A nuclear-powered satellite configuration

Abstract

The present invention provides a nuclear-powered satellite configuration, comprising: a core reactor, a deployable truss, and a satellite platform body; one end of the deployable truss is embedded in the satellite platform body, and the other end is connected to the core reactor; when retracted, the deployable truss is completely enclosed within the satellite platform body; after the core reactor is unlocked, the deployable truss extends and pushes out the core reactor, separating the satellite platform body from the core reactor. The present invention utilizes a large-scale deployable truss, which, when retracted, is completely enclosed within the satellite platform, and the platform cabin is completely enclosed within the radiant heat sink. This improves the utilization rate of the fairing envelope space, lowers the center of mass of the entire satellite, and effectively reduces the radiation impact of the core reactor on the satellite platform when deployed. The satellite platform body, which utilizes a modular compartment design, facilitates compartment development, production, assembly, and testing, and facilitates the implementation of safety and reliability assurance measures. The payload cabin's docking mechanism docks with a fully loaded propulsion cabin, allowing for in-orbit replacement of the propulsion cabin module, extending the satellite's service life.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite configurations, and in particular to a large-scale, high-load-bearing nuclear-powered satellite configuration. Background Art

[0002] Space nuclear propulsion boasts advantages such as independence from sunlight, autonomous energy generation, a wide power range, high energy density, and strong environmental adaptability. These advantages offer significant advantages for deep space probes and spacecraft requiring high power, which struggle to utilize solar energy. Currently, the power range of nuclear-powered spacecraft launched and under development has evolved from tens of watts to several kilowatts, tens of kilowatts to megawatts. This growth in nuclear power has driven the rapid development of high-specific impulse electric propulsion. In line with current Earth-Moon situational demands, nuclear-powered platforms are evolving towards ultra-high-power and highly maneuverable cargo platforms.

[0003] As the application demand for nuclear-powered platforms expands, the mass of nuclear reactors is increasing, and they need to carry large-mass propellants, which has an impact on satellite platforms and puts forward higher requirements:

[0004] 1) The mass of the core increases and is concentrated, resulting in a high center of mass for the satellite and large dynamic response;

[0005] 2) The strong radiation from the nuclear reactor will pose a certain radiation hazard to the satellite platform. A deployable truss is required to separate the nuclear reactor and the satellite platform, which increases inertia. Furthermore, the deployable truss drive system is complex and heavy. The launch stage raises the center of mass of the entire satellite, resulting in a large dynamic response. However, after deployment in orbit, the rigidity is weak, causing significant disturbance to the platform and complicating orbit control.

[0006] 3) Nuclear thermal power conversion is less than 30%, and the waste heat requires a large-area radiation heat dissipation system;

[0007] 4) It must have strong maneuverability for cargo transportation, a propellant capacity greater than 5 tons, and the ability to provide on-orbit refueling and propellant replacement;

[0008] 5) Meet the docking requirements of at least two large cargo spacecraft.

[0009] In summary, a nuclear-powered cargo platform weighs over 14 tons and carries over 5 tons of fuel, making existing satellite systems large-scale and structurally complex. This requires breaking through the constraints of payload envelope, rigidity, and weight. Within these constraints, how to meet the functional requirements of the entire system, achieve lightweight structural design, and achieve modular assembly has become an urgent challenge in the field. Currently, no similar technologies have been described or reported, and no similar materials have been collected domestically or internationally. Summary of the Invention

[0010] In view of the above-mentioned deficiencies in the prior art, the present invention provides a large-scale, high-load-bearing nuclear-powered satellite configuration.

[0011] The present invention is achieved through the following technical solutions.

[0012] A nuclear-powered satellite configuration includes: a nuclear reactor, a deployable truss, and a satellite platform body; wherein:

[0013] One end of the deployable truss is embedded in the satellite platform body, and the other end of the deployable truss is connected to the core stack;

[0014] The deployable truss is completely enclosed within the satellite platform body in the folded state;

[0015] After the core stack is unlocked, the deployable truss pushes the core stack out in an expanded state, separating the satellite platform body from the core stack.

[0016] Optionally, the expandable truss includes a plurality of interconnected expandable truss units; wherein each of the expandable truss units includes: an upper triangular frame, a lower triangular frame, a folding rod, a tension cable, a nut, a lead screw and a motor; the upper triangular frame and the lower triangular frame are connected by three equal-length lead screws and fixed by corresponding lead screws; the three folding rods are vertically arranged between the upper triangular frame and the lower triangular frame and close to the lead screw, and a plurality of tension cables are cross-arranged between the upper triangular frame and the lower triangular frame, wherein the two ends of each tension cable are respectively connected to the nut, and the motor is driven and connected to the three equal-length lead screws.

[0017] Optionally, the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in each of the expandable truss units are made of carbon fiber materials; or, the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in the two sections of the expandable truss units close to one end of the nuclear stack are made of stainless steel materials, and the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in the remaining expandable truss units are made of materials with high elasticity model and low density characteristics.

[0018] Optionally, the tension rope is made of titanium wire or non-expanding steel material.

[0019] Optionally, the folding rod comprises a plurality of interconnected rod bodies, wherein two adjacent rod bodies are connected via a locking hinge to achieve the folding of the folding rod.

[0020] Optionally, the satellite platform body includes: a platform cabin, a payload cabin and a propulsion cabin; wherein, the platform cabin and the payload cabin are connected by an eccentric pin connection structure; the propulsion cabin includes two forms: a launch propulsion cabin and an on-orbit propulsion cabin, and the launch propulsion cabin is connected to the payload cabin by an explosive bolt, and when the fuel in the launch propulsion cabin's tank is exhausted, the launch propulsion cabin is separated from the payload cabin by igniting the explosive bolt; the on-orbit propulsion cabin is docked and separated from the payload cabin by a docking mechanism, completing the on-orbit replacement of the on-orbit propulsion cabin and realizing the on-orbit refueling of fuel.

[0021] Optionally, the platform cabin adopts a frame panel hexagonal configuration, one end face of which is provided with a truss-type connector, and the other end face of which is provided with a lower end frame for connection with the load cabin; wherein:

[0022] The inner end of the truss-type connector is connected to the deployable truss, one end of the deployable truss is embedded in the platform cabin and is completely enclosed inside the platform cabin in the folded state, and the outer end of the truss-type connector is connected to the nuclear stack; the nuclear stack transmits force to the six main load-bearing vertical rods of the frame panel hexagonal configuration through the truss-type connector and explosive bolts, and unlocks and separates the nuclear stack from the platform cabin by igniting the explosive bolts.

[0023] Optionally, the payload cabin adopts a central load-bearing cylinder hexagonal configuration, one end of which is equipped with a first end frame for connecting to the platform cabin, and the other end of which is equipped with a second end frame for fastening connection to the launch propulsion cabin and a docking mechanism for on-orbit replacement with the on-orbit propulsion cabin.

[0024] Optionally, the eccentric pin connection structure includes an eccentric pin, a clamp and a cotter pin; wherein:

[0025] The eccentric pin comprises a cylindrical body, a portion of the outer edge of the cylindrical body is provided with a protruding circular ring for limiting position, an anti-rotation groove is provided on the cylindrical body at one end of the protruding circular ring, and the outer circle of the cylindrical body at the other end of the protruding circular ring is eccentric relative to the inner circle of the cylindrical body, and the direction of the eccentricity is orthogonal to the slotting direction of the anti-rotation groove;

[0026] After the platform cabin is connected to the load cabin, the eccentric pin is rotated to a tightening angle, the clamp is used to prevent the eccentric pin from rotating, and the cotter pin is used to lock the clamp to complete the cabin section connection.

[0027] Optionally, the launch propulsion module includes an outer support cylinder, a spherical shell fixedly connected to the interior of the outer support cylinder, a tank fixed to the spherical shell, a tapered section structure with a variable cross-section connected to one end of the outer support cylinder, and a plurality of lugs provided at the other end of the outer support cylinder; wherein:

[0028] The variable-section cone structure is connected to the load compartment via explosive bolts;

[0029] The lugs are used for connecting and separating the propulsion module from the carrier rocket.

[0030] Optionally, the on-orbit propulsion module includes an outer bearing cylinder, a spherical shell fixedly connected to the interior of the outer bearing cylinder, a tank fixed to the spherical shell, a cross partition and a connecting inverted cone structure connected to one end of the outer bearing cylinder, and a plurality of lugs provided at the other end of the outer bearing cylinder; wherein:

[0031] The cross partition and the connecting inverted cone structure are connected to the load compartment via explosive bolts;

[0032] The lugs are used for connecting and separating the propulsion module from the carrier rocket.

[0033] Optionally, the docking mechanism includes a hard docking ring and a soft docking ring provided inside the hard docking ring; wherein:

[0034] The soft docking ring is provided with a plurality of guide lobes, a capture lock and a card plate; when docking is required, the guide lobes are extended and inserted into each other, and then locked by the capture lock and the card plate;

[0035] The hard docking ring is provided with a plurality of docking locks, and after docking is completed, the docking locks are used to lock each other.

[0036] Due to the adoption of the above technical solution, the present invention has at least one of the following beneficial effects compared with the prior art:

[0037] The present invention provides a nuclear-powered satellite configuration that uses a large-scale deployable truss. When folded, the truss is completely enclosed within the satellite platform, and the platform cabin is completely enclosed within the radiant heat dissipation plate. This can improve the utilization rate of the fairing envelope space and lower the center of mass of the entire satellite. When deployed, it can reach 13 meters, which can effectively reduce the radiation impact of the nuclear reactor on the satellite platform.

[0038] The present invention provides a nuclear-powered satellite configuration featuring a modular, compartmentalized satellite platform. This design facilitates modular development, production, assembly, and testing, and facilitates the implementation of safety and reliability assurance measures. Furthermore, this modular design approach allows for scalability in terms of functionality and lifespan. For example, when fuel is depleted, a fully loaded propulsion module can be replaced in orbit, extending the satellite's service life.

[0039] The present invention provides a nuclear-powered satellite configuration that adopts a stable hexagonal platform cabin and payload cabin, which can significantly increase the installation surface of a single machine; uses a segmented central load-bearing cylinder as the main load-bearing structure, effectively improving the rigidity of the entire satellite; and uses a high-modulus, low-density material to reduce the weight of the deployable truss.

[0040] The present invention provides a nuclear-powered satellite configuration that utilizes a propulsion module with an external bearing cylinder as its primary load-bearing structure. This design effectively increases the bending resistance of the base and can effectively carry concentrated mass loads, such as large tanks. The propulsion module is connected to the payload module via explosive bolts. When the fuel in the tank is depleted, the explosive bolts are ignited to separate the propulsion module from the satellite. The payload module's docking mechanism then docks with the fully loaded propulsion module, completing the in-orbit replacement of the propulsion module module and extending the satellite's service life.

[0041] The nuclear-powered satellite configuration provided by this invention can provide a theoretical and methodological basis for the configuration, layout, and structural design of large satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0043] Figure 1 The figure is a schematic diagram of the configuration structure of a nuclear-powered satellite in one embodiment of the present invention.

[0044] Figure 2 This is a schematic diagram of the configuration structure of a nuclear-powered satellite in a folded state in a preferred embodiment of the present invention.

[0045] Figure 3 Schematic diagram of a deployable truss structure in a preferred embodiment of the present invention.

[0046] Figure 4 This is a schematic diagram of the satellite platform structure in a preferred embodiment of the present invention.

[0047] Figure 5 It is a schematic diagram of the platform cabin structure in a preferred embodiment of the present invention.

[0048] Figure 6 This is a schematic diagram of the load compartment structure in a preferred embodiment of the present invention.

[0049] Figure 7 Schematic diagram of the eccentric pin connection structure in a preferred embodiment of the present invention.

[0050] Figure 8 It is a schematic diagram of the structure of the launch propulsion module in a preferred embodiment of the present invention.

[0051] Figure 9 This is a schematic diagram of the structure of an on-orbit propulsion module in a preferred embodiment of the present invention.

[0052] Figure 10 Schematic diagram of the docking mechanism structure in a preferred embodiment of the present invention.

[0053] In the figure: 1 is the nuclear reactor, 2 is the deployable truss, 3 is the satellite platform body, 21 is the upper triangular frame, 22 is the lower triangular frame, 23 is the lead screw, 24 is the nut, 25 is the tension cable, 26 is the folding rod, 27 is the locking hinge, 31 is the platform cabin, 32 is the payload cabin, 33 is the propulsion cabin, 311 is the main load-bearing vertical rod, 312 is the lower end frame, 313 is the truss-type connector, 314 is the explosive bolt, 321 is the central load-bearing cylinder, 322 is the first end frame, 323 is the second end frame, and 324 is the docking machine on the second end frame. Structure, 41 is an eccentric pin, 42 is a clamp, 331 is an outer bearing cylinder, 332 is a bearing spherical shell, 333 is a tank, 334 is a variable-section cone structure, 335 is a lug, 336 is a flange, 337 is a heat protection shield, 338 is a connecting surface, 339 is an engine, 3310 is a cross partition, 3311 is a connecting inverted cone, 3312 is a docking mechanism on the propulsion cabin, 51 is a hard docking ring, 52 is a soft docking ring, 521 is a guide petal, 522 is a capture lock, 523 is a clamp, and 511 is a docking lock. DETAILED DESCRIPTION

[0054] The following is a detailed description of an embodiment of the present invention. This embodiment is implemented based on the technical solution of the present invention, and provides a detailed implementation method and specific operation process. It should be noted that those skilled in the art may make various modifications and improvements without departing from the scope of the present invention, and these modifications and improvements fall within the scope of protection of the present invention.

[0055] Figure 1 A schematic diagram of the configuration structure of a nuclear-powered satellite provided in one embodiment of the present invention.

[0056] like Figure 1 As shown, the nuclear-powered satellite configuration provided by this embodiment may include: a nuclear reactor, a deployable truss, and a satellite platform body; wherein:

[0057] One end of the deployable truss is embedded in the satellite platform body, and the other end of the deployable truss is connected to the nuclear reactor;

[0058] The deployable truss is completely enclosed inside the satellite platform body in the retracted state;

[0059] After the core stack is unlocked, the truss can be deployed to push out the core stack in an expanded state, separating the satellite platform body from the core stack.

[0060] In a preferred embodiment, the expandable truss includes a plurality of interconnected expandable truss units; wherein each expandable truss unit includes: an upper triangular frame, a lower triangular frame, a folding rod, a tension cable, a nut, a lead screw and a motor; the upper triangular frame and the lower triangular frame are connected by three lead screws of equal length and fixed by corresponding nuts; the three folding rods are vertically arranged between the upper triangular frame and the lower triangular frame and close to the lead screws, and a plurality of tension cables are cross-arranged between the upper triangular frame and the lower triangular frame, wherein the two ends of each tension cable are respectively connected to the nut, and the motor is driven and connected to the three lead screws of equal length.

[0061] Among them, multiple expandable truss units are mainly folded and collapsed through folding rods, and the rods are connected by hinges to achieve folding and collapsing.

[0062] In a preferred embodiment, the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in each expandable truss unit are respectively made of carbon fiber material; or, the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in the two sections of expandable truss units close to one end of the nuclear pile are respectively made of stainless steel, and the upper triangular frame, lower triangular frame, folding rod, nut and lead screw in the remaining expandable truss units are respectively made of materials with high elastic modulus and low density characteristics.

[0063] In a specific application example, the material with high elastic modulus and low density can be carbon fiber, polyethylene fiber, etc., or a material with similar properties.

[0064] In a preferred embodiment, the tension cable is made of titanium wire or invar material.

[0065] In a preferred embodiment, the folding rod comprises a plurality of interconnected rod bodies, wherein two adjacent rod bodies are connected via a locking hinge to achieve the folding of the folding rod.

[0066] In a preferred embodiment, the satellite platform body includes: a platform cabin, a payload cabin and a propulsion cabin; wherein, the platform cabin and the payload cabin are connected by an eccentric pin connection structure; the propulsion cabin includes two types: a launch propulsion cabin and an on-orbit propulsion cabin, and the launch propulsion cabin is connected to the payload cabin by an explosive bolt, and when the fuel in the launch propulsion cabin's tank is exhausted, the launch propulsion cabin and the payload cabin are separated by igniting the explosive bolt; the on-orbit propulsion cabin is docked and unlocked and separated from the payload cabin through a docking mechanism, completing the on-orbit replacement of the on-orbit propulsion cabin and realizing the on-orbit refueling of the fuel.

[0067] In a preferred embodiment, the platform cabin adopts a frame panel hexagonal configuration, one end face of which is provided with a truss-type connector, and the other end face of which is provided with a lower end frame for connecting to the load cabin; wherein:

[0068] The inner end of the truss-type connector is connected to the deployable truss, one end of the deployable truss is embedded in the platform cabin and is completely enclosed inside the platform cabin in the retracted state. The outer end of the truss-type connector is connected to the nuclear reactor; the nuclear reactor transmits force to the six main load-bearing vertical rods of the frame panel hexagonal configuration through the truss-type connector and explosive bolts, and unlocks and separates the nuclear reactor from the platform cabin by igniting the explosive bolts.

[0069] In a preferred embodiment, the payload cabin adopts a central load-bearing cylinder hexagonal configuration, one end of which is equipped with a first end frame for connecting to the platform cabin, and the other end of which is equipped with a second end frame for fastening connection to the launch propulsion cabin and a docking mechanism for on-orbit replacement with the on-orbit propulsion cabin.

[0070] In a preferred embodiment, the eccentric pin connection structure includes an eccentric pin, a clamp and a cotter pin; wherein:

[0071] The eccentric pin includes a cylindrical body, a portion of the outer edge of the cylindrical body is provided with a protruding circular ring for limiting position, an anti-rotation groove is provided on the cylindrical body at one end of the protruding circular ring, and the outer circle of the cylindrical body at the other end of the protruding circular ring is eccentric relative to the inner circle of the cylindrical body, and the eccentric direction is orthogonal to the slotting direction of the anti-rotation groove;

[0072] After the platform cabin is connected to the payload cabin, the eccentric pin is rotated to the tightening angle. The clamp is used to prevent the eccentric pin from rotating, and the cotter pin is used to lock the clamp to complete the cabin connection.

[0073] In a preferred embodiment, the launch propulsion module includes an outer support cylinder, a spherical shell fixedly connected to the interior of the outer support cylinder, a tank fixed to the spherical shell, a tapered section structure with a variable cross-section connected to one end of the outer support cylinder, and a plurality of lugs provided at the other end of the outer support cylinder; wherein:

[0074] The variable-section cone structure is connected to the load compartment via explosive bolts;

[0075] The lugs are used to connect and separate the propulsion module from the launch vehicle.

[0076] In a preferred embodiment, the on-orbit propulsion module includes an outer support cylinder, a spherical shell fixedly connected to the interior of the outer support cylinder, a tank fixed to the spherical shell, a cross partition and a connecting inverted cone structure connected to one end of the outer support cylinder, and a plurality of lugs provided at the other end of the outer support cylinder; wherein:

[0077] The cross partition and the connecting inverted cone structure are connected to the load compartment through explosive bolts;

[0078] The lugs are used to connect and separate the propulsion module from the launch vehicle.

[0079] In a preferred embodiment, the docking mechanism includes a hard docking ring and a soft docking ring disposed inside the hard docking ring; wherein:

[0080] The soft docking ring is equipped with multiple guide flaps, capture locks and card holders. When docking is required, the guide flaps extend and insert into each other, and then are locked by the capture locks and card holders.

[0081] The hard docking ring is provided with multiple sets of docking locks, and when docking is completed, the docking locks are used to lock each other.

[0082] The above-described embodiment of the present invention proposes a large-scale, high-load-bearing nuclear-powered satellite configuration for ultra-high-power nuclear satellite transport platforms exceeding 200 kW. A large-scale deployable truss is embedded in the satellite platform body at one end and connected to the core at the other. When retracted, it is completely enclosed within the satellite platform body, improving fairing envelope space utilization and lowering the satellite's center of mass. The deployed distance from the satellite platform body can reach up to 13 meters, effectively mitigating the radiation impact of the core on the satellite platform body. The satellite platform body adopts a modular, compartmentalized design, facilitating its development, production, assembly, and testing. Specifically, it includes a platform cabin, a payload cabin, and a propulsion cabin. The platform and payload cabins adopt a stable hexagonal configuration, facilitating the installation of directional antennas at various angles. The platform cabin utilizes a frame-panel design, while the payload cabin utilizes a central bearing cylinder as the primary load-bearing structure, enhancing overall satellite rigidity. The platform and payload cabin sections are connected using an eccentric pin connection. This ingenious design, simple manufacturing process, and high connection rigidity provide axial preload to the connected sections, effectively reducing structural dynamic response. The propulsion module uses an external bearing cylinder as the main load-bearing structure, which can effectively increase the root bending resistance and effectively carry concentrated mass loads, such as large-capacity tanks. The propulsion module includes two types: launch propulsion module and on-orbit propulsion module. The launch propulsion module is connected to the payload module via explosive bolts. When the tank fuel is exhausted, the explosive bolts are ignited to separate the propulsion module from the satellite. The on-orbit propulsion module uses a docking mechanism to dock with the payload module, completing the on-orbit replacement of the propulsion module and achieving on-orbit fuel refueling.

[0083] The technical solutions provided by the above embodiments of the present invention are further described below with reference to the accompanying drawings.

[0084] The above embodiment of the present invention provides a large-scale, high-load-bearing nuclear-powered satellite configuration, which specifically includes the following parts:

[0085] First, the satellite configuration mainly consists of three parts: the core 1, the large-scale deployable truss 2, and the satellite platform body 3;

[0086] The overall configuration of the nuclear-powered satellite is similar to a dumbbell. Figure 1For thermal protection and nuclear radiation shielding, a deployable truss separates the core reactor and the satellite platform body at a safe distance. This dumbbell-shaped configuration has a large moment of inertia in the direction perpendicular to the deployable truss extension, but a smaller moment of inertia parallel to the direction of the deployable truss extension, allowing the gravity gradient to stabilize the entire satellite's attitude. The core reactor uses a Stirling dynamic cycle power generation method based on the work of the working fluid, converting the heat energy generated by the core reactor into electrical energy to provide power and propulsion for the spacecraft. The satellite platform body maintains the basic operations of the entire spacecraft and provides a reliable space and temperature for space missions and payloads.

[0087] Second, a large-scale deployable truss is embedded in the satellite platform at one end and connected to the core at the other end, such as Figure 2 As shown, when retracted, the deployable truss is completely enclosed within the satellite platform, while the platform cabin is enclosed within the thermal radiation plate and connected to the core via explosive bolts and truss-type connectors, transmitting the ascent load. Once the satellite is in orbit, the explosive bolts separate, unlocking the core, and the deployable truss is deployed to push out of the core, separating the satellite platform from the core by a safe distance.

[0088] The deployable truss adopts modular design, and the number of deployable truss units can be increased to build a large, lightweight deployable truss structure to meet the needs of large-scale deployment. Figure 3 As shown, each extension truss unit primarily consists of an upper triangular frame 21, a lower triangular frame 22, a folding rod 26, a locking hinge 27, a tension cable 25, and a nut 24. The drive mechanism is realized by a motor driving three equal-length lead screws 23. The lead screws are mounted on the upper end of the lower triangular frame, which serves as the base. The motor drives the lead screws, which in turn drive the nut to push out the upper triangular frame, thereby pulling the folding rod to unfold. Once unfolded, the tension cable is used to tighten the folding rod. The folding rod and the upper and lower triangular frames can all be made of carbon fiber. This ensures the effective rigidity of the truss structure while effectively reducing the mass of the entire system.

[0089] To ensure both high stiffness and strength after deployment, the deployable truss' geometric parameters were optimized, with the folding rod diameter, triangular frame cross-sectional area, and tension cable preload as design variables, prioritizing truss stiffness over strength. The two sections of the deployable truss near the nuclear reactor can be made of stainless steel to withstand the high temperatures generated by the reactor, while other sections can be constructed of high-elastic modulus, low-density materials. Components such as the lead screws and upper and lower triangular frames are typically constructed of carbon fiber with a high strength-to-weight ratio. Tension cables are made of titanium or non-inflated steel. This approach ensures the effective stiffness of the truss structure while significantly reducing the overall system's mass.

[0090] Third, the satellite platform body adopts a multi-cabin structure, specifically including a platform cabin 31, a payload cabin 32 and a propulsion cabin 33;

[0091] like Figure 4 As shown in the figure, the platform module is the part that maintains the basic operation of the entire spacecraft. It is located on the top of the satellite platform body. This part includes the overall structure, thermal control system, power management system that maintains the basic operation of the entire device, measurement and control system and attitude and orbit control system; the payload module is located in the middle section of the satellite platform. It is the core module for realizing space missions and is loaded with corresponding payloads according to specific missions; the propulsion module is located at the bottom of the satellite platform. It has a fuel loading capacity of more than 5t and provides power for orbit change maneuvers and orbital round-trip transportation.

[0092] Fourth, the platform cabin and payload cabin adopt a stable hexagonal configuration. The platform cabin adopts a frame panel configuration, and the payload cabin uses a segmented central load-bearing cylinder as the main load-bearing structure to improve the stiffness of the entire satellite and lower the center of mass of the entire satellite.

[0093] like Figure 5 As shown, the platform cabin adopts a hexagonal configuration of frame panel type, which can effectively lower the center of mass of the entire satellite compared to the load-bearing cylinder. During the launch phase, the nuclear pile transmits force to the six main load-bearing vertical rods 311 of the platform cabin through the truss-type connector 313 and six explosive bolts 314, satisfying the optimal force transmission path. The base of the deployable truss is embedded in the lower end frame 312 (i.e., the bottom plate) of the platform cabin. When folded, it is completely enclosed in the platform cabin to improve the utilization rate of the fairing envelope space and lower the center of mass of the entire satellite. The top is fixed to the nuclear pile through the ring section of the truss-type connector. After entering orbit, the explosive bolts are ignited, the nuclear pile and the platform cabin are unlocked and separated, and the deployable truss pushes the nuclear pile out under the drive of the motor.

[0094] like Figure 6 As shown, the payload cabin has a hexagonal configuration with a central bearing cylinder 321 as the main bearing structure, which improves the stiffness and bending resistance of the entire satellite; the top of the payload cabin is equipped with a first end frame 322 for connecting with the cabin of the platform cabin; the bottom of the payload cabin is equipped with a second end frame 323 and a docking mechanism 324, the second end frame is used to achieve a fast connection between the launch segment and the propulsion cabin, and the docking mechanism is used for on-orbit replacement of the propulsion cabin, thereby extending the life of the entire satellite and expanding the satellite service capability.

[0095] The end frames between the platform compartment and the payload compartment sections are connected by an eccentric pin connection structure.

[0096] Furthermore, the eccentric pin connection structure includes an eccentric pin 41 , a clamp 42 and a cotter pin.

[0097] like Figure 7As shown, the eccentric pin is a modified circular cylindrical pin with a protruding ring (called a stop ring) at the outer edge at approximately 2 / 5 of its height for positioning. An anti-rotation groove is cut into the cylinder above the stop ring, and below the stop ring, the outer circle of the cylinder is eccentric relative to the inner circle, with the eccentric direction perpendicular to the groove. After the end frames are connected, the eccentric pin is inserted into the pin hole and rotated to the tightening angle. The clamp is then tied into the clamp groove of the first end frame of the cabin section to prevent the eccentric pin from rotating. Finally, the cabin section connection is completed by locking with a cotter pin.

[0098] Fifth, the propulsion module uses the external bearing cylinder 331 as the main bearing structure and is connected to the payload module through explosive bolts. When the fuel in the tank 333 is exhausted, the propulsion module is separated from the satellite by igniting the explosive bolts, and the docking mechanism 324 of the payload module is docked with the docking mechanism 3312 of the fully loaded propulsion module to complete the on-orbit replacement of the propulsion module module and realize the on-orbit refueling of the fuel.

[0099] like Figure 8 As shown, the launch propulsion module utilizes an outer support cylinder 331 as the primary load-bearing structure. Four large-capacity tanks 333 are secured to a load-bearing spherical shell 332, which is fixed to the outer support cylinder via flanges 336. The upper section of the outer support cylinder is connected to the connection surface 338 of the variable-section cone structure 334 and to the second end frame at the bottom of the payload compartment via explosive bolts, ensuring continuous force transmission within the main structure. The lower end of the outer support cylinder is machined with eight lugs 335 for connecting and disconnecting from the launch vehicle. A heat shield 337 is positioned between the engine 339 and the tanks 333.

[0100] After the fuel in the propulsion module is exhausted, the explosive bolts at the top of the variable-section cone section are ignited to separate the propulsion module from the satellite. Figure 9 It is an independent on-orbit propulsion module that is transported into space as a space-replaceable propulsion module, such as Figure 9 As shown, its configuration is essentially identical to the original input propulsion module, differing in that the top force transmission structure, instead of a tapered section, is replaced with a connecting inverted cone 3311 and a cross-partition 3310. A docking mechanism 3312 has also been added for in-orbit docking with the satellite's payload module, enabling on-orbit replacement of the propulsion module and extending the satellite's service life. Connecting inverted cone 3311 is bolted to cross-partition 3310, docking mechanism 3312, and load-bearing spherical shell 332.

[0101] Furthermore, the docking mechanism adopts the standard docking mechanism of the surrounding heterogeneous structure of the Chinese space station, such as Figure 10As shown, the docking mechanism includes a hard docking ring 51 and a soft docking ring 52. The soft docking ring is retractable, extending during docking and freely moving up, down, left, and right to improve docking tolerance. The guide flaps 521 interlock to further adjust the docking angle, and then the capture lock 522 and the clamping plate 523 lock to complete the soft docking between the cabins. The hard docking ring is equipped with 12 sets of docking locks 511, which can ensure the rigidity and strength of the connection surface, while also ensuring safe separation after the mission is completed.

[0102] The nuclear-powered satellite configuration provided by this invention utilizes a large-scale deployable truss. When retracted, it is completely enclosed within the satellite platform, and the platform cabin is completely enclosed within the radiant heat sink. This improves the space utilization of the fairing envelope and reduces the center of mass of the entire satellite. When deployed, it can reach 13 meters, effectively reducing the radiation impact of the nuclear reactor on the satellite platform. The satellite platform body adopts a modular compartment design, which facilitates the development, production, assembly, and testing of compartments and facilitates the implementation of safety and reliability assurance measures. In addition, this modular compartment design approach allows for scalability in terms of functionality and lifespan. For example, after fuel depletion, a fully loaded propulsion cabin can be replaced in orbit, extending the satellite's service life. The stable hexagonal configuration of the platform cabin and payload cabin significantly increases the mounting surface area of ​​each unit. The use of segmented central bearing tubes as the primary load-bearing structure effectively improves the overall satellite rigidity. The use of external bearing tubes as the primary load-bearing structure of the propulsion cabin effectively increases the bending resistance at the root and can effectively carry concentrated mass loads such as large-capacity tanks. The propulsion module is connected to the payload module through explosive bolts. When the fuel in the tank is exhausted, the explosive bolts are ignited to separate the propulsion module from the satellite, and the payload module's docking mechanism is used to dock with the fully loaded propulsion module to complete the in-orbit replacement of the propulsion module module and extend the satellite's service life.

[0103] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in this field.

[0104] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art may make various variations or modifications within the scope of the claims, which do not affect the essence of the present invention.

Claims

1. A nuclear-powered satellite configuration, characterized in that: include: nuclear reactor, deployable truss and satellite platform body; One end of the deployable truss is embedded in the satellite platform body, and the other end of the deployable truss is connected to the core stack; the deployable truss is completely enclosed within the satellite platform body in the folded state; after the core stack is unlocked, the deployable truss is pushed out of the core stack in the deployed state, separating the satellite platform body from the core stack; wherein: The expandable truss includes a plurality of interconnected expandable truss units; each of the expandable truss units includes: an upper triangular frame, a lower triangular frame, a folding rod, a tension cable, a nut, a lead screw and a motor; the upper triangular frame and the lower triangular frame are connected by three equal-length lead screws and fixed by corresponding lead screws; the three folding rods are vertically arranged between the upper triangular frame and the lower triangular frame and close to the lead screws, and a plurality of tension cables are cross-arranged between the upper triangular frame and the lower triangular frame, wherein the two ends of each tension cable are respectively connected to the nut, and the motor is driven and connected to the three equal-length lead screws; The satellite platform body includes: a platform cabin, a payload cabin and a propulsion cabin; the platform cabin adopts a frame panel type hexagonal configuration, and the payload cabin adopts a central load-bearing cylinder type hexagonal configuration; the platform cabin and the payload cabin are connected by an eccentric pin connection structure; the propulsion cabin includes two forms: a launch propulsion cabin and an on-orbit propulsion cabin. The launch propulsion cabin is connected to the payload cabin by explosive bolts, and when the fuel in the launch propulsion cabin's tank is exhausted, the launch propulsion cabin and the payload cabin are separated by igniting the explosive bolts; the on-orbit propulsion cabin is docked and separated from the payload cabin by a docking mechanism, completing the on-orbit replacement of the propulsion cabin and realizing the on-orbit refueling of fuel.

2. The nuclear-powered satellite configuration according to claim 1, characterized in that: Also includes any one or more of the following: - The upper triangular frame, lower triangular frame, folding rod, nut and lead screw of each of the expandable truss units are made of carbon fiber material; or the upper triangular frame, lower triangular frame, folding rod, nut and lead screw of the two sections of the expandable truss units near one end of the core are made of stainless steel, and the upper triangular frame, lower triangular frame, folding rod, nut and lead screw of the remaining expandable truss units are made of materials with high elastic modulus and low density; -The tension rope is made of titanium wire or invar steel; The folding rod comprises a plurality of interconnected rod bodies, wherein two adjacent rod bodies are connected via a locking hinge to enable the folding rod to be foldable.

3. The nuclear-powered satellite configuration according to claim 1, characterized in that: One end face of the platform cabin is provided with a truss-type connector, and the other end face thereof is provided with a lower end frame for connecting with the load cabin; wherein: The inner end of the truss-type connector is connected to the deployable truss, one end of the deployable truss is embedded in the platform cabin and is completely enclosed inside the platform cabin in the folded state, and the outer end of the truss-type connector is connected to the nuclear stack; the nuclear stack transmits force to the six main load-bearing vertical rods of the frame panel hexagonal configuration through the truss-type connector and explosive bolts, and unlocks and separates the nuclear stack from the platform cabin by igniting the explosive bolts.

4. The nuclear-powered satellite configuration according to claim 1, characterized in that: One end of the payload cabin is equipped with a first end frame for connecting to the platform cabin, and the other end is equipped with a second end frame for fastening connection to the launch propulsion cabin and a docking mechanism for on-orbit replacement with the on-orbit propulsion cabin.

5. The nuclear-powered satellite configuration according to claim 1, characterized in that: The eccentric pin connection structure includes an eccentric pin, a clamp and a cotter pin; wherein: The eccentric pin comprises a cylindrical body, a portion of the outer edge of the cylindrical body is provided with a protruding circular ring for limiting position, an anti-rotation groove is provided on the cylindrical body at one end of the protruding circular ring, and the outer circle of the cylindrical body at the other end of the protruding circular ring is eccentric relative to the inner circle of the cylindrical body, and the direction of the eccentricity is orthogonal to the slotting direction of the anti-rotation groove; After the platform cabin is connected to the load cabin, the eccentric pin is rotated to a tightening angle, the clamp is used to prevent the eccentric pin from rotating, and the cotter pin is used to lock the clamp to complete the cabin section connection.

6. The nuclear-powered satellite configuration according to claim 1, characterized in that: The launch propulsion module includes an outer support cylinder, a spherical shell fixedly connected to the interior of the outer support cylinder, a tank fixed to the spherical shell, a tapered section structure with a variable cross-section connected to one end of the outer support cylinder, and a plurality of lugs provided at the other end of the outer support cylinder; wherein: The variable-section cone structure is connected to the load compartment via explosive bolts; The lugs are used for connecting and separating the propulsion module from the carrier rocket.

7. The nuclear-powered satellite configuration according to claim 1, characterized in that: The on-orbit propulsion module includes an outer bearing cylinder, a spherical shell fixedly connected to the interior of the outer bearing cylinder, a tank fixed to the spherical shell, a cross partition and an inverted cone structure connected to one end of the outer bearing cylinder, and a plurality of lugs provided at the other end of the outer bearing cylinder; wherein: The cross partition and the connecting inverted cone structure are connected to the load compartment via explosive bolts; The lugs are used for connecting and separating the propulsion module from the carrier rocket.

8. The nuclear-powered satellite configuration according to claim 1, characterized in that: The docking mechanism includes a hard docking ring and a soft docking ring arranged inside the hard docking ring; wherein: The soft docking ring is provided with a plurality of guide lobes, a capture lock and a card plate; when docking is required, the guide lobes are extended and inserted into each other, and then locked by the capture lock and the card plate; The hard docking ring is provided with a plurality of docking locks, and after docking is completed, the docking locks are used to lock each other.

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