Miniaturized fast-response low-cost cargo transportation system and method for space station

Abstract

The invention relates to a space station miniaturized fast-response low-cost cargo transportation system and method, and belongs to the technical field of space station cargo transportation. The system comprises a cargo transportation aircraft, a carrier rocket and a maneuvering launching platform, the cargo transportation aircraft adopts the small carrier rocket to be launched into an orbit through land, sea and air-based launching platforms, all-phase autonomous rapid intersection and mechanical arm hovering capture butt joint are adopted, the cargo transportation aircraft enters and exits a space station through an air brake cabin, and up-down transportation of cargoes is achieved. The method has no constraint on a launching site and a launching window, and the time from task receiving to transportation to a space station does not exceed 3 days; high-precision and high-value rendezvous and docking measuring equipment and docking mechanisms do not need to be configured, high-thrust rockets are not needed either, the comprehensive cost of tasks is greatly reduced, meanwhile, the return capsule is configured, descending goods of the space station can be carried to return to the ground, platform equipment can be repeatedly used after returning, and cost is further reduced and efficiency is further improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of space station cargo transportation, and relates to a miniaturized, fast-response, and low-cost cargo transportation system and method for a space station. Background Art

[0002] The space cargo transportation system consists of space cargo transportation vehicles and launch vehicles. Its main function is to transport materials to the space station, store materials in orbit, and remove waste from the space station.

[0003] The existing space cargo transportation systems in the world mainly include the Russian Progress cargo spacecraft (launched by the Soyuz carrier rocket), the American Cygnus cargo spacecraft (launched by the Antares carrier rocket), and the American Dragon cargo spacecraft (launched by the Falcon 9 carrier rocket). The main technical indicators of various space cargo transportation systems are shown in Table 1.

[0004] Table 1 Comparison of main indicators of various foreign space cargo transport aircraft

[0005]

[0006] The existing space cargo transport system, which carries out space station cargo resupply according to mission plans, has a transport capacity of over 2 tons. However, the launch preparation time for launch vehicles and cargo transport vehicles is long, the resupply cycle can take several months, and the overall mission cost is high. This large-tonnage space cargo transport system struggles to meet emergency or temporary uplink needs for maintenance parts, medicines, fresh fruits and vegetables, and small, flexible downlink needs for ten-kilogram space products during the resupply cycle. Summary of the Invention

[0007] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, the present invention provides a miniaturized, fast-response, low-cost cargo transportation system and method for a space station.

[0008] The technical solution of the present invention is: a miniaturized, fast-response, low-cost cargo transportation system for a space station, including a cargo transport aircraft, a carrier rocket and a mobile launch platform, all of which are designed as an integrated whole; the carrier rocket is mounted on the mobile launch platform; the cargo transport aircraft is located on top of the carrier rocket and connected to it, and the cargo transport aircraft adopts 0-360° full-phase autonomous rendezvous, robotic arm hovering capture and docking, and enters and exits the space station through an airlock; the cargo transport aircraft includes a return capsule module, a propulsion capsule module and a cargo capsule module, and the three are arranged in sequence from top to bottom and are electrically connected; the return capsule module is used for downlink cargo loading, the propulsion capsule module is used for attitude and orbit control, and the cargo capsule module is used for uplink cargo loading.

[0009] Furthermore, the mobile launch platform includes a land launch vehicle, a sea launch platform or an air launch platform.

[0010] Furthermore, the cargo transport aircraft and the carrier rocket share a control system to uniformly control the engines of the cargo transport aircraft and the carrier rocket; the cargo transport aircraft uses the last stage of the carrier rocket to change its orbit.

[0011] Furthermore, the launch vehicle adopts a solid, liquid or solid-liquid hybrid engine.

[0012] Furthermore, the return capsule module and cargo cabin module of the cargo transport aircraft are flexibly combined and arranged according to different transport tasks.

[0013] Furthermore, the return capsule module includes a heat protection structure, a sealed cabin, and a parachute cabin; the heat protection structure is used for heat protection during the launch process without a fairing, as well as heat protection, deceleration and landing during the re-entry process, to protect the downlink cargo and the return capsule module equipment; the sealed cabin is used to load sealed cargo or cold chain cargo; the parachute cabin is used to install a parachute for a cushioned landing or a fixed-point landing.

[0014] Furthermore, the return capsule module adopts a rotational body configuration, and after ballistic re-entry into the atmosphere, a parachute is opened to decelerate the landing; or adopts a lifting body configuration, and after lifting re-entry into the atmosphere, it lands horizontally on the airport runway and opens a parachute to further decelerate.

[0015] Furthermore, the cargo hold module includes two forms: a sealed cargo hold and an unsealed cargo hold; the sealed cargo hold is used for loading maintenance spare parts and pharmaceutical cargo inside the cabin, and can also load refrigerated or frozen cargo; the unsealed cargo hold is used for loading maintenance spare parts and cargo outside the cabin; a body-mounted solar array is configured on the outer surface of the cargo hold module to provide energy supply for the cargo transport aircraft; a rendezvous sensor is configured at the bottom of the cargo hold module for relative position attitude measurement, and a robotic arm adapter is configured to cooperate with the space station robotic arm to capture, transfer and release.

[0016] Furthermore, the propulsion module includes a propulsion system and a control system; the propulsion system uses non-toxic propellant and is delivered pre-filled, and no filling operation is required at the launch site; the control system is used for attitude and orbit control and information management of the cargo transport aircraft, and is the control center of the cargo transport aircraft; solar panels are installed on the outside of the propulsion module, which are folded and retracted during launch and unfolded after entering orbit to provide energy supply for the cargo transport aircraft.

[0017] A small-scale, fast-response, and low-cost cargo transportation method for a space station, comprising:

[0018] Determine the launch window for the cargo transport vehicle and launch the carrier rocket;

[0019] After launch, the cargo transport vehicle enters the target orbit, uses rendezvous sensors for absolute and relative positioning, and approaches the space station through ground guidance or autonomous guidance;

[0020] After the cargo transport vehicle approaches the space station, it hovers and is captured by the space station's robotic arm;

[0021] The space station's robotic arm transfers the cargo transport vehicle to the airlock. After the airlock is closed, the astronauts on the space station transfer the uplink cargo and load the return cargo.

[0022] After the cargo transport vehicle completes its cargo supply mission, the robotic arm will transfer it from the airlock to the outside of the space station and release it;

[0023] After the cargo transport aircraft separates from the robotic arm, it uses the engine to maneuver and evacuate to 5km, and then uses the engine to achieve a controlled re-entry of the aircraft;

[0024] Before re-entering the atmosphere, the return module separates from the propulsion module and cargo module assembly. After re-entering the atmosphere, the return module uses its own aerodynamic shape to slow down. When it reaches 10km from the landing point, it deploys a circular parachute for a cushioned landing or a wing-shaped parachute for a fixed-point landing.

[0025] After the return capsule module returns, ground personnel take out the downlink return cargo.

[0026] The beneficial effects of the present invention compared with the prior art are:

[0027] (1) The present invention proposes a miniaturized, fast-response, low-cost space station cargo transportation system that can quickly deliver emergency and temporary cargo such as spare parts and medicines weighing hundreds of kilograms to the space station. It can be launched by land, sea, or air, and has no restrictions on launch sites or launch windows. The time from receiving the mission to delivery to the space station does not exceed 3 days.

[0028] (2) The cargo transport aircraft of the present invention is equipped with a return capsule, which can carry ten kilograms of downlink cargo from the space station back to the ground. After returning, the platform equipment can be reused, further reducing costs and increasing efficiency.

[0029] (3) The cargo transport aircraft of the present invention adopts a robotic arm to hover and capture, and enters and exits the space station through the airlock. It does not need to be equipped with high-precision, high-value rendezvous and docking measurement equipment and docking mechanisms, nor does it require a high-thrust rocket, which greatly reduces the overall cost of the mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 A small, fast-response, and low-cost cargo transportation system for the space station;

[0031] Figure 2 It is a modular and modular space cargo transport vehicle;

[0032] Figure 3 Capturing space cargo transport vehicles for robotic arms;

[0033] Figure 4 To transport cargo vehicles into and out of the space station through the airlock;

[0034] Figure 5 Separation of the return capsule of the space cargo transport vehicle;

[0035] Figure 6 Parachute landing for the return capsule of the space cargo transport vehicle;

[0036] Figure 7 It is a lifting body return space cargo transport vehicle;

[0037] Figure 8 It is a non-returnable space cargo transport vehicle. DETAILED DESCRIPTION

[0038] The present invention will be further explained and illustrated below with reference to the accompanying drawings and specific embodiments.

[0039] like Figure 1 As shown, a miniaturized, fast-response, low-cost cargo transportation system for a space station includes a cargo transport aircraft, a small carrier rocket, and a mobile launch platform. It has land-sea-air based launch capabilities and can realize small-scale, flexible downlink cargo transportation such as 100-kilogram emergency and temporary cargo rapid replenishment and 10-kilogram space products.

[0040] like Figure 2 As shown, the cargo transport aircraft adopts a modular design, including a cargo module, a propulsion module, and a re-entry module. The three-compartment configuration is centered around the propulsion module, allowing the re-entry and cargo modules to be flexibly combined to suit different transport missions. The launch vehicle can be a small solid, liquid, or solid-liquid hybrid. The mobile launch platform includes a land launch vehicle, a sea launch vessel (platform), or an air launch platform.

[0041] The cargo transport aircraft, carrier rocket and launch platform of the present invention adopt an integrated design.

[0042] The cargo transport vehicle is launched without a fairing. Its configuration and thermal design allow it to withstand the aerodynamic environment of the launch phase of the carrier rocket. The cargo transport vehicle and the carrier rocket share a common control system. The cargo transport vehicle's control system implements the carrier rocket's navigation, guidance, and control, and the carrier rocket is no longer equipped with related equipment. The cargo transport vehicle uses the carrier rocket's terminal stage to change its orbit and adopts a rendezvous strategy based on Hohmann or Lambert orbit change, which can achieve 0-360° full-phase rapid rendezvous and docking, further shortening flight time and improving rapid response capabilities. By fully utilizing the maneuverability of land-, sea-, and air-based launch platforms, the coplanar launch window can be expanded from one per day to multiple, improving mission adaptability.

[0043] The cargo transport aircraft adopts a modular design, including a cargo cabin module, a propulsion cabin module, and a return cabin module. Through different module combinations, it can realize the uplink transportation function of different types of cargo and the downlink transportation function of space station products.

[0044] The cargo transport vehicle features a three-compartment design. From top to bottom, in launch configuration, it consists of the reentry module, propulsion module, and cargo module. The cargo module's base is connected to the launch vehicle, eliminating the need for a fairing during launch. Each module is connected only electrically, allowing for independent production, testing, and trials, ensuring decoupled development processes.

[0045] The specific design of each module is as follows: The cargo compartment module is used for uplink cargo loading, and is divided into two types: sealed and unsealed. The sealed cargo compartment is used for loading cargo such as maintenance spare parts and medicines inside the cabin, and can also provide a low-temperature environment for loading refrigerated / frozen cargo; the unsealed cargo compartment is used for loading cargo such as maintenance spare parts outside the cabin. A body-mounted solar array is configured on the outer surface of the cargo compartment module to provide energy supply for the cargo transport vehicle. A rendezvous sensor is configured at the bottom of the cargo compartment module for relative position and attitude measurement, and a robotic arm adapter is configured to cooperate with the space station robotic arm to capture, transfer and release. The cargo transport vehicle is captured and docked by the robotic arm, and enters and exits the space station through the airlock, which simplifies the configuration of the rendezvous and docking system and reduces the system weight, power consumption and cost.

[0046] The propulsion module is used for attitude and orbit control and includes a propulsion system and a control system. The propulsion system uses green, non-toxic propellant and is delivered pre-filled, eliminating the need for refilling at the launch site. The propulsion system includes gas cylinders, tanks, and engines. The gas cylinders are used to hold pressurized gas, the tanks are used to hold propellant, and the engines are used to provide thrust and impulse. The control system is used for attitude and orbit control and information management of the cargo transport vehicle and serves as the control center of the cargo transport vehicle. The propulsion module is located between the cargo module and the reentry module, near the center of mass of the cargo transport vehicle. This facilitates six-degree-of-freedom control of position and attitude while avoiding cross-compartment connections in the propulsion pipeline. Solar panels can be installed on the outside of the propulsion module, folding and stowing during launch and unfolding after entering orbit to provide energy for the cargo transport vehicle.

[0047] The return capsule module is used for loading downlink cargo, and includes a thermal protection structure, a sealed cabin, a parachute compartment, etc. The thermal protection structure is used for heat protection during the launch process to achieve fairing-free launch, as well as heat protection, deceleration and landing during the re-entry process to protect downlink cargo and platform equipment. Rigid or flexible thermal protection structures can be used; the sealed cabin is used to load sealed or cold-chain downlink cargo such as space products, test samples, and sampling specimens; the parachute compartment is used to install parachutes, which can use a circular parachute for cushioned landing or a wing-shaped parachute for fixed-point landing. The return capsule module generally adopts a rotating body configuration, which opens a parachute to slow down the landing after ballistic re-entry into the atmosphere. It can also adopt a lifting body configuration, which lands horizontally on the airport runway after lifting re-entry into the atmosphere and opens a parachute to further decelerate. After the return capsule module returns to the ground with the downlink cargo from the space station, the platform equipment can be reused after testing, which can further reduce the overall cost of the system.

[0048] The small-tonnage cargo transport vehicle of this invention utilizes a universal ship-rocket interface design and can be launched using a variety of small launch vehicles, including solid, liquid, or hybrid launch vehicles. The launch window for these small launch vehicles is constrained only by the coplanarity between the cargo transport vehicle and the space station, providing a daily launch window.

[0049] The launch platforms of the present invention include land-based launch vehicles, sea-based launch vessels (platforms), and airborne launch platforms. Different launch platforms can be flexibly selected based on mission requirements and carrier rockets, enabling launches from all regions. The launch platforms possess a certain degree of maneuverability, which can create multiple coplanar conditions with the space station, enabling multiple launch windows per day.

[0050] A small-scale, fast-response, and low-cost cargo transportation method for a space station, the specific process is as follows:

[0051] The space cargo transportation system of the present invention uses a small-tonnage cargo transportation aircraft to be launched into orbit through a land-, sea-, or air-based launch platform using a small carrier rocket, adopts full-phase autonomous rapid rendezvous, a robotic arm hovering capture and docking, enters and exits the space station through the airlock, and realizes the uplink and downlink of cargo.

[0052] The launch window for cargo transport vehicles only needs to consider the coplanarity constraint with the space station orbit, and there is a launch window every day. Through launch platform maneuvers, the launch window can be further expanded, with multiple launch windows per day.

[0053] After launch, the spacecraft is sent into the target orbit using the carrier rocket and spacecraft engine, and absolute and relative positioning is performed using sensors, and the spacecraft approaches the space station through ground guidance or autonomous guidance. After the cargo transport spacecraft approaches the space station, it hovers and is captured by the space station's robotic arm. Figure 3 shown.

[0054] The space station's robotic arm transfers the cargo transport vehicle to the airlock. After the airlock is closed, the astronauts in the space station transfer the uplink cargo and load the return cargo. After the cargo transport vehicle completes its cargo replenishment mission, the robotic arm transfers it from the airlock to the outside of the space station and releases it. Figure 4 shown.

[0055] After the cargo transport aircraft separates from the robotic arm, it uses the engine to maneuver and evacuate to a certain distance (preferably 5km), and then uses the engine to achieve controlled re-entry of the aircraft. Before re-entering the atmosphere, the return capsule module is separated from the propulsion module + cargo module combination. The return capsule module generally adopts a rotating body configuration. After re-entering the atmosphere, it uses its own aerodynamic shape to slow down, such as Figure 5 When the aircraft reaches a certain distance from the landing point (for example, 10 km), a circular parachute is deployed for cushioned landing or a wing-shaped parachute is deployed for fixed-point landing. Figure 6 The return module can also adopt a lifting body configuration, and after re-entering the atmosphere, it will land horizontally on the airport runway and open the parachute to further slow down, as shown in Figure 2. Figure 7 shown.

[0056] After the return module returns, ground personnel retrieve the downlink cargo and conduct inspections and reliability assessments of the platform equipment. Damaged or substandard modules are repaired and replaced, allowing the module to resume cargo transport, thus achieving reusability.

[0057] When there is no need for downlink cargo, two cargo cabin modules can be used in combination with the propulsion cabin module, the return cabin module can be replaced with the cargo cabin module, and a heat shield can be added on top to solve the aerodynamic and heat protection problems of the launch stage, such as Figure 8 shown.

[0058] The three-cabin modular and combined configuration layout design of the present invention is not limited to miniaturized cargo transport aircraft that enter and exit the space station through the airlock, but is also suitable for large cargo transport aircraft that are launched by large rockets, directly rendezvous and dock with the space station, and support the entry and exit of astronauts.

[0059] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A small-scale, fast-response, low-cost cargo transportation system for a space station, characterized by: The cargo transport aircraft, carrier rocket and mobile launch platform are designed as an integrated whole; the carrier rocket is mounted on the mobile launch platform; the cargo transport aircraft is located on top of the carrier rocket and connected to it. The cargo transport aircraft adopts 0-360° full-phase autonomous rendezvous and robotic arm hovering capture and docking, and enters and exits the space station through the airlock; the cargo transport aircraft includes a return capsule module, a propulsion capsule module and a cargo capsule module, which are arranged in sequence from top to bottom and are electrically connected; the return capsule module is used for downlink cargo loading, the propulsion capsule module is used for attitude and orbit control, and the cargo capsule module is used for uplink cargo loading.

2. The space station miniaturized, fast-response, low-cost cargo transportation system according to claim 1, characterized in that: The mobile launch platform includes a land launch vehicle, a sea launch platform or an air launch platform.

3. The miniaturized, fast-response, and low-cost cargo transportation system for a space station according to claim 1, characterized in that: The cargo transport aircraft and the carrier rocket share a set of control systems to uniformly control the engines of the cargo transport aircraft and the carrier rocket; the cargo transport aircraft uses the final stage of the carrier rocket to change its orbit.

4. The miniaturized, fast-response, low-cost cargo transportation system for a space station according to claim 3, characterized in that: The carrier rocket adopts a solid, liquid or solid-liquid hybrid engine.

5. The miniaturized, fast-response, low-cost cargo transportation system for a space station according to claim 3, characterized in that: The return capsule module and cargo cabin module of the cargo transport aircraft are flexibly combined and arranged according to different transport tasks.

6. The space station miniaturized, fast-response, low-cost cargo transportation system according to claim 5, characterized in that: The return capsule module includes a heat protection structure, a sealed cabin, and a parachute cabin; the heat protection structure is used for heat protection during the launch process without a fairing, as well as heat protection, deceleration and landing during the re-entry process, to protect the downlink cargo and the return capsule module equipment; the sealed cabin is used to load sealed cargo or cold chain cargo; the parachute cabin is used to install a parachute for a cushioned landing or a fixed-point landing.

7. The space station miniaturized, fast-response, low-cost cargo transportation system according to claim 6, characterized in that: The reentry module adopts a rotating body configuration, which opens a parachute to slow down and land after ballistic re-entry into the atmosphere; or adopts a lifting body configuration, which lands horizontally on the airport runway after lifting re-entry into the atmosphere and opens a parachute to further slow down.

8. The space station miniaturized, fast-response, low-cost cargo transportation system according to claim 5, characterized in that: The cargo hold module includes two types: sealed cargo hold and unsealed cargo hold; the sealed cargo hold is used for loading maintenance spare parts and pharmaceutical cargo inside the cabin, and can also load refrigerated or frozen cargo; the unsealed cargo hold is used for loading maintenance spare parts and cargo outside the cabin; the outer surface of the cargo hold module is equipped with a body-mounted solar array to provide energy supply for the cargo transport aircraft; the bottom of the cargo hold module is equipped with a rendezvous sensor for relative position attitude measurement, and a robotic arm adapter is equipped to cooperate with the space station robotic arm to capture, transfer and release.

9. The miniaturized, fast-response, low-cost cargo transportation system for a space station according to claim 1, characterized in that: The propulsion module includes a propulsion system and a control system. The propulsion system uses non-toxic propellant and is delivered pre-filled, so no filling operation is required at the launch site. The control system is used for attitude and orbit control and information management of the cargo transport aircraft and serves as the control center of the cargo transport aircraft. Solar panels are installed on the outside of the propulsion module, which are folded and stowed during launch and unfolded after entering orbit to provide energy supply for the cargo transport aircraft.

10. A space station miniaturized, fast-response, low-cost cargo transportation method, characterized in that: include: Determine the launch window for the cargo transport vehicle and launch the carrier rocket; After launch, the cargo transport vehicle enters the target orbit, uses rendezvous sensors for absolute and relative positioning, and approaches the space station through ground guidance or autonomous guidance; After the cargo transport vehicle approaches the space station, it hovers and is captured by the space station's robotic arm; The space station's robotic arm transfers the cargo transport vehicle to the airlock. After the airlock is closed, the astronauts on the space station transfer the uplink cargo and load the return cargo. After the cargo transport vehicle completes its cargo supply mission, the robotic arm will transfer it from the airlock to the outside of the space station and release it; After the cargo transport aircraft separates from the robotic arm, it uses the engine to maneuver and evacuate to 5km, and then uses the engine to achieve a controlled re-entry of the aircraft; Before re-entering the atmosphere, the return module separates from the propulsion module and cargo module assembly. After re-entering the atmosphere, the return module uses its own aerodynamic shape to slow down. When it reaches 10km from the landing point, it deploys a circular parachute for a cushioned landing or a wing-shaped parachute for a fixed-point landing. After the return capsule module returns, ground personnel take out the downlink return cargo.

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