JPH06244631A - Antenna module for space - Google Patents

Abstract

(57) [Abstract] [Purpose] To obtain an antenna module that is extremely lightweight, highly rigid, withstands vibration loads when launching a rocket well, has fewer parts, and is inexpensive to manufacture. [Structure] The antenna module for space according to the present invention includes a main reflecting mirror 3 formed of a part of a paraboloid of revolution, and the main reflecting mirror 3 described above.
Offset gregorian composed of a sub-reflecting mirror 11 formed of a part of a spheroid having one focus as its own focus, and a feeding unit 4 placed at another focus of the spheroid of the sub-reflecting mirror 11 described above. Type antenna system, the main reflecting mirror 3, the sub-reflecting mirror 11, and the power feeding section 4 which constitute the above antenna system are supported at predetermined positions and directions, and a radio wave ray path is avoided at or near the focal point of the main reflecting mirror 3. The antenna tower 5 is provided with an opening 9.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention is a spacecraft that is mounted on space equipment such as artificial satellites, and is used for transmission and reception with space equipment such as ground stations and other artificial satellites in orbit after launch. The present invention relates to an antenna module.

[0002]

2. Description of the Related Art FIG. 6 shows AIAA 1978 ANTE.
NNA CONFERENCE PUBLICATIO
N "78-592 DESIGN OF ANTEN
NAMODULE STRUCTURE FOR IN
It is a figure which shows the principal part detail of the conventional space antenna module shown by "TELSAT V SPACECRAFT". 3 is a main reflecting mirror made of a part of a paraboloid of revolution, 4 is a feeding part, 5 is an antenna tower, 6 is a flip-and-deploy mechanism,
Reference numeral 7 is a holding and releasing mechanism. Further, FIG. 7 is a diagram showing a transmission range of a radio wave passing through the inside of the antenna tower 5, 8 is a ray path, and 9 is an opening of the antenna tower 5. In this antenna module 2, the main reflecting mirror 3
Is held in a stored state by the holding and releasing mechanism 7 so that the occupied area is reduced, and after reaching the track,
The holding / releasing mechanism 7 is actuated by a telemetry command or the like from the ground to release the restraint, and thereafter, the flipping and deploying mechanism 6 shifts to the deployed state shown in FIG. In this unfolded state, the feeding portion 4 directly faces the main reflecting mirror 3, and in the meantime, as shown in the figure, an opening 9 is formed on the wall surface of the antenna tower 5 to avoid the ray path as the ray path 8 expands. It is provided.

FIG. 8 shows ESA Proceedings.
of an internationali conf
erence SP-238 SPACECRAFT
STRUCTURES "TELE-X ANTENN
A MODULE STRUCTURE QUALIF
It is a figure which shows the principal part detail of the conventional space antenna module shown by "ICATION PROGRAM" (1985). 3 is a main reflecting mirror consisting of a part of a paraboloid of revolution,
Reference numeral 4 is a power feeding portion, 5 is an antenna tower, 6 is a flip-and-deploy mechanism, 7 is a holding / releasing mechanism, and 10 is a sub-reflecting mirror which is a part of a rotating hyperboloid. Further, FIG. 9 is a diagram showing a transmission range of a radio wave passing through the inside of the antenna tower 5, 8 is a ray path,
Reference numeral 9 is an opening of the antenna tower 5. In this unfolded state, as shown in the figure, the ray path 8 expands from the power feeding section 4 toward the sub-reflecting mirror 10, is reflected by the sub-reflecting mirror 10 and further expands toward the main reflecting mirror 3, and in between. As shown in the figure, an opening 9 is provided on the wall surface of the antenna tower 5 as the ray path 8 is enlarged so as to avoid the ray path.

[0004]

The conventional space antenna module is constructed as described above, and a very large opening must be provided on the wall surface of the antenna tower in order to avoid the ray path of radio waves. Therefore, there were the following problems.

Since a very large opening must be provided on the wall surface of the antenna tower, a slant member cannot be inserted in the wall surface, and the antenna tower has low rigidity in the direction in which this opening is distorted, and the antenna module as a whole Also has extremely low dynamic rigidity against the vibration load at launch.

In the vibration environment of many launch vehicles,
Since it is necessary to reinforce this low-rigidity direction, a complicated reinforcement structure must be added to the extent that radio wave ray paths can be avoided, resulting in a heavy antenna antenna module for space use that is also expensive to manufacture. Absent.

The present invention has been made in order to solve the above-mentioned problems, and it is possible to secure a sufficiently high dynamic rigidity against a vibration load at the time of launch, and to have a high structural reliability. The purpose is to obtain a space antenna module with a simple structure, small weight, and low manufacturing cost.

[0008]

A space antenna module according to the present invention comprises an antenna system, a main reflecting mirror having a part of a paraboloid of rotation, and two main focal points of the main reflecting mirror. One of the spheroids, one of which matches, is used as the sub-reflector, and the feed unit is placed at the remaining focal point of the sub-reflector, which is of the offset Gregorian type. The focal point of the main reflecting mirror where the ray path of the radio wave between the mirror and the sub-reflecting mirror converges or the vicinity thereof, and the aperture of the antenna tower wall surface for avoiding the ray path is determined to be as small as possible.

[0009]

By using the above means and setting the opening of the wall surface of the antenna tower to a position where it can be made as small as possible, it becomes possible to increase the rigidity of the wall surface of the antenna tower in the direction in which this opening is distorted, and It is possible to obtain an antenna module having high dynamic rigidity against vibration load.

Further, it is possible to increase the rigidity in the direction in which the opening of the antenna tower is distorted without adding a complicated reinforcing structure, and the weight can be reduced accordingly, and the number of parts can be reduced. Can be lowered.

[0011]

Embodiment 1 FIG. 1 is a diagram showing an embodiment of a space antenna module according to the present invention. In the figure, 1 is an artificial satellite main body, 2 is an antenna module, 3 is a main reflecting mirror formed of a part of a paraboloid of revolution, 4 is a feeding part, 5 is an antenna tower, and 6
A splashing and deploying mechanism, 7 is a holding / releasing mechanism, 8 is a ray path, 9 is an opening of the antenna tower 5, 11 is a sub-reflecting mirror that is a part of a spheroid, and 12 is the focal position of the main reflecting mirror 3. The focus position of the sub-reflecting mirror 11 and 13 are the remaining focus positions of the sub-reflecting mirror 11 on which the feeding section 4 is arranged.
Is the same as the conventional device. The antenna module 2 of the present embodiment has an antenna system configuration in which a part of a paraboloid of revolution is used for the main reflecting mirror 3 and a part of a spheroid is used for the sub-reflecting mirror 11, and a sub-reflection of the spheroid is used. One of the two focal points of the mirror 11 is aligned with the focal position of the main reflecting mirror 3, and the feeding portion 4 is arranged at the remaining focal position 13 of the offset Gregorian type, and the wall surface position of the antenna tower 5 is It is characterized in that the aperture 9 of the antenna tower wall surface for avoiding the ray path is minimized by adjusting the ray path 8 of the radio wave between the reflecting mirror 3 and the sub-reflecting mirror 11 to the focal point position 12 or its vicinity where the ray path 8 converges. .

2 and 3 are views showing an embodiment of a space antenna module according to the present invention in which the antenna tower 5 is composed of a truss tube and a joint. FIG. 3 is a view showing the range of transmission of radio waves passing through the inside of the antenna tower from the front. In the drawing, 1 is an artificial satellite body, 2 is an antenna module, 4 is a power supply section, 5 is an antenna tower, and 6
A splashing and deploying mechanism, 7 is a holding / releasing mechanism, 8 is a ray path, 11 is a sub-reflecting mirror formed by a part of a spheroid, 12 is a focal position of the sub-reflecting mirror 11 that matches the focal position of the main reflecting mirror, 13 is The remaining focus position of the sub-reflecting mirror 11 in which the power feeding unit 4 is arranged, 15 is a cross section of the conical antenna ray tower 8 at the wall surface position of the antenna tower, and 16 is a slant member attached to the wall surface position of the antenna tower 5. , 18 are joints, and 19 are truss tubes, where 1, 4, 18, and 19 are the same as conventional devices.

The antenna module 2 of the above embodiment is
The cross section 15 at the wall surface position of the antenna tower 5 having a conical shape with the focal point 12 formed by the ray path 8 of the radio wave between the main reflecting mirror 3 and the sub reflecting mirror 11 at the apex was attached to the wall surface position of the antenna tower 5. It is characterized in that it is inserted into the triangular extra space of the diagonal member 16 which is the two intersecting truss tubes to avoid the ray pass. Therefore, it is not necessary to newly provide an opening on the wall surface of the antenna tower for avoiding the ray path, and the antenna tower can have high rigidity by the two diagonal members 16 intersecting each other.

Second Embodiment FIGS. 4 and 5 are views showing a second embodiment of a space antenna module in which a wall surface of an antenna tower 5 according to the present invention is composed of a panel and a joint. In the figure, 1 is an artificial satellite body, 2 is an antenna module, 4 is a power feeding unit, 5 is an antenna tower, 8 is a ray path, and 9 is an antenna tower 5.
, 11 is a sub-reflecting mirror consisting of a part of a spheroid,
12 is the focal position of the sub-reflecting mirror 11 that coincides with the focal position of the main reflecting mirror 3, 13 is the remaining focal position of the sub-reflecting mirror 11 on which the feeding portion 4 is arranged, and 14 is the wall thickness of the wall member of the antenna tower ( t), 15 is a cross section at the wall surface position of the conical antenna tower formed by the radio ray path 8, 17 is a panel, 1
8 is a joint. 1, 4, 17, and 18 are the same as the conventional device. This shows a situation in which the ray path 8 of the radio wave emitted from the power feeding section 4 is reflected by the sub-reflecting mirror 11 and converges toward the focal position 12, and the opening 9 on the antenna tower wall surface for avoiding the ray path 8 is shown. In consideration of the wall thickness dimension 14, is a finite size surrounding the cross section 15 at the wall surface position of the conical antenna tower formed by the radio wave path 8.

FIG. 5 is a front view of the wall surface of the antenna tower of FIG. 4, and an opening 9 for avoiding the ray path 8 is formed in the entire antenna tower wall surface of the antenna module of the embodiment of the present invention. Shows that a very small area is enough.

The space antenna module 2 of the above embodiment can obtain high rigidity by making the opening 9 on the wall surface of the antenna tower as small as possible. Further, by using the panel on the wall surface through which the ray pass passes, it is possible to provide an opening having an arbitrary shape matching the ray pass shape and the focal position at an arbitrary position within the panel. Therefore, for a ray path having an arbitrary shape such as a multi-beam having a plurality of power feeding portions, it is possible to set the opening portion without impairing the rigidity and without adding a complicated reinforcing structure.

[0017]

As described above, according to the space antenna module of the present invention, it is necessary to add a complicated reinforcing structure to obtain an antenna module having high dynamic rigidity against a vibration load at the time of launch. In addition, the number of parts is further reduced, the weight is light, and the manufacturing cost is low.

[Brief description of drawings]

FIG. 1 is a diagram showing an embodiment of a space antenna module according to the present invention.

FIG. 2 is a diagram showing a space antenna module according to the first embodiment of the present invention.

FIG. 3 is a diagram showing a radio wave passage range of the space antenna module and an opening of the antenna tower according to the first embodiment of the present invention.

FIG. 4 is a diagram showing a radio wave passage range of an antenna module for space and an opening of an antenna tower according to a second embodiment of the present invention.

FIG. 5 is a diagram showing a radio wave passage range of an antenna module for space and an opening of an antenna tower according to a second embodiment of the present invention.

FIG. 6 is a diagram showing details of a conventional space antenna module.

FIG. 7 is a view showing a radio wave passage range of a conventional space antenna module and an opening of an antenna tower.

FIG. 8 is a diagram showing details of another conventional space antenna module.

FIG. 9 is a diagram showing a radio wave passage range of another conventional space antenna module and an opening of an antenna tower.

[Explanation of symbols]

 1 Artificial Satellite Main Body 2 Antenna Module 3 Main Reflector 4 Feeding Part 5 Antenna Tower 6 Splashing and Deploying Mechanism 7 Holding and Releasing Mechanism 8 Ray Pass 9 Antenna Tower Aperture 10 Sub-Reflecting Mirror Part of Rotating Hyperboloid 11 Rotating Paraboloid Sub-reflector consisting of a part of the sub-reflector 12 Focus of the sub-reflector that matches the focus of the main reflector 13 The other focus of the sub-reflector where the feeding part is placed 14 Wall thickness of the antenna tower 15 Ray-path antenna tower Wall thickness of the wall 16 The diagonal member mounted on the wall of the antenna tower 17 Panel 18 Joint 19 Truss tube

Claims (3)

[Claims] 1. A main reflecting mirror made of a part of a paraboloid of revolution, a sub-reflecting mirror made of a part of an ellipsoid of revolution having a focal point of the main reflecting mirror as one of its focal points, and a rotation of the sub-reflecting mirror. An offset Gregorian type antenna composed of a power feeding section placed on another focus of an ellipsoid, a main reflecting mirror, a sub reflecting mirror, and a power feeding section which constitute the above antenna are supported at a predetermined position and a predetermined posture, An antenna module for space, comprising: an antenna tower provided with an opening for avoiding a ray pass of a radio wave at or near a focal point of a main reflecting mirror. 2. The antenna module for space use according to claim 1, wherein the wall surface of the antenna tower through which the ray pass passes is constituted by a truss tube and a joint, and the gap between the truss tubes is a ray pass opening. 3. The wall surface through which the ray pass of the antenna tower is constructed by a panel and a joint, and a hole suitable for the ray pass shape is formed as a ray pass opening in a part of the panel. Space antenna module.