CN116588354A - High-power space nuclear power tugboat adopting folding hinge column unfolding mechanism - Google Patents

High-power space nuclear power tugboat adopting folding hinge column unfolding mechanism Download PDF

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Publication number
CN116588354A
CN116588354A CN202310601441.6A CN202310601441A CN116588354A CN 116588354 A CN116588354 A CN 116588354A CN 202310601441 A CN202310601441 A CN 202310601441A CN 116588354 A CN116588354 A CN 116588354A
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CN
China
Prior art keywords
folding
nuclear power
tug
main body
body section
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Pending
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CN202310601441.6A
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Chinese (zh)
Inventor
周思引
苏瑞祺
聂万胜
杨露
李新洪
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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Peoples Liberation Army Strategic Support Force Aerospace Engineering University
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Priority to CN202310601441.6A priority Critical patent/CN116588354A/en
Publication of CN116588354A publication Critical patent/CN116588354A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/408—Nuclear spacecraft propulsion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/428—Power distribution and management
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/646—Docking or rendezvous systems

Abstract

The invention discloses a high-power space nuclear power tug adopting a folding hinge column unfolding mechanism, which comprises a tug body capable of being folded and contained in a rocket fairing; the tug body comprises a nuclear power source load, a folding main beam, a radiating fin structure and a spacecraft platform structure; the spacecraft platform structure comprises a main body section frame, two overturning and unfolding section frames and an electric propeller group; the bottom of the main body section frame is provided with an airship butt joint; the two overturning and unfolding section frames are symmetrically arranged at two ends of the main body section frames and can be folded and stored at the tops of the main body section frames at two sides of a nuclear power source load; the folding main beam and the radiating fin are symmetrical in structure and can be folded and contained in the main body section frame; the radiating fin structure can be synchronously unfolded along with the unfolding of the folding main beam. The invention has low folding rate and small occupied space after folding, can be launched to a low-earth orbit by using a carrier rocket, and can shuttle a freight spacecraft or a manned spacecraft between the low-earth orbit and a ring moon/ring fire orbit.

Description

High-power space nuclear power tugboat adopting folding hinge column unfolding mechanism
Technical Field
The invention relates to the technical field of spacecraft engineering, in particular to a high-power space nuclear power tugboat adopting a folding hinge column unfolding mechanism.
Background
With the progress of space technology, future human beings must go to large-scale construction of extraterrestrial star bases such as moon and Mars and various roads for deep space flight. At present, the rail transfer is mainly carried out in a chemical propulsion mode for human exploration and development tasks, and because the space chemical propulsion ratio is low, the single transportation quantity is small, the cost is high, and the requirements of building moon/Mars base and frequently reciprocating moon/ground fire in the future cannot be met. The thrust and specific impulse of the existing electric propulsion are limited by the energy of the spacecraft and are insufficient for supporting the interplanetary transport mission. This results in very difficult interplanetary travel, especially manned travel.
With the development of nuclear energy technology, a nuclear power spacecraft based on a space pile has the characteristics of high power supply energy density, long service life, continuous and stable energy output, no influence of illumination intensity, no need of carrying complex and huge chemical fuel and the like when high-power nuclear power propulsion is used, and the continuous and reliable energy and power of the spacecraft can be effectively ensured to be repeatedly used for a long time when the nuclear power spacecraft is applied to flight tasks such as interplanetary navigation and the like. Because of the adoption of space nuclear power, high-power electricity utilization such as effective load and the like on the spacecraft can be ensured, and powerful support is provided for electric propulsion thrust and specific impulse.
In order to realize the transportation of goods and personnel among the extraterrestrial stars such as the earth moon, the ground fire and the like, and reduce the cost and the technical difficulty as much as possible, the space ferry scheme is a preferred scheme, and the goods and personnel capsule are ferred to and from different stars by designing a high-power space nuclear power tug, so that the task cost is expected to be greatly reduced, and the development of space transportation industry is promoted.
However, the design of the high-power nuclear power spacecraft is obviously different from that of the traditional spacecraft, and in order to realize the sailing of the space nuclear power tugboat between stars, and considering the huge mass, volume and other complex factors of the space nuclear reactor, the overall optimization design is required to be carried out based on tasks, and the spaceflight launching capability is considered, so that the high-power space nuclear power tugboat is extremely complex. Therefore, the invention provides a high-power space nuclear power tugboat adopting a folding and hinging column unfolding mechanism.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides the high-power space nuclear power tugboat adopting the folding hinge column unfolding mechanism, wherein a folding main beam in the high-power space nuclear power tugboat adopting the folding hinge column unfolding mechanism can drive a radiating fin structure to fold, and the folding main beam has low folding rate and small occupied space after folding, so that the folding main beam can be stored in a main body section frame inner cavity and can be folded and stored in a rocket fairing, and a carrier rocket can be used for launching; meanwhile, nuclear power source load is used for supplying power for the electric propeller group, so that long-term transportation of the tugboat among the ground, moon, ground fire and other extraterrestrial stars is ensured; in addition, the large-area radiating fin structure can radiate heat for nuclear power source load.
In order to solve the technical problems, the invention adopts the following technical scheme:
a high-power space nuclear power tug adopting a folding hinge column unfolding mechanism comprises a tug body which can be folded and contained in a rocket fairing cavity.
The tug body comprises a nuclear power source load, a folding main beam, a radiating fin structure and a spacecraft platform structure.
The spacecraft platform structure comprises a main body section frame, two overturning and unfolding section frames and an electric propeller group.
The bottom of the main body section frame is provided with a main platform, and the center of the main platform is provided with an airship interface which can be externally connected with an airship; the main body section frame is of a hollow structure, and the nuclear power source load is placed in the center of the top of the main body section frame.
Two upset expansion section frames are symmetrically arranged at the two ends of the main body section frame, and each upset expansion section frame can rotate around the corresponding side end part of the main body section frame by 180 degrees, so that the top of the main body section frame which is stored at the two sides of the nuclear power source load can be folded.
Each overturning and unfolding section frame is internally provided with an electric propeller group.
The folding main beam is folded and accommodated in the hollow cavity of the main body section frame right below the nuclear power source load; the top end of the folding girder is connected with a nuclear power source load, and the bottom end of the folding girder is arranged on the bottom surface of the hollow cavity of the main body section frame; the folding main beam can be actively unfolded, and the unfolding direction is vertical to the main body section frame.
The radiating fin structures are symmetrically arranged at two sides of the folding main beam and can be folded and contained in the hollow cavities of the main body section frames at two sides of the main beam; the radiating fin structure can be synchronously unfolded along with the unfolding of the folding main beam.
The folding main beam comprises n+1 transverse frames, 3n longitudinal beams and 6n telescopic diagonal members.
Each transverse frame is triangular, wherein the bottom surface of the transverse frame at the bottommost layer is arranged on the bottom surface of the hollow cavity of the main body section frame, and the top surface of the transverse frame at the topmost layer is connected with a nuclear power source load; the n+1 transverse frames are formed as n-layer main beam folding units.
Two coincident corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a longitudinal beam; each longitudinal beam can be folded and stored in the triangular inner cavity of the bottom transverse frame.
Two diagonal corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a telescopic diagonal member; each telescopic diagonal member can actively stretch and retract and is accommodated at the top of the corresponding side edge of the bottom layer transverse frame.
Each transverse frame is an equilateral triangle.
A spring damper is arranged in each telescopic diagonal member, and the spring damper can realize active telescopic and vibration reduction.
Each fin structure comprises n rows of fin plates; the heights of the n rows of radiating fin plates are equal to each other and equal to the heights of the main beam folding units; one end of each row of heat dissipation fin plates is connected with at least one corner point of the transverse frame in the corresponding layer of main beam folding unit; two adjacent rows of heat dissipation fin plates are hinged; each row of fin plates includes a fin units.
Each radiating fin unit comprises a coolant pipeline, a heat pipe and carbon fiber fins; wherein, the coolant pipeline is consistent with the unfolding direction of the folding main beam; the heat pipe is vertically connected with the coolant pipeline; the carbon fiber fins are arranged on the top surfaces of the heat pipes and the coolant pipelines.
Setting the length of each row of radiating fin plates as L, the thickness of each row of radiating fin plates as d, and the height of each row of radiating fin plates as h, wherein the occupied space after each radiating fin structure is folded is ndhL; wherein d <0.04h.
The heat dissipation area of the two heat dissipation fin structures can exceed 650m 2 Can radiate the waste heat generated by the power load of the 1.6MW nuclear power.
The folding rate of the folded main beam is lower than 4%.
When the frame of the overturning and unfolding section is folded and stored at two sides of a nuclear power load, the longitudinal section of the tug body is regular hexagon, and the nuclear power load is in a hexagonal frustum shape.
The invention has the following beneficial effects:
1. the folding main beam can drive the radiating fin structure to fold, and the folding main beam has low folding rate and small occupied space and can be stored in the inner cavity of the main body section frame, so that the tugboat body can be folded and stored in the rocket fairing, thereby being capable of using a carrier rocket for launching, improving the one-time ground moon/ground fire transportation capability and reducing the transportation cost.
2. The invention uses a nuclear power source to supply power for the electric propeller group, thereby providing guarantee for long-term transportation of tugboat between the earth and moon, ground fire and other extraterrestrial stars; meanwhile, after the tug body is unfolded, the nuclear power load is far away from the spacecraft platform structure, and heat can be dissipated for the nuclear power load through the large-area radiating fin structure. In the invention, the heat dissipation area of the two heat dissipation fin structures can exceed 650m 2 Can radiate 3.4MW waste heat generated by a 1.6MW nuclear power supply.
3. Because the nuclear power load is far away from the spacecraft platform structure, namely the unfolded tug body is of a dumbbell-shaped structure, the arrangement of the spring damper can avoid the vibration problem of the tug body of the dumbbell-shaped structure, and the stability of the tug body is improved.
4. According to the invention, the main platform and the airship butt joint can be in butt joint with an external airship, and the propellant is supplied to the electric propulsion group through the airship, so that the one-time ground month/ground fire transportation capability is further improved, and the transportation cost is reduced.
5. The invention has the capability of multiple orbit changes and multiple inter-star transportation tasks, thereby realizing the reciprocating ferry of the freight spacecraft or the manned spacecraft between the low-earth orbit ferry to the orbit such as the ring moon orbit/ring fire orbit and the like.
Drawings
FIG. 1 is a schematic diagram of a high power space nuclear power tug employing a folding hinge column deployment mechanism according to the present invention prior to deployment.
Fig. 2 is a schematic view showing a structure in which a tug body is folded and accommodated in a rocket fairing.
Fig. 3 is a schematic structural view of the tug body during the overturning of the frame of the overturning and unfolding section.
Fig. 4 is a schematic diagram of the structure of the tug body after the frame of the overturning and unfolding section of the tug body is overturned.
Fig. 5 is a partially expanded view of the folded main beam of the present invention.
Fig. 6 is a schematic structural view of the tug body of the present invention after deployment.
Fig. 7 is an enlarged schematic view of the circled area in fig. 6.
Fig. 8 is a schematic structural diagram of a fin unit according to the present invention.
Fig. 9 is a schematic structural view of the folded main beam and heat sink structure after folding.
Fig. 10 is a schematic structural view of the tug body of the present invention after docking with the airship after deployment.
The method comprises the following steps:
1. nuclear power source load;
2. folding the main beam;
201. a transverse frame; 202. an elbow hinge; 203. a longitudinal beam; 204. telescoping diagonal members;
3. a heat sink structure;
301. a coolant line; 302. a heat pipe; 303. a carbon fiber fin;
4. a spacecraft platform structure;
401. an electric propeller group; 402. platform loading; 403. a main body section frame; 404. overturning and unfolding the section frame; 405. an airship interface; 406. a rotating mechanism;
5. rocket cowling; 6. an airship.
Detailed Description
The invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it should be understood that the terms "left", "right", "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and "first", "second", etc. do not indicate the importance of the components, and thus are not to be construed as limiting the present invention. The specific dimensions adopted in the present embodiment are only for illustrating the technical solution, and do not limit the protection scope of the present invention.
As shown in fig. 2, a high power space nuclear power tug employing a folding hinge post deployment mechanism includes a tug body that can be folded and received within a cavity of a rocket fairing 5.
As shown in fig. 1, 3 and 4, the tug body comprises a nuclear power load 1, a folding main beam 2, a fin structure 3 and a spacecraft platform structure 4.
In this embodiment, when the tug body is not in operation, the tug body is in a storage state as shown in fig. 1, and its longitudinal section is regular hexagon.
The nuclear power load is preferably a hexagonal frustum-shaped, in which a nuclear reactor (also known as a nuclear power source) is built, capable of powering the subsequent electric propulsion unit 401.
The spacecraft platform structure comprises a main body section frame 403, two flip-open section frames 404, and an electric propulsion assembly 401.
The main platform is arranged at the bottom of the main section frame, the main platform center is provided with an airship interface 405, and the airship interface can be externally connected with an airship 6 as shown in fig. 10, and the airship can be a freight airship or a manned airship. The freight airship can supply the propellant to the electric propulsion group, so that the one-time ground month/ground fire transportation capacity is further improved, and the transportation cost is reduced.
The main platforms located on both sides of the airship interface are capable of mounting platform loads 402, such as communications antennas, electrical storage and distribution equipment, control equipment, and the like.
The main body section frame is of a hollow structure, and a nuclear power source load is placed in the center of the top of the main body section frame.
The two overturning and unfolding section frames are symmetrically arranged at two ends of the main body section frame, and each overturning and unfolding section frame preferably performs overturning rotation of 180 degrees around the corresponding side end parts of the main body section frame through a rotating mechanism 406, so that the top of the main body section frame which is stored at two sides of a nuclear power source load can be folded.
Each overturning and unfolding section frame is internally provided with an electric propeller group, and the electric propeller group consists of a plurality of high-power electric propellers and a plurality of propellant storage tanks and provides thrust for the tugboat.
The folding main beam is folded and accommodated in the hollow cavity of the main body section frame right below the nuclear power source load; the top end of the folding girder is connected with a nuclear power source load, and the bottom end of the folding girder is arranged on the bottom surface of the hollow cavity of the main body section frame; the folding main beam can be actively unfolded, and the unfolding direction is vertical to the main body section frame.
As shown in fig. 5, the folding main beam includes n+1 transverse frames 201, 3n stringers 203, and 6n telescoping diagonal members 204.
Each transverse frame is triangular, and is further preferably equilateral. The bottom surface of the transverse frame at the bottommost layer is arranged on the bottom surface of the hollow cavity of the main body section frame, and the top surface of the transverse frame at the topmost layer is connected with a nuclear power source load; the n+1 transverse frames are formed as n-layer main beam folding units.
Two coincident corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a longitudinal beam; the middle of each longitudinal beam is preferably provided with an elbow hinge 202 which can be folded and accommodated in the triangular inner cavity of the bottom transverse frame.
Two diagonal corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a telescopic diagonal member; each telescopic diagonal member can actively stretch and retract and is accommodated at the top of the corresponding side edge of the bottom layer transverse frame.
A spring damper is arranged in each telescopic diagonal member, and the spring damper can realize active telescopic and vibration reduction.
The connection part of the folding girder and the spacecraft platform structure is set as an origin O, the unfolding direction of the folding girder is an X axis, the central axis of the spacecraft platform structure is a Y axis, and the axis passing through the origin O and perpendicular to the XOY plane is a Z axis. The invention decomposes the vibration acting on the folding girder into:
A. reciprocating vibration along the X axis;
B. plane vibration in the XOY plane;
C. plane vibration in the XOZ plane.
The reciprocating vibration along the X axis and the plane vibration in the XOZ plane can not damage the whole structure, and only the plane vibration in the XOY plane can damage the radiating fin structures on two sides of the folding girder.
In order to avoid plane vibration in the XOY plane, the telescopic diagonal piece in the XOY plane is a spring damper with larger damping, so that the vibration intensity can be quickly attenuated, and resonance is prevented. To reduce the overall structural mass, the remaining telescoping diagonal members may employ spring dampers with relatively low damping ratios.
The vibration generated by the operation in space is a minute vibration, but if the minute vibration is not controlled, the vibration will develop into a large vibration once resonance occurs. If a rigid girder is used, a high requirement on the strength of the girder is required, and the structural quality of the rigid girder is very high. The folding main beam of the invention can not cause resonance due to the existence of the spring damper, thereby achieving the purpose of controlling the overall stability. In addition, the folding main beam is composed of n layers of main beam folding units, the spring damper of each main beam folding unit can cut down the energy of vibration section by section, the problem of vibration is overcome, and the folding main beam can be made lighter because the vibration deformation is overcome without depending on the structural strength of the folding main beam, and the structural quality of the folding main beam is reduced. The structure has lower folding rate than the rigid main girder, can lead the main girder to have smaller volume after folding, and improves the space utilization rate in the fairing.
The radiating fin structures are symmetrically arranged at two sides of the folding main beam and can be folded and contained in the hollow cavities of the main body section frames at two sides of the main beam; the radiating fin structure can be synchronously unfolded along with the unfolding of the folding main beam.
As shown in fig. 6 and 7, each fin structure includes n rows of fin plates; the heights of the n rows of radiating fin plates are equal to each other and equal to the heights of the main beam folding units; one end of each row of heat dissipation fin plates is connected with at least one corner point of the transverse frame in the corresponding layer of main beam folding unit (in the embodiment, the heat dissipation fin plates are preferably connected with one corner point at the top); two adjacent rows of heat dissipation fin plates are hinged; each row of fin plates includes a fin units.
As shown in fig. 8, each fin unit includes a coolant line 301, a heat pipe 302, and a carbon fiber fin 303; wherein, the coolant pipeline is consistent with the unfolding direction of the folding main beam; the heat pipe is vertically connected with the coolant pipeline; the carbon fiber fins are distributed on the top surfaces of the heat pipes and the coolant pipelines, and the carbon fiber fins are preferably 0.16mm thick bare carbon fibers of light heat conducting materials, so that the radiating fin units can be made extremely thin.
During operation of the nuclear power source, high temperature coolant is pumped into the coolant lines. When the high-temperature coolant flows through the unit coolant pipelines of the heat dissipation structure, the heat pipe can transfer heat to the bare carbon fiber fins, and the bare carbon fiber fins dissipate heat in a radiation heat dissipation mode, so that the temperature of the coolant is reduced. The cooled coolant flows back to the nuclear power supply again, so as to achieve the purpose of radiating the nuclear power supply.
Setting the length of each row of radiating fin plates as L, the thickness of each row of radiating fin plates as d, and the height of each row of radiating fin plates as h, wherein the occupied space after each radiating fin structure is folded is ndhL; wherein d <0.04h.
The heat dissipation area of the two heat dissipation fin structures can exceed 650m 2 Can radiate the waste heat generated by the power load of the 1.6MW nuclear power.
The folding rate of the folded main beam is lower than 4%, namely, the main beam with the length of 50m is less than 2m before being unfolded. In the present invention, the structure of the folded main beam and the two side fin structures is shown in fig. 9.
The invention can be used for towing large-scale freight transport airships and manned airships to transfer ground fire and moon, improves the ability of human development and utilization of moon and sparks, and lays a foundation for large-scale construction of moon and sparks and frequent round trip of ground fire and moon.
The invention relates to a working process of a nuclear power tugboat, which comprises the following steps.
Step 1, transmitting: the tug body is folded and accommodated in the rocket fairing cavity, and is transported to a set low earth orbit through the carrier rocket.
And 2, spreading the tug body, wherein the specific spreading process comprises the following steps.
Step 2-1, unfolding a spacecraft platform structure: the overturning unfolding section frame and the main section frame are unlocked, and are outwards rotated for 180 degrees under the drive of a motor in the rotating mechanism and locked at two sides of the main section frame.
Step 2-2, unfolding a folding main beam: the n layers of girder folding units in the folding girder are unfolded sequentially from top to bottom or from outside to inside. The main beam folding unit positioned at the outermost layer is called a first layer main beam folding unit, and the unfolding process of the first layer main beam folding unit is as follows: the 6 telescopic diagonal members in the first-layer main beam folding unit are unlocked, the upper-layer transverse frame is actively driven to move upwards, and the upper-layer transverse frame drives the longitudinal beam to move, so that the elbow hinge extends out of the triangular inner cavity of the lower-layer transverse frame and is unfolded, and when the elbow hinge is completely unfolded, the longitudinal beam is in a vertical state. And by analogy, the unfolding of the remaining girder folding units is completed, and at this time, the nuclear power load at the top end of the first layer of girder folding units is far away from the spacecraft platform structure.
Step 2-3, radiating fin structure expansion: when each layer of girder folding units are unfolded, a whole row of heat dissipation fin plates on two sides of the current layer of girder folding units are driven to be unfolded synchronously; when the n-layer girder folding units are unfolded, the n rows of radiating fin plates of each radiating fin structure are unfolded synchronously, so that the tug body is unfolded.
Step 3, nuclear power generation: when the tug body is fully unfolded, a nuclear reactor in a nuclear power load is started, helium is heated, and a closed-cell brayton cycle unit is blown to generate power.
Step 4, heat dissipation: nuclear reactors generate electricity while producing a large amount of waste heat. Thus, while the nuclear reactor is being started, high temperature coolant is pumped into the coolant lines. When the high-temperature coolant flows through the unit coolant pipelines of the heat dissipation structure, the heat pipe can transfer heat to the bare carbon fiber fins, and the bare carbon fiber fins dissipate heat in a radiation heat dissipation mode, so that the temperature of the coolant is reduced. The cooled coolant flows back to the nuclear power supply again, so that the purpose of removing waste heat for the nuclear power supply is achieved.
Step 5, adjusting the pose: and 3, supplying power to the electric propeller group by the electric energy generated by the nuclear power generation in the step, wherein the electric propeller group works to generate thrust, so that the tug can automatically adjust the posture and the track to be docked.
Step 6, butt joint: the cargo or manned spacecraft will launch from the earth into the low earth orbit and dock with the spacecraft docking interface on the tug body to form a composite. Wherein the cargo ship can also supply propellant to the electric propulsion unit while carrying cargo.
And 7, ferrying, which specifically comprises the following steps.
Step 7-1, ferrying from low earth orbit to ring moon/ring fire orbit: the combined body is accelerated by the electric propeller group, enters the earth-moon/earth-fire transfer track, is captured by the attraction of moon/Mars, and then is decelerated to the ring-moon/ring-fire track. On the moon-surrounding/fire-surrounding track, the combination body is separated, and the freight airship or the manned airship automatically decelerates to realize moon-falling/fire; the tugboat stays on the ring moon/ring fire track.
Step 7-2, returning to the low earth orbit from the ring moon/ring fire orbit: after the freight transport airship or the manned airship finishes the task, the unmanned aerial vehicle takes off from the moon/fire surface, enters the lunar-surrounding/fire-surrounding track and is in butt joint with the tugboat, and the combination is formed again. The combination body is changed into orbit again, and is separated after returning to the low earth orbit, and the freight spacecraft or the manned spacecraft returns to the earth; the tug stays on track to wait for the next task.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes can be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and all the equivalent changes belong to the protection scope of the present invention.

Claims (10)

1. A high-power space nuclear power tug adopting a folding and hinging column unfolding mechanism is characterized in that: comprises a tug body which can be folded and accommodated in a rocket fairing cavity;
the tug body comprises a nuclear power source load, a folding main beam, a radiating fin structure and a spacecraft platform structure;
the spacecraft platform structure comprises a main body section frame, two overturning and unfolding section frames and an electric propeller group;
the bottom of the main body section frame is provided with a main platform, and the center of the main platform is provided with an airship interface which can be externally connected with an airship; the main body section frame is of a hollow structure, and the nuclear power source load is placed in the center of the top of the main body section frame;
the two overturning and unfolding section frames are symmetrically arranged at two ends of the main body section frame, and each overturning and unfolding section frame can overturn and rotate 180 degrees around the corresponding side end part of the main body section frame, so that the tops of the main body section frames stored at two sides of a nuclear power source load can be folded; each overturning and unfolding section frame is internally provided with an electric propeller group;
the folding main beam is folded and accommodated in the hollow cavity of the main body section frame right below the nuclear power source load; the top end of the folding girder is connected with a nuclear power source load, and the bottom end of the folding girder is arranged on the bottom surface of the hollow cavity of the main body section frame; the folding main beam can be actively unfolded, and the unfolding direction is vertical to the main body section frame;
the radiating fin structures are symmetrically arranged at two sides of the folding main beam and can be folded and contained in the hollow cavities of the main body section frames at two sides of the main beam; the radiating fin structure can be synchronously unfolded along with the unfolding of the folding main beam.
2. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 1, wherein: the folding main beam comprises n+1 transverse frames, 3n longitudinal beams and 6n telescopic diagonal members;
each transverse frame is triangular, wherein the bottom surface of the transverse frame at the bottommost layer is arranged on the bottom surface of the hollow cavity of the main body section frame, and the top surface of the transverse frame at the topmost layer is connected with a nuclear power source load; n+1 transverse frames are formed into n layers of main beam folding units;
two coincident corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a longitudinal beam; each longitudinal beam can be folded and accommodated in the triangular inner cavity of the bottom transverse frame;
two diagonal corner points of two adjacent transverse frames in each layer of folding units are respectively connected through a telescopic diagonal member; each telescopic diagonal member can actively stretch and retract and is accommodated at the top of the corresponding side edge of the bottom layer transverse frame.
3. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 2, wherein: each transverse frame is an equilateral triangle.
4. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 2, wherein: a spring damper is arranged in each telescopic diagonal member, and the spring damper can realize active telescopic and vibration reduction.
5. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 2, wherein: each fin structure comprises n rows of fin plates; the heights of the n rows of radiating fin plates are equal to each other and equal to the heights of the main beam folding units; one end of each row of heat dissipation fin plates is connected with at least one corner point of the transverse frame in the corresponding layer of main beam folding unit; two adjacent rows of heat dissipation fin plates are hinged; each row of fin plates includes a fin units.
6. The high power space nuclear power tug employing a folding and hinge post deployment mechanism of claim 5, wherein: each radiating fin unit comprises a coolant pipeline, a heat pipe and carbon fiber fins; wherein, the coolant pipeline is consistent with the unfolding direction of the folding main beam; the heat pipe is vertically connected with the coolant pipeline; the carbon fiber fins are arranged on the top surfaces of the heat pipes and the coolant pipelines.
7. The high power space nuclear power tug employing a folding and hinge post deployment mechanism of claim 5, wherein: setting the length of each row of radiating fin plates as L, the thickness of each row of radiating fin plates as d, and the height of each row of radiating fin plates as h, wherein the occupied space after each radiating fin structure is folded is ndhL; wherein d <0.04h.
8. The high power space nuclear power tug employing a folding and hinge post deployment mechanism of claim 7, wherein: the heat dissipation area of the two heat dissipation fin structures can exceed 650m 2 Can radiate the waste heat generated by the power load of the 1.6MW nuclear power.
9. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 2, wherein: the folding rate of the folded main beam is lower than 4%.
10. The high power space nuclear power tug employing a folding hinge post deployment mechanism of claim 1, wherein: when the frame of the overturning and unfolding section is folded and stored at two sides of a nuclear power load, the longitudinal section of the tug body is regular hexagon, and the nuclear power load is in a hexagonal frustum shape.
CN202310601441.6A 2023-05-25 2023-05-25 High-power space nuclear power tugboat adopting folding hinge column unfolding mechanism Pending CN116588354A (en)

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