CN111056047B - Truss type foldable and unfoldable space capsule based on shape memory polymer composite material - Google Patents
Truss type foldable and unfoldable space capsule based on shape memory polymer composite material Download PDFInfo
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- CN111056047B CN111056047B CN201811206337.2A CN201811206337A CN111056047B CN 111056047 B CN111056047 B CN 111056047B CN 201811206337 A CN201811206337 A CN 201811206337A CN 111056047 B CN111056047 B CN 111056047B
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- 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
Abstract
The invention provides a truss type collapsible and expandable space capsule based on a shape memory polymer composite material, which comprises a plurality of capsule body supporting beams and a plurality of end enclosure supporting beams; two ends of the cabin body support beams are supported by the circumferential support beams to form a cylindrical frame structure; two ends of the end socket supporting beams are supported by the annular supporting beams and the annular butt joints to form a circular truncated cone frame structure; the circular truncated cone frame structure extends towards the outer side of the cylindrical frame structure along the axial direction of the cylindrical frame structure; the cabin body supporting beam, the seal head supporting beam, the annular supporting beam and the annular butt joint are all made of shape memory polymer composite materials. The space capsule is made of the shape memory polymer composite material, so that the weight is greatly reduced, and the space occupied by the shape memory polymer composite material is small due to the folding characteristic of the shape memory polymer composite material.
Description
Technical Field
The invention relates to the technical field of space capsules, in particular to a truss type foldable space capsule based on a shape memory polymer composite material.
Background
The capsule is an important spacecraft explored by the space, and with the development of the space technology, the capsule with the traditional metal and rigid structure can not meet the requirement of the capsule due to the defects of large mass, large occupied launching space and the like. In recent years, flexible capsule technology at home and abroad becomes a research hotspot, particularly, inflatable capsule structures have achieved a lot of results, and are currently in a space test stage at abroad, but the inflatable capsule has integral structural rigidity, a central core column is still required to provide and reduce the utilization rate of the structure in the capsule, and in addition, the inflatable structure is easy to deflate after being impacted by meteorites and the like, so that the integral structure collapses.
Disclosure of Invention
In view of the above, the present invention is directed to a shape memory polymer composite-based truss type collapsible and expandable capsule, so as to solve the problems of heavy mass and large occupied space of the existing capsule.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a truss type collapsible and expandable space capsule based on shape memory polymer composite materials comprises a plurality of capsule body supporting beams and a plurality of end socket supporting beams; two ends of the cabin body support beams are supported by the circumferential support beams to form a cylindrical frame structure; two ends of the end socket supporting beams are supported by the annular supporting beams and the annular butt joints to form a circular truncated cone frame structure; the circular truncated cone frame structure extends towards the outer side of the cylindrical frame structure along the axial direction of the cylindrical frame structure; the cabin body supporting beam, the seal head supporting beam, the annular supporting beam and the annular butt joint are all made of shape memory polymer composite materials.
Optionally, many the cabin body supporting beam and many the head supporting beam all the symmetric distribution, just the cabin body supporting beam with the head supporting beam is connected.
Optionally, the number of the cabin supporting beams and the number of the head supporting beams are six.
Optionally, the outer surfaces of the cylinder frame structure and the circular truncated cone frame structure are provided with skins.
Optionally, the skin is constructed of a flexible fabric and a film material.
Optionally, the cabin supporting beam and the head supporting beam are both composed of a plurality of truss units; the truss elements are made of a shape memory polymer composite.
Optionally, the truss unit comprises an upper chord beam and a lower chord beam; a plurality of supporting webs are arranged between the upper chord beam and the lower chord beam; the end parts of the upper chord beam and the lower chord beam are connected through the end web; a reinforcing web is arranged between the end web and the support web adjacent to the end web; one end of the reinforcing web is connected with the upper chord beam, and the other end of the reinforcing web is connected with the lower chord beam; the upper chord member, the lower chord member, the support web, the end web, and the reinforcement web are made of a shape memory polymer composite material.
Optionally, adjacent to the supporting web, the upper chord beam and the lower chord beam form an isosceles trapezoid.
Optionally, the upper chord beam and the lower chord beam are provided with heating means.
Optionally, the heating device is a flexible heating film; the thickness of the flexible heating film is 0.1 mm-5 mm.
Compared with the prior art, the truss type collapsible and deployable space capsule based on the shape memory polymer composite material has the following advantages:
the truss type collapsible and expandable space capsule based on the shape memory polymer composite material is provided with a plurality of capsule body supporting beams and a plurality of end socket supporting beams, and the plurality of capsule body supporting beams and the plurality of end socket supporting beams are supported by the circumferential supporting beams and the circumferential butt joints to form a cylinder frame structure and a circular truncated cone frame structure, and the design of the cylinder frame structure and the circular truncated cone frame structure can improve the space of the manufactured space capsule on one hand and improve the bearing capacity of the manufactured space capsule on the other hand, and can keep good structural rigidity when the space capsule is impacted by space rubbish and meteorite or the capsule body leaks air, and the capsule body supporting beams, the end socket supporting beams, the circumferential supporting beams and the circumferential butt joints are all made of the shape memory polymer composite material, so that the weight of the manufactured space capsule can be greatly reduced, and the shape memory polymer composite material has expandability, the manufactured capsule can also have the folding characteristic, and the occupied space of the manufactured capsule is further reduced.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a shape memory polymer composite based truss type collapsible space capsule according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the shape memory polymer composite based truss type collapsible capsule of FIG. 1 with a skin;
FIG. 3 is a schematic structural view of the truss unit of FIG. 1;
FIG. 4 is a front view of FIG. 3;
FIG. 5 is a schematic structural view of one embodiment of the truss elements of FIG. 4 shown collapsed along dashed lines;
FIG. 6 is a schematic structural view of another embodiment of the truss elements of FIG. 4 shown collapsed along dashed lines;
FIG. 7 is a schematic drawing of the collapsed form of the SMP composite based truss type collapsible capsule of FIG. 1;
FIG. 8 is a flow chart of a method of making the truss unit of FIG. 3;
FIG. 9 is a flowchart illustrating an embodiment of step S4 in FIG. 8;
FIG. 10 is a flowchart illustrating an embodiment of step S42 in FIG. 9;
FIG. 11 is a flowchart illustrating an embodiment of step S5 in FIG. 8;
fig. 12 is a schematic structural view of a truss unit mold in the method of manufacturing the truss unit of fig. 8;
fig. 13 is an assembly view of the truss unit mold of fig. 12.
Description of reference numerals:
1-cabin body support beam, 2-end enclosure support beam, 3-annular support beam, 4-cylinder frame structure, 5-annular butt joint, 6-circular platform frame structure, 7-skin and 8-truss unit;
81-core mould unit, 82-outer mould unit, 83-upper chord beam, 84-lower chord beam, 85-supporting web, 86-end web and 87-reinforcing web;
811-end mandrel, 812-reinforcement mandrel, 813-support mandrel;
821-vacuum pumping port, 822-glue injection port, 823-upper outer die, 824-lower outer die, 825-left block and 826-right block.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example 1
Referring to fig. 1, 2 and 7, a truss-type collapsible space capsule based on shape memory polymer composite comprises a plurality of capsule body support beams 1 and a plurality of head support beams 2; two ends of the cabin body support beams 1 are supported by the circumferential support beams 3 to form a cylindrical frame structure 4; two ends of the end socket support beams 2 are supported by the annular support beams 3 and the annular butt joints 5 to form a circular truncated cone frame structure 6; the circular truncated cone frame structure 6 extends towards the outer side of the cylindrical frame structure 4 along the axial direction of the cylindrical frame structure 4; the cabin body supporting beam 1, the end socket supporting beam 2, the annular supporting beam 3 and the annular butt joint 5 are all made of shape memory polymer composite materials. In order to enhance the structural strength of the manufactured space capsule, ensure the air tightness of the space capsule and improve the radiation-proof and impact-proof capabilities of the space capsule, skins 7 are arranged on the outer surfaces of the cylindrical frame structure 4 and the circular truncated cone frame structure 6, and the skins 7 are made of flexible fabrics and thin film materials.
The truss type collapsible and expandable space capsule based on the shape memory polymer composite material is provided with a plurality of capsule body supporting beams 1 and a plurality of end socket supporting beams 2, the capsule body supporting beams 1 and the end socket supporting beams 2 are supported by the hoop supporting beams 3 and the hoop butt joint 5 to form a cylinder frame structure 4 and a circular truncated cone frame structure 6, and the design of the cylinder frame structure 4 and the circular truncated cone frame structure 6 can improve the space of the manufactured space capsule on one hand and improve the bearing capacity of the manufactured space capsule on the other hand, so that the space capsule can maintain good structural rigidity when being impacted by space rubbish and meteor stones or the gas leakage of the capsule body, and the capsule body supporting beams 1, the end socket supporting beams 2, the hoop supporting beams 3 and the hoop butt joint 5 are made of the shape memory polymer composite material in the embodiment, and the shape memory polymer composite material has the light weight and the weight of common carbon fiber reinforced composite material, The capsule has the characteristics of high strength, specific strength and specific modulus, has the characteristics of generating large deformation in the environment above the glass transition temperature of the material, remembering the given shape after cooling, and returning to the original shape after heating up again, and can have the characteristics of large contraction and expansion ratio and light weight by designing the capsule by using the material with the shape memory effect and high utilization rate, so that the occupied space and weight of the prepared capsule can be reduced, and the prepared capsule can well meet the limitation of carrier rocket carrying capacity and carrying space envelope.
In this embodiment, the plurality of cabin support beams 1 and the plurality of head support beams 2 are symmetrically distributed, and the cabin support beams 1 are connected to the head support beams 2. In this embodiment, the plurality of cabin body support beams 1 and the plurality of head support beams 2 are symmetrically distributed, and the cabin body support beams 1 and the head support beams 2 are connected, so that the structures of the manufactured space capsule are integrated, and the force transmission uniformity of the cylindrical frame structure 4 and the circular truncated cone frame structure 6 is improved.
Moreover, in this embodiment, the number and the cross-sectional dimension of the cabin supporting beams 1 and the head supporting beams 2 are related to the carrying capacity of the manufactured capsule, when the carrying capacity of the manufactured capsule is higher, the cross-sectional dimension of the cabin supporting beams 1 and the head supporting beams 2 can be kept unchanged, the number of the cabin supporting beams 1 and the head supporting beams 2 is increased, or the number of the cabin supporting beams 1 and the head supporting beams 2 is kept unchanged, the cross-sectional dimension of the cabin supporting beams 1 and the head supporting beams 2 is increased, but when the number of the cabin supporting beams 1 and the head supporting beams 2 is larger, the synchronicity of simultaneous heating and unfolding of the plurality of cabin supporting beams 1 and the head supporting beams 2 is reduced, the number of required heating circuits is increased, which is not beneficial to the simplification of the whole structure, and when the number of the cabin supporting beams 1 and the head supporting beams 2 is larger, the furled space of the cabin supporting beams 1 and the head supporting beams 2 is reduced, the difficulty of drawing in the cabin body supporting beams 1 and the end socket supporting beams 2 is increased, so in the embodiment, in order to ensure the bearing capacity and the drawing simplicity of the manufactured space cabin, the cabin body supporting beams 1 and the end socket supporting beams 2 are all six in number, and the cabin body supporting beams 1 and the end socket supporting beams 2 are rigidly connected with the circumferential supporting beams 3 into a whole in a bolt and gluing mode.
Example 2
As shown in fig. 3 to fig. 6, the present embodiment is different from the above embodiments in that: in the embodiment, the cabin supporting beam 1 and the head supporting beam 2 are both composed of a plurality of truss units 8; the truss units 8 are made of shape memory polymer composite materials, wherein a plurality of truss units are rigidly connected into a whole in a bolt and glue joint mode, and each truss unit comprises an upper chord beam 83 and a lower chord beam 84; a plurality of supporting webs 85 are arranged between the upper chord beam 83 and the lower chord beam 84; the ends of the upper chord 83 and the lower chord 84 are connected by an end web 86; a reinforcing web 87 is provided between the end web 86 and the support web 85 adjacent the end web 86; one end of the reinforcing web 87 is connected with the upper chord beam 83, and the other end of the reinforcing web 84 is connected with the lower chord beam 85; the upper chord 83, lower chord 84, support webs 85, end webs 86, and reinforcing webs 87 are made of a shape memory polymer composite material.
In the embodiment, the upper chord beam 83, the lower chord beam 84, the support web 85, the end web 86 and the reinforcing web 87 of the truss unit 8 constituting the cabin supporting beam 1 and the head supporting beam 2 are all made of shape memory polymer composite materials, so that the cabin supporting beam 1 and the head supporting beam 2 of the embodiment have the characteristics of light weight, high mechanical property, fatigue resistance, corrosion resistance and aging resistance, and the truss units 8 forming the cabin body supporting beams 1 and the head supporting beams 2 can change shapes in a heating mode to realize the collapsibility of the manufactured space cabin, the space capsule can be in a folded state before the launch of the carrier rocket, and is thermally driven to be unfolded when reaching a space preset position, thereby saving a large space for the carrier rocket, and the unfolding speed of the space capsule is controllable when the space capsule is unfolded through thermal drive, so that the space capsule is butted with other capsule sections and then unfolded, and large impact on other spacecrafts cannot be caused.
In this embodiment, the supporting web 85, the upper chord beam 83 and the lower chord beam 84 form an isosceles trapezoid, when the manufactured capsule needs to be folded, the lower bottom edge of the isosceles trapezoid is heated, under the action of external force, the lower bottom edge of the isosceles trapezoid bends towards the upper bottom edge, the upper bottom edge and the lower bottom edge do not interfere with each other, so that bending is facilitated, meanwhile, the geometric structure of the isosceles trapezoid has high stability, and the bearing capacity of the manufactured capsule in this embodiment is further improved.
Furthermore, in this embodiment, in order to further increase the load carrying capacity of the resulting capsule, the reinforcing web 87 forms a right triangle with the support web 85 adjacent to the end web 86, i.e. the reinforcing web 87 is a right-angled side, the support web 85 adjacent to the end web 86 is a hypotenuse, and the upper chord 83 and the lower chord 84 are the other right-angled side.
In addition, in the embodiment, in order to facilitate the folding and unfolding of the manufactured space capsule, the upper chord beam 83 and the lower chord beam 84 are provided with heating devices (not shown in the figure), wherein the heating devices are flexible heating films, the thickness of the flexible heating films is 0.1 mm-5 mm, and the length and the width of the flexible heating films can be set according to the sizes of the capsule body support beam 1 and the head support beam 2. And the thermal driving mode for folding and unfolding the space capsule in the embodiment can also be sunlight irradiation driving, ultraviolet light irradiation driving, microwave driving, magnetic field heat generation driving and the like.
The method for stretching and furling the truss type foldable and deployable space capsule based on the shape memory polymer composite material comprises the following specific steps:
heating the maximum deformation parts of the truss units 8 forming the cabin body support beam 1 and the head support beam 2, which are the lower bottom edges of the isosceles trapezoids in the embodiment, namely the positions of the dotted lines in the figure, and heating the circumferential support beam 3;
when the deformation part of the truss unit 8 and the circumferential support beam 3 are heated to the glass transition temperature of the memory resin in the shape memory polymer composite material, the truss unit 8 and the circumferential support beam 3 are changed according to the pre-designed shape through external force;
fixing the truss units 8 and the circumferential support beams 3 in a predetermined state by a jig when the truss units 8 and the circumferential support beams 3 are deformed to the state by an external force, and disconnecting the heating device;
when the temperature of the material is reduced to room temperature, the clamp is removed, and the shape of the truss unit 8 and the annular supporting beam 3 after being folded by external force is fixed by the material;
when the truss units 8 and the circumferential support beams 3 are to be restored to the original shapes, they are thermally driven by the heating means.
In this embodiment, because the cabin supporting beams 1 and the head supporting beams 2 are six, the hoop supporting beams 3 can be bent into an equihexagonal shape in the folding process, so that the space cabin is axially folded, and a certain internal space is reserved for storing the inward folded parts of the cabin supporting beams 1 and the head supporting beams 2.
Example 3
Referring to fig. 8 to 13, the method for manufacturing the truss unit 8 constituting the cabin support beam 1 and the head support beam 2 according to the present embodiment includes:
s1, setting the core module 81 according to the shape and size of the truss unit 8, and attaching a release fabric to the core module 81, wherein the core module 81 includes an end core module 811, a reinforcing core module 812, and a supporting core module 813, and the end core module 811, the reinforcing core module 812, and the supporting core module 813 are arranged in the order of the end core module 811, the reinforcing core module 812, the supporting core module 813, the reinforcing core module 812, and the end core module 811 from left to right from the illustrated direction to form the core module 81, that is, the end core module 811 and the reinforcing core module 812 are both located at both ends of the supporting core module 813, and the reinforcing core module 812 is located between the end core module 811 and the supporting core module 813 adjacent to the end core module 811; the supporting core dies 813 can be provided in a plurality of pieces according to the size requirement of the truss unit to be manufactured, the section of the supporting core dies 813 is one or more of an isosceles trapezoid, a triangle, a rectangle or other polygons, in this embodiment, in order to improve the structural stability and the flexibility of the truss unit to be manufactured, the supporting core dies 813 with the section of the isosceles trapezoid are preferred, and the supporting core dies 813 are arranged in sequence in the order that the upper base is at the bottom, the upper base is at the top, the upper base is at the bottom, and the upper base is at the top … …, the section of the corresponding reinforcing core die 812 is preferably a right-angled triangle to further improve the bearing capacity of the truss unit to be manufactured, the inclined side of the reinforcing core die 812 has the same length as the waist of the supporting core die 813 and is parallel to the waist of the supporting core die closest to the end core die 811, the section of the end core die 811 is preferably a rectangle, the long side of the end core die 811 is equal to and parallel to the straight corner side of the reinforcing core die 812, the shapes of the end core mold 811 and the reinforcing core mold 812 are not limited to the above shapes, and can be adjusted as needed;
s2, laying a fiber reinforced layer on the core mold unit 81 pasted with the demolding cloth, and combining the core mold unit 81 according to the shape and the size of the truss unit 8, wherein the fiber reinforced layer is one of a carbon fiber reinforced layer, a glass fiber reinforced layer and a Kevlar fiber reinforced layer, the number of the laid layers of the fiber reinforced layer is changed along with the bearing capacity of the manufactured truss unit, if the bearing capacity of the truss unit 8 is large, the number of the laid layers of the fiber reinforced layer is large, and if the bearing capacity of the truss unit 8 is small, the number of the laid layers of the fiber reinforced layer is correspondingly reduced, so that the cost is saved;
s3, sequentially paving a fiber reinforced layer, demolding cloth and a flow guide medium on the outer surface of the combined core mold unit 81 from inside to outside, wherein the flow guide medium is a flow guide plastic net, and the flow guide plastic net can guide and guide the introduction of the memory resin, so that the uniformity of the memory resin in the fiber reinforced layer is improved, the uniformity of the manufactured truss unit 8 is further improved, and the performance of the manufactured truss unit 8 is further improved;
s4, closing the core mould unit 81 paved with the fiber reinforced layer, the demoulding cloth and the flow guide medium to form a closed truss unit mould;
s5, injecting memory resin into the closed truss unit mold, leading the memory resin into the fiber reinforced layer and curing to form an initial truss unit, wherein in order to improve the curing performance of the memory resin, the liquefaction of the memory resin led into the fiber reinforced layer is divided into three stages, namely a preheating stage, a first heating stage and a second heating stage, the preheating temperature of the preheating stage is less than the heating temperature of the first heating stage and less than the heating temperature of the second heating stage, and the preheating temperature of the preheating stage, the heating temperature of the first heating stage, the heating temperature of the second heating stage, and the constant temperature time of the preheating stage, the first heating stage and the second heating stage are adaptively adjusted according to the type of the memory resin;
and S6, demolding, and trimming the initial foldable fiber reinforced memory resin matrix composite truss unit to obtain the truss unit 8.
According to the preparation method of the truss unit 8 for forming the cabin supporting beam 1 and the head supporting beam 2, the fiber reinforced layer is laid on the truss unit mold, and the memory resin is introduced into the fiber reinforced layer through the vacuumizing assisted memory resin injection process, so that the truss unit 8 is prepared.
In this embodiment, the step S4 of closing the core mold unit 81 on which the fiber reinforced layer, the release fabric, and the fluid medium are laid to form a closed truss unit mold includes:
s41, arranging an outer die unit 82 outside the core die unit 81 paved with the fiber reinforced layer, the release cloth and the flow guide medium, wherein the outer die unit 82 comprises an upper outer die 823, a lower outer die 824, a left block 825 and a right block 826, the upper outer die 823, the lower outer die 824, the left block 825 and the right block 826 form a closed frame structure, and the core die unit 81 paved with the fiber reinforced layer, the release cloth and the flow guide medium is arranged in the closed frame structure;
s42, vacuumizing to form a closed truss unit mold;
and step S42, vacuumizing to form a closed truss unit mold, which is realized by the following specific steps:
s421, arranging a vacuum pumping port 821 on the outer mold unit 81 (specifically the upper outer mold 823);
s422, putting the core mold unit 81 and the outer mold unit 2 paved with the fiber reinforced layer, the demolding cloth and the flow guide medium into a vacuum bag;
s423, arranging a vacuum tube at the vacuum port 821;
s424, leading the vacuumizing tube out of the vacuum bag and sealing the vacuum bag by using a sealing rubber strip;
and S425, vacuumizing through a vacuumizing tube.
In this embodiment, in step S5, injecting a memory resin into the closed truss unit mold, so that the memory resin is introduced into the fiber reinforced layer and cured to form an initial truss unit, which specifically includes:
s51, arranging a glue injection port 822 on the outer mold unit 82 (specifically the lower outer mold 824);
s52, arranging a glue injection pipe at the glue injection port 822;
s53, leading the glue injection pipe out of the vacuum bag and sealing the vacuum bag by using a sealing adhesive tape;
and S54, injecting the memory resin into the closed truss unit mould through the glue injection pipe, and leading the memory resin into the fiber reinforced layer and curing to form the initial truss unit.
In this embodiment, the evacuation tube and the glue injection tube are led out, and the vacuum bag is sealed by the sealing rubber strip, so that the manufacturing process of the truss unit 8 in this embodiment is in a fully closed state, and the influence of the introduction of bubbles on the performance of the manufactured truss unit 8 is avoided.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. A truss type collapsible and expandable space capsule based on a shape memory polymer composite material is characterized by comprising a plurality of capsule body supporting beams (1) and a plurality of end enclosure supporting beams (2); the cabin body support beams (1) and the head cover support beams (2) are symmetrically distributed, and the cabin body support beams (1) are connected with the head cover support beams (2); two ends of the cabin body support beams (1) are supported by the circumferential support beams (3) to form a cylindrical frame structure (4); two ends of the end socket supporting beams (2) are supported by the annular supporting beams (3) and the annular butt joints (5) to form a circular truncated cone frame structure (6); the circular truncated cone frame structure (6) extends towards the outer side of the cylindrical frame structure (4) along the axial direction of the cylindrical frame structure (4); the cabin body supporting beam (1), the end socket supporting beam (2), the circumferential supporting beam (3) and the circumferential butt joint (5) are all made of shape memory polymer composite materials;
the cabin body supporting beam (1) and the seal head supporting beam (2) are both formed by a plurality of truss units (8); the truss unit (8) is made of a shape memory polymer composite material; the truss unit (8) comprises an upper chord beam (83) and a lower chord beam (84); a plurality of supporting webs (85) are arranged between the upper chord beam (83) and the lower chord beam (84), and the adjacent supporting webs (85), the upper chord beam (83) and the lower chord beam (84) form an isosceles trapezoid; the ends of the upper chord beam (83) and the lower chord beam (84) are connected through an end web (86); a reinforcing web (87) is arranged between the end web (86) and the support web (85) adjacent to the end web (86); one end of the reinforcing web (87) is connected with the upper chord beam (83), and the other end of the reinforcing web (87) is connected with the lower chord beam (84); the upper chord member (83), the lower chord member (84), the support web (85), the end web (86), and the reinforcement web (87) are made of a shape memory polymer composite material.
2. The shape memory polymer composite based truss type collapsible space capsule according to claim 1, wherein the number of the capsule body support beams (1) and the head support beams (2) is six.
3. The smp composite based truss type collapsible capsule according to claim 1, wherein the outer surfaces of the cylindrical frame structure (4) and the truncated cone frame structure (6) are provided with a skin (7).
4. The truss-like collapsible capsule based on shape memory polymer composite as claimed in claim 3 wherein the skin (7) is constructed of flexible fabric and film material.
5. The SMP composite based truss type collapsible capsule of claim 1 wherein said upper chord (83) and said lower chord (84) are provided with heating means.
6. The SMP composite-based truss-like collapsible space capsule of claim 5 wherein said heating means is a flexible heating membrane; the thickness of the flexible heating film is 0.1 mm-5 mm.
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| CN113309227B (en) * | 2021-05-28 | 2022-11-15 | 哈尔滨工业大学建筑设计研究院 | Moon cabin body structure system combining mechanical expansion and inflation expansion and method |
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