High-power space nuclear-powered spacecraft system using a multi-core combined layout architecture

Abstract

A high-power space nuclear-powered spacecraft system adopting a multi-core combined arrangement architecture belongs to the field of spacecraft engineering technology. The present invention is to solve the problem that the existing spacecraft using nuclear energy have low power and cannot be used for high-power space nuclear energy. The present invention includes a nuclear reactor assembly, an extension mechanism, a spacecraft platform and a radiation radiator; the nuclear reactor assembly and the spacecraft platform are connected and isolated by an extension mechanism, and the radiation radiator is installed on the extension mechanism; the nuclear reactor assembly includes a support frame and a reactor group, a radiation shielding body and a plurality of control rod groups installed in the support frame from front to back; the reactor group is composed of a plurality of reactors combined in the form of an array, the number of reactors in the reactor group is the same as the number of control rod groups, and each reactor is controlled by a control rod group. The present invention is mainly used to provide high-power space nuclear energy.

Description

Technical Field

[0001] The present invention belongs to the field of spacecraft engineering technology, and in particular relates to a high-power space nuclear-powered spacecraft system adopting a multi-core combined arrangement architecture. Background Art

[0002] With the continuous development of aerospace science and technology, the demand for space energy continues to grow. Limited by the level of traditional energy technology, space energy is limited by quality, life, etc., and it is currently difficult to apply to high-power application scenarios. Nuclear energy has the advantages of high energy density, long life, and no need for sunlight and oxygen, and is suitable for space environments. Publication No. CN114044170A discloses a nuclear-powered spacecraft using a modular shielding structure, which includes a reactor, a shielding assembly, a deployment mechanism support, a solar cell sail panel, and a space instrument and equipment cabin; this patent uses a reactor to provide nuclear energy, and the overall power is small, and it is impossible to provide high-power space nuclear energy. If high-power space nuclear energy is developed, there are problems such as high R&D costs, long R&D cycles, and high reliability and safety requirements. Further, a high-power space nuclear-powered spacecraft system using a multi-core combined layout architecture is provided. Summary of the invention

[0003] The technical problem to be solved by the present invention is that the existing spacecraft using nuclear energy have low power and cannot be used for high-power space nuclear energy; therefore, a high-power space nuclear power system using a multi-core combination layout architecture is provided, the structure of which has modular characteristics and high full life cycle reliability. Through the single module combination layout, a space nuclear power system with a larger power magnitude is constructed, which can reduce research and development funds and development cycles, and provide a new way for the application of high-power space nuclear power systems.

[0004] The technical solution adopted by the present invention to solve the above technical problems is:

[0005] A high-power space nuclear-powered spacecraft system adopting a multi-core combined arrangement architecture comprises a nuclear reactor assembly, an extension mechanism, a spacecraft platform and a radiation radiator; the nuclear reactor assembly and the spacecraft platform are connected and isolated by the extension mechanism, and the radiation radiator is installed on the extension mechanism;

[0006] The nuclear reactor assembly comprises a support frame and a reactor group, a radiation shield and a plurality of control rod groups which are sequentially installed in the support frame from front to back; the reactor group is composed of a plurality of reactors combined in an array, the number of reactors in the reactor group is the same as the number of control rod groups, and each reactor is controlled by a control rod group.

[0007] Furthermore, each control rod group includes a drive motor and a control rod; the drive motor is installed on a side of the radiation shielding body away from the reactor group, one end of the control rod is connected to the drive end of the drive motor, and the other end of the control rod passes through the radiation shielding body and is connected to the reactor.

[0008] Furthermore, the support frame includes a reactor outer support frame, a reactor inner support frame, a shield support frame and a control rod group support frame which are connected in sequence; the reactor outer support frame is sleeved outside the reactor inner support frame, and the reactor group is installed between the two and remains fixed; the radiation shield is installed in the shield support frame 103, and the plurality of control rod groups are installed in the control rod group support frame.

[0009] Furthermore, the reactor inner support frame is in the shape of a polygonal column, and each side wall of the polygonal column is recessed inward to form an arc-shaped surface, and the arc-shaped surface is matched with the outer surface of the reactor.

[0010] Furthermore, the number of the reactors is three and they are arranged in an equilateral triangle, and the inner support frame of the reactor is a triangular prism.

[0011] Furthermore, the number of the reactors is four and they are arranged in a quadrilateral manner, and the inner support frame of the reactor is a rectangular parallelepiped.

[0012] Furthermore, the spacecraft platform includes a space instrument and equipment cabin, two solar cell panels, two solar wings, a number of propellant tanks and a number of propulsion systems; the space instrument and equipment cabin is connected to the end of the extension mechanism, and the two solar cell panels are respectively installed on both sides of the space instrument and equipment cabin through a solar wing, and have gathering and extension functions; after the several propulsion systems are installed in the space instrument and equipment cabin, the several propellant tanks are installed under the space instrument and equipment cabin.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. The multi-core combination layout architecture of the present invention has a modular feature, that is, one reactor corresponds to one control rod group, and the number and power of the reactors opened can be adjusted according to the mission requirements, quickly forming a space nuclear power system covering different power levels from tens of kilowatts to hundreds of kilowatts to meet the needs of different tasks.

[0015] 2. The relatively high-power nuclear power system formed by the present invention is composed of low-cost, mature technology, and low-power space reactors arranged in parallel, without the need to develop high-power nuclear reactors, thus reducing the R&D cost and the overall cost;

[0016] 3. The present invention has multiple redundancy functions. A single reactor system failure will not cause the entire system to fail completely. After necessary treatment, the power can be reduced to continue operating. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings are incorporated as part of this application and are used to provide a further understanding of the present invention.

[0018] Figure 1 This is a schematic diagram of the overall structure of the spacecraft system after it is extended;

[0019] Figure 2 This is a schematic diagram of the overall structure of the spacecraft system gathered into the fairing;

[0020] Figure 3 is a schematic diagram of the structure of the reactor;

[0021] Figure 4 Figure 1 is a schematic diagram of the arrangement of reactors. Figure (a) is a schematic diagram of the arrangement of three reactors, and Figure (b) is a schematic diagram of the arrangement of four reactors.

[0022] Explanation of the reference numerals: 1. Support frame; 101. Reactor outer support frame; 102. Reactor inner support frame; 103. Shield support frame; 104. Control rod group support frame; 2. Reactor group; 201. Reactor; 3. Radiation shield; 4. Control rod group; 401. Drive motor; 402. Control rod; 5. Extension mechanism; 6. Radiant radiator; 7. Space instrument and equipment compartment; 8. Solar cell panels; 9. Solar wings; 10. Propellant tank; 11. Propulsion system; 12. Fairing. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. The following embodiments are used to illustrate the present invention but are not used to limit the scope of the present invention.

[0024] In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0025] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] See also Figure 1 and Figure 2 The embodiment of the present application provides a high-power space nuclear-powered spacecraft system adopting a multi-core combination arrangement architecture, which includes a nuclear reactor assembly A, an extension mechanism 5, a spacecraft platform C and a radiation heat sink 6; the nuclear reactor assembly A and the spacecraft platform C are connected and isolated by the extension mechanism 5, and the extension mechanism 5 has a telescopic function. When the spacecraft system needs to be installed in the fairing 12 and carried, the extension mechanism 5 realizes the retraction between the nuclear reactor assembly A and the spacecraft platform C. When the spacecraft system needs to be used in space, the extension mechanism 5 can realize the extension between the nuclear reactor assembly A and the spacecraft platform C. The specific structural form of the extension mechanism 5 is not limited, as long as it can realize the telescopic function and can achieve the minimum contraction volume; the radiation heat sink 6 is installed on the extension mechanism 5 to dissipate the waste heat of the reactor into space.

[0027] In this embodiment, Figure 1 and Figure 2 As shown, the nuclear reactor assembly A comprises a support frame 1 and a reactor group 2, a radiation shield 3 and a plurality of control rod groups 4 which are sequentially installed in the support frame 1 from front to back.

[0028] In this embodiment, the support frame 1 includes a reactor outer support frame 101, a reactor inner support frame 102, a shield support frame 103 and a control rod group support frame 104 which are connected in sequence; the reactor outer support frame 101 is sleeved outside the reactor inner support frame 102, and the reactor group 2 is installed between the two and remains fixed; the radiation shield 3 is installed in the shield support frame 103, and the plurality of control rod groups 4 are installed in the control rod group support frame 104; the structural forms of the reactor outer support frame 101, the reactor inner support frame 102, the shield support frame 103 and the control rod group support frame 104 are adjusted as needed, and there is no special restriction on the specific structure and specific size of the whole and the part, as long as the overall volume is minimized to facilitate the transportation of the spacecraft.

[0029] In this embodiment, Figure 4As shown, the reactor group 2 is composed of a number of reactors 201 of smaller power levels assembled in the form of an array into a larger power nuclear power system, that is, if the number of reactors 201 is three, they are arranged in the form of an equilateral triangle, and if the number of reactors 201 is four, they are arranged in the form of a quadrilateral; wherein the reactor inner support frame 102 is a polygonal prism, and each side wall of the polygonal prism is concave inward to form an arc surface, and the arc surface fits with the outer surface of the reactor 201. Its specific shape is adjusted according to the number of reactors 201, that is, when the number of reactors 201 is three, the reactor inner support frame 102 is a triangular prism, and each side wall of the triangular prism is concave inward to form an arc surface, and the arc surface matches the outer surface of the reactor 201; when the number of reactors 201 is four, the reactor inner support frame 102 is a rectangular parallelepiped, and each side wall of the rectangular parallelepiped is concave inward to form an arc surface, and the arc surface matches the outer surface of the reactor 201; the reactor 201 is in the reactor inner support frame 102 and The stability of the system can be maintained by fixing the reactor external support frame 101; a number of reactors 201 are arranged in the form of the above array to reduce the overall volume of the reactor group 2 and meet the size envelope of the launch vehicle fairing 12; and the above structural form can not only improve the power level and system reliability, but also meet the space launch size and weight envelope, and will not have a significant impact on the original technical system and plan of the system as a whole. In addition, it can also verify the assembly and use technology of space energy facilities and provide support for the construction of energy facilities in future star bases.

[0030] In this embodiment, Figure 3 As shown, the reactor 201 is composed of a cylindrical body 202, a hemispherical upper end 203 and a hemispherical lower end 204, and a nuclear fuel assembly is placed inside the reactor.

[0031] In this embodiment, Figure 1 and Figure 2 As shown, the number of reactors 201 in the reactor group 2 is the same as the number of control rod groups 4. Each reactor 201 is controlled by a control rod group 4 and forms an independent modular control system. The failure of a single reactor control system will not cause the entire system to fail completely. After necessary treatment, the power can be reduced to continue to operate. Each reactor is independently equipped with a reactivity control system, and a synchronous control system is set in the middle of multiple reactors to synchronously control the reactivity of multiple reactors.

[0032] In this embodiment, Figure 1 and Figure 2As shown, each control rod group 4 includes a drive motor 401 and a control rod 402; the drive motor 401 is installed on the side of the radiation shielding body 3 away from the reactor group 2, one end of the control rod 402 is connected to the drive end of the drive motor 401, and the other end of the control rod 402 passes through the radiation shielding body 3 and is connected to the reactor 201, and is used for the corresponding start-up and shutdown of the reactor 201 and the adjustment of the power of the reactor 201.

[0033] In this embodiment, Figure 1 and Figure 2 As shown, the spacecraft platform C includes a spacecraft instrument and equipment cabin 7, two solar cell sail panels 8, two solar wings 9, a plurality of propellant tanks 10 and a plurality of propulsion systems 11; the spacecraft instrument and equipment cabin 7 is connected to the end of the extension mechanism 5, and the two solar cell sail panels 8 are respectively installed on both sides of the spacecraft instrument and equipment cabin 7 through a solar wing 9, and have gathering and extension functions. When the spacecraft system needs to be installed in the fairing and carried, the solar cell sail panels 8 are folded to the side wall of the spacecraft instrument and equipment cabin 7, and when the spacecraft system needs to be used in space, the solar cell sail panels 8 are extended; the plurality of propulsion systems 11 are installed behind the spacecraft instrument and equipment cabin 7 for the navigation of the spacecraft, and the plurality of propellant tanks 10 are installed under the spacecraft instrument and equipment cabin 7 and provide energy for the propulsion system 11.

[0034] This embodiment uses mature, relatively low-power space reactors arranged in parallel to form a relatively high-power space nuclear power system, which greatly reduces the cost of research and development. It is estimated that by arranging 3-4 space reactors with tens of kilowatts in parallel to form a space nuclear power system with a capacity of hundreds of kilowatts, the launch cost will be reduced by tens of billions of yuan compared to the newly developed space nuclear power system with a capacity of hundreds of kilowatts. This can greatly save costs, shorten the research and development cycle, and improve system reliability and redundancy. Moreover, this simplified configuration can not only improve the power level and system reliability at the same time, but also meet the size and weight envelope of space transportation. On the whole, it will not have a significant impact on the original technical system and scheme of the system. In addition, it can also verify the assembly and use technology of space energy facilities, and provide support for the construction of energy facilities in future star bases.

[0035] Although the present invention is described herein with reference to specific embodiments, it should be understood that these embodiments are merely examples of the principles and applications of the present invention. It should therefore be understood that many modifications may be made to the exemplary embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that the various dependent claims and features described herein may be combined in a manner different from that described in the original claims. It should also be understood that features described in conjunction with individual embodiments may be used in other described embodiments.

Claims

1. A high-power space nuclear-powered spacecraft system with a multi-core combined layout architecture, Features: It comprises a nuclear reactor assembly (A), an extension mechanism (5), a spacecraft platform (C) and a radiation radiator (6); the nuclear reactor assembly (A) and the spacecraft platform (C) are connected and isolated via the extension mechanism (5), and the radiation radiator (6) is mounted on the extension mechanism (5); The nuclear reactor assembly (A) comprises a support frame (1) and a reactor group (2), a radiation shield (3) and a plurality of control rod groups (4) which are sequentially installed in the support frame (1) from front to back; the reactor group (2) is composed of a plurality of reactors (201) in an array, the number of reactors (201) in the reactor group (2) is the same as the number of control rod groups (4), and each reactor (201) is controlled by one control rod group (4); The support frame (1) comprises a reactor outer support frame (101), a reactor inner support frame (102), a shield support frame (103) and a control rod group support frame (104) which are connected in sequence; the reactor outer support frame (101) is sleeved outside the reactor inner support frame (102), and the reactor group (2) is installed between the two and remains fixed; the radiation shield (3) is installed in the shield support frame (103), and the plurality of control rod groups (4) are installed in the control rod group support frame (104); the reactor inner support frame (102) is a polygonal prism, and each side wall of the polygonal prism is concave inward to form an arc surface, and the arc surface matches the outer surface of the reactor (201); The number of the reactors (201) is three or four. When the number of the reactors (201) is three, the three reactors (201) are arranged in an equilateral triangle, and the reactor inner support frame (102) is a triangular prism; When the number of reactors (201) is four, the four reactors (201) are arranged in a quadrilateral manner, and the reactor inner support frame (102) is a rectangular parallelepiped.

2. The high-power space nuclear-powered spacecraft system adopting a multi-core combined arrangement architecture according to claim 1, Features: Each control rod group (4) comprises a drive motor (401) and a control rod (402); the drive motor (401) is installed on a side of the radiation shield (3) away from the reactor group (2); one end of the control rod (402) is connected to the drive end of the drive motor (401); and the other end of the control rod (402) passes through the radiation shield (3) and is connected to the reactor (201).

3. The high-power space nuclear-powered spacecraft system adopting a multi-core combined arrangement architecture according to claim 2, Features: The spacecraft platform (C) comprises an aerospace instrument and equipment cabin (7), two solar cell sailboards (8), two solar wings (9), a plurality of propellant tanks (10) and a plurality of propulsion systems (11); the aerospace instrument and equipment cabin (7) is connected to the end of the extension mechanism (5); the two solar cell sailboards (8) are respectively installed on both sides of the aerospace instrument and equipment cabin (7) through a solar wing (9) and have the functions of gathering and extending; after the plurality of propulsion systems (11) are installed in the aerospace instrument and equipment cabin (7), the plurality of propellant tanks (10) are installed under the aerospace instrument and equipment cabin (7).

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