JP3868689B2 - Expansion membrane antenna for space - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to an expansion membrane antenna for space use, and more particularly to formation of a mirror surface thereof.
[0002]
[Prior art]
A conventional expansion membrane antenna for a large space, for example, has to be highly flexible or easily foldable in order to be housed in a launch vehicle. For this reason, the antenna mirror surface is composed of a radio wave reflection film using a metal mesh knitted with gold-plated fine metal wires and a deployment structure that expands it on a track, and what is commonly called a mesh mirror surface Mostly.
However, the above-mentioned fine metal wires cannot be formed infinitely thin lines, and there is a limitation in the knitting method, so that only a mirror surface that can be formed only at a low frequency up to several gigahertz can be formed.
Further, the mesh mirror surface described above is not economical because the material itself is expensive because gold plating is used, and a complicated and expensive deployment mechanism is required to widen the mesh.
For this reason, future plans such as observation at a frequency of about 50 GHz, VSOP2 (10 m diameter, Japan, 2008) and ARISE (14 m diameter, US, 2015) are more economical and more New structures with high accuracy are needed.
[0003]
By the way, the expansion membrane antenna tested by the SPATRAN 207 satellite launched in 1996 was developed as a mirror structure satisfying the above requirements (RE Freeland et al, “Validation of Unique Concept for a Low”). -Cost, Lightweight Space-deployable Antenna Structure ", IAF-93-I.1.204 (1993)). The shape of the mirror surface of the expansion membrane antenna in the orbit of this satellite is shown in FIG. 7, and the cross-sectional view of the mirror surface is shown in FIG.
[0004]
7 and 8, 1 is a satellite body of SPATRAN 207, 2 is a storage box that is attached to the satellite body 1 and stores the antenna mirror surface when stored, 3 is an expansion strut, and supports the antenna mirror surface from the satellite body 2 side. By means of expansion means not shown, expansion gas can be inserted on the track.
Reference numeral 4 denotes an expansion torus as an annular support. The annular support is positioned outside the peripheral edge of the balloon membrane 10 to be described later, expands the balloon membrane 10 and supports it in the expanded state. The expansion torus 4 of this example is attached to the distal end portion of the expansion strut 3 and expands in an annular shape by the expansion means on the track.
Reference numeral 5 denotes a tension cable, one end of which is attached to the inner peripheral portion of the expansion torus 4 and the other end is connected to a stitching portion 6 constituting the peripheral end of the antenna reflector.
The stitching portion 6 includes a transmission film 7 made of, for example, a dielectric thin film as a radio wave incidence side film disposed on the radio wave incidence side, and a plastic film 8 as a radio wave reflection side film having a radio wave reflection surface. In the state of being crushed, each of the circumferential portions, that is, the peripheral portions are stitched portions. Reference numeral 9 denotes an aluminum coat applied to the upper surface, that is, the concave surface of the plastic film 8 in order to increase the radio wave reflectance.
Hereinafter, in the present specification, the peripheral edges of the radio wave incident side film (transmission film 7) and the radio wave reflection side film (plastic film 8) are stitched together, and are formed so as to be freely expandable and contractible by taking gas into and out of the inside. The expanded body is referred to as a balloon membrane 10.
[0005]
In the above structure, an inexpensive aluminum-plated plastic film having a thickness of 6 μm is used as a radio wave reflecting film instead of an expensive gold-plated mesh, and the film is expanded by using 40 g or less of nitrogen instead of a complicated deployment mechanism. In other words, by using a method for creating a mirror surface, it was possible to form a smooth and highly accurate mirror surface at a low cost.
However, the following inconvenience occurred in the actual test.
That is, normally, on the track, the expansion strut 3 and the expansion torus 4 are expanded by expansion means (not shown). After the expansion torus 4 is expanded, the permeable membrane 7 and the plastic are expanded by expansion means (not shown). A gas such as nitrogen gas is injected into the balloon film 10 formed of the film 8 to expand the balloon film 10 and expand the plastic film 8 in a parabolic shape. The balloon membrane 10 has a predetermined shape by a balance between the force in the center direction of the balloon membrane 10 acting on the cable 5 and the force acting in the radial direction of the balloon membrane 10 acting on the tension cable 5 due to the expansion of the expansion torus 4. It was supposed to expand.
[0006]
However, the expansion / deployment of the balloon membrane 10 failed. The cause is reported to be that there was no control device for inflating and deploying, so that disordered deployment occurred and a pressure valve (not shown) that inflates the mirror surface failed (RE Freeland et al, "Significance of the Inflatable Antenna Experiment Technology ", AIAA-98-2104, SDM '98 (1998)).
In addition to the above disadvantages, variations in the material and thickness of the membrane material and variations in dimensions at the time of manufacture directly affect the developed shape of the balloon membrane 10, so that high mirror surface accuracy cannot be stably obtained. There was also a problem.
[0007]
[Problems to be solved by the invention]
As the mirror surface of a future, inexpensive, high-precision large-scale space expansion membrane antenna, the expansion membrane structure is basically compatible, but it is stable against various variations such as the specific method of expansion and deployment control and dimensions during manufacture. Unless the problem of sexuality is solved, there is little possibility of obtaining a desired mirror surface.
An object of the present invention is to solve the above-mentioned problems and to provide an expansion membrane antenna for space provided with a large-sized and highly accurate expansion membrane antenna mirror surface that is inexpensive and highly reliable.
[0008]
[Means for Solving the Problems]
  The invention of claim 1The surface is covered with a lattice network, and it expands in a parabolic shape by injecting gas into it.With balloon membraneThe parallelogram links positioned on the outer periphery of the lattice net covering the surface of the balloon membrane are composed of a lateral member forming a pair of upper and lower lateral sides parallel to the lateral direction, and a pair of left and right parallel to the longitudinal direction. A plurality of parallelogram links, each of which is composed of a vertical member that constitutes the vertical side of each other, and an oblique member that can be extended and contracted on a diagonal line and that is symmetrically disposed on the vertical member shared by each adjacent parallelogram link. Has a structure in which the sides are shared with each other in a ring shape so as to form a regular polygon, and has a shaft hole at the end of the lateral member constituting the synchronous deployment truss, and A gear mounted on a vertical member and disposed opposite to an end of the adjacent transverse member and a plurality of parallelogram links of the synchronously deploying truss are engaged with each other by the gear of the adjacent lateral member. And turn the gear above And a control motor for controllingIt is characterized by that.
[0009]
  The invention of claim 2A balloon membrane whose surface is covered with a lattice network and expands in a parabolic manner by injecting gas inside, and a parallelogram link positioned outside the periphery of the lattice network covering the surface of the balloon membrane is A plurality of horizontal members that constitute a pair of upper and lower lateral sides parallel to the direction, a longitudinal member that constitutes a pair of left and right vertical sides parallel to the longitudinal direction, and loop wires stretched diagonally. The parallel quadrilateral links have a structure in which the sides are shared with each other in a ring shape so as to form a regular polygon, and a shaft hole is formed at the end of the transverse member constituting the synchronous deployment truss. A plurality of parallel quadrilateral links of the synchronous deployment truss, and a gear mounted on the vertical member and disposed relative to an end of the adjacent horizontal member. Installed so that gears mesh with each other Is, and a rotary drum rotating controlling the gearIt is characterized by that.
[0010]
  The invention of claim 3A balloon membrane whose surface is covered with a lattice network and expands in a parabolic manner by injecting gas into the inside, and a parallelogram link positioned outside the periphery of the lattice network covering the surface of the balloon membrane A horizontal member that forms a pair of upper and lower horizontal sides parallel to the direction, a vertical member that forms a pair of left and right vertical sides parallel to the vertical direction, and each of the adjacent parallelogram links that can be expanded and contracted diagonally. A synchronously deployed truss comprising a diagonal member arranged symmetrically with the longitudinal member to be shared, and having a structure in which the plurality of parallelogram links are annularly coupled so as to share a side and to form a regular polygon. And a pulley having an axial hole at the end of the transverse member constituting the synchronous deployment truss and attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member;  A plurality of parallelogram links of the synchronous deployment truss are mounted such that the pulleys of the lateral members adjacent to each other are coupled by a synchronous belt, and a control motor that controls the rotation of the pulleys is provided.It is characterized by that.
[0011]
  The invention of claim 4A balloon membrane whose surface is covered with a lattice network and expands in a parabolic manner by injecting gas into the inside, and a parallelogram link positioned outside the periphery of the lattice network covering the surface of the balloon membrane A plurality of horizontal members constituting a pair of upper and lower lateral sides parallel to the direction, a longitudinal member constituting a pair of left and right vertical sides parallel to the longitudinal direction, and loop wires stretched diagonally. The parallel quadrilateral link has a structure in which the sides are shared with each other in a ring shape so as to form a regular polygon, and a shaft hole is formed at the end of the transverse member constituting the synchronous deployment truss. A pulley attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member, and a plurality of parallel quadrilateral links of the synchronous deployment truss. Pulley is synchronized belt It mounted as engaged, and and a rotary drum rotating controlling the pulleyIt is characterized by that.
[0012]
  The invention of claim 5 is the invention of claim 1.OrClaim4In the expansion membrane antenna for space described inThe balloon film is formed by bonding a lattice network formed of thin dielectric wires to the outer surface of one or both of the radio wave incident side film and the radio wave reflection side film of the balloon film.It is characterized by that.
[0014]
DETAILED DESCRIPTION OF THE INVENTION
Embodiment 1 FIG.
Embodiment 1 shows an embodiment of an annular support that is located outside the peripheral edge of the balloon membrane 10 and that supports the balloon membrane 10 via the tension cable 5 in a state of surrounding the balloon membrane 10 in an annular shape. The annular support has a synchronous deployment truss structure in which the constituent members are uniform, expand at a controlled speed, and the overall shape deforms and expands similarly.
Hereinafter, this synchronous deployment truss structure will be described with reference to FIGS. 1 (a) to 1 (c). 1A and 1B are structural views of an antenna mirror surface, where FIG. 1A is a plan view of a mirror surface viewed from a radio wave axis, FIG. 1B is a side view of a balloon membrane 10, and FIG. Note that the same reference numerals as those in FIGS. 7 and 8 described as the prior art have substantially the same or corresponding contents, and the description thereof is omitted.
[0015]
As shown in FIG. 1 (a), the synchronous deployment truss 12 as an annular support is located on the outermost peripheral surface of the mirror surface, that is, on the outer periphery of the balloon membrane 10, and a plurality of parallelogram links have their sides aligned with each other. It is a structure that is connected in an annular shape so as to share a regular polygonal shape.
FIG. 2 shows in detail the structure and operation of the basic periodic portion of the synchronous deployment truss 12 shown in FIG. 1, and FIG. 2 (a) shows the shape when housed in the rocket, FIG. 2 (b). ) Shows the shape during development, and FIG. 2C shows the shape after completion of development.
[0016]
2 (a) to 2 (c), 13 is a transverse member constituting a pair of upper and lower lateral sides parallel to the transverse direction constituting each of the parallelogram links, and 13a is an upper part thereof. A horizontal member 13b as a horizontal side, and a horizontal member 13b as a lower horizontal side.
Similarly, 14 is a longitudinal member constituting a pair of left and right longitudinal sides parallel to the longitudinal direction constituting each parallelogram link, and 14a is a longitudinal side located relatively on the left side in the figure. 14b shows a vertical member as a vertical side located on the right side.
The adjacent parallelogram links are connected in series in a ring shape by sharing the vertical members 14 as the vertical sides. That is, in the illustrated embodiment 1, the adjacent one of the horizontal members 13a and the other horizontal member 13b are pin-coupled so as to share the vertical member 14.
[0017]
Reference numeral 15 denotes a stretchable oblique member as a stretchable oblique member that runs so as to connect diagonal lines of each parallelogram link, and as shown in FIG. 2 (b), the upper end side of one longitudinal member 14a The both ends of the diagonal member 15 are pin-coupled to the lower end side of the other adjacent vertical member 14b. In this case, the stretchable diagonal members 15 of the adjacent parallelogram links are arranged so as to be symmetric with respect to the common longitudinal member 14. In this way, the attachment positions of the gear terminals 16 are not arranged alternately, but are aligned at the upper stage or the lower stage, thereby preventing interference between members.
In FIG. 2B, the angle θ in the figure indicates the rotation angle of the transverse member 13 with respect to the longitudinal member 14 during deployment.
[0018]
FIG. 3 is an exploded view showing details of a connecting portion between the horizontal member 13 and the vertical member 14 shown in FIG.
Reference numeral 16 in the drawing is a gear terminal having meshing teeth at its end, and this gear terminal 16 has a shaft hole and is attached to the end of the lateral member 13.
17 is a pin terminal attached to the other end of the horizontal member 13, 18 is a vertical member terminal which is attached to the end of the vertical member 14 and is interposed so that the gear terminals 16 of the adjacent horizontal members 13 mesh with each other. is there. This vertical member terminal 18 has a bearing hole for bearing two adjacent gear terminals 16, 16.
Pins 19 and 19 are gear shafts that are inserted through the shaft holes of the two gear terminals 16 and 16, pass through the bearing holes of the vertical member terminal 18, and pin-couple the horizontal member 13 and the vertical member 14. It is.
Reference numeral 20 denotes a C-clip attached to the tip of the pins 19 and 19, and 21 denotes an attachment instead of the clip 20 at one or more places, and an output shaft is connected to the pin 19 via a housing part. It is a control motor as a development control means constituting a drive system attached to the vertical member terminal 18.
[0019]
FIG. 4 is a cross-sectional view showing the configuration of the stretchable diagonal member 15 as the stretchable diagonal member shown in FIG.
In the figure, reference numeral 22 is an outer pipe, 23 is a pin terminal attached to the end of the outer pipe 22 and coupled to the vertical member 14 through a terminal similar to the vertical member terminal 18 not shown, and 24 is the outer pipe. 22 is an inner pipe that moves on the inside, 22 is a pin terminal that is attached to the end of the inner pipe 24 and is pin-coupled to the longitudinal member 14, and 26 is a spring terminal that is attached to the other end of the inner pipe 24. A coil spring 27 is attached between the pin connector 23 and the spring terminal 26 and serves as an urging means that always generates a force for bringing both together.
[0020]
As described above, the synchronously deployable truss structure according to the first embodiment has the telescopic oblique member 15 and the parallel or parallel terminals with the gear terminals 16 and 16 mounted as gears at the lower or upper lateral member 13 end. A truss structure in which a plurality of quadrilateral links are connected in series in an annular manner so that the gears of the adjacent lateral members 13 and 13, that is, the gear terminals 16 and 16, mesh with each other and the gear (the gear terminal 16) directly or indirectly. And a control motor 21 as a drive system for rotational control.
The operation of this synchronous deployment truss structure will be described below with reference to FIGS.
First, the expansion strut 3 for electrically and mechanically coupling the satellite body 2 and the expansion membrane antenna mirror surface by an expansion device or a deployment mechanism (not shown), or a function corresponding to the function performed by the expansion strut 3 The product is inflated or expanded.
After deployment, for example, by a command from the ground, a parallelogram link housed in a zigzag shape as shown in FIG. 2A by a drive system (drive means) such as a release mechanism (not shown). As shown in FIG. 2 (b), the length of the stretchable diagonal member 15 is shortened by the contraction force of the coil spring 27 incorporated in the stretchable diagonal member 15, so that the parallelogram link shape becomes rectangular. Deploy to get closer.
[0021]
At the time of deployment, the transverse member 13 rotates from zero to 90 degrees with respect to the longitudinal member 14, but since this rotation angle θ is transmitted to the adjacent transverse member 13 by the gear terminal 16, all the parallelogram links are Rotate simultaneously by the same angle and have the same deformation shape. In this case, the rotational speed of the transverse member 13 can be controlled to a desired or predetermined speed by the control motor 21.
[0022]
As described above, in the synchronous deployment truss 12 shown in the first embodiment, the parallelogram links connected in an annular manner are synchronized as described above, and are deployed in a concentric circle at the same time in the same shape. In order to go, the balloon membrane 10 supported in the ring of a series of parallelogram links that circulate in an annular shape is spread uniformly through the tension cable 5.
That is, in the synchronous deployment truss 12 designed in a circumferential shape, the diameter of the circle in the middle of deployment is approximately SIN [θ] times the diameter after deployment, so the value of this rotation angle θ and the rate of change (speed) By controlling the above, the balloon membrane 10 can be spread uniformly at a predetermined speed.
Then, after the synchronous deployment truss 12 is completely deployed (rotation angle θ = 90 degrees), a gas such as air or nitrogen is inserted into the balloon membrane 10 by, for example, an air insertion cylinder as a gas insertion means (not shown). Then, the balloon membrane 10 expands in a parabolic shape as shown in FIG.
[0023]
In the first embodiment, as shown in FIG. 1B, thin dielectric wires are formed on the outer surfaces of both the transmission film 7 as the radio wave incident side film and the dielectric film 8 as the radio wave reflection side film of the balloon film 10. For example, a triangular lattice network formed of stretched cables is joined.
The lattice network 11 attached to the outer surface of the balloon film 10 may be provided on either the radio wave incident side film or the radio wave reflection side film of the balloon film 10. Further, the lattice is not limited to a triangular shape, and may have an appropriate shape.
Thus, by covering the surface of the balloon membrane 10 with the lattice network 11, a predetermined surface accuracy is achieved under a predetermined atmospheric pressure.
[0024]
For example, assuming that the average radius of curvature of the balloon membrane 10 is ρ, the membrane tension is N, the radius of the circumscribed circle of the average triangular lattice of the lattice network 11 is R, and the cable tension is T, the optimum surface of the balloon membrane 10 to be obtained. The accuracy δ is given by [Equation 1].
[Formula 1]
δ = 0.2 × [R²/ (2ρ)] × [T / (N × L)]
Considering that the optimum surface accuracy δ obtained with the mesh expansion mirror surface is given by [Equation 2], the optimum surface accuracy of the balloon membrane is the normal design range (1 >> [T / (N × L)]). It can be seen that a much better value can be obtained than the optimum surface accuracy obtained with the mesh expansion mirror surface.
[Formula 2]
δ> 0.2 × [R²/ (2ρ)]
Even when the material of the balloon membrane 10 varies, the shape of the balloon membrane 10 can be suppressed to local deformation because of the lattice network 11, and therefore there is little possibility of significant deterioration in surface accuracy.
[0025]
According to the first embodiment, when the antenna is deployed, the synchronous deployment truss 12 is constituted by the parallelogram links in which the stretchable diagonal members 15 having contraction force are arranged on the diagonal lines, and each parallelogram link is a gear terminal. The balloon film 10 can be expanded in synchronism at 16 and at a desired speed by the control motor 21, so that the balloon membrane 10 can be spread radially and uniformly, thereby increasing the reliability of the expansion. That is, since the synchronous deployment truss 12 is completely synchronized by the gear terminal 16 and the deployment speed is controlled to a desired value by the control motor 21, material breakage due to variation in expansion is avoided, and the balloon membrane 10 is reliable. High and stable expansion can be performed.
In addition, since the surface of the balloon membrane 10 is covered with a lattice network 11 formed of a dielectric cable, an expansion membrane antenna for space having a mirror surface that is less affected by variations in the material and dimensions of the membrane is provided. Can do.
[0026]
In the first embodiment, the lattice network 11 is attached to the outer surfaces of both the permeable membrane 7 and the plastic membrane 8. However, the same effect can be obtained by using only the surface of the plastic membrane 8. This is effective when a mirror surface is used in a high frequency band such as the Ku to Ka band, and even if a slight amount of radio wave blocking becomes a problem. In this case, since the symmetry of the net shape is lost, an accurate detailed balance calculation and a manufacturing method are required.
In addition, although the triangular mesh is used as the mesh shape of the lattice net 11, a square or hexagonal shape can provide a qualitatively equivalent effect. This is useful when manufacturing is easy or when an interface with special accessories is required. That is, by replacing the lattice network having a triangular mesh shape with a square or hexagonal lattice network, it can be manufactured at low cost or adapted to a special interface.
Further, by attaching a triangular lattice network formed of, for example, a dielectric cable to the outside of the balloon membrane 10, a highly accurate mirror surface that is resistant to variations in materials or manufacturing can be obtained.
Further, the position of the gear terminal 16 of the synchronous deployment truss 12 is set at the end of the vertical member 14 to which the stretchable diagonal member 15 is not attached. Can obtain an equivalent effect. This is effective when interference between the gear terminal 16 and other members must be avoided.
[0027]
Embodiment 2. FIG.
In the second embodiment, in the structure of the synchronous deployment truss 12 of the first embodiment, the synchronization of the deployment is realized by using a pulley instead of the gear, that is, the gear terminal 16. This will be described with reference to FIG. FIG. 5 is a side view showing a state in which the pulleys 28 and 28 of the adjacent lateral members 13 are in contact with each other (corresponding to a state in which the gear terminals 16 and 16 are engaged with each other). The vertical member terminal 18 having a bearing hole for bearing is omitted.
In FIG. 5, 28 is a pulley attached to the cross member 13 instead of the gear terminal 16, and 29 is a synchronous belt which is brought into contact with each other, i.e., the adjacent pulley 28 and the pulley 28. is there.
[0028]
Next, the operation of this synchronous deployment truss structure will be described. Since the synchronous belt 29 is looped between the parallelogram pulley 28 and the pulley 28 adjacent to each other so as to draw a figure of 8, the same as in the case of the gear terminal 16 of the first embodiment, The rotation angle θ of the horizontal member 13 is transmitted to the adjacent horizontal member 13.
In the first embodiment, when a temperature difference or an extreme temperature change occurs between the adjacent gear terminals 16 and 16, the gear terminals 16 are engaged with each other, the contact resistance is increased, and the transmission of the deployment angle is efficient. However, since the synchronization belt 29 is used in the second embodiment, perfect synchronization is somewhat sacrificed by giving the synchronization belt 29 appropriate elasticity. Since there is no contact between the gear of the horizontal member 13 and the gear of the horizontal member 13, the spread angle can be transmitted without increasing the contact resistance. Therefore, the second embodiment is extremely effective when used on a trajectory having a severe thermal environment.
[0029]
Embodiment 3 FIG.
In the third embodiment, in the synchronous deployment truss structure of the first embodiment, the driving force and the deployment speed are controlled by using a wire and a rotating drum instead of the telescopic oblique member 15 and the control motor 21. . This will be described with reference to FIGS. 6 (a) to 6 (c). 6 (a) shows a shape when stored, FIG. 6 (b) shows a shape during development, and FIG. 6 (c) shows a shape after development. FIGS. 2 (a) to 2 (c) in the first embodiment. It corresponds to.
[0030]
6A to 6C, reference numeral 30 in the figure is a loop wire. One end of the loop wire 30 is fixed to a rotating drum 32 described later, and the other end extends to the synchronous deployment truss 12 side.
The intermediate portion of the loop wire 30 extending to the side of the synchronous deployment truss 12 is arranged to extend to the diagonal position of each parallelogram link constituting the synchronous deployment truss 12, that is, the position of the oblique member 15. , It makes a round in the circumferential direction of the synchronous deployment truss 12.
A transmission pulley 31 is attached to the vertical member 14 of each parallelogram link, changes the direction of the loop wire 30 and shifts to the adjacent parallelogram link.
The rotating drum 32 is a drum that winds and unwinds the loop wire 30, and is installed at a proper position of the synchronous deployment truss 12.
[0031]
Next, the operation of the third embodiment will be described.
First, when a mirror surface holding mechanism (not shown) is released during storage, the rotating drum 32 rotates and starts to wind up the loop wire 30.
When the loop wire 30 is wound up, the loop wire 30 is routed on the diagonal line of each parallelogram link while being redirected by the transmission pulley 31, so that the synchronous deployment is performed in accordance with the shortening of the diagonal line. As shown in FIG. 6B, the parallelogram links constituting the truss 12 are deformed toward the rectangular shape as the transverse member 13 rotates.
The rotation angle θ of the lateral member 13 is synchronized with the gear terminal 16 in the case of the first embodiment and by the synchronization belt 29 in the case of the second embodiment. This is achieved by controlling the rotational speed.
In the third embodiment, the parallelogram is hung around the transmission pulley 31 appropriately disposed without using the elastic member 15 having the complicated elastic mechanism parts used in the first or second embodiment. Since one loop wire 30 extending on the diagonal line of the link is wound up by a rotating drum, a lightweight and inexpensive synchronous deployment truss can be obtained.
[0032]
【The invention's effect】
  According to the invention of claim 1,Each of the plurality of parallelogram links includes a horizontal member that forms a pair of upper and lower horizontal sides parallel to the horizontal direction, a vertical member that forms a pair of left and right vertical sides parallel to the vertical direction, and each parallelogram A parallelogram link having a telescopic diagonal member that runs so as to connect diagonal lines of the shape link, and a gear mounted on the end of the transverse member, is arranged in series in an annular manner so that the gear of the adjacent transverse member is engaged. Because it was a synchronously deployed truss structure equipped with a truss structure coupled to and a drive system for rotating the gear,With a mirror surface that allows shape control during expansionIn other words, antenna mirror surface capable of expansion and deployment controlAn expansion antenna for space equipped with
[0033]
  According to the invention of claim 2,Each of the plurality of parallelogram links includes a horizontal member that forms a pair of upper and lower horizontal sides parallel to the horizontal direction, a vertical member that forms a pair of left and right vertical sides parallel to the vertical direction, and each parallelogram Loop wires stretched diagonally of the shape link, and parallel parallel links with gears attached to the ends of the transverse members in series so that the gears of the transverse members adjacent to each other mesh. Because it is a synchronized deployment truss structure with a combined truss structure and a drive system that rotates the gears, expansion and deployment control is possibleA space expansion antenna having an antenna mirror surface can be provided.
[0034]
  According to the invention of claim 3,Each of the plurality of parallelogram links includes a horizontal member that forms a pair of upper and lower horizontal sides parallel to the horizontal direction, a vertical member that forms a pair of left and right vertical sides parallel to the vertical direction, and each parallelogram A parallel link with multiple parallelogram links that have a telescopic diagonal member running so as to connect the diagonals of the link and with a pulley attached to the end of the transverse member. Since the truss structure and the synchronous deployment truss structure with the drive system that rotates the pulley,It is possible to provide a space expansion antenna having an antenna mirror surface capable of expansion and deployment control.
  In addition, by replacing the gear terminal with a pulley and a synchronous belt, it is possible to ensure deployment synchronization with a low resistance even under severe thermal deformation.
[0035]
  According to the invention of claim 4,Each of the plurality of parallelogram links includes a horizontal member that forms a pair of upper and lower horizontal sides parallel to the horizontal direction, a vertical member that forms a pair of left and right vertical sides parallel to the vertical direction, and each parallelogram Truss which has a loop wire stretched on the diagonal line of a link and a plurality of parallelogram links each having a pulley attached to the end of the transverse member, and the pulleys of the transverse members adjoining each other by a belt Because it is a synchronous deployment truss structure with a structure and a drive system that rotates the pulley,It is possible to provide a space expansion antenna having an antenna mirror surface capable of expansion and deployment control.
  Also, by replacing with a pulley and a synchronous belt instead of a gear terminal, it is possible to ensure deployment synchronization with a low resistance even under severe thermal deformation..
[0036]
  According to the fifth aspect of the present invention, since the lattice network is attached to the outer surface of the balloon membrane, it is possible to provide a space expansion antenna having a highly accurate antenna mirror surface with little mirror deterioration even with respect to material / dimension variations. .
[Brief description of the drawings]
FIGS. 1A and 1B are structural views of an antenna mirror surface according to a first embodiment, where FIG. 1A is a plan view of a mirror surface viewed from a radio wave axis, FIG. 1B is a side view of a balloon membrane 10, and FIG. FIG.
FIGS. 2A and 2B are diagrams showing in detail the structure and operation of the basic period portion of the synchronous deployment truss of the first embodiment, wherein FIG. 2A is a diagram showing a shape when housed in the rocket, and FIG. (C) is a figure which shows the shape after completion | finish of expansion | deployment.
FIG. 3 is an exploded view showing details of a connecting portion between a horizontal member and a vertical member according to the first embodiment.
4 is a cross-sectional view showing a configuration of a stretchable diagonal material as an oblique member according to Embodiment 1. FIG.
FIG. 5 is a side view showing a state where pulleys of lateral members adjacent to each other in Embodiment 2 are met.
FIGS. 6A and 6B are diagrams showing a synchronous deployment truss structure according to a third embodiment, where FIG. 6A is a diagram illustrating a shape when stored, FIG. 6B is a diagram illustrating a shape during deployment, and FIG. 6C is a diagram illustrating a shape after deployment. It is.
FIG. 7 is a perspective view of a conventional space expansion antenna.
8 is a cross-sectional view of the mirror surface of FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Satellite, 2 Storage box, 3 Expansion strut, 4 Expansion torus, 5 Tension cable, 6 Sewing part, 7 Permeation membrane, 8 Plastic membrane, 9 Aluminum coating, 10 Balloon membrane, 11 Grid network, 12 Synchronous deployment truss (circle) Annular support), 13 transverse member, 14 longitudinal member, 15 telescopic diagonal material, 16 gear terminal (gear), 18 longitudinal member terminal, 21 control motor (drive system / deployment control means), 22 outer pipe, 24 inner pipe, 28 pulleys, 29 synchronous belts, 30 loop wires, 31 transmission pulleys, 32 rotating drums (drive system / deployment control means).

Claims (5)

A balloon membrane whose surface is covered with a lattice network and expands in a parabolic shape by injecting gas into the interior ,
The parallelogram links positioned on the outer periphery of the lattice network covering the surface of the balloon membrane include a pair of lateral members that form a pair of upper and lower lateral sides parallel to the lateral direction, and a pair of left and right parallel to the longitudinal direction. It is composed of a vertical member that constitutes the vertical side, and an oblique member that can be expanded and contracted on a diagonal line, and is symmetrically disposed on the vertical member shared by each adjacent parallelogram link,
A synchronous deployment truss having a structure in which the plurality of parallelogram links are connected in a ring shape to share a side with each other to form a regular polygon;
A gear having an axial hole at the end of the transverse member constituting the synchronous deployment truss and attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member;
A plurality of parallel quadrilateral links of the synchronous deployment truss, mounted so that the gears of the lateral members adjacent to each other mesh with each other, and a control motor for controlling the rotation of the gears;
An expansion membrane antenna for space , comprising: A balloon membrane whose surface is covered with a lattice network and expands in a parabolic shape by injecting gas into the interior,
The parallelogram links positioned on the outer periphery of the lattice network covering the surface of the balloon membrane include a pair of lateral members that form a pair of upper and lower lateral sides parallel to the lateral direction, and a pair of left and right parallel to the longitudinal direction. Consists of a vertical member constituting the vertical side and a loop wire stretched diagonally,
A synchronous deployment truss having a structure in which the plurality of parallelogram links are connected in a ring shape to share a side with each other to form a regular polygon;
A gear having an axial hole at the end of the transverse member constituting the synchronous deployment truss and attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member;
A plurality of parallel quadrilateral links of the synchronously deployable truss, mounted so that the gears of the lateral members adjacent to each other mesh with each other, and a rotary drum for controlling the rotation of the gears;
An expansion membrane antenna for space , comprising: A balloon membrane whose surface is covered with a lattice network and expands in a parabolic shape by injecting gas into the interior,
The parallelogram links positioned on the outer periphery of the lattice network covering the surface of the balloon membrane include a pair of lateral members that form a pair of upper and lower lateral sides parallel to the lateral direction, and a pair of left and right parallel to the longitudinal direction. It is composed of a vertical member that constitutes the vertical side, and an oblique member that can be expanded and contracted on a diagonal line, and is symmetrically disposed on the vertical member shared by each adjacent parallelogram link,
A synchronous deployment truss having a structure in which the plurality of parallelogram links are connected in a ring shape to share a side with each other to form a regular polygon;
A pulley having an axial hole at the end of the transverse member constituting the synchronous deployment truss and attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member;
A plurality of parallelogram links of the synchronous deployment truss, mounted so that the pulleys of the lateral members adjacent to each other are coupled by a synchronous belt, and a control motor for controlling the rotation of the pulleys;
An expansion membrane antenna for space , comprising: A balloon membrane whose surface is covered with a lattice network and expands in a parabolic shape by injecting gas into the interior,
The parallelogram links positioned on the outer periphery of the lattice network covering the surface of the balloon membrane include a pair of lateral members that form a pair of upper and lower lateral sides parallel to the lateral direction, and a pair of left and right parallel to the longitudinal direction. Consists of a vertical member constituting the vertical side and a loop wire stretched diagonally,
A synchronous deployment truss having a structure in which the plurality of parallelogram links are connected in a ring shape to share a side with each other to form a regular polygon;
A pulley having an axial hole at the end of the transverse member constituting the synchronous deployment truss and attached to the longitudinal member and disposed opposite to the end of the adjacent transverse member;
The parallelogram linkage plurality of the synchronous deployable truss is mounted such that the flop Ri adjacent the transverse member is coupled by synchronous belt with each other, a rotary drum rotating controlling the pulley
An expansion membrane antenna for space , comprising: 2. The balloon film according to claim 1, wherein a lattice network formed of thin dielectric wires is bonded to an outer surface of one or both of a radio wave incident side film and a radio wave reflection side film of the balloon film. 5. The space expansion membrane antenna according to any one of items 1 to 4 .

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