Patent Publication Number: US-6214144-B1

Title: Method of making tensioned mesh for large deployable reflectors

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This is a division of application Ser. No. 08/888,487 filed Jul. 7, 1997 now U.S. Pat. No. 5,969,695. 
     The present invention is related to U.S. patent application Ser. No. 08/888,762, entitled “Edge-Supported Umbrella Reflector With Low Storage Profile” (PD-970097) and U.S. patent application Ser. No. 08/888,486, entitled “A Continually Adjustable Nonreturn Knot” (PD-960515), both of which are filed on the same day as the present invention and the disclosures of which are hereby incorporated by reference herein. 
    
    
     TECHNICAL FIELD 
     The present invention relates to systems for controlling and retaining tension in a mesh reflector in the deployed condition, as well as for managing the mesh during launch and transport in the stowed condition. 
     BACKGROUND ART 
     Dish-shaped mesh reflectors are used in various communication systems today, particularly on satellites in orbit around the Earth. Various systems are known for tensioning the various components of a mesh reflector as it is being made and assembled, and for managing the mesh during transport and launch. The known methods for tensioning the mesh reflectors, however, and for retaining the tension in the stowed and launch stages, are relatively costly and involve the use of unnecessary weight. For satellites in particular, any savings in cost and weight can be very significant. 
     Known mesh tensioning systems use rigid or semi-rigid edge strips along the outer edges (catenaries) of the mesh and often along the gore seams to lock-in tension in the mesh from the time the mesh is laid out until it is installed on a foldable reflector structure. Known systems for retention of the mesh typically use flat straps tensioned by metallic helical springs located behind the mesh. 
     Known mesh management systems are typically either containment or control systems. In the first category, the mesh is confined to a certain volume and limited in movement within that volume by friction as the layers of the mesh are compressed together. The second category uses positive means to control the location of the mesh prior to deployment and is more reliable. 
     Known methods, apparatuses, and systems for mesh integration and tension control, mesh retention, and mesh management, add additional weight and cost to the spacecraft and satellite. Although such systems are known to work relatively satisfactory, they may increase thermal distortion and make the adjustment of the mesh surface shape more difficult. 
     It is an object of the present invention to provide improved methods, apparatuses, and systems for mesh integration and tension control, mesh retention, and mesh management for mesh-type reflectors, particularly for use in satellites. It is also an object of the present invention to reduce the weight and expense of the tensioning, retention, and management systems for mesh reflectors. 
     It is another object of the present invention to avoid the use of semi-rigid and rigid strips on the mesh during manufacture and assembly, particularly to save weight and cost, enhance reflector transparency, and eliminate mesh stiffening. It is a still further object of the present invention to enhance thermal stability and mesh shape adjustability of a mesh reflector. 
     It is an additional object of the present invention to provide a more accurate and direct tensioning control system for a mesh reflector while at the same time reducing weight and solar blockage by eliminating straps and metallic springs used in prior art systems. It is also an additional object of the present invention to provide a mesh retention system which utilizes small bending springs located at chord intersections. 
     It is still a further object of the present invention to provide a mesh management system that provides complete mesh control that automatically releases during deployment of the reflector. It is another object of the present invention to use a mesh management system on a deployable umbrella-type reflector which controls the mesh and edge members in the stowed condition in order to assure reliable deployment of the reflector in space. 
     These and other objects and purposes of the present invention will become apparent from the following description of the invention, particularly when viewed in accordance with the accompanying drawings and appended claims. 
     SUMMARY OF THE INVENTION 
     The present invention provides unique methods, apparatuses, and systems for mesh integration and tension control, mesh retention, and mesh management of a mesh-type reflector. Any deployable mesh-type reflector can benefit from the present invention. In particular, current and future Geo-mobile communication satellites can use the invention in place of mesh reflectors utilizing known art and save expense and weight while enhancing performance and reliability. Other deployable reflectors may also be able to use certain features and aspects of the present invention. 
     When the mesh reflector is being made, gore-size tensioning tables are used to establish the requisite tension in the gores. Double-sided adhesive tape is used to temporarily lock-in the pre-tensions in the gores on the tensioning table until the gores are sewn together. String-like chord members positioned in sewn-over pockets at the outer edges of the gores serve as the catenary members. Once the gores are sewn together forming the flexible mesh reflector member, the pre-tensioned mesh member is positioned on a reflector framework made of a plurality of ribs arranged around a center hub in an elliptical or circular pattern. The mesh reflector is then secured to, and tensioned on, the reflector frame structure. The reflecting surface shape is approximated by many substantially flat trapezoidal facets whose corners or nodes are positioned near attachment points on the frame structure. The edges of the facets are retained in a substantially straight condition by a network of tensioned edge members positioned toward the focus side of the dish-shaped mesh reflector. 
     Small nodal assemblies with composite bending springs are positioned on each of the corners or nodes of the facets forming the mesh reflecting surface. The assemblies are attached to the framework structure through the mesh and include small “omega”-shaped springs. Adjacent pairs of the spring members are alternately oriented in the radial and tangential directions at the nodal assemblies to permit desired tensioning in both radial and tangential edge members. Light thermally stable chord members form the edge members constituting the retention network. Each chord member has one end attached to a bending spring and the other end attached to an adjacent nodal assembly, preferably using an unique adjustable knot mechanism. 
     Once all of the nodal assemblies and chord members are positioned in place, each chord member is tensioned to a specified value selected to minimize mesh pillowing and tangential loading on the reflector ribs. Compared to prior mesh assemblies which utilize straps tensioned by springs located behind the mesh, the chord member and nodal assembly system is lighter, less expensive, provides less solar blockage, and is easier to accurately tension. 
     The mesh management system in accordance with the present invention maintains the reflector mesh under tension control during ground handling, launch, and boom deployments, and then automatically releases the tension as the reflector is deployed into its final shape and position. The mesh management system utilizes a framework of chord members, small pieces of tubing, guide washers, beads, and a pair of comb-like rack members. The guide washers are attached to the non-focus side of the mesh reflector member and chord tensioning members are positioned through the washers from the central hub of the reflector to the outer edges of the gores. A single chord member is used near the hub of the reflector and is spliced into two pieces as it approaches the outer edges of the gores. The inner ends of the mesh management chord members are secured to the reflector hub while loops formed at the outer ends are individually slipped over teeth or fingers of the comb-like rack members. The rack members in turn are pivotally secured to the main reflector rib member. Small flexible tubular members are positioned over the mesh management chords adjacent the outer edges of the reflector and beads or similar structures are positioned on the tubular members and used to help hold the mesh into a certain configuration for stowing and launch. 
     With the mesh management system, the chord members force the majority of the gore material inwardly when the reflector is collapsed and stowed. Near the outer edges of the mesh, however, the management system with the chord members and beaded tubular members urge the outer portions of the mesh upwardly toward the hub or center of the reflector. When the reflector is stowed, loops at the ends of the mesh management chord members are secured to the rack members and the comb teeth are retained in a certain orientation prohibiting release of the chord members. When final deployment commences, the rack members are allowed to rotate allowing the loops to slide off freeing the chord members and tubular members. 
     With the present invention, initial constraint and final release of the comb-like rack members is achieved without the need for an active release system or separate ground commands. The present invention provides mesh control at less expense and weight and is more reliable than known systems. The present invention requires fewer elements and control steps in order to disengage the stowed mesh and free it at time of deployment. 
     The above and additional elements, features, benefits and advantages of the present invention will become apparent from the following description of the present invention, particularly when viewed in accordance with the attached claims and accompanying drawings. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     FIG. 1 illustrates a spacecraft and satellite communication system with a dish-shaped reflector member; 
     FIG. 2 illustrates a reflector member in its stowed and launch position on a spacecraft; 
     FIG. 3 illustrates a reflector member in its deployed condition; 
     FIG. 3A is an enlarged view of a portion of the deployed reflector system as shown in FIG. 3; 
     FIG. 4 illustrates a deployed reflector mesh in accordance with the present invention; 
     FIG. 5 illustrates a preferred mesh member for use with the present invention; 
     FIG. 5A is an enlarged view of a mesh structure preferred for use with the present invention; 
     FIG. 6 is a representative view of one of the rib members of the frame structure for use with a mesh member in accordance with the present invention; 
     FIG. 6A is an enlarged view of a portion of the rib structure shown in FIG. 6; 
     FIG. 7 illustrates a pair of gore members for use as part of a mesh reflector member in accordance with the present invention; 
     FIG. 8 illustrates a gore lay-up table for use with the present invention; 
     FIG. 9 is a portion of a gore member positioned on a lay-up table as shown in FIG. 8; 
     FIGS. 10 and 11 illustrate various steps in the formation of the pre-tensioned gore members in accordance with the present invention; 
     FIG. 12 depicts one of the several tensioning procedures utilized with the present invention; 
     FIG. 13 is an enlarged view of a portion of the mesh reflector member shown in FIG.  12  and illustrating the unique nodal assemblies and chord members utilized with the present invention; 
     FIG. 14A is a plan view and 
     FIGS. 14B and 14C are elevational views of a nodal assembly preferably utilized with the present invention; 
     FIG. 15 is an enlarged view of the center or hub portion of a reflector member made in accordance with the present invention; 
     FIG. 16 is a partial cross-sectional view of the hub structure as shown in FIG. 15, the cross-section being taken along line  16 — 16  in FIG.  15  and in the direction of the arrows; 
     FIG. 17 illustrates a representative knot mechanism preferred for use with the present invention; 
     FIGS. 18A,  18 B, and  18 C are three elevational views illustrating the tensioning and securing procedure utilized at facet corners on the outer edges or catenaries of the mesh member; 
     FIG. 19 is a plan view of a deployed mesh member in accordance with the present invention; 
     FIG. 20 is an enlarged view of a portion of the deployed mesh member as shown in FIG. 19; 
     FIGS. 21 and 22 are partial cross-sectional views of a portion of the mesh and mesh management system as illustrated in FIG. 20, with FIGS. 21 and 22 being taken along lines  21 — 21  and  22 — 22 , respectively, in FIG. 20; 
     FIG. 23 illustrates a splicing mechanism for use with the present invention; 
     FIG. 24 illustrates a representative tubular member for use with the mesh management system; 
     FIG. 25 is an enlarged view of a portion of the reflector member in a stowed condition (as shown in FIGS.  1  and  2 ); and 
     FIG. 26 illustrates one of the comb members preferably used with the present invention. 
    
    
     BEST MODE FOR CARRYING OUT THE INVENTION 
     As indicated above, the present invention relates to unique methods, apparatuses, and systems for mesh integration and tension control, mesh retention, and mesh management of a mesh reflector system preferably for use with a spacecraft or satellite. A deployed dish-shaped communication reflector member utilized with the present invention is shown in FIGS. 1 and 3 and is indicated by the reference numeral  30 . 
     The invention is a large deployable, offset-fed reflector  30  which uses a soft tricot mesh as its reflecting surface. The overall arrangement depicting both the deployed and stowed configurations is shown in FIG.  1 . The back-up support structure uses an umbrella-like construction with an odd number of contoured radial ribs arranged around a small center circular hub. One of the ribs, referred to as the main rib member, has a heavier torque-box construction and is used to provide an “edge-support” for the reflector. The remaining “secondary” ribs are of a lighter, planar-truss construction and are tapered toward their outer edges. A deployment boom or arm is used to connect the reflector to the spacecraft or satellite. 
     The present invention is also related to the invention entitled “Edge-Supported Umbrella Reflector With Low Storage Profile” (PD-970097) which is the subject of co-pending related U.S. patent application Ser. No. 08/888,762, which is assigned to the same assignee as the present invention. The disclosure of this related patent application is incorporated herein by reference. 
     When the reflector  30  is utilized in a satellite communication system, the reflector is deployed in the position shown in FIGS. 1 and 3 and connected to the spacecraft body member  32  by the deployable boom or arm member  34 . 
     The reflector member is shown in its collapsed and stowed position in FIGS. 1 and 2 and referred to by reference numeral  30 ′. The reflector member is contained in its stowed position for launch and transport to its orbiting site in space. In this regard, the satellite body member  32  and reflector member  30 ′ are positioned in the payload fairing of the rocket structure  36 , as shown in FIG.  1 . After the communication satellite is released from the payload fairing  36 , the reflector member  30  is deployed from its stowed position  30 ′ to its deployed position  30  by appropriate commands from the ground control. 
     The spacecraft  32  has an antenna feed  38  which is directed toward the reflector  30 . Due to the positions and orientations of the reflector and antenna feed, the reflector member  30  has an elliptical shape. This is better shown in FIGS. 4 and 19. It is to be understood, however, that the present invention is not limited to reflectors having an elliptical shape or any certain size. Instead, the present invention can be used with many types of deployable reflectors, whether elliptical, circular or any other shape necessary for use with the satellite or other communication system. 
     For satellite use, the present invention has particular use in current and future Geo-mobile communication satellites. The invention saves significant expense and weight while enhancing performance and reliability of the reflector. 
     More specifically, the present invention comprises a mesh reflector member  40  attached to a structural framework  42  which has a concave or dish-shape as conventionally known in the field. The key aspects of the present invention relate to systems and procedures for manufacturing, pre-tensioning, and assembling the gore members forming the mesh reflector member  40 , systems and procedures for securing the mesh reflector member  40  on the framework structure  42  and tensioning it thereon, and systems and procedures for managing and maintaining tension in the mesh member  40  when it is contained in its stowed and launch position. 
     The framework structure used with the present invention comprises a plurality of curved rib members  46 , one of which is shown in FIG.  6 . The rib members  46  are preferably honeycomb truss members made from a Nomex core sandwiched between thin graphite face sheets for strength and reduction in weight. It is also possible, in accordance with the present invention to provide rib members of any conventional type, such as round tubular members and the like. With a particular reflector design utilizing the present invention, preferably one main rib member and thirty secondary rib members  46  are utilized; The main rib member  48  is the rib member which is connected to the deployable arm  34  and is wider and significantly stiffer torsionally than the secondary rib members. 
     The rib members  46  are approximately 1 inch in width and range from approximately 20 feet to 25 feet in length, depending on their position in the elliptical design or configuration of the reflector member. The rib members provide stiffness and stability for the mesh reflector and retain the reflector in its dish-shape or concave shape when the reflector is deployed. The inner ends  50  of the rib members  46  and  48  are pivotally connected to a substantially circular hub member  52 . A central stem member  54  is attached to a base plate member  56  and is positioned as shown in FIG. 3A when the reflector member  30  is deployed. The outer end  58  of the stem member  54  is attached by a plurality of upper strap members  60  to the rib members  46  and  48 , which help retain the rib members in their deployed positions. The base plate member  56  is also attached to the rib members  60  by a plurality of lower strap members  62 . A motor  63  is used to slide the stem member  54  through the hub member  52  and into its deployed position which tensions the strap members  60  and  62 . 
     As shown in FIG. 4, the preferred reflector mesh member  40  is elliptical in shape and has thirty-one triangular or wedge-shaped gore members  70 . Each of the gore members  70  has ten facet members  72  which are generally trapezoidal in shape, as better shown in FIG.  7 . Each of the trapezoidal shaped facets have four corners or “nodes”. Each of the gore members has an inner end  74  which is adapted to be attached to the central base plate member of the reflector and an outer end or edge  76  at its opposite end. The outer edges of the gores are radially tensioned by circumferential catenary members. 
     In the regard, although the present invention is preferably shown with thirty-one gore members and ten facet members, it is obvious that a greater or lesser number of gore members and facet members can be utilized depending on the precise size and shape of the reflector member to be utilized. 
     The preferred structure or mesh used with the present invention is a two-bar tricot mesh structure with 5-10 openings per inch. A representative tricot structure of this type is shown in FIGS. 5 and 5A and referred to generally by the reference numeral  80 . Also, preferably the material used for the mesh structure is a plated 55 denier Kevlar yarn, although any knitted or soft mesh structure conventionally used with mesh reflectors can be utilized. 
     The mesh structure  40  is initially installed under a certain minimum pre-tension at room temperature. This ensures adequate tension necessary for proper electrical performance at a worse case (maximum) temperature after extended thermal cycling (at end-of-life) of the material. The tension is typically different in the as-knit and transverse directions due to the orthotropic properties of the mesh. One of the methods used to maintain pre-tension in the mesh as it is made and installed, is to tension the catenary members around the outer perimeter of the mesh member  40 . These members are enclosed in a pocket which can be referred to as the catenary tube. 
     As mentioned above, the mesh member  40  of the reflector member  30  is divided into triangular shaped gore members  70  and the gore members are further subdivided by a set of ellipses into substantially flat trapezoidal facets  72 . In order to avoid congestion due to the intersection of the large number of gores involved at the center of the mesh member, a circular center mesh panel member  71  is provided at that location, as shown in FIGS. 15 and 16. The center mesh panel member  71  is secured under tension around its edges to an annular flat ring member  74  which is approximately one foot in diameter and preferably made of Kevlar material. The ring member  74 , in turn, is attached to the central base plate member  56 . 
     For pre-tensioning of the gore members  70 , a mesh preparation lay-out table  90  is utilized. This is shown in FIG.  8 . The table  90  has a large flat surface  92  which is sufficiently large to hold a pair of gore members  70  in the positions shown in FIG. 8. A plurality of roller members  94  are provided along the four outer edges of the table  90 . The table surface  92  is isolated from the table support structure  96  using vibration isolators and at least one vibrator motor  98  is utilized to vibrate the surface  92  to reduce friction and ensure that the pre-tensioning of the mesh material is uniform through each of the facets and gore members. In this regard, in order to initially tension the mesh material on the table  90 , a plurality of small weights  100 , preferably spaced only a few inches apart, are secured to the edges of the mesh material and positioned over the roller members  94 . 
     A set of Mylar plots representing flat pattern templates for each gore section is prepared using conventional computer graphic techniques. For efficient use of the material, each pair of gore patterns is set up in a head-to-toe manner as shown in FIGS. 7 and 8. The mesh preparation table  90  is sized to be able to handle the largest of the flat gore member patterns. 
     For preparation of the gore members, the mesh templates  102  are taped or otherwise secured to the surface  92  of the table  90 . The mesh material is then laid over the templates and stretched using strings, hooks, and small dead weights  100  appropriately spaced around the four sides of the table. This produces the desired mesh tension in both the as-knit and mesh transverse directions. In this regard, the as-knit direction of the mesh on the table  90  is shown by the arrow  97  and the transverse direction is shown by the arrow  99 . 
     Tension within the mesh material on the table  90  is equalized by using the vibration feature as mentioned above. The tension strain in the mesh material is then “locked in” and the gore members are formed by placing two rows of a relatively stiff double-sided adhesive tape on the mesh forming the outline of the gores corresponding to the templates  102 . As shown in FIGS. 9 and 10, two rows of tape  104  and  106  are placed along the elongated sides of each gore member, while four rows of tape  114 ,  115 ,  116  and  117  are positioned along the catenary edges  76 . The two rows of tape  104  and  106  are positioned on either side of the desired gore seam lines with a sufficient gap or space  108  left between them to allow for subsequent sewing together of adjacent gore members with stitches  110 . 
     Preferably, locations where the mesh member is to be attached to the reflector ribs, as well as other locations where the mesh member is to be attached to the mesh retention strings as discussed below, are marked on the mesh by appropriate indicators, such as stitches  112  using temporary colored threads. These indicators are accurately transferred from target locations computer plotted on the Mylar mesh templates. 
     The double-sided tape members are only provided for temporary use during the formation of the gore members. The tape holds the requisite shape and tension in the gore members until they can be stitched along the outside edges. Thereafter, the tape is pealed off and discarded. With the invention, no rigid or semi-rigid panels or members are permanently left in the gore members, and no added weight is included. As to the tensioning strain, preferably the mesh is tensioned on the order of 0.125 to 0.25 pounds/foot (about 2 to 4 ounces/foot). 
     Preferably, tape member  104  is approximately 0.5 inches in width and tape member  106  is approximately 1.0 inch in width. Space or gap  108  is also approximately 0.5 inches in width. Along the outer or catenary edges of the gore members, the four pieces of tape member  114 ,  115 ,  116  and  117  are each approximately 0.5 inches in width. A 0.5 inch gap  118  is provided between the two catenary rows of double-sided tape members in order to provide a space for stitching in a pocket  119  for positioning of a string chord member  120  as shown in FIG.  11 . The chord member  120  is preferably a length of Kevlar string approximately 0.50 mm in diameter and which is longer than the outer edges of the gore members in order to provide two loose ends for tensioning, as described below. When the outer ends of the gore members are folded over in the manner shown in FIG.  11  and stitched together by appropriate zig-zag threads  122 , the tape members  114 - 117  are removed. The tape members are used to temporarily hold the requisite tension in the mesh member adjacent the ends of the gores and also to provide a temporary means for holding the ends in the folded over position, as shown in FIG. 11, thereby holding the chord member  120  therein until the final stitching  122  takes place. 
     Similarly, tape members  104  and  106  are utilized to temporarily hold the requisite tensioning in the gore members and to temporarily hold adjacent gore members together in an overlapping condition, as shown in FIG. 10, so they can be stitched in place by zigzag stitches  110 . In this regard, after the two gore members are stitched together as shown in FIG. 10, the tape members  104  are removed and the overlapping free ends containing tape members  106  are trimmed from the mesh member. 
     Once the tape members  104 ,  106 , and  114 - 117  are first positioned around the outer edges of each of the gore members  70  holding or “locking in” the requisite shape and tension, and the mesh and other attachment locations are marked up, the weights  100  are removed and the mesh material is trimmed on the table  90  into wedge-shaped configurations generally along the outer edges  106 ′ and  114 ′ of the tape members. Thereafter, once the adjacent gore members are stitched together as shown in FIG. 10, and the catenary ends of the gore members are overlapped entrapping Kevlar chord members  120 , as shown in FIG. 11, the mesh material is further trimmed along the outside edges of the stitching  110  and  122  in order to finish the completed gore members  70 . 
     The present invention avoids the use of rigid or semi-rigid strips (e.g. graphite strips) used with some known mesh-type satellite reflectors. This saves weight and cost, enhances reflector transparency, and eliminates added mesh stiffening, thus enhancing thermal stability and mesh shape adjustability. 
     When the reflector member  30  is in its stowed and collapsed condition, the rib members  46  and  48  are positioned generally parallel to each other. This is shown in FIG.  1 . On the other hand, when the rib reflector member  40  is in its deployed condition, the rib members are flared out in an umbrella-shape, such as shown in FIGS. 1 and 3. The rib members form a framework structure for the reflector which has a concave dish-shape. When the mesh member  40  is positioned on the reflector member consisting of the framework structure of rib members, a retention system is used to retain the mesh member in its desired shape. The tensioning should be adjusted such that the reflector member retains its precise concave shape and is not over-tensioned or under-tensioned. The system also retains the mesh member on the ribbed framework structure. The preferred tensioning system utilized in the present invention is shown in one or more of FIGS. 12-18. 
     FIG. 12 illustrates the forces and system for properly tensioning the chord members in the catenaries on the outer edges of the mesh member  40 . As explained above, a Kevlar string-like chord member  120  is positioned in a pocket  119  (or catenary tube) in the outer edge of each of the gore members. The loose ends of adjacent chord members situated next to each other when the gore members are sewn together are tensioned adjacent the ends of the rib members  46 . In FIG. 12, the length L is fixed once the geometry of the reflector member is established. The distance A is variable for each of the catenaries and is selected such that the appropriate tension is provided in the mesh member without bending the rib members in the circumferential direction. In this regard, the tension T can be approximately defined by the following formula: 
     
       
           T=p   r   ·L   2 /8 A    
       
     
     where T is the catenary tension and Pr is the mesh radial tension. T 1 /T 2  has a resultant force TR 12  directed along the rib member  46 . Similarly, the adjacent tensions and adjacent catenary members along each of the gore members have resultant forces in directions along their respective rib members. Once A is selected for the first catenary member, then A can be determined for each of the other gore members around the circumference of the mesh member. 
     The ideal mesh reflecting surface shape is approximated by the plurality of substantially flat trapezoidal facets contained on the mesh member. When the mesh member is positioned on the framework structure comprised of the rib members  46  and  48 , the four corners or nodes of the facets are positioned along the rib members and are adapted to be the attachment points for the mesh member  40  on the framework structure. The four perimeter edges of each of the facets are kept substantially straight by a network of tensioned chord members positioned along the length of each of the rib members and in the front (or focus side) of the reflector. At the same time, and for the same reason, a plurality of chord members are positioned stretched between adjacent rib members along each of the edges of the facet members, again connecting the corners or nodal points. 
     Unique nodal assembly mechanisms  130  are positioned at each of the corners of the trapezoidal facets along the rib members. The positioning of the nodal assemblies  130  is particularly shown in FIG.  13  and the details of the nodal assemblies  130  themselves are particularly shown in FIGS. 14A,  14 B and  14 C. In this regard, FIG. 14A is a top plan view of one of the nodal assembly mechanisms with its cover removed, while FIGS. 14B and 14C are side elevational views thereof. 
     The nodal assemblies  130  are small radio frequency (RF) transparent button-like devices and are positioned on the focus side of the mesh member  40 . The nodal assembly mechanisms  130  have a pair of prongs or clevis members  132  which are pivotally attached by rivet or pivot member  134  to a U-shaped support bracket  136  positioned on the rib members  46 . The prongs  132  are fed through mesh openings to the back (non-focus) side of the mesh. The assembly members  130  are pivotally attached to the rib members so that they can be self-aligning to the ideal reflecting surface. This permits the nodal spring assemblies to be tangential to the mesh surface while tilting to one side or the other relative to the rib, thus compensating for the angularity between the mesh member and the rib planes. The pivot members  134  are preferably small rivet members and are secured to the bracket members  135  and clevis members  132  by an adhesive  138  or the like. Also, as shown, the attachment bracket members  136  are adapted to fit over the rib members  46  and are secured thereto by bonding with an appropriate adhesive. 
     Nine or ten nodal assembly members  130  are positioned along each of the rib members. For every other rib, one nodal assembly member  130  is positioned on the ring member  74 , as shown in FIG. 15, and the other nodal assembly members  130  on all ribs are positioned on the intersections of the facet members on the rib members. The outer ends of the rib member are connected to the mesh members in another manner, as described above and as further described below with reference to FIGS. 18A-18C. Also, for illustrative purposes, a series of ten nodal assembly members  130  positioned along one of the rib members is depicted in FIG.  19 . 
     Each of the nodal assembly mechanisms  130  has a central stem or body member  140 , an omega-shaped composite (fiberglass) bending spring member  142 , a base plate member  146 , and a cover member  144 . The Omega-shaped spring members housed within the nodal assemblies provide a constant, repeatable and easily measurable tension to the chord members  150  which are positioned between adjacent assembly mechanisms  130 . Each of the spring members  142  has a pair of spring arm members  143  that are secured to adjacent aligned chord members  150 , such as by use of a knot structure sealed with a fast curing adhesive. 
     As shown in FIG. 14A, the arm members of the spring member  142  are shown in their untensioned positions in phantom lines  143   a  and in their biased and tensioned positions by the reference numerals  143 . As shown in FIG. 13, the nodal assemblies and spring members  142  are alternately oriented in radial and tangential directions on the reflector member  30  at the various nodal positions. This permits proper tensioning of both the radial and tangential chord or edge members  150 . 
     The Omega-shaped spring members are preferably made of a fiberglass reinforced composite (which may have a low concentration carbon powder to prevent electrostatic discharge), have a high RF transparency, a PIM-free nature, and high structural efficiency. Such material also has a high elastic bending strain limit, a high specific elastic bending strength, and a high specific elastic bending energy absorption. As a result, spring members made of such material can have a weight less than 0.2 grams, a free length of approximately 0.25 inches, and provide greater than 0.30 inches of elastic deflection, while elastically storing greater than 0.75 pound-inches of energy. The Omega-shapes of the spring members  142  also provides for a large bending radius at the location of highest bending moments and thus minimize tangential and through-the-thickness stresses. For higher energy absorption efficiency, the spring members  142  are tapered in width, as shown in FIGS. 14B and 14C. With such a structure, the spring members are widest at the maximum bending moment location and narrowest near their free ends where the bending moment is minimal. This increases the spring efficiency at minimal cost and without deterioration in manufacturing accuracy. 
     In order to enhance the efficiency of the spring members  142  and the nodal assembly mechanisms  130  around the surface of the reflector member  40 , a plurality (preferably three) different spring members  142  are provided for each reflector member  30 . Each of the spring members has a different maximum and minimum width and are used at different locations on the reflector member depending upon the chord tensioning requirements for those locations. The different spring members can be produced from the same basic molding/layup operation by simply varying the width of the spring members when they are cut from the mold. 
     The cover members  144  which attach to the stem or body member of each of the nodal assemblies  130  can be an injection molded member which “snaps” onto the body member  140 , or a machined fiberglass disk bonded to the body member. The cover member  144  prevents possible entanglement of the mesh material which could result from contact between the mesh member and/or retention chords with the Omega-shaped springs during launch or weightlessness in space prior to deployment. 
     The radial and tangential chord members  150  are preferably made of 600-1200 denier Kevlar (or Vectran) material and form a “spider-web” retention network. One end of each of the chord members  150  is attached to an Omega-shaped spring member using a knot mechanism or the like which is later sealed using a fast curing adhesive  152 . The other end of each of the chord members  150  is attached to the base plate member  146  of the nodal spring assembly mechanism  130 . After the mesh and spider-web network are attached to the ribbed reflector structure, each of the chord members  150  is tensioned to a specific tension level. 
     The tensioning of the chord members  150  should satisfy two criteria. First, the tension should be sufficiently high to limit mesh pillowing (which is its tendency to move toward the focus of the reflector caused by the mesh tension and curvature). Since the various chord members have varying lengths, and since the tension required is proportional to the square of the chord length, the required minimum tension varies significantly from one chord member to another. Secondly, since the reflector rib members are relatively flexible in the circumferential direction, the tensions in any pair of circumferential chord members meeting at a particular rib member should be proportioned such that the resultant force lies in the plane of the rib member. 
     As indicated above, the lightweight Kevlar ring member  74  is located adjacent the outer edges of the mesh circular center panel member  71 . The ring member  74  is bolted or otherwise secured to the reflector hub  56  at a number of positions with plastic fasteners such as screws. The ring member  74  also has a plurality of holes or openings (not shown) for accepting the attachment clevis members  132  of the nodal spring assembly mechanism  130 . The clevis members are secured to the ring with small rivets which are fed through the clevis holes as they protrude behind the ring. The free ends of the rivets are swaged or upset to prevent them from being loosened or removed during handling and launch vibration. 
     Two rows or sets of nodal spring assemblies  130  are positioned along the main rib member  48 . The base plate members  146  of the assembly mechanisms  130  are bolted or otherwise secured to the edges of the main reflector rib  48  at the appropriate facet nodal locations. The nodal spring assembly members  130  are also preferably pivotally attached to the main rib member  48  using rivets sealed with an adhesive. 
     As shown in FIG. 15, sixteen nodal assembly members  130  are positioned around the center ring member  74 . These resiliently connect one-half of the radial chord members  150  to the center of the reflector. The other radial chord members  150  are fixedly secured, such as being tied and glued, to the center ring member  74 . The alternate biased and unbiased connection of the radial chord members to the center ring member  74  is a continuation of the manner in which the chord members  150  are tensioned throughout the face of the reflector member. 
     When the chord members  150  are attached to the base plate members  146  of the nodal spring assembly mechanisms  130 , they are preferably secured with a knot mechanism  160  as shown in FIG.  17 . Also, preferably a similar knot mechanism  160  is used to secure the radial inner ends of the chord members  150  to the center ring member  74 . The latter situation is shown in FIG. 15 by the circular area numbered with the reference numeral  17 , which is a reference to FIG.  17 . In this regard, the knot mechanism utilized with the present invention is the subject of a separate patent application filed concurrently herewith, namely U.S. Ser. No. 08/888,486, entitled “A Continuously Adjustable Non-return Knot” (PD-960515), which is assigned to the same assignee as the present invention. The disclosure of that co-pending patent application is incorporated herein by reference. 
     In general, the preferred knot mechanism  160  used with the present invention utilizes a series of three holes, referenced by the letters A, B and C in FIG. 17, in which the end of the chord member  150  is threaded through in the manner shown. Since the end  150   a  of the chord member  150  is threaded under portion  150   b  of the chord member, the knot mechanism is self-tightening when force is applied in the direction of the arrow  162  to chord member  150 . When it is desired to release the tension in the chord member, a release string member  164  is utilized. The release member  164  is attached to portion  150   b  of the chord member  150  and when pulled, allows the end  150   a  of the chord member to free itself and slide back from beneath portion  150   b  thus relieving the tension in the chord  150 . One of the main advantages of the knot mechanism  160  is that the spider-web network comprising the plurality of chord members  150  can be loosely assembled in its preferred location and then be tightened or loosened and adjusted according to the requisite tension needed in the particular chord members. 
     In order to determine that the appropriate tension has been applied to a particular edge member, the deflection of the biasing elements (distance D in FIG. 14A) is measured using an appropriate measuring tool or instrument as the member is tensioned. 
     FIGS. 18A-18C show the manner in which the mesh member  40  is secured to the outer ends of the rib members  46 . A saddle attachment bracket  166  is positioned over the rib member  46  and secured thereto by bonding with an appropriate adhesive. The string member  172  is passed through openings  170  in the mesh member  40  and its ends are wrapped around and tied to bracket member  166 . 
     Compared to known reflector tensioning network systems which utilize straps and tensioning by springs located behind the mesh member, the chord members used with the present invention are lighter and less expensive, provide less solar blockage, and are easier to accurately tension. 
     The details and features of the mesh management system in accordance with the present invention are particularly shown with reference to FIGS. 19-25 (and also with reference to portions of FIGS.  15  and  16 ). For use on a deployable umbrella-type reflector member, the mesh management system controls the mesh and its edge members while in the stowed and launch condition. It is preferred to maintain the mesh under tension in the stowed position so that the mesh does not become repositioned or tangled during the tremendous vibration forces caused during transportation, handling, and launch to which the mesh member is subjected prior to deployment of the satellite and reflector. This ensures that the mesh member will not tangle, but will deploy when desired. 
     Once all of the nodal spring assembly mechanisms  130  and chord members  150  are loosely positioned in place around the surface of the mesh member  40 , and the catenary chord members  120  are in position, final adjustments of the tension at all portions and positions on the mesh member can be made. For this purpose, the reflector rib structure and mesh member  40  are mated on the ground at an assembly site and the reflector member  30  is assembled and tensioned in its final configuration. Thereafter, the mesh retention system is affixed to the reflector member and mesh member so that the tension in the mesh member can be maintained when the reflector member is folded to its stowed and launch condition. 
     The mesh management system includes a set of flexible string-like chord members  180  which are attached at their inner ends to stem member  54 , as shown in FIG.  16 . The individual chord members  180  are positioned through holes or openings  178  situated in guide plate member  179  attached to one end of the stem member  54 . 
     Although only a few representative chord members  180  are shown in FIGS. 19 and 20, it is to be understood that these are representative of the actual situation in which similar chord members  180  are positioned radially in each gore member around the entire circumference of the mesh member. The chord members  180  are positioned generally in between each of the rib members and thus approximately in the centers of each of the gore members  70 . 
     Chord members  180  are positioned through small insulated guide washers  182  which are secured to the mesh member  40 . The washer members  182  are positioned along the non-focus side of the mesh member gores along each of the facets approximately in the middle between the side edges of the gore members. The washers are tied by strings or thread members  184  to the mesh members  40  and hang from the mesh member in the manner shown in FIGS. 21 and 22. The inner portions of each of the chord members  180  comprises a single string or chord member  180   a.  This is shown in FIGS. 20 and 23. These members  180   a  are spliced by bead-shaped splice members  186  to form a pair of chord members  180   b  and  180   c  which extend toward the outer edges (catenary edges) of the mesh member. Preferably, a knot mechanism of the type shown in FIG.  17  and/or described in copending application Ser. No. 08/888,486 is utilized since it will permit the adjustment of the length, and tension, in the chords after the reflector is stowed. The two chord string members  180   b  and  180   c  are separated and pass through two sets of separate guide washer members  182  uniformly positioned near the center of the outer facet members  72 , as shown in FIGS. 19 and 20. 
     Tubular members  190  are positioned over the outer ends of each of the string/chord members  180   b  and  180   c.  The tubular members  190  are positioned through washer members  182  attached to the underside of the three most outer facet members  72 ′ as shown in FIG. 20. A plurality of bead members  192  are positioned and snugly fit on the tubular member  190  and secured from sliding in one direction by a piece of tape wrapped several times around the tubular member or by other stop member  194 . The outermost end  181  of each of the string members has a loop member  183  thereon which is adapted to mate with one of the fingers or teeth  196  on comb-like rack members  200 . 
     A pair of comb-like rack members  200  are provided, one on each side of the main reflector rib member  48 . The rack members  200  are pivoted to the member  48  by pin member  202  which is positioned through one of the openings in the rack member  200 . The rack member  200  has a plurality of teeth or fingers  196  on one end and each of the finger members are adapted to hold one or more of the loops  183  on the ends  181  of the chord/string members  180   b  and  180   c.  This is particularly shown in FIGS. 25 and 26. Preferably, in order to reduce potential tangling and to assure ready deployment, a separate loop  183  is positioned on each of the individual teeth or finger members  196 . 
     Over the majority of the area of the mesh member, where the circumferential span of the mesh between the support structure members/rib members is less than twice the inside diameter of the stowed reflector bundle  30 ′, the mesh and its retention chords are pushed radially inwardly by N number of management chord/string members and are stretched along the width of each gore. As indicated, the chord/string members are stretched between the stem member  54  at the center of the reflector and one of the teeth of the comb-like rack members near the outer perimeter of the reflector. Control of the gore and edge members is achieved by passing the stretched mesh management chord members through insulating washers which are sewn to the mesh member. 
     Near the bottom or outer perimeter edge of the mesh member where its circumferential span is several times the stowed bundle inside diameter, the mesh member and its edge catenary members are pushed upwards, that is toward the center or hub. Preferably, there are three points along each mesh management chord at which the washers  182  attached to the mesh are pushed upward or inwardly by the bead members  192  on the tubular members  190 . The small flexible tubular members  190  are placed over the chord members near their outer edges and the beads are snugly fitted over the tube members and adapted to push the mesh upward by contact with the washer members  182 . When the reflector is stowed, the tube members  190  are prevented from sliding off the chord members by the rack member  200 . 
     When the reflector member  30  is stowed, or positioned in its stowed condition, the mesh management chord members  180  are secured to the comb-like rack members  200  through the loop members  183  at their outer or bottom ends. The teeth or fingers  196  are maintained in the direction pointing away from the center hub due to contact of the opposite end  204  of the rack members with one end  46 ′ of one of the rib members  46 . The rack member  200  is placed against the outer end of the rib member  46  closest to the member in which the rack member  200  is pivotally attached. 
     When final deployment commences relative to the reflector member  30 , and the rib members  46  are spread out toward their umbrella-like configuration, the rack members  200  are allowed to rotate (around pivot member  202 ) until the teeth or finger members  196  are pointed in an upward direction thereby allowing the chord loops  183  to slide off. This frees the chord members  180  and tubular members  190  and allows the mesh member  40  to be deployed to its stretched and taught configuration as the reflector ribs move to their final deployed positions. 
     Along the inner ⅔ of the mesh, where the circumferential span is less than the inside diameter of the stowed reflector bundle, the mesh member is pushed radially inwardly by the chords  180   a  stretched along the middle of each gore member between points near the center of the hub and the bottom end of the reflector. Along the bottom or outer ⅙th of the mesh member, where its circumferential span is significantly larger than the stowed reflector bundle inside diameter, the mesh members are pushed upwards, that is toward the hub member, at several points (for example, 6 points per gore) until the mesh member and the circumferential chords are taught. Along the remaining intermediate ⅙ of the mesh member, the mesh circumferential spans are divided into thirds and several rings or washers are attached at about the one-third and two-third points. The rings are pulled radially inwardly, that is toward the center line of the stowed reflector, by two chord members  180   b  and  180   c  stretched near the middle of each gore. 
     The inside diameter of the tubular members  190  are sufficiently large to easily pass the chord members  180  and the outer loops  183  through them, and yet their outer diameters are sufficiently small to easily pass through the washer members  182 . The bead members  192  are large enough to push the washers without passing through them, or jamming into them, and have center holes which snugly fit over the flexible tubing. The beads are positioned over the tubular members  190  at locations where the washers need to be pushed toward the hub member. 
     When the reflector is stowed with the lower (outer) chord loops  183  placed over the rack teeth  196  and the chord sufficiently tensioned, the flexible tubes  190  are pushed downward until they come in contact against the rack member  200 . The bead members  192  are then slid along the tubes and used to push the washers  182  upwardly, that is toward the hub, until the mesh member is stretched and the circumferential mesh retention chord members are snug. The beads are then fixed such as they are prevented from sliding back along the tubes. This is accomplished by adding the piece of Kapton tape or stop members  194  which prevent the bead members  192  from going over them. When the racks are released and the mesh management chord members and loops  183  are freed, the tube members  190  are then permitted to slide downwardly away from the hub allowing the mesh to stretch as the reflector rib members  46  and  48  are opened outwardly. 
     When the deflector member  30  is deployed, the tube members  190  are positioned behind the reflector and behind the mesh member and are trapped by the bead members  192  and washer members  182 . 
     With the present invention, initial constraint and the final release of the rack members is achieved without the need for any active release mechanism or system. Instead, this function is performed by using the relative positions and motion between pairs of reflector ribs, when the reflector is stowed and as deployment commences. 
     With the present invention, control of the mesh member is secured at significantly less cost and weight than known systems. The invention also is more reliable since is requires fewer elements to disengage in order to free the mesh member at deployment time. 
     While the best mode for carrying out the invention has been described in detail, those familiar with the art to which this invention relates will recognize various alternative designs and embodiments for practicing the invention as defined by the following claims.