Remotely deployable, unmanned satellite antenna

A remotely deployable, unmanned, inflatable satellite antenna is provided with shock absorbing supports inside a body of the antenna. The shock absorbing supports operatively connect the satellite receiver to the body interior surface and support the satellite receiver inside the body interior while allowing limited movement of the satellite receiver relative to the body interior surface in response to a shock force exerted on the body exterior surface when the antenna is deployed by air drop and impacts with the ground.

FIELD

The field of this disclosure is satellite antennas. More particularly, the field of this disclosure is an inflatable satellite antenna that is remotely deployable.

BACKGROUND

Transportable, inflatable antennas have been in use for many years. The typical antenna includes an inflatable sphere that contains the dish of the antenna and supports the feeder horn of the antenna.

The inflatable antenna can be deflated for transportation. The reduced size of the deflated antenna makes it easy to transport to a desired location. At the desired location the antenna is then inflated by one or more operator personnel. The dish and horn of the antenna are connected to the control electronics by the personnel. The antenna is then positioned for operation and secured in place on the ground by the personnel.

Inflatable antennas of the type described above require one or more personnel for their set up at the desired ground location.

SUMMARY

The remotely deployable, unmanned, satellite antenna of this disclosure is an improvement over prior portable, inflatable antennas in that it does not require personnel for its set up and orientation on the ground.

The remotely deployable, unmanned, satellite antenna of this disclosure comprises a body having a spherical exterior surface and a spherical interior surface that surrounds a hollow interior of the antenna. The antenna body is collapsible to a collapsed configuration for transportation, and inflatable to expand to its spherical configuration for deployment.

A satellite receiver is provided inside the body interior.

A rotation device is also provided inside the body interior. The rotation device is operatively connected to the satellite receiver and is operable to rotate the satellite receiver about first and second mutually perpendicular axes inside the body interior to properly orient the receiver in the deployed antenna.

An energy source is also provided inside the body interior. The energy source is operatively connected to the satellite receiver and the rotation device to supply electric energy to the receiver and device.

Shock absorbing supports are provided inside the body interior. The shock absorbing supports operatively connect the satellite receiver, the rotation device and the energy source to the body interior surface. The shock absorbing supports support the satellite receiver, the rotation device and the energy source inside the body interior while allowing limited movement of the satellite receiver, rotation device and energy source relative to the body interior surface in response to a shock force exerted on the body exterior surface. The shock absorbing supports enable the satellite antenna to be air droppable to a desired ground location. The shock absorbing supports shield the satellite receiver, the rotation device and the energy source inside the body interior when the body exterior surface impacts with the ground from the air dropped deployment.

In one embodiment of the remotely deployable, unmanned satellite antenna the satellite receiver comprises a dual reflector feed inside the body interior. The dual reflector feed minimizes the effects of phase aberrations and “spreading” of the focal point due to the spherical reflector.

In another embodiment the phase aberrations and “spreading” of the focal point are minimized by the feed of the satellite receiver with a dielectric lens.

The body of the satellite antenna can also have at least a portion constructed as wave partially reflecting and partially transmitting.

In addition to the energy source inside the antenna body, a solar cell outside the body can be communicated with the satellite receiver. The solar cell can be a flexible, lightweight, impact resistant solar cell sheet that can be located outside the body and attached to the body using a flexible cord. Alternatively, thin solar cells can be deposited or attached to the body interior surface.

The elements of the satellite antenna of this disclosure discussed above enable the satellite antenna to be remotely deployable and unmanned.

Each figure shown in this disclosure shows a variation of an aspect of the embodiments presented, and only differences will be discussed in detail.

DETAILED DESCRIPTION

FIG. 1is a representation of a cross section of the remotely deployable, unmanned, satellite antenna10of this disclosure showing the internal components of the antenna. The antenna10is an inflatable antenna having a spherical body12with a spherical exterior surface14and a spherical interior surface16when inflated. The spherical interior surface16surrounds a hollow interior18of the body and the other components of the satellite antenna to be described. As with all inflatable satellite antennas, the antenna body12is collapsible to a collapsed configuration for transportation, and is inflated and expanded to its spherical configuration represented inFIG. 1for deployment. The body12is constructed of materials typically employed in constructing inflatable satellite antennas. The body could be partially wave reflective and partially wave transparent. When expanded, the body12has approximately a three meter diameter dimension. However, the body12could have other dimensions. A portion20of the body interior surface16functions as the reflector surface of the antenna. In the representation of the antenna10shown inFIG. 1, the bottom half of the body interior surface16functions as the reflector surface.

A satellite receiver24is provided inside the body interior18. In order to minimize some phase aberrations and “spreading” of the focal point introduced by the spherical reflector surface20, the satellite receiver24could comprise a dual reflector feed represented by the second curved surface26on the receiver. Alternatively, the satellite receiver24could comprise a dielectric lens. The dielectric lens could be constructed from polytetrafluoroethylene (Teflon®), fused quartz, cross-linked polystyrene, foams, or other low-loss dielectric material.

The satellite receiver24is operatively connected to the body interior surface16by a tubular shock absorbing first support32and a tubular shock absorbing second support34. The shock absorbing first support32and second support34support the satellite receiver24inside the body interior18while allowing limited movement of the satellite receiver relative to the body interior surface16in response to a shock force exerted on the body exterior surface14. A tubular housing36having opposite first38and second40ends connects the shock absorbing first support32and the shock absorbing second support34. The tubular housing36is cylindrical and has a center, first axis42. The shock absorbing first support32and the shock absorbing second support34are coaxial and have a common center axis with the tubular housing center axis42. The housing36is operatively connected to the satellite receiver24through a bracket44that is mounted to the housing36by a pivot connection46. The pivot connection46enables the bracket44to pivot about a second axis48that is mutually perpendicular with the first center, first axis42of the tubular housing36.

Referring toFIGS. 3 and 4, the shock absorbing first support32has a tubular length with opposite proximal52and distal54ends. The first support proximal end52is received in the tubular housing first end38for reciprocating movement of the first support32relative to the housing36. The first support32is moveable relative to the tubular housing36and the satellite receiver24between a retracted position represented inFIG. 3, and an extended position represented inFIG. 4. In the retracted position of the shock absorbing first support32the shock absorbing first support distal end54is in close proximity to the receiver24. In the extended position of the shock absorbing first support32relative to the satellite receiver24the shock absorbing first support distal end54is displaced from the satellite receiver24. The shock absorbing first support distal end54is attached to the body interior surface16, thereby operatively connecting the satellite receiver24to the body interior surface16.

The shock absorbing second support34has basically the same construction as the first support32. The shock absorbing second support also has a tubular length with opposite proximal58and distal60ends. The second support proximal end58is received in the tubular housing second end40for reciprocating movement of the second support34relative to the housing36. The shock absorbing second support34is moveable relative to the tubular housing36and the satellite receiver24between a retracted position of the shock absorbing second support34represented inFIG. 3, and an extended position of the shock absorbing second support34represented inFIG. 4. In the retracted position of the shock absorbing second support34the shock absorbing second support distal end60is in close proximity to the satellite receiver24. In the extended position of the shock absorbing second support34the shock absorbing second support distal end60is displaced from the satellite receiver24. The shock absorbing second support distal end60is attached to the body interior surface16, thereby operatively connecting the satellite receiver24to the body interior surface16.

The shock absorbing first support32and the shock absorbing second support34are in their retracted positions relative to the housing36and the satellite receiver24represented inFIG. 3when the antenna body12is collapsed to its collapsed configuration for transportation of the antenna10. The shock absorbing first support32and the shock absorbing second support34are in their extended positions relative to the housing36and the satellite antenna24represented inFIG. 4when the antenna body12is expanded to its spherical configuration for deployment.

A spring device64biases the shock absorbing first support32and the shock absorbing second support34to their extended positions represented inFIG. 4. In the embodiment of the antenna10shown in the drawing figures, the spring device64is a single coil spring that extends through the tubular housing36and across the exteriors of the shock absorbing first support32and the shock absorbing second support34and is secured to the respective distal ends54,60of the supports. Other equivalent types of springs could be employed as the spring device64. For example, the spring device64could be comprised of two separate coils springs. When the antenna body12is collapsed to its collapsed configuration, the spring device64is compressed into the tubular housing36as represented inFIG. 3. With the spring device64compressed, latching devices (not shown) are provided at the opposite ends of the tubular housing36to hold the spring device64in its compressed condition. When expanding the antenna body12to its spherical configuration, the latching devices are released allowing the spring device64to bias the shock absorbing first support32and the shock absorbing second support34to their extended positions from the opposite ends of the housing36. When the shock absorbing first support32and the shock absorbing second support34are biased to their extended positions by the spring device as represented inFIG. 4, any impact of the body exterior surface14will be resisted by the spring device64and the shock of the impact will be absorbed by the spring device64.

A first rotation device70, for example an electric motor is positioned in the tubular housing36and the tubular first support32. The first rotation device70is operatively connected between the shock absorbing first support32and the tubular housing36. Operation of the first rotation device70selectively rotates the tubular housing36about the first axis42and thereby rotates the satellite receiver24in a circle around the first axis42inside the antenna body interior18. This enables adjusting the position of the satellite receiver24around the center of the reflective surface portion20of the body interior surface16. This in turn enables adjustment of the position of the satellite receiver24relative to the reflective surface20once the antenna10has been deployed.

A second rotation device72is positioned in the tubular housing36and the tubular second support34. The second rotation device72is operatively connected between the tubular housing36and the pivot connection46of the bracket44to the housing. Selective operation of the second rotation device72pivots the bracket44on the housing36about the second axis48and causes the satellite receiver24to move in an arc relative to the reflective surface portion20of the body interior surface16. This movement of the satellite receiver24about the second axis48also enables adjusting the position of the receiver relative to the reflector surface position20after the antenna10has been deployed.

Control electronics74for the satellite antenna10are positioned in the tubular housing36and in the tubular shock absorbing second support34. The control electronics74are connected in communication with the satellite receiver24, the latch devices (not shown), the first rotation device70and the second rotation device72. The control electronics74include software to operate the satellite receiver24, the latch devices (not shown), the first rotation device70and the second rotation device72.

An energy source76, such as a battery is positioned in the tubular housing36and the tubular first support32. The energy source76is operatively connected to the satellite receiver24, the latch devices (not shown), the first rotation device70, the second rotation device72and the control electronics74. The energy source76provides electric energy to the satellite receiver24, the latch mechanisms (not shown), the first rotation device70, the second rotation device72and the control electronics74when the satellite10is deployed to enable operation of all the satellite components.

Additionally, a further energy source such as solar cells could be provided on the body interior surface16or could be provided outside the body12. For example, a blanket80of solar cells represented inFIG. 1could be provided outside the antenna body12and communicating through electrical wiring82with the control electronics74and the energy source76inside the tubular housing36. The control electronics84would be powered by the solar blanket80in addition to the energy source76inside the antenna10.

Thus, the shock absorbing first support32and shock absorbing second support34support the satellite receiver24, the first70and second72rotation devices, the energy source76and the control electronics74inside the body interior18while allowing limited movement of the satellite receiver24, the rotation devices70,72, the energy source76and the control electronics74relative to the body interior surface16in response to a shock force exerted on the body exterior surface14. The shock absorbing first support32and second support34enable the satellite antenna10to be air droppable to a desired ground location. Shock absorbing first support32and shock absorbing second support34shield the satellite receiver24, the rotation devices70,72, the energy source76and the control electronics74inside the body interior18when the body exterior surface14impacts with the ground from the air dropped deployment. The antenna is weighted so that it will orient itself as shown inFIGS. 1 and 2when air dropped so that the shock absorbing first support32and shock absorbing second support34will absorb the force of impact.

The elements of the satellite antenna10of this disclosure discussed above enable the satellite antenna10to be remotely deployable and unmanned.

As various modifications could be made in the construction of the apparatus and its method of operation herein described and illustrated without departing from the scope of the invention, it is intended that all matter contained in the foregoing description or shown in the accompanying drawings shall be interpreted as illustrative rather than limiting. Thus, the breadth and scope of the present disclosure should not be limited by any of the above described exemplary embodiments, but should be defined only in accordance with the following claims appended hereto and their equivalents.