraft, has limit screw holes and serves as an assembly station for installing the base plate connection mechanism and providing a release device. An external robotic arm, one end of which is fixed to the robotic arm base of the payload compartment, and the other end of which grasps the release device through the robotic arm target adapter, is used to transfer the release device to the release position or send the release device back to the outside of the airlock compartment. Furthermore, when the release device is assembled into a microsatellite release device configuration, it is composed of a release device back plate, a release device base plate, an active end of the base plate connecting mechanism, a release device controller, a robotic arm target adapter, and a microsatellite release unit. The release device back plate and the release device base plate are fixedly connected to each other. The microsatellite release unit is installed on the release device back plate. The release device controller is electrically connected to the microsatellite release unit and controls its release action. The microsatellite release unit is interconnected and constrained with the microsatellite. The microsatellite release device can release microsatellites not exceeding 1000mm×500mm×700mm and can release microsatellites weighing 10~200kg.

[0015] Furthermore, when the release device is assembled into a cubestar release device configuration, it comprises a release device back plate, a release device base plate, an active end of the base plate connecting mechanism, a release device controller, a robotic arm target adapter, and a cubestar release unit. The release device back plate and the release device base plate are fixedly connected to each other. The cubestar release unit is mounted on the release device back plate. The release device controller is electrically connected to the cubestar release unit and controls its release action. The cubestar is filled into the cubestar release unit, and the cubestar release device is capable of releasing... The device can release cubes of different sizes: 1U, 1.5U, 2U, 3U, and 6U. The 1U cubes are approximately 100mm × 100mm × 100mm in size. The back plate of the cube release device has two cube release units, with release stations for 3U and 6U cubes. The cube release device can release up to 36U cubes at a time. The 3U cube release units can be combined in three ways: three 1U cubes, two 1.5U cubes, and one 1U cube and one 2U cube.

[0016] Compared with the prior art, the present invention has at least one of the following beneficial effects: (1) The release device is reusable and can be flexibly configured, which significantly reduces launch costs and improves mission adaptability. In this invention, both the microsatellite release device and the CubeSat release device adopt a modular and detachable design. After the release mission is completed, astronauts can disassemble the device into individual components and store them in a storage box for reassembly and use in the next mission. The release device can be stored long-term inside the manned spacecraft cabin, and a single device can support multiple release missions, avoiding the drawback of traditional disposable release devices that are discarded after the mission ends. Furthermore, the release device can be assembled in orbit into a microsatellite release device configuration or a CubeSat release device configuration according to mission requirements. The microsatellite release device can release microsatellites weighing 10-200 kg, while the CubeSat release device can release CubeSats of different sizes from 1U to 6U, with a maximum release capacity of 36U at a time. Compared with traditional methods, there is no need to develop dedicated interfaces for different satellite sizes or replace the entire release device, thus achieving both cost savings and mission flexibility.

[0017] (2) Make full use of existing manned spacecraft platform resources, without the need for additional dedicated launch resources. This invention utilizes the existing airlock, payload transfer mechanism, and extravehicular robotic arm of manned spacecraft to complete the on-orbit release of micro- and nano-satellites. The payload transfer mechanism, via the airlock, enables the automatic release and return of the release device containing the satellite. The extravehicular robotic arm completes the grasping, transfer, pointing, and retrieval of the release device. No additional dedicated launch device or launch vehicle is required, achieving efficient reuse of manned spacecraft platform resources and further lowering the threshold for micro- and nano-satellites to enter space.

[0018] (3) Give full play to the advantages of astronauts in on-orbit operation and improve mission reliability and support capabilities. In this invention, astronauts are deeply involved in the entire on-orbit release process, including transferring the microsatellites from the cargo spacecraft to the sealed cabin, assembling the release device, loading the microsatellites and setting their status, installing them onto the payload transfer mechanism, and disassembling and storing them after release. Simultaneously, the microsatellites can be loaded into standard cargo packages and securely secured during the ascent with the cargo spacecraft, effectively reducing the impact of launch vibrations and shocks. This allows the satellite body to eliminate the need for anti-mechanical reinforcement structures, saving mass and volume. After the satellite is transported to the manned spacecraft, it can also perform self-checks within the sealed cabin. If necessary, astronauts can perform on-orbit repairs or replace components, effectively reducing the risk of mission failure and improving the overall reliability and support capabilities of the microsatellite release mission. Attached Figure Description

[0019] Figure 1 This is a structural diagram of the manned spacecraft's on-orbit release configuration according to the present invention; Figure 2 This is a structural diagram of the microsatellite release device of the present invention; Figure 3 This is a structural diagram of the CubeSat release device of the present invention; Figure 4 This is a diagram of the microsatellite release device and microsatellite structure of the present invention; Figure 5 This is a structural diagram showing the distribution of the release stations for the 3U and 6U CubeSats of the present invention; Figure 6 This is a structural diagram of the combination method of the 3U CubeSat specification of the present invention; Figure 7 This is a schematic diagram of the on-orbit connection of the microsatellite of the present invention; Figure 8 This is a structural diagram of the microsatellite release device mounted on the load transfer mechanism of the present invention; Figure 9 This is a schematic diagram of the CubeSat loading process in orbit according to the present invention; Figure 10 This is a structural diagram of the back plate on which the release device is installed on the load transfer mechanism of the present invention; Figure 11 This is a structural diagram of the CubeSat release unit mounted on the load transfer mechanism of the present invention; Figure 12 This is a structural diagram of the load transfer mechanism of the present invention, showing the release device extending outside the airlock chamber; Figure 13 This is a diagram showing the attitude structure of the micro-nano satellite released in orbit by the manned spacecraft according to the present invention. Figure 14 This is a flowchart illustrating the on-orbit release process of the manned spacecraft according to the present invention.

[0020] Figure Labels 1-Sealed chamber; 2-Airlock chamber; 3-Load transfer mechanism; 4-Robotic arm; 5-Robotic arm base; 6-Robotic arm target adapter; 7-Workbench; 8-Release device backplate; 9-Release device baseplate; 10-Baseplate connection mechanism active end; 11-Baseplate connection mechanism passive end; 12-Release device controller; 13-Microsatellite release unit; 14-CubeSat release unit; 15-Microsatellite release device; 16-CubeSat release device; 17-Microsatellite; 18-CubeSat. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0022] Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0023] First Embodiment This embodiment provides a manned spacecraft multi-type micro-nano satellite on-orbit release method and a manned spacecraft multi-type micro-nano satellite on-orbit release device, such as... Figure 1 As shown, it mainly includes a manned spacecraft sealed cabin 1, an airlock cabin 2, a robotic arm 4, a robotic arm base 5, and a release device. One end of the manned spacecraft robotic arm 4 is fixed to the robotic arm base 5 of the sealed cabin 1, and the other end is used to grasp the release device, realizing the transfer and attitude adjustment of the release device.

[0024] Specifically, the device includes: The sealed cabin 1 of the manned spacecraft serves as the mounting base for all its components; Airlock 2, connected to the sealed compartment 1, is used to provide a transition passage for cargo to enter and exit the compartment. It has an openable and closable inner and outer door and is capable of leak detection, depressurization and repressurization operations. The load transfer mechanism 3 is installed inside the airlock 2 and can extend into or out of the airlock to carry and transfer the release device. The release device includes a detachable and assembleable release device back plate 8, a release device base plate 9, an active end 10 of the base plate connecting mechanism, a passive end 11 of the base plate connecting mechanism, a release device controller 12, and a robotic arm target adapter 6. The release device can be assembled into a microsatellite release device 15 configuration or a CubeSat release device 16 configuration according to mission requirements. Workbench 7, located inside the sealed cabin of the manned spacecraft, has limit screw holes and is used to install the base plate connection mechanism and provide an assembly station for releasing the device; The external robotic arm 4 has one end fixed to the robotic arm base 5 of the payload compartment 1, and the other end grasps the release device through the robotic arm target adapter 6, which is used to transfer the release device to the release position or send the release device back to the outside of the airlock compartment. Furthermore, when the release device is assembled into the configuration of the microsatellite release device 15, such as Figure 2 As shown, the device is assembled from a release device backplate 8, a release device base plate 9, a base plate connecting mechanism active end 10, a release device controller 12, a robotic arm target adapter 6, and a microsatellite release unit 13. The release device backplate 8 and the release device base plate 9 are fixedly connected to each other. The microsatellite release unit 13 is mounted on the release device backplate 8. The release device controller 12 is electrically connected to the microsatellite release unit 13 and controls its release action. The microsatellite release unit 13 and the microsatellite 17 are interconnected and constrained (e.g., ...). Figure 4 The microsatellite release device 15 is capable of releasing microsatellites of no more than 1000mm×500mm×700mm and of weighing 10~200kg.

[0025] Furthermore, when the release device is assembled into a cubestar release device 16 configuration, such as Figure 3 As shown, the device is assembled from a release device back plate 8, a release device base plate 9, a base plate connecting mechanism active end 10, a release device controller 12, a robotic arm target adapter 6, and a cubesat release unit 14. The release device back plate 8 and the release device base plate 9 are fixedly connected to each other. The cubesat release unit 14 is mounted on the release device back plate 8. The release device controller 12 is electrically connected to the cubesat release unit 14 and controls its release action. The cubesat 18 are filled into the cubesat release unit 14, as shown. Figure 5 As shown, the cubestar release device 16 can release cubestars of different sizes: 1U, 1.5U, 2U, 3U, and 6U. The 1U cubestar is approximately 100mm × 100mm × 100mm. Two cubestar release units 14 are mounted on the back plate 8 of the device, with release stations for 3U and 6U cubestars. The cubestar release device 16 can release a maximum of 36U cubestars at a time, and the 3U cubestar release units have three combination methods (e.g., ...). Figure 6As shown): 3 combinations of 1U cube stars, 2 combinations of 1.5U cube stars, and 1 combination of 1U cube star and 1 2U cube star.

[0026] The microsatellite in-orbit filling process is as follows Figure 7 As shown, the astronauts install the microsatellite 17 into the microsatellite release unit 13 of the microsatellite release device 15 on the workbench. After installation, as shown... Figure 8 As shown, the astronauts install the microsatellite release device 15 (including microsatellite 17) onto the payload transfer mechanism 3. During the CubeSat release mission, the on-orbit loading process of the CubeSat is as follows: Figure 9 As shown, the astronauts loaded CubeSat 18 into CubeSat release unit 14 and tightened it on the workbench. Figure 10 As shown, the astronauts install the release device backplate 8 on the payload transfer mechanism 3, as... Figure 11 As shown, the CubeSat release unit 14 (including CubeSat 18) is then installed onto the CubeSat release device 16, completing the installation of the CubeSat release device 16 on the load transfer mechanism 3.

[0027] After the microsatellite release device 15 or the CubeSat release device 16 is installed, as follows: Figure 12 As shown, the load transfer mechanism 3, carrying the release device, extends outside the airlock. The robotic arm 4, outside the airlock, moves to the desired gripping position via path planning and grips the release device, then moves it to the designated release position outside the airlock (see...). Figure 13 ), and perform the release action.

[0028] Second Embodiment like Figure 14 As shown, this embodiment provides a method for the on-orbit release of multiple types of micro- and nano-satellites from a manned spacecraft, including the following steps: S1: Ascent and Preparation: The microsatellite will be ascended to the manned spacecraft aboard the cargo spacecraft, where the astronauts will transfer the microsatellite into the sealed cabin and perform a self-test.

[0029] In step S1, the specific method by which the micro-nano satellite is transported to the manned spacecraft aboard the cargo spacecraft is as follows: Microsatellites are loaded into standard cargo bags during cargo spacecraft launch and secured securely inside the cargo bags to reduce the impact of vibration and shock during launch. This allows microsatellites to eliminate the need for reinforcement structures to resist mechanical environments, saving the mass and volume of the microsatellite itself. The specific method for the microsatellite to perform self-check is as follows: the astronauts transport the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, and perform a self-check on the microsatellite inside the sealed cabin to ensure that all functions and performance of the microsatellite are in good working order before release. If necessary, the astronauts can perform on-orbit repairs or replace parts of the microsatellite.

[0030] In step S1, the microsatellite enters the manned spacecraft via a cargo spacecraft ascent. Before launch, it is loaded into a standard cargo package and securely fastened, effectively reducing the impact of the severe vibrations and shocks generated during the launch phase on the satellite's structure. Because the cargo spacecraft provides a gentler transport environment than the launch vehicle, and the standard cargo package itself has excellent vibration damping and protection, the microsatellite does not require additional mechanical reinforcement structures as in traditional launch methods. This significantly saves the satellite's mass and volume resources, allowing more of the limited space and weight to be allocated to the payload, improving the overall efficiency and economy of the microsatellite. Furthermore, after arriving at the manned spacecraft with the cargo spacecraft, the microsatellite is not directly released into orbit. Instead, astronauts first transfer it from the cargo spacecraft to the sealed cabin of the manned spacecraft, where a comprehensive on-orbit self-test is conducted in the suitable environment of the cabin to confirm that its functions and performance remain intact after the launch and ascent process. Once the self-inspection detects any abnormalities or malfunctions, the astronauts can fully utilize their on-orbit operational advantages, using the tools and spare parts provided in the sealed cabin to repair or replace faulty components of the microsatellite, ensuring the satellite is in optimal working condition before being released into orbit. This "first launch, then self-inspection, then repairability" model, compared to the conventional launch method where all satellite states are solidified before launch and cannot be intervened after entering orbit, significantly reduces the risk of mission failure and improves the overall reliability and support capabilities of microsatellite release missions.

[0031] S2: Release device self-inspection and assembly: Astronauts take out the scattered release device components, perform a self-inspection on the release device, and assemble the release device components into a microsatellite release device configuration or a CubeSat release device configuration on the workbench according to mission requirements. Then, they fill the microsatellite into the release device and set its status.

[0032] In step S2, the specific method of the release device self-test is as follows: after the astronaut takes out the release device component on the workbench inside the cabin, he performs a self-test on the release device through the release device controller to confirm that all functions of the release device are normal. The specific method for assembling the microsatellite release device configuration according to mission requirements is as follows: the astronauts take out the release device back plate, release device base plate, base plate connecting mechanism active end and microsatellite release unit stored separately in the sealed cabin, and complete the assembly to form the microsatellite release device configuration on the workbench in the cabin. After assembly, the astronauts transfer the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the microsatellite installation tool to connect the microsatellite to the microsatellite release unit, and set the status of the microsatellite through the operation interface on the release device. The specific method for assembling the CubeSat release device configuration according to mission requirements is as follows: astronauts take out the release device backplate, release device base plate, base plate connecting mechanism active end, and CubeSat release unit, which are stored separately in the sealed cabin, and assemble them on the workbench inside the cabin to form the CubeSat release device configuration. After assembly, the astronauts transfer the CubeSat from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the CubeSat installation tool to fill the CubeSat release unit and press it tightly, and set the status of the CubeSat through the operation interface on the release device.

[0033] In step S2, the release device is stored in the sealed cabin of the manned spacecraft as distributed components during its on-orbit operation. This design saves valuable storage space within the cabin and facilitates long-term preservation and management. When a release mission is required, the astronauts first remove each component and perform a self-test on the device via the release device controller to ensure that each component functions normally and that electrical connections are reliable, avoiding potential malfunctions caused by long-term on-orbit storage that could affect mission execution. Subsequently, the astronauts flexibly choose to assemble either a microsatellite release device configuration or a CubeSat release device configuration according to the specific requirements of the mission. Both configurations are assembled based on the same set of standardized interface components—namely, the release device backplate, the release device baseplate, and the active end of the baseplate connection mechanism—and only require replacing the corresponding release unit (microsatellite release unit or CubeSat release unit) to achieve the release capability of microsatellites and nanosatellites of different sizes, fully demonstrating the modular design and multi-functional technical advantages of the device. After assembly, the astronauts transfer the microsatellites from the cargo spacecraft to the sealed cabin, use the corresponding installation tools to connect or load them into the release unit, and set the satellite's status through the operating interface on the release device to ensure that the release parameters, separation sequence, and control commands all meet mission requirements. The entire S2 step achieves a flexible release mode of "one machine for multiple uses, ready to use immediately after installation," providing efficient and reliable technical support for manned spacecraft to deploy different types and specifications of microsatellites on demand in orbit.

[0034] S3: Install and exit the cabin: The astronauts install the release device containing the micro-nano satellite onto the payload transfer mechanism, execute the automatic cargo exit procedure, and the payload transfer mechanism transfers the release device along with the micro-nano satellite to the outside of the cabin via the airlock.

[0035] In step S3, the astronaut installs the release device containing the micro-nano satellite onto the payload transfer mechanism in the following specific manner: The astronauts opened the airlock cabin door, and the ground requested the payload transfer mechanism to extend into the sealed cabin. The astronauts installed the passive end of the base plate connection mechanism on the payload transfer mechanism and installed the release device containing the micro-nano satellites onto the passive end of the payload transfer mechanism. The specific method for executing the automatic cargo exit procedure is as follows: the payload transfer mechanism retracts into the airlock, the astronauts close the inner hatch and check for leaks in the inner hatch, after the leak check is normal, the airlock is reused and depressurized, after the airlock is depressurized, the outer hatch is opened, and the payload transfer mechanism carrying the release device extends to the position of the outer hatch of the airlock, realizing the exit of the micro-nano satellite together with the release device.

[0036] In step S3, the astronauts install the assembled and loaded release device (including microsatellites) onto the payload transfer mechanism. This installation process relies on the opening of the airlock's inner hatch and the payload transfer mechanism extending into the sealed cabin according to ground commands. The astronauts install the passive end of the base plate connecting mechanism onto the payload transfer mechanism, and then install the release device onto the passive end. The rapid engagement design of the active and passive ends of the connecting mechanism allows the astronauts to easily and reliably lock the release device and payload transfer mechanism within the limited space inside the cabin, without the need for complex tools and operations, ensuring the convenience and reliability of the installation operation. Subsequently, the system executes the automatic cargo ejection procedure. The payload transfer mechanism, carrying the release device, automatically retracts into the airlock. The astronauts close the inner hatch and perform a leak check on the inner hatch. The purpose is to reliably isolate the sealed cabin from the airlock, ensuring that the air pressure and atmospheric environment inside the sealed cabin are not affected during the airlock depressurization process, thus guaranteeing the safety of the astronauts' working environment in orbit. After leak detection is successful, the airlock is reused and depressurized. This effectively conserves precious gas resources on board the manned spacecraft and prepares for the subsequent opening of the outer hatch and the vacuum environment of outer space. Once the airlock is depressurized, the outer hatch is opened, and the payload transfer mechanism, carrying the release device, extends to the outer hatch position. This allows for the smooth and safe transfer of the release device, along with the microsatellite, from the sealed cabin to the outer space environment without affecting the normal atmospheric pressure environment of the sealed cabin. The entire S3 procedure relies on the existing cargo airlock function of the manned spacecraft. Through a standardized automated exit process of "hatch isolation - leak detection - depressurization - outer hatch opening - extension," it ensures the absolute safety of astronauts and equipment inside the sealed cabin while efficiently completing the cross-environment transfer of the microsatellite from inside to outside the cabin, fully demonstrating the mature technological advantages of the manned spacecraft platform in cargo entry and exit.

[0037] S4: Robotic arm release: The robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism. The release device is then transferred outside the cabin and its position is adjusted to meet the release and launch orientation. After receiving the command, the release device releases the micro-nano satellite into orbit.

[0038] In step S4, the specific method by which the robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism is as follows: the robotic arm moves to the position to be grabbed outside the cabin through path planning. After the load transfer mechanism extends, the robotic arm grabs the release device through the robotic arm target adapter, thereby separating the release device from the load transfer mechanism. The specific method for transferring the release device to the outside of the cabin and adjusting its position is as follows: the robotic arm transfers the release device to a designated position outside the cabin and adjusts the position of the robotic arm so that the release device meets the release and launch orientation. The specific method by which the release device releases the microsatellite into orbit after receiving the command is as follows: the command is sent by ground request or by the astronaut, the controller of the microsatellite release device or CubeSat release device receives the telemetry and control command, drives the microsatellite release unit or CubeSat release unit to perform the release action, and completes the on-orbit separation of the microsatellite or CubeSat.

[0039] In step S4, after the release device, along with the microsatellite, is transferred outside the airlock, the subsequent operations are taken over by the external robotic arm. After the payload transfer mechanism extends, the robotic arm autonomously moves along a pre-planned path to the grab position at the airlock exit. The target adapter at the end of the robotic arm cooperates with the target adapter on the release device to achieve precise capture of the release device. After capturing the release device, the robotic arm operates to disengage the active end of the release device's base plate connection mechanism from the passive end of the payload transfer mechanism, completing the separation of the release device from the payload transfer mechanism. The robotic arm continues to move with the release device, transferring it to a designated release position outside the airlock, and precisely adjusts the angles of its joints and end-effector attitude according to the predetermined release and launch orientation requirements, ensuring that the release device meets the pointing accuracy and orientation requirements for satellite release. At this point, the ground control system sends a command upon request, or the astronauts manually send a command based on the actual mission situation. Upon receiving this command, the controller on the release device drives the microsatellite or CubeSat release unit to perform unlocking and ejection actions according to the preset separation sequence, completing the separation of the microsatellite or CubeSat from the release device and allowing the microsatellite / nanosatellite to enter its predetermined orbit at the correct speed and direction. The entire S4 step fully utilizes the flexible operation and wide-range transfer capabilities of the extravehicular robotic arm, realizing the mission switch from the extravehicular release device to the satellite itself for orbital release. Simultaneously, both ground control and astronauts can intervene and control the release timing, ensuring the flexibility and reliability of the release mission.

[0040] S5: Recovery into the cabin: After the release is completed, the robotic arm will send the release device back to the airlock exit position and reconnect it with the load transfer mechanism before withdrawing. The automatic cargo entry procedure will be executed, and the release device will return to the sealed cabin through the airlock.

[0041] In step S5, the specific method of recycling into the chamber is as follows: After the microsatellite or CubeSat is released, the robotic arm grabs the release device and transfers it back to the airlock exit position. The release device is then installed on the payload transfer mechanism and connected. The robotic arm releases the release device at its end and withdraws. The outer hatch of the airlock is closed and leaks are checked. After the leaks are detected and approved, the airlock is repressurized. After repressurization, the astronauts open the inner hatch, and the payload transfer mechanism rotates 90° and extends into the sealed cabin, allowing the release device to return to the sealed cabin via the airlock.

[0042] In step S5, after the microsatellite is released into orbit, the extravehicular robotic arm immediately performs the recovery operation of the release device. The robotic arm re-grabs the release device from the extravehicular release position and transfers it back to the airlock exit position, precisely installing the release device onto the payload transfer mechanism. A locking connection is achieved through the cooperation of the active and passive ends of the base plate connection mechanism. The robotic arm then releases the release device and withdraws to a safe position, making room for the subsequent closure of the airlock. Next, the automatic cargo entry procedure is executed: First, the outer hatch of the airlock is closed, and a leak check is performed on the outer hatch. After confirming a good seal, the airlock is repressurized to restore its internal pressure to the same working pressure as the sealed cabin. This ensures that the pressure environment inside the sealed cabin is not affected when the inner hatch is opened, guaranteeing astronaut safety and a stable working environment. After repressurization, the astronauts open the inner hatch, and the payload transfer mechanism rotates 90° and extends into the sealed cabin, transferring the release device from the airlock back into the sealed cabin. This completes the entire recovery and entry operation. This step, through a standard process of "robotic arm return - hatch isolation - leak detection - repressurization - return," ensures the safe recovery of the release device from outside the cabin to inside. This not only guarantees a safe transition of the pressure difference environment inside and outside the manned spacecraft but also provides a complete closed-loop guarantee for the reuse of the release device. Through this process, a single release device can complete its entire lifecycle operation in orbit, from "ascent to exit the cabin - release - recovery - re-entry," and can be reused for subsequent release missions, fully demonstrating the core technological advantages of this invention: "reusability" and "cabin-to-external coordination."

[0043] S6: Disassembly and Storage: The astronauts separate the release device from the payload transfer mechanism and disassemble the release device into its components, storing them in a storage box for future reuse.

[0044] In step S6, the specific method of disassembling and storing is as follows: Inside the sealed cabin, the astronauts remove the microsatellite release device or CubeSat release device from the payload transfer mechanism. They then disassemble the release device backplate, release device base plate, microsatellite release unit or CubeSat release unit, and the active end of the base plate connection mechanism. The disassembled components are placed in storage boxes to save storage space. The storage boxes are then placed in the designated storage location within the manned spacecraft's sealed cabin for reassembly and reuse during the next on-orbit release mission.

[0045] In step S6, after the release device returns to the sealed cabin via the airlock and extends into the sealed cabin via the payload transfer mechanism, the astronauts perform the disassembly and storage operations of the release device. The astronauts first detach the microsatellite or CubeSat release device from the payload transfer mechanism, separating it from the passive end of the base plate connection mechanism. Then, they sequentially disassemble the release device backplate, release device base plate, microsatellite or CubeSat release unit, and the active end of the base plate connection mechanism into independent components. The advantages of this modular disassembly design are: firstly, the disassembled components can be tightly stacked in dedicated storage boxes, significantly reducing space occupation compared to maintaining the assembled state, thus solving the problem of limited storage resources within the sealed cabin of the manned spacecraft; secondly, the dispersed storage of each component facilitates condition monitoring and maintenance during long-term on-orbit storage, avoiding the impact on the device's service life and reliability due to prolonged assembly stress or connector stress. The storage boxes are placed in designated storage locations within the sealed cabin of the manned spacecraft, achieving standardized management of the release device. When another on-orbit release mission is required, the astronauts only need to retrieve the corresponding components from the storage box, reassemble and self-test them according to step S2, without waiting for a new release device to be carried up with the cargo spacecraft. This enables the release device to be reused multiple times in orbit. Thus, this invention, through a complete closed-loop process of "ascent-assembly-filling-exit-release-recovery-entry-disassembly-storage-reuse," achieves the reusability of multiple types of micro- and nano-satellite release devices for manned spacecraft in orbit. Compared with traditional one-time release methods, this significantly reduces the cost of a single release and improves the utilization efficiency of on-orbit resources for manned spacecraft.

[0046] The above description is merely a preferred embodiment of the present invention, and the scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principle of the present invention should also be considered within the scope of protection of the present invention.

[0047] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0048] It should be noted that the above embodiments can be freely combined as needed. The above description is only a preferred embodiment of the present invention. It should be pointed out that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for on-orbit release of multiple types of micro / nano satellites from a manned spacecraft, characterized in that, Includes the following steps: S1: Ascent and Preparation: The micro-nano satellite will be ascended to the manned spacecraft aboard the cargo spacecraft, where the astronauts will transfer the micro-nano satellite into the sealed cabin and perform a self-test. S2: Release device self-inspection and assembly: Astronauts take out the scattered release device components, perform a self-inspection on the release device, and assemble the release device components into a microsatellite release device configuration or a CubeSat release device configuration on the workbench according to mission requirements. Then, they fill the microsatellite and nanosatellite into the release device and set its status. S3: Install and exit the cabin: The astronauts install the release device containing the micro-nano satellite onto the payload transfer mechanism, execute the automatic cargo exit procedure, and the payload transfer mechanism transfers the release device along with the micro-nano satellite to the outside of the cabin through the airlock. S4: Robotic arm release: The robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism. The release device is transferred outside the cabin and its position is adjusted to meet the release and launch orientation. After receiving the command, the release device releases the micro-nano satellite into orbit. S5: Recovery into the cabin: After the release is completed, the robotic arm will send the release device back to the airlock exit position and reconnect it with the load transfer mechanism before withdrawing. The automatic cargo entry procedure will be executed, and the release device will return to the sealed cabin through the airlock. S6: Disassembly and Storage: The astronauts separate the release device from the payload transfer mechanism and disassemble the release device into its components, storing them in a storage box for future reuse.

2. The method for on-orbit release of multiple types of micro-nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S1, the specific method by which the micro-nano satellite is transported to the manned spacecraft aboard the cargo spacecraft is as follows: Microsatellites are loaded into standard cargo bags during cargo spacecraft launch and secured securely inside the cargo bags to reduce the impact of vibration and shock during launch. This allows microsatellites to eliminate the need for reinforcement structures to resist mechanical environments, saving the mass and volume of the microsatellite itself. The specific method for the microsatellite to perform self-check is as follows: the astronauts transport the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, and perform a self-check on the microsatellite inside the sealed cabin to ensure that all functions and performance of the microsatellite are in good working order before release. If necessary, the astronauts can perform on-orbit repairs or replace parts of the microsatellite.

3. The method for on-orbit release of multiple types of micro-nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S2, the specific method of the release device self-test is as follows: after the astronaut takes out the release device component on the workbench inside the cabin, he performs a self-test on the release device through the release device controller to confirm that all functions of the release device are normal. The specific method for assembling the microsatellite release device configuration according to mission requirements is as follows: the astronauts take out the release device back plate, release device base plate, base plate connecting mechanism active end and microsatellite release unit stored separately in the sealed cabin, and complete the assembly to form the microsatellite release device configuration on the workbench in the cabin. After assembly, the astronauts transfer the microsatellite from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the microsatellite installation tool to connect the microsatellite to the microsatellite release unit, and set the status of the microsatellite through the operation interface on the release device. The specific method for assembling the CubeSat release device configuration according to mission requirements is as follows: astronauts take out the release device backplate, release device base plate, base plate connecting mechanism active end, and CubeSat release unit, which are stored separately in the sealed cabin, and assemble them on the workbench inside the cabin to form the CubeSat release device configuration. After assembly, the astronauts transfer the CubeSat from the cargo spacecraft to the sealed cabin of the manned spacecraft, use the CubeSat installation tool to fill the CubeSat release unit and press it tightly, and set the status of the CubeSat through the operation interface on the release device.

4. The method for on-orbit release of multiple types of micro / nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S3, the astronaut installs the release device containing the micro-nano satellite onto the payload transfer mechanism in the following specific manner: The astronauts opened the airlock cabin door, and the ground requested the payload transfer mechanism to extend into the sealed cabin. The astronauts installed the passive end of the base plate connection mechanism on the payload transfer mechanism and installed the release device containing the micro-nano satellites onto the passive end of the payload transfer mechanism. The specific method for executing the automatic cargo exit procedure is as follows: the payload transfer mechanism retracts into the airlock, the astronauts close the inner hatch and check for leaks in the inner hatch, after the leak check is normal, the airlock is reused and depressurized, after the airlock is depressurized, the outer hatch is opened, and the payload transfer mechanism carrying the release device extends to the position of the outer hatch of the airlock, realizing the exit of the micro-nano satellite together with the release device.

5. The method for on-orbit release of multiple types of micro-nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S4, the specific method by which the robotic arm grabs the release device from the airlock hatch and separates it from the load transfer mechanism is as follows: the robotic arm moves to the position to be grabbed outside the cabin through path planning. After the load transfer mechanism extends, the robotic arm grabs the release device through the robotic arm target adapter, thereby separating the release device from the load transfer mechanism. The specific method for transferring the release device to the outside of the cabin and adjusting its position is as follows: the robotic arm transfers the release device to a designated position outside the cabin and adjusts the position of the robotic arm so that the release device meets the release and launch orientation. The specific method by which the release device releases the microsatellite into orbit after receiving the command is as follows: the command is sent by ground request or by the astronaut, the controller of the microsatellite release device or CubeSat release device receives the telemetry and control command, drives the microsatellite release unit or CubeSat release unit to perform the release action, and completes the on-orbit separation of the microsatellite or CubeSat.

6. The method for on-orbit release of multiple types of micro / nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S5, the specific method of recycling into the chamber is as follows: After the microsatellite or CubeSat is released, the robotic arm grabs the release device and transfers it back to the airlock exit position. The release device is then installed on the payload transfer mechanism and connected. The robotic arm releases the release device at its end and withdraws. The outer hatch of the airlock is closed and leaks are checked. After the leaks are detected and approved, the airlock is repressurized. After repressurization, the astronauts open the inner hatch, and the payload transfer mechanism rotates 90° and extends into the sealed cabin, allowing the release device to return to the sealed cabin via the airlock.

7. The method for on-orbit release of multiple types of micro / nano satellites from a manned spacecraft according to claim 1, characterized in that, In step S6, the specific method of disassembling and storing is as follows: Inside the sealed cabin, the astronauts remove the microsatellite release device or CubeSat release device from the payload transfer mechanism. They then disassemble the release device backplate, release device base plate, microsatellite release unit or CubeSat release unit, and the active end of the base plate connection mechanism. The disassembled components are placed in storage boxes to save storage space. The storage boxes are then placed in the designated storage location within the manned spacecraft's sealed cabin for reassembly and reuse during the next on-orbit release mission.

8. A manned spacecraft multi-type micro-nano satellite on-orbit release device for performing the manned spacecraft multi-type micro-nano satellite on-orbit release method as described in any one of claims 1-7, characterized in that, include: The sealed cabin (1) of the manned spacecraft serves as the mounting base for all components; Airlock (2), connected to the sealed compartment (1), is used to provide a transition channel for cargo to enter and exit the compartment, and has an openable inner and outer door, and is capable of leak detection, depressurization and repressurization operations. The load transfer mechanism (3) is installed inside the airlock (2) and can extend into the sealed chamber (1) or out of the airlock to carry and transfer the release device. The release device includes a detachable and assembleable release device back plate (8), a release device base plate (9), an active end (10) of the base plate connecting mechanism, a passive end (11) of the base plate connecting mechanism, a release device controller (12), and a robotic arm target adapter (6). The release device is assembled into a microsatellite release device (15) configuration or a CubeSat release device (16) configuration according to mission requirements. The workbench (7) is set inside the sealed cabin of the manned spacecraft and has limit screw holes for installing the base plate connection mechanism and providing an assembly station for the release device. An external robotic arm (4) has one end fixed to a robotic arm base (5) outside the sealed chamber (1), and the other end grabs a release device through the robotic arm target adapter (6) to transfer the release device to a release position or send the release device back to the outside of the airlock.

9. The on-orbit release device for multi-type micro / nano satellites in manned spacecraft according to claim 1, characterized in that, When the release device is assembled into a microsatellite release device (15) configuration, it is composed of a release device back plate (8), a release device base plate (9), a base plate connecting mechanism active end (10), a release device controller (12), a robotic arm target adapter (6), and a microsatellite release unit (13). The release device back plate (8) and the release device base plate (9) are fixedly connected to each other. The microsatellite release unit (13) is installed on the release device back plate (8). The release device controller (12) is electrically connected to the microsatellite release unit (13) and controls its release action. The microsatellite release unit (13) and the microsatellite (17) are connected and constrained to each other. The microsatellite release device (15) can release microsatellites not exceeding 1000mm×500mm×700mm and can release microsatellites weighing 10~200kg.

10. The on-orbit release device for multi-type micro / nano satellites in manned spacecraft according to claim 1, characterized in that, When the release device is assembled into a cubesat release device (16) configuration, it is composed of a release device back plate (8), a release device base plate (9), a base plate connecting mechanism active end (10), a release device controller (12), a robotic arm target adapter (6), and a cubesat release unit (14). The release device back plate (8) and the release device base plate (9) are fixedly connected to each other. The cubesat release unit (14) is installed on the release device back plate (8). The release device controller (12) is electrically connected to the cubesat release unit (14) and controls its release action. 8) Fill into the cube star release unit (14). The cube star release device (16) can release cube stars of different specifications such as 1U, 1.5U, 2U, 3U and 6U. Two cube star release units (14) are installed on the back plate (8) of the cube star release device, and there are 3U and 6U cube star release stations. The cube star release device (16) can release up to 36U cube stars at a time. The 3U cube star release unit has three combination methods: 3 1U cube stars, 2 1.5U cube stars, and 1 1U cube star and 1 2U cube star.

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