US3618101A

US3618101A - Collapsible parabolic antenna

Info

Publication number: US3618101A
Application number: US853423A
Authority: US
Inventors: Franz Emde; Hans-Joachim Ludwig
Original assignee: Telefunken Patentverwertungs GmbH
Current assignee: Telefunken Patentverwertungs GmbH
Priority date: 1968-08-27
Filing date: 1969-08-27
Publication date: 1971-11-02
Anticipated expiration: 1988-11-02
Also published as: FR2016447B1; FR2016447A1; DE1791007B1

Abstract

A collapsible parabolic antenna for use with a communications satellite. Two 100* reflector segments are rotated laterally by torsion springs and moved axially by a coil spring, so as to be brought into proper position with respect to a fixed 160* segment. The moveable segments are held in place in back of the fixed segment by electromagnetic or pyrotechnic devices that can be actuated by remote control to release the moveable segments at the appropriate time.

Description

Inventors Appl. No. Filed Patented Assignee Priority States atent Franz Emde;

Hans-Joachim Ludwig, both of Backnang, Wurttemberg, Germany Aug. 27, 1969 Nov. 2, 1971 Telefunken Patentverwertungsgesellsclhait m.b.lll

lUlrn/Danulbe, Germany Aug. 27, 1968 Germany COLLAPSllBlLE PARABOLIC ANTENNA 9 Claims, Drawing Figs.

US. Cl

lint. Cl

................................................ ..ll-ll0lq /20 H 13,ol,l1

[] Fieldol'searcli 343/781, 840,912,915,705,D1G.3

[56] lleierenees Cited UNITED STATES PATENTS 2,560,218 7/1951 Dunlap 343/840 3,105,486 10/1963 Glenn 343/915 3,503,072 3/1970 Thompson 343/840 Primary Examiner-Eli Lieberman Att0rney-$pencer & lKaye ABSTRACT: A collapsible parabolic antenna for use with a communications satellite. Two reflector segments are rotated laterally by torsion springs and moved axially by a coil spring, so as to be brought into proper position with respect to a fixed segment. The moveable segments are held in place in back of the fixed segment by electromagnetic or pyrotechnic devices that can be actuated by remote control to release the moveable segments at the appropriate time.

PATENIED Nova m 3618101 SHEET 1 BF 3 IN VEN TORS Franz Emde 8 Hans-Joachim Ludwig AT TORN E Y5 PATENTEU Nnv2 IENI SHEET 2 OF 3 rilllllllvlrtlil Fig. 2

ATTO RN E VS PATENTEDNUVZ l9?! 3,618J01 sum 3 BF 3 Fig. 6 L 7 6' Franz Emde 8m Hunsfiooclmm Ludwig BY fi ATTORNEYS 1 COLLAPSIBLE PARABOLIC ANTENNA BACKGROUND OF THE INVENTION The present invention relates to a collapsible satellite antenna which is preferably constructed in the form of a parabolic reflector.

Due to space limitations in the transport vehicles presently available, antennas for communications satellites must be collapsible so that they take up a minimum of space during the transport phase. When the satellite has reached its orbit, the antennas are brought into their operating position by suitable drive means.

SUMMARY OF THE INVENTION One of the objects of the present invention is to construct an antenna reflector in such a manner that it takes a relatively small amount of space and can be easily and reliably brought into its final operating position.

In the antenna reflector according to the present invention this is achieved by dividing the reflector into a fixed and one or more moveable segments. In the transport phase the segments are superimposed on one another in order to save space. The moveable segments can be rotated out of their basic positions with respect to the fixed segment by means of torsion springs, which are actuated electromagnetically or pyrotechnically by remote control. The moveable segments can also be axially displaced with respect to the fixedsegment after completion of the rotary movement by means of a tension spring. In this manner the several segments combine to form the antenna reflector.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic front view of an antenna reflector according to the present invention. FIG. 2 is a schematic front view of the antenna reflector of FIG. 1 in a folded position. FIG. 2a is a cross-sectional view generally taken along the plane defined by line 2a-2a of FIG. 2.

FIG. 3 is a cross-sectional view generally taken along the plane defined by line 3-3 of FIG. 2.

FIG. 4 is a cross-sectional view generally taken along the plane defined byline 44 of FIG. 7.

FIG. 5 is a cross-sectional view generally taken along the plane defined by line 5-5 of FIG. 8.

FIG. 6 is a cross-sectional view generally taken along the plane defined by line 6-6 of FIG. 9.

FIG. 7 is a schematic back view of one the antenna.

FIG. 8 is a schematic back view of another moveable segment of the antenna.

FIG. 9 is a schematic back view of the fixed segment of the antenna.

moveable segment of DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 shows a parabolic antenna made up of three segments. A large segment 1 is rigidly connected in a fixed position to the structure of a communications satellite.

Smaller segments

2 and 3 are mounted so as to be rotatable with respect to fixed segment ll. While the satellite is being transported into its orbit the

moveable segments

2 and 3 are disposed behind or overlap fixed segment 1, as shown in FIGS. 2 and 3. The size of the reflector segments will be determined by the availability of space in the satellite transport vehicle. If possible, however, the fixed segment 1 will be selected of such a size that its antenna surface would be sufficient for communication between the communications satellite and ground station. This is desirable as insurance against the possibility that the antenna will not unfold properly. To be consistent with the objective of the present invention it is necessary for each moveable segment to be no larger than the fixed segment 1. In the preferred embodiment shown in the drawings the fixed segment I has 160 of arc, and each

moveable segment

2, 3 has l00ofarc.

As can be seen in FIG. 3, a hollow post 4i, preferably in the form of a thin-walled cylinder, is rigidly connected in a rearward direction at the apex of fixed segment 1.

Sleeves

5 and 6 are rigidly and rearwardly connected to the apexes of

moveable segments

2 and 3 respectively. Sleeve 5 is seen from FIG. 3 to be rotatable about post 6 and sleeve 6 is seen to be rotatable about sleeve 5. Thus, both

sleeves

5 and 6 are rotatable with respect to post 4. The

sleeves

5 and 6 are also axially displaceable with respect to post 41. FIGS. 4 through 9 show the particular construction of the

sleeves

5 and 6 that makes this axial movement possible.

Sleeves

5 and 6 are furnished with flanges 17 that hold the

reflector segments

2 and 3 in position. That portion of the

sleeves

5 and 6 not necessary to grip the

segments

2 and 3 has been removed to a distance equal to the combined thickness of a reflector segment and a pair of flanges 17 so that a cutout area 20 is formed. For example, in the preferred embodiment each

moveable segment

2 and 3 has of arc. This means that 360l00 =2607 of arc will be cut from the circumference of sleeves 5 and 6 (see FIGS. 7 and 8). In the same manner, post 4 will have a cutout portion 22 similar to 20 of

sleeves

5 and 6 where the arc in the preferred embodiment will be 360 l60 2O0,as shown in FIG. 9. As can be seen from FIGS. 6 through 9, when the moveable segments 2'and 3 have moved, laterally, or rotated. to their unfolded positions they are then free to move axially until the surfaces 19 of the

sleeves

5 and 6 come in contact with upper flange surface 18 of post 41.

The energy to rotate

moveable segments

2 and 3 is stored in torsion springs 10 and 12 (see FIG. 3).

Torsion springs

10 and 12 are disposed adjacent each other in a suitable housing 9. Housing 9 is supported by post 41, and! is thus rigidly connected to the satellite structure. One end of each

torsion spring

10 and 12 is rigidly connected to housing 9 in a well-known manner (not shown). The other or free end of each

torsion spring

10 and 12 is passed out of housing 9 through openings 21. The free end of spring 10 is connected to bracket 8, which is attached to the rear surface of moveable segment 2. In the same manner, the free end of torsion spring 12 is connected to bracket 7, which is attached to the rear surface of moveable segment 3. The force for the axial movement of

segments

2 and 3 is stored in coil spring 11. One: end of coil spring 11 is rigidly attached to post 41 by means of pin 15, and the other end is moveably attached to post 4 by means of slideably mounted pin 13 (see FIG. 3). Pin 13 is slideably mounted in opposing slots 14 formed in the walls of post 4 (only one of slots 14 can be distinguished in FIG. 3), and pin 13 is of a length sufficient to extend past the adjacent end wall portions of

sleeves

5 and 6.

The

moveable segments

2 and 3 are held in their folded positions behind fixed segment 1 by means of locking devices 23. Locking device 23 includes locking members 20 and 3a (see FIG. 2a) which are either pyrotechnic e.g., exploding bolts) or electromagnetic devices capable of being unlocked by remote control. When locking members 2a and 3a are unlocked, springs 10-12

move segments

2 and 3 into their operating position. Torsion springs 10 and 12 are arranged so that they are deflected sufficiently when

moveable segments

2 and 3 are in their folded position to store the energy required for rotating the

moveable segments

2 and 3. In the same manner, coil spring 11 is in tension when

moveable segments

2 and 3 are folded behind fixed segment 1. By proper selection of the tension on coil spring 11, the tension remaining after the

moveable segments

2 and 3 have moved axially into position is sufficient to hold

segments

2 and 3 in their operating position without additional locking means being required. If desired, however, resilient locking members can be mounted on the edges ofthe fixed segment 1.

The operation of the device is apparent from the above description and the drawings. When the satellite is in orbit and it is time to unfold the antenna, locking devices 23 are un locked by remote control. The

moveable segments

2 and 3 are then free to rotate with respect to fixed segment I as springs 10 and 12 untwist. When the

moveable segments

2 and 3 have rotated to their proper position with respect to fixed segment 1, they are moved axially by the force exerted on them by coil spring 11 through a pin 13 to form an operating parabolic antenna. While the preferred embodiment of the present invention is shown with two moveable segments, it is to be noted that the scope of the invention only requires at least one moveable segment.

It will be understood that the above description of the present invention is susceptible to various modifications, changes and adaptations.

We claim:

1. A collapsible antenna comprising, in combination: at least one fixed reflector segment and at least one moveable reflector segment, mounting means defining a common axis for permitting said at least one moveable segment to move first laterally and then axially relative to said fixed segment from a folded position overlapping said fixed segment to an operative position adjacent said fixed segment, and means including spring means to move said moveable segment from said folded position to said operative position, said spring means including at least one torsion spring and one coil spring, said at least one torsion spring causing said at least one moveable segment to move laterally, and said coil spring causing the axial movement of said at least one moveable segment.

2. The antenna defined in claim 1, wherein said segments in operative position are arranged to form a parabolic reflector.

3. The collapsible antenna defined in claim 1 wherein said means to cause said at least one moveable segment to move further includes locking means to hold said at least one moveable segment in its folded position, said locking means being unlocked by remote control to permit said at least one moveable segment to move on its open position.

4. The collapsible antenna defined in claim 1 wherein said fixed segment is rigidly attached to an antenna exciter.

5. The collapsible antenna defined in claim 4 wherein the antenna exciter is a communications satellite and said fixed segment is of such a size that its reflector surface is sumcient for communications between said satellite and a ground station.

6. The collapsible antenna of claim 1 further comprising clamping and locking means on said fixed segment to hold said at least one moveable segment in operative position.

7. A collapsible antenna comprising, in combination: at least one fixed reflector segment and at least one moveable reflector segment, mounting means defining a common axis for pen-nitting said at least one moveable segment to move first laterally and then axially relative to said fixed segment from a folded position overlapping said fixed segment to an operative position adjacent said fixed segment and including a post rigidly attached to said fixed segment and a sleeve attached to said at least one moveable segment, said sleeve being rotatably mounted on said post, and cutout portions in said at least one sleeve, said cutout portion permitting said sleeve to move axially until said at least one moveable segment forms a continuous reflector surface with said fixed segment, and means including spring means to move said moveable segment from said folded position to said operative position.

8. The collapsible antenna defined in claim 7 wherein there are two moveable segments, each having a sleeve attached and a cutout portion, one of said sleeves being rotatably mounted on the other of said sleeves.

9. The collapsible antenna defined in claim 8 wherein said spring means includes two torsion springs to rotate said moveable segments with respect to said fixed segments, and a coil spring to cause said moveable segments to move axially with respect to said fixed segment.

t i i l innme

Claims

5. The collapsible antenna defined in claim 4 wherein the antenna exciter is a communications satellite and said fixed segment is of such a size that its reflector surface is sufficient for communications between said satellite and a ground station.

7. A collapsible antenna comprising, in combination: at least one fixed reflector segment and at least one moveable reflector segment, mounting means defining a common axis for permitting said at least one moveable segment to move first laterally and then axially relative to said fixed segment from a folded position overlapping said fixed segment to an operative position adjacent said fixed segment and including a post rigidly attached to said fixed segment and a sleeve attached to said at least one moveable segment, said sleeve being rotatAbly mounted on said post, and cutout portions in said at least one sleeve, said cutout portion permitting said sleeve to move axially until said at least one moveable segment forms a continuous reflector surface with said fixed segment, and means including spring means to move said moveable segment from said folded position to said operative position.