Patent Grant
7248228
1. Statement of the Technical Field
The inventive arrangements relate to the field of RF antennas, and more particularly, to antenna pedestals.
2. Description of the Related Art
Oftentimes RF communication antennas are operated in environments which are not ideal. For example, it is common to find communication antennas mounted to mobile craft, such as aircraft, watercraft, automobiles and military vehicles, all of which experience some levels of vibration. Such vibration can induce beam radial errors in communication antenna reflectors, especially antennas which communicate via microwave signals having beam radiation patterns.
Vibration can include up to six acceleration components which interfere with antenna tracking. Specifically, the acceleration components include translational components along the x, y and z axes and rotational components about each of the three axes. Random vibrations typically are a composite of all six vibration components.
Vibration dampeners for absorbing vibration energy are known. However, simultaneously dampening of all six acceleration components has proven to be particularly difficult. For example, U.S. Pat. No. 6,695,106 to Smith et al. discloses a tunable vibration isolator for isolating a fuselage of a helicopter or rotary wing aircraft from other aircraft components, such as the engine or transmission. Smith's vibration isolator is of limited value, however, because it primarily dampens only a single translational component of vibration.
U.S. Pat. No. 6,471,435 to Lee discloses a flexural joint with two degrees of freedom. However, as noted, vibration can include up to six acceleration components. Thus, the flexural joint disclosed by Lee would not provide optimum vibration dampening for a communication antenna which is mounted onto a mobile craft.
U.S. Pat. No. 6,290,183 to Johnson et al. discloses a three-axis vibration device for use in a spacecraft vibration isolation system. The vibration device utilizes a plurality of dual-beam flexure isolation devices disposed between a payload and the spacecraft. Notably, the center of gravity of the payload is significantly offset from the flexure isolation devices. This arrangement results in a large moment of the payload mass relative to the vibration device. In consequence, the excitation response of the payload mass at the system resonant frequency will be high.
The present invention relates to a vibration isolation system for a payload mass, such as an RF communications antenna. The vibration isolation system provides a level of vibration isolation for all vibration in the three translational and three rotational components, while minimizing the moment of the payload mass relative to the isolation system. The vibration isolation system can include a base to which a payload having mass, for example a communications antenna and antenna pedestal, is coupled and a plurality of vibration isolators.
Each of the vibration isolators can include a semi-rigid first support member having a first portion positioned below the base and an opposing second portion positioned above the base. For example, the first support member can be a vertical support member. Each of the vibration isolators also can include a second support member having a first portion fixed to the base and an opposing second portion extending above the base. The second support member can be, for example, a support tube. In this arrangement the first support member can be positioned coaxially within the support tube and extend through a respective aperture defined in the base.
An elastomeric coupling can be provided to couple the second portion of the first support member to the second portion of the second support member. A height of the elastomeric coupling with respect to the base can be approximately equal to a height above the base of a center of gravity of a combined mass of the base and the payload.
Each of the second support members can include a cap member. The cap member can be fixed the second portion of a respective support tube. The elastomeric coupling can be positioned between the cap members and the second portion of the first support member.
The present invention relates to a vibration isolation system (hereinafter “isolation system”) for a payload mass, such as an RF communications antenna. The isolation system provides a level of vibration isolation for all vibration in the three translational and three rotational components, while minimizing the moment of the payload mass relative to the isolation system. Accordingly, the excitation response of the payload mass at the system resonant frequency is minimal relative to the level of vibration excitation. Additionally, the rotational and translational modes of the system can be independently tuned to achieve desired natural frequencies. Advantageously, the modes can be selected to be at frequencies which are significantly lower or higher than the fundamental frequencies of respective vibration components. In consequence, vibration attenuation is much improved relative to vibration isolation systems of the prior art.
A plurality of vibration isolators 114 can be provided to couple the base 104 to a platform 116. The vibration isolators 114 can be distributed around the base 104 at selected locations. The arrangement of the vibration isolators 114 can be selected to adjust a rotational natural frequency of the base 104 and payload 102 about the three axes without impacting translational mode dampening of the system. More particularly, dampening of the rotational vibration components can be increased by increasing a distance of each of the vibration isolators 114 from a vertical center of gravity 128 of the combined mass of the payload 102 and base 104, while locating the vibration isolators closer to the center of gravity 128 can decrease the rotational dampening of the system 100. The ability to selectively tune rotation vibration dampening independently of translational vibration dampening is an important advantage of the present system 100 because rotational vibration components are largely responsible for high beam radial errors in communication antennas.
An exploded view of a vibration isolator 114 is shown in
The first support member 202 can comprise metal, fiberglass, composite material, plastic, or any other semi-rigid material suitable for supporting the mass of the payload while providing a degree of structural compliance and vibration energy absorption. As defined herein, the term “semi-rigid” as applied to the first support member 202 means that the first support member 202 can flex in a radial direction to absorb vibration energy, while simultaneously supporting at least a portion of the mass of the payload. Notably, the present invention does not require that the first support member 202 have a specific spring constant, stiffness or strength. Rather, the vertical support member 202 can be selected to provide a desired amount of vibration absorption and/or support stiffness which is optimized for the particular payload. For example, a structural compliance of the support member 202 can be selected to tune the fundamental modes of the system 100 to a desired natural frequency which maximizes the effectiveness of the vibration isolator 114. More particularly, the natural frequency can be selected to be significantly lower or higher than the fundamental frequency of the primary vibrational input.
In the arrangement shown, the second support member 208 is embodied as a rigid support tube having mounting plates 214 and 216 attached to respective ends 210 and 212 of the second support member 208. An inner diameter 218 of the second support member 208 can be greater than an outer diameter 220 of the first support member 202 so that the first support member 202 can be coaxially positioned within the second support member 208. It is preferred that the diameter 218 of the second support member 208 is sufficient to allow a degree of movement and/or flexure of the first support member 202 within the second support member 208. In an alternate arrangement (not shown) the first support member 202 and the second support member 208 can be disposed in a non-coaxial manner. Moreover, the second support member 208 can be flexible or semi-rigid.
The first support member 202 can extend through the second support member 208 so that the second end 206 of the first support member 202 is disposed above the mounting plate 216. Further, the second end 206 of the first support member 202 can engage an elastomer support 222. The elastomer support 222 can be rigid or semi-rigid. Further, the elastomer support 222 can comprise a socket 224 for receiving the second end 206 of the first support member 202. One or more fasteners 226 can fix the elastomer support 222 to the first support member 202.
An elastomeric coupling 228 can be fixed to the elastomer support 222 in any suitable manner, for example with fasteners 230, so that the elastomer is coupled to the first support member 202. The elastomeric coupling 228 can comprise an elastomer, which can be any suitable polymer having elastic properties. For example, a suitable elastomer can be rubber or neoprene, although the invention is not limited in this regard. One example of an elastomeric coupling 228 that can be used is a J-6332-183 Flex-Bolt® Sandwich Mount available from Western Rubber & Supply, Inc. of Livermore, Calif. The J-6332-183 Flex-Bolt® Sandwich Mount can receive a maximum compression load of 13,440 lb and a maximum shear load of 1,680 lb. Further, the J-6332-183 Flex-Bolt® Sandwich Mount has a compression stiffness of 42,100 lb/in. and a shear stiffness of 4,200 lb/in. Still, other elastomeric couplings can be used and the invention is not limited in this regard. For example, if the payload has relatively little mass, an elastomeric coupling having less load capability and stiffness can be used. Similarly, if the payload has a relatively large mass, an elastomeric coupling having greater load capability and stiffness can be used. A wide range of such elastomeric couplings are available from Western Rubber & Supply, Inc., as well as other vendors.
A cap member 232 can be provided to couple the elastomeric coupling 228 to the second support member 208. In particular, the cap member 232 can be configured to position the elastomeric coupling 228 between the cap member 232 and the elastomer support 222. For example, the cap member can define a cavity 234 in which the elastomeric coupling 228 is disposed. One or more fasteners 236 can fix the elastomeric coupling 228 to the cap member 232. Further, one or more fasteners 238 can fix the cap member 232 to the mounting plate 216. As shown, the elastomer support 222 is not coupled directly to the second support member 208, but instead is coupled to the second support member 208 via the elastomeric coupling 228 and the cap member 232. This configuration enables the elastomeric coupling 228 to provide vibration isolation between the first support member 202 and the second support member 208.
In an embodiment in which the support member must be welded to the platform 116, a base ring 238 and a base disk 240 can be provided to minimize weld distortions, which can cause misalignment of the first support member 202 relative to the base. In particular, the base ring 238 can be welded to the platform 116. The base disk 240 can be disposed within the base ring 238 and welded to the base ring 238. The first end 204 of the first support member 202 can be fixed to the base disk 240. For example, the first end 204 can be provided with threads and screwed into a threaded receiving aperture 242 in the base disk 240. Alternatively, the first end 204 of the first support member 202 can be welded to the base disk 240.
Again turning attention to
As shown, the vibration isolators 114 can be distributed around the base 104. Positioning of the vibration isolators 114 in this fashion provides both translational and rotational vibration isolation. In particular, each of the first support members 202 can bend in a same x and/or y direction to isolate translational vibration components along the x and y axes. The elastomeric couplings 228 also can stretch and compress along the x and/or y axes to provide a degree of isolation for such translational vibration components. Further, each of the elastomeric couplings 228 can compress and stretch in unison along the z axis to isolate translational components along the z axes.
To isolate rotational vibration components about the z axis, each of the first support members 202 can deflect circumferentially about the z axis and the elastomeric couplings 228 can compress and stretch in unison about the same z axis. Finally, elastomeric couplings 228 coupled to a first side 120 of the base 104 can compress while elastomeric couplings 228 coupled to an opposing second side 122 of the base 104 can stretch, and vice versa. Similarly, elastomeric couplings 228 coupled to a third side 124 of the base 104 can compress while elastomeric couplings 228 coupled to a fourth opposing side 126 of the base 104 can stretch, and vice versa. Such compression and stretching of the elastomeric couplings can isolate rotational vibration components about the x and y axes.
A perspective view of the antenna isolation system of
While the preferred embodiments of the invention have been illustrated and described, it will be clear that the invention is not so limited. Numerous modifications, changes, variations, substitutions and equivalents will occur to those skilled in the art without departing from the spirit and scope of the present invention as described in the claims.
This application is a divisional of U.S. patent application Ser. No. 10/987,061, filed Nov. 12, 2004 now U.S. Pat. No. 7,104,515, which claims benefit of United States. The aforementioned related patent application is herein incorporated by reference.
This invention was made with U.S. government support under Prime Contract Number HQ0006-01-C-0001 awarded by the Department of Defense. The U.S. government has certain rights in this invention.
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| Number | Date | Country | |
|---|---|---|---|
| 20070139292 A1 | Jun 2007 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 10987061 | Nov 2004 | US |
| Child | 11487659 | US |
