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WO2012020960A2 - Structure multifonctionnelle utilisable dans l'espace à l'aide d'un matériau composite de renfort en treillis - Google Patents

Structure multifonctionnelle utilisable dans l'espace à l'aide d'un matériau composite de renfort en treillis Download PDF

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Publication number
WO2012020960A2
WO2012020960A2 PCT/KR2011/005780 KR2011005780W WO2012020960A2 WO 2012020960 A2 WO2012020960 A2 WO 2012020960A2 KR 2011005780 W KR2011005780 W KR 2011005780W WO 2012020960 A2 WO2012020960 A2 WO 2012020960A2
Authority
WO
WIPO (PCT)
Prior art keywords
electronic
space
lattice
grid
multifunctional
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/KR2011/005780
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English (en)
Korean (ko)
Other versions
WO2012020960A3 (fr
Inventor
이주훈
장태성
서현석
임재혁
김원석
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Korea Aerospace Research Institute KARI
Original Assignee
Korea Aerospace Research Institute KARI
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Korea Aerospace Research Institute KARI filed Critical Korea Aerospace Research Institute KARI
Publication of WO2012020960A2 publication Critical patent/WO2012020960A2/fr
Publication of WO2012020960A3 publication Critical patent/WO2012020960A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • 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
    • B64G1/223—Modular spacecraft systems
    • 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
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
    • 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
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/54—Protection against radiation
    • B64G1/546—Protection against radiation shielding electronic equipment

Definitions

  • the present invention relates to a multifunctional structure for space using a grid-reinforced composite structure, and more specifically, as an advanced space structure technology, structure functions, electronics, compared to existing satellite structures have only functions limited to load support and internal equipment protection.
  • the present invention relates to a grid-reinforced composite multifunctional structure that not only provides various functions with functions, heat transfer function, radiation shielding and electronic interference shielding function, but also greatly improves weight saving and space utilization.
  • the multi-functional structure is a technology in which a flexible electronic PCB composed of a multi-chip module is attached to a lightweight composite panel using an adhesive material, and a radiation shielding and electronic interference shielding function is realized by covering the electronic PCB with a tungsten or tantalum foil.
  • the electronic PCB is bonded on the structural panel.
  • Electronic PCBs composed of multi-chip modules have the advantage of miniaturization, but have a disadvantage of requiring high costs in the manufacturing process.
  • the present invention is to minimize the volume occupied by the electronic portion outside the structure by inserting the electronic PCB integral to perform the electronic function in the structure. Therefore, it does not require the electronic box housing used to mount the electronic PCB, the weight saving effect can be obtained by the removal of the electronic box housing.
  • This configuration is achieved by using a grid reinforced composite panel as a satellite structure, using the space between adjacent grids as the electronic PCB insertion area.
  • the grid reinforcement panel is generally very excellent in stiffness and strength, it is intended to take advantage of the advantage that the structure itself can be made lightweight by applying a composite material.
  • an electronic interference shielding protective cover is used to safely accommodate the electronic PCB and shield the electronic interference.
  • the electronic part inserted into the structure is composed of a single PCB or a plurality of PCBs, and should be adhered to the structure or be fastened by a fastening component.
  • the lightweight lattice reinforced composite panel applied in the present invention may utilize both an equilateral triangle or a square or an equilateral triangle and a rectangular lattice form and an easily changeable lattice form.
  • the present invention relates to a grid-reinforced composite structural panel used as a space structure, a grating frame 10 formed by coupling a plurality of gratings 11, and a face member 20 bonded to one surface of the grating frame 10; And at least one electronic PCB 30 provided in the lattice space 21 formed by the lattice frame 10 and the face member 20 to perform an electronic function; and provided in the electronic PCB 30.
  • electrical wiring 50 for electrical data transfer and power distribution between the electronic PCB 30.
  • the radiation shielding plate 60 is inserted into the bottom of the grid space 21 to protect the electronic components such as the electronic PCB 30 from the space radiation environment; characterized in that it further comprises.
  • shielding cover 70 for shielding the electronic interference in the space environment to protect the electronic PCB 30 from external shocks, and shielding cover 70 for shielding the electronic interference; characterized in that it further comprises.
  • the lattice frame 10 is characterized in that the lattice 11 is repeatedly arranged while forming an equilateral triangle structure.
  • the grid frame 10 is characterized in that the grid 11 is repeatedly arranged while forming a rectangular structure.
  • the lattice frame 10 is characterized in that the lattice 11 is repeatedly arranged while forming an equilateral triangle structure and a square structure.
  • a part of the plurality of gratings 11 is removed to form a grating space 21 having a specific shape.
  • the grid 11 and the face member provided in the grid space 21 of the edge of the multifunctional structure and provided at the edge of the multifunctional structure in order to easily assemble and connect the multifunctional structure with the skeleton structure 1 of the space structure, the grid 11 and the face member provided in the grid space 21 of the edge of the multifunctional structure and provided at the edge of the multifunctional structure.
  • the grid frame 10 and the face member 20 is characterized in that composed of carbon fiber reinforced plastic (CFRP) material.
  • CFRP carbon fiber reinforced plastic
  • the grating frame 10 and the face plate 20 is characterized in that composed of a pitch-based carbon fiber reinforced composite material having a large thermal conductivity to dissipate heat generated by the electronic PCB (30).
  • the radiation shielding plate 60 or the shielding cover 70 is characterized in that the carbon fiber reinforced composite material prepreg and the metal thin film is composed of a multi-layer combination material.
  • the space satellite structure is to be equipped with electronic functions, thermal control function, radiation shielding function, and electronic period shielding function in the grid reinforced composite structural panel beyond the simple structural function of the original load supporting and equipment protection.
  • the electronic box is equipped with an electronic PCB assembly to the satellite structure, connecting the complex electrical wiring, the thermal control to each electronic box independently, but the present invention is to perform the electronic function
  • the structure is configured to provide a variety of functions.
  • FIG. 1 is a perspective view showing a multifunctional structure according to the present invention.
  • FIG. 6 is a perspective view illustrating an example in which the multifunctional structure according to the present invention is combined with a skeleton structure of a space structure;
  • FIG. 7 is a perspective view showing an example in which a doubler is coupled to a multifunctional structure according to the present invention.
  • FIG. 8 is a plan view (a) showing a shape in which the doubler is coupled to the multifunctional structure according to the present invention and A-A cross-sectional view (b) of the plan view,
  • FIG. 9 is a perspective view showing a shape in which the radiation shielding plate is coupled to the multifunctional structure according to the present invention.
  • FIG. 10 is a cross-sectional view of the electronic PCB is mounted on the multifunctional structure according to the present invention.
  • FIG. 11 is a perspective view of the electrical wiring connection between the electronic PCB in the multifunctional structure according to the present invention.
  • FIG. 12 is a perspective view of a state in which the electromagnetic interference shielding cover is mounted on the multifunctional structure according to the present invention.
  • FIG. 1 is a perspective view showing a multifunctional structure according to the present invention.
  • the present invention relates to a flat panel 100 used as a space structure, and includes an electronic PCB 30 in a grid space 21 in a lightweight composite structure 100 reinforced with a grid frame 10. ), And the electrical wiring 50 of the power distribution and data transfer functions is provided.
  • the shielding cover 70 may be additionally mounted.
  • a composite material having a high thermal conductivity may be disposed on the face member 20 of the structure panel.
  • Double panels (80) for mechanical connection are attached to the structural panels to facilitate the installation of structural panels equipped with electronic and heat transfer functions, as well as radiation shielding and electromagnetic interference shielding functions on the satellites.
  • the grid-reinforced composite structure panel which is a multifunctional structure of the present invention, can be used as a part of a satellite body, and is equipped with an electronic function, a heat transfer function, a radiation shielding function, and an electronic interference shielding function, so that the structure has various functions and reduces weight.
  • the efficiency of the structure is maximized by greatly improving the space utilization.
  • the present invention basically comprises a grating frame 10, the face plate 20, the electronic PCB 30, the connector 40 and the electrical wiring 50, the radiation shielding plate 60, the shield cover 70, it is possible to further include a doubler (80).
  • the lattice frame 10 is a lattice reinforcement frame formed by combining a plurality of grids 11 and has a rigidity and good load support, but may be lightly configured.
  • the grating frame 10 is used as a grating reinforced structural panel as a basic structure for supporting loads and protecting electronic equipment together with a facesheet 20 to be described below.
  • the facesheet 20 is bonded to one surface of the grating frame 10 and used together with the grating frame 10 as a grating reinforced structural panel as a basic structure for supporting loads and protecting electronic equipment.
  • the grid frame 10 and the face plate 20 is made of a lightweight carbon fiber reinforced plastic (CFRP), not only has a lightweight property, but also has an excellent rigidity and strength due to the reinforced grid structure.
  • CFRP carbon fiber reinforced plastic
  • a pitch-based carbon fiber reinforced composite material (CFRP) having a very high thermal conductivity may be applied to the grating 11 and the face plate 20.
  • a grid-reinforced composite structural panel is manufactured by applying a pan-based CFRP to the grating 11 and the face plate 20, and then pitch is promoted for the purpose of promoting thermal conductivity.
  • a series CFRP can be added to the faceplate.
  • FIG. 2 to 5 show various embodiments of the grating frame used in the multifunctional structure according to the present invention.
  • FIG. 2 illustrates that the grating 11 is repeatedly arranged while forming an equilateral triangle structure
  • FIG. 3 illustrates that the grating 11 is repeatedly arranged while forming a rectangular structure
  • FIG. 4 illustrates the grating ( 11 shows repeated arrangement while forming an equilateral triangle structure and a square structure.
  • FIG. 5 illustrates that a part of the plurality of gratings 11 is removed to form a grating space 21 having a specific shape.
  • an isotropic lattice of equilateral triangle structure in which the lattice 11 is disposed in the 60 °, 0 °, and ⁇ 60 ° directions may be used in the lattice reinforced composite structure panel.
  • a panel used in general is a quadrangular shape, when the regular triangular structure is repeatedly arranged, the triangular structure, not the equilateral triangle, may be disposed on the edge of the panel.
  • a grid frame having a rectangular structure in which the grid 11 is disposed in 0 ° and 90 ° directions may be used in the grid reinforced composite structure panel.
  • the overall rectangular shape structure is repeatedly arranged.
  • an isotropic lattice of an equilateral triangle structure and a lattice of a rectangular structure may be mixed and used in a lattice reinforced composite structure panel.
  • a triangular structure other than an equilateral triangle may be disposed at a portion where the edge portion or the equilateral triangle structure of the panel is adjacent to the rectangular structure.
  • the grating space 21 according to the shape of each grating 11 is formed. Therefore, a grid space of triangles other than an equilateral triangle, a square, or an equilateral triangle is formed. Since the electric PCB 30 mounted in the grid space may have various shapes, the shapes shown in FIGS. Part of the grid 11 was removed from the grid frame shape to secure a grid space having a specific shape.
  • the grid reinforced composite structure panel may be configured by removing some of the grids in order to secure the grid space 21 having a useful size and shape.
  • this is only an example and the present invention is not limited thereto.
  • the lattice configuration may be modified by an easy design so that the insertion and embedding of the electronic PCB may be desired according to the shape or size of the electronic PCB. have.
  • the present invention as shown in Figures 2 to 5, the lattice-reinforced composite material by the geometrical dimensions of the lattice structure, such as the thickness (t), height (h) of the grid, the spacing between adjacent grids (d, d1, d2)
  • the stiffness and strength of the structural panels can vary, and each geometric dimension can be adjusted during manufacturing to ensure that the desired stiffness and strength are achieved.
  • the thickness of the face material also depends on the thickness of the carbon fiber reinforced composite material laminated, it is possible to adjust the stacking direction and thickness to obtain sufficient rigidity and strength.
  • the present invention is a multi-functional structure 100 to which the grid reinforced composite structure panel is applied, as shown in Figure 6, the structure of the satellite is directly coupled to the frame of the satellite (frame), that is, the skeleton structure (1) of the space structure Can serve as a panel.
  • Armature fastening bolts (bolts) 2 are used to mount the grid reinforced structural panels to the satellite armature 1.
  • the sleeve bushing 3 guides the correct position of the fastening bolts and prevents the bolt heads from damaging the face material surface during fastening.
  • a doubler 80 made of metal or CFRP material is additionally mounted to the grid reinforced composite structural panel.
  • the doubler 80 is bonded to the interface between the lattice 11 and the face member 20 using an adhesive when manufacturing the lattice-reinforced composite structural panel, and serves to reinforce the fastening support strength.
  • FIG. 8 is a plan view (a) and AA cross-sectional view (b) showing a shape in which a doubler is coupled to a multifunctional structure according to the present invention, in which a doubler 80, a face plate 20, and a sleeve bushing 3 are combined; The cross section of the shape is shown.
  • the doubler 80 is to supplement the thickness of the thin face 20, the multifunctional structure 100 of the present invention facilitates the bolt coupling to the skeleton structure (1) of the space structure.
  • the sleeve bushing 3 also supplements the bolted connection.
  • the present invention is utilized for the purpose of attaching or mounting a plurality of electronic PCB 30 in the grating space 21 formed between adjacent gratings.
  • 9 is a perspective view showing a shape in which the radiation shielding plate is coupled to the multifunctional structure according to the present invention.
  • the shielding plate 60 is bonded.
  • the thickness of the radiation shield plate 60 is adjusted to obtain a sufficient radiation shielding effect, the light density shield plate is made by placing a dense metal and a lightweight CFRP material in a thin film multilayer, the grid space to be mounted electronic PCB Attach to the bottom of 21.
  • a single number of electronic PCBs 30 may be attached to the lattice space 21.
  • 10 is a cross-sectional view of the electronic PCB is mounted on the multifunctional structure according to the present invention.
  • a plurality of electronic PCBs 30 may be installed in the same lattice space 21 while maintaining a predetermined interval using the spacers 22.
  • the use of spacers is very useful when mounting electronic components on both sides of the electronic PCB 30 to increase the mounting density or stacking a plurality of electronic PCBs 30.
  • the spacer 22 is provided with only one electronic PCB 30 in one lattice space 21, both ends of the electronic PCB 30 so that the electronic PCB 30 does not contact the floor. It can also be used as a stand.
  • the electrical data transfer and power distribution between the electronic PCB 30 is made through the electrical wiring (50, harness), for connecting the electrical wiring generated in the grid Slot 12 guides the path of electrical wiring 50.
  • Data transmission and power distribution between the electronic PCB 30 and the outside are made through a connector 40.
  • the present invention includes a cover 70 for shielding the electronic PCB 30 from external impact and shielding the electromagnetic interference.
  • the cover fastening bolt 71 and the screw fastening cover nut 13 attached to the lattice 11 are used when the cover 70 is attached.
  • the shielding cover 70 is composed of a metal thin film and a lightweight CFRP material, and can be manufactured by arranging them in multiple layers.
  • the grid reinforced composite panel fastening the electromagnetic interference shield cover 70 includes an electronic PCB (30) therein, the radiation shielding function and heat transfer function and electromagnetic It acts as a multi-functional structure with a shielding function, and itself is assembled to a satellite to function as a satellite structural panel.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Casings For Electric Apparatus (AREA)
  • Aerials With Secondary Devices (AREA)

Abstract

La présente invention concerne une structure multifonctionnelle utilisable dans l'espace et réalisée avec un matériau composite de renfort en treillis. Elle concerne plus particulièrement un matériau composite de renfort en treillis, qui est une technologie de structure innovante utilisable dans l'espace et offrant diverses fonctions, dont une fonction de sauvetage, une fonction électronique, une fonction de conductivité thermique et une fonction de protection contre les rayonnements et contre les interférences électromagnétiques; et qui présente un poids considérablement réduit pour une utilisation plus efficiente de l'espace par comparaison avec la structure de satellite existante dont les fonctions de support de charge et de protection des équipements internes sont limitées. La structure multifonctionnelle de l'invention comprend: une armature en treillis formée par assemblage de plusieurs treillis; un élément de surface couplé à une surface de l'armature en treillis; au moins une carte de circuit imprimé (PCB) servant à l'exécution d'une fonction électronique et disposée dans l'espace de treillis créé par l'armature en treillis et l'élément de surface; et un fil électrique ménagé sur la PCB pour assurer un relais électronique des données, et pour répartir l'alimentation entre la PCB et un connecteur qui partage l'énergie avec l'extérieur et relaye des données.
PCT/KR2011/005780 2010-08-10 2011-08-09 Structure multifonctionnelle utilisable dans l'espace à l'aide d'un matériau composite de renfort en treillis Ceased WO2012020960A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020100076779A KR101037346B1 (ko) 2010-08-10 2010-08-10 격자 강화 복합재 구조를 이용한 우주용 다기능 구조체
KR10-2010-0076779 2010-08-10

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WO2012020960A2 true WO2012020960A2 (fr) 2012-02-16
WO2012020960A3 WO2012020960A3 (fr) 2012-05-03

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PCT/KR2011/005780 Ceased WO2012020960A2 (fr) 2010-08-10 2011-08-09 Structure multifonctionnelle utilisable dans l'espace à l'aide d'un matériau composite de renfort en treillis

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WO (1) WO2012020960A2 (fr)

Cited By (5)

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EP3109171A1 (fr) * 2015-06-24 2016-12-28 Airbus DS GmbH Panneau porte-outils pour un satellite modulaire et satellite modulaire
WO2017060392A1 (fr) * 2015-10-07 2017-04-13 Comat Aerospace Sa Panneau de satellite a feuille monocouche, procédé et appareil de production d'un tel panneau
CN109131939A (zh) * 2018-07-20 2019-01-04 中国空间技术研究院 一种基于电磁辐射环境的卫星设备布局方法及系统
CN113581493A (zh) * 2021-07-30 2021-11-02 北京微焓科技有限公司 板状卫星主框架及板状卫星
CN113581496A (zh) * 2021-09-10 2021-11-02 中国科学院微小卫星创新研究院 一种用于量产化小卫星的热控系统

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RU2535780C2 (ru) * 2013-03-06 2014-12-20 Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" Узел закрепления оборудования к силовой сетчатой конструкции из полимерных композиционных материалов
KR101343912B1 (ko) 2013-10-07 2013-12-20 한국항공우주연구원 우주 임무 적용을 위한 격자-강화된 경량 복합재료 전자장비 하우징
RU201018U1 (ru) * 2018-05-24 2020-11-24 Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" Универсальный узел крепления элементов к силовой сетчатой конструкции
RU199885U1 (ru) * 2020-01-16 2020-09-24 Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" Узел крепления элементов конструкции и оборудования космического аппарата
RU197988U1 (ru) * 2020-01-16 2020-06-10 Акционерное общество «Информационные спутниковые системы» имени академика М.Ф. Решетнёва" Узел крепления
RU202292U1 (ru) * 2020-09-25 2021-02-10 Акционерное общество "Информационные спутниковые системы"имени академика М.Ф. Решетнёва" Опорный узел

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JP4532425B2 (ja) * 2006-03-22 2010-08-25 三菱電機株式会社 人工衛星機器パネル

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3109171A1 (fr) * 2015-06-24 2016-12-28 Airbus DS GmbH Panneau porte-outils pour un satellite modulaire et satellite modulaire
WO2017060392A1 (fr) * 2015-10-07 2017-04-13 Comat Aerospace Sa Panneau de satellite a feuille monocouche, procédé et appareil de production d'un tel panneau
FR3042176A1 (fr) * 2015-10-07 2017-04-14 Comat- Concept Mec Et Assitance Technique Panneau de satellite a feuille monocouche, procede et appareil de production d'un tel panneau
CN109131939A (zh) * 2018-07-20 2019-01-04 中国空间技术研究院 一种基于电磁辐射环境的卫星设备布局方法及系统
CN113581493A (zh) * 2021-07-30 2021-11-02 北京微焓科技有限公司 板状卫星主框架及板状卫星
CN113581496A (zh) * 2021-09-10 2021-11-02 中国科学院微小卫星创新研究院 一种用于量产化小卫星的热控系统

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Publication number Publication date
KR101037346B1 (ko) 2011-05-26
WO2012020960A3 (fr) 2012-05-03

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