Patent Description:
The invention has been developed primarily for use in/with disaster management and will be described hereinafter with reference to this application. However, it will be appreciated that the invention is not limited to this particular field of use, and may be applied to use in a wide variety of applications, especially in remote areas.

At present, when and natural disaster occurs, infrastructure, and especially communications infrastructure can be disrupted. This may be due to disruptions in electrical supply to communications networks, or because of physical destruction of the communications hardware.

Recovery and management efforts may be disrupted by lack of a reliable communication infrastructure. People that are in strife due to the natural disaster also find it difficult to communicate their situation to the authorities that can help them.

Gyrochutes, also known as rotary chutes and/or unpowered autogyros, are known, and are unpowered vehicles that include one or more sets of blades that operate to generate autorotation of the gyrochute. Autorotation of the gyrochute creates lift from the movement of air over the aerofoil blades. Further, the blades generate drag acting upwardly in a vertical direction as the gyrochute falls through the air. The vertical forces acting on the gyrochute to cause it to fall slower are typically generated by a combination of airflow over the blades from rotation about a central axis to create lift, as well as from vertical airflow as the gyrochute drops downwardly through the air, creating drag.

<CIT> (D1) relates to a flying micro-rotorcraft unit for remote tactical and operational missions. The flying micro-rotocraft unit includes an elongated body, a navigation module for determining a global position of the body during flight of the unit, and a rotor means. The unit is arranged such that the rotor is connected to the upper end of the elongated body, and the navigation module is located on top of the central hub of the rotor.

<CIT> (D2) discloses a method, system, and apparatus for reconnaissance for staging a mission in a target area of a remote location. The invention includes a satellite surveillance means, a radio beacon/video camera transceiver means, a communication means connecting the surveillance means and the transceiver means, a communication means connecting the transceiver means to a base station, and an analysis means for analyzing video, positional, and other data from the target area.

<CIT> (D3) discloses a pyrotechnic flare suspended from a foldable, rotatable, bladed rotor, and a power generating means operated by the heat from the flare and drives the rotor.

<CIT> (D4) discloses a gryochute for attaching to a payload, wherein the gyrochute is comprised of a shaft, rotor blades, attachment means to a payload, and a blade restraining element to prevent the rotor blades from rising above a certain angle when the gyrochute is in use.

<CIT> (D5) discloses a computing system for matching a ground station to a plurality of aerial vehicles, such as high-altitude aerial balloons, for establishment of a link to an airborne network.

The present invention seeks to provide an aerially distributable communications device, which will overcome or substantially ameliorate at least some of the deficiencies of the prior art, or to at least provide an alternative.

It is to be understood that, if any prior art information is referred to herein, such reference does not constitute an admission that the information forms part of the common general knowledge in the art, in Australia or any other country.

According to a first aspect, claim <NUM> defines an aerially distributable communications device for aerial deployment as a node of a communications network, the aerially distributed communications module including:.

wherein the blades of the set of blades at least partly define an aerofoil shape along their length, and the pitch of the aerofoil shape is variable along the length of the blade.

In one embodiment, the gyrochute includes a body, the body including a hub and a hollow formation extending around the outside of the at least one or more set of blades.

In one embodiment, the hollow formation is a cylindrical formation, and the at least one or more set of blades are rigidly connected to the cylindrical formation.

In one embodiment, the cylindrical formation includes an annular flange extending outwardly from an upper edge of the cylindrical formation, the vertices of the cylindrical formation curve into the annular flange at a curved upper surface; and wherein the annular flange includes a curved lower surface and the curved upper surface of the annular flange is configured for inducing a main column of airflow flowing upwardly through the cylindrical formation, to flow radially outwardly over the curved upper surface in use to induce lift force.

In one embodiment, the at least one of the set of blades includes a planar extended trailing edge portion.

In one embodiment, the pitch of the autorotation portion is variable.

In one embodiment, the gyrochute includes at least a plurality of blade sets.

In one embodiment, the gyrochute includes a first blade set comprising a plurality of primarily lift force inducing blades attached at a hub, and a second blade set comprising a plurality of primarily rotation inducing blades.

In one embodiment, at least one or more blades of the at least one or more blade sets are foldable blades.

In one embodiment, at least one or more blades of the at least one or more blade sets are configured to be removably connectable to the body by a connector arrangement.

In one embodiment, the aerially distributable communications device further includes a controller, and wherein the controller includes at least one or more selected from:.

The following example embodiments are not claimed, unless otherwise indicated.

In one embodiment, the at least one or more set of blades are configured to induce autorotation and lift forces when falling through the air.

In one embodiment, the hollow formation is connected to the hub.

In one embodiment, the at least one or more set of blades are configured to generate vertical friction or drag forces when falling through the air.

In one embodiment, the at least one or more set of blades are configured to generate vertical forces when falling through the air from drag or air friction moving vertically over the gyrochute.

In one embodiment, the at least one or more set of blades are configured to generate vertical forces when falling through the air from lift generated from airflow moving over the at least one or more set of blades.

In one embodiment, the autorotation portion is configured to generate lift as the gyrochute is falling downwardly through the air, and wherein the lift includes at least a component for generating a rotational moment in the gyrochute.

In one embodiment, the gyrochute includes three blades.

In one embodiment, the blades are connected to each other at a hub.

In one embodiment, the at least one or more set of blades are rigidly connected to the hub.

In one embodiment, the at least one or more set of blades are rotationally connected to the hub to freely rotate about the hub.

In one embodiment, the communications module is at least partly located in the hub.

In one embodiment, the hollow formation is symmetrical.

In one embodiment, the hollow formation is one or more selected from:.

In one embodiment, the hollow formation is segmented.

In one embodiment, at least one or more blade is connected to a segment of the hollow formation.

In one embodiment, a blade is associated with each segment of the hollow formation.

In one embodiment, at least one or more blades is associated with a vertical fin.

In one embodiment, a plurality of vertical fins together make up a segmented hollow formation.

In one embodiment, at least one or more of the vertical fins are aerofoil shaped in cross-section.

In one embodiment, the aerofoil shape of the at least one or more vertical fins is configured to be streamlined in the horizontal direction in use.

In one embodiment, the aerofoil shape of the at least one or more vertical fins is configured to be streamlined in the vertical direction in use.

In one embodiment, the hollow formation includes curved vertices.

In one embodiment, at least one of the blades is rigidly connected to the cylindrical formation.

In one embodiment, the gyrochute includes an annular flange.

In one embodiment, the annular flange extends outwardly from the hollow formation.

In one embodiment, the annular flange extends outwardly from the cylindrical formation.

In one embodiment, the annular flange extends outwardly from an upper edge of the cylindrical formation.

In one embodiment, the annular flange includes a curved upper surface.

In one embodiment, the annular flange is aerofoil shaped.

In one embodiment, the curved upper surface is aerofoil shaped.

In an alternative embodiment, the annular flange includes a flat upper surface.

In one embodiment, the upper surface of the annular flange defines an inner edge and an outer edge.

In one embodiment, the inner edge of the upper surface of the annular flange extends further downwardly than the outer edge.

In one embodiment, the annular flange includes a curved lower surface.

In an alternative embodiment, the annular flange includes a flat lower surface.

In one embodiment, the flat lower surface intersects the outer vertical surface at an angle.

In one embodiment, the lower surface of the annular flange includes an outer edge.

In one embodiment, the lower surface of the annular flange includes an inner edge.

In one embodiment, the lower surface of the annular flange extends tangentially to the outer surface of the cylindrical formation.

In one embodiment, the lower surface of the annular flange curves outwardly and away from the outer surface of the cylindrical formation.

In one embodiment, the flat upper surface of the annular flange extends at an obtuse angle to the inner surface of the cylindrical formation when viewed in a radial plane.

In one embodiment, the curved upper surface of the annular flange is configured for inducing the main column of airflow to flow radially outwardly over the curved upper surface in use.

In one embodiment, the gyrochute includes at least one or more control surfaces.

In one embodiment, the annular flange includes at least one or more movable control surfaces.

In one embodiment the control surfaces include flange control surfaces configured to be movable for reconfiguring the position of the annular flange.

In one embodiment, the at least one or more movable flange control surfaces on the annular flange is rotatable about an upper edge of the hollow formation.

In one embodiment, the annular flange is pivotally movable relative to the hollow formation.

In one embodiment, the annular flange is segmented.

In one embodiment, each segment of the annular flange is associated with a segment of the hollow formation.

In one embodiment, the annular flange includes a pivoting arrangement.

In one embodiment, the pivoting arrangement is one or more selected from:.

In one embodiment, one or more sets of blades include at least one or more movable blade control surfaces.

In one embodiment, the at least one or more control surfaces include at least one or more control motors.

In one embodiment, the control motors are controllable by a controller.

In one embodiment, the control motors are controllable wirelessly from a remote controller.

In one embodiment, the aerially distributable communications device includes at least one or more legs extending underneath the communication module.

In one embodiment, the legs are resilient.

In one embodiment, the legs are composed of spring steel.

In one embodiment, the legs extend from the cylindrical formation.

In one embodiment, the communications module includes a controller.

In one embodiment, the gyrochute includes a single set of blades.

In one embodiment, the gyrochute includes an extended trailing edge portion.

In one embodiment, at least one or more of the blades includes an aerofoil portion and an extended trailing edge.

In one embodiment, the extended trailing edge is substantially planar.

In one embodiment, the trailing edge extends substantially parallel with an upper edge of the cylindrical formation.

In one embodiment, the pitch of the aerofoil portion is below the horizontal.

In one embodiment, the pitch of the aerofoil portion is below the horizontal when the aerially distributable communications device is falling in equilibrium.

In one embodiment, the pitch of the aerofoil portion can be controlled by the controller.

In one embodiment, the pitch of the aerofoil portion is between <NUM>° and <NUM>° in use with respect to the horizontal when the aerially distributable communications device is falling in equilibrium.

In one embodiment, the pitch of the aerofoil portion varies between <NUM>° and <NUM>° below the horizontal along its length.

In one embodiment, the trailing edge extends substantially horizontally in use when the aerially distributable communications device is falling in equilibrium and/or stable flight.

In one embodiment, the gyrochute includes a first blade set comprising a plurality of primarily lift force inducing blades attached at a hub.

In one embodiment, the plurality of lift force inducing blades extend radially from the hub.

In one embodiment, the lift force inducing blades are configured to present a constant pitch in use when the gyrochute is in equilibrium and/or stable flight.

In one embodiment, the lift force inducing blades include a pitch that is substantially horizontal.

In one embodiment, the lift force inducing blades are configured to present a pitch of between <NUM>° and <NUM>° downwardly from the horizontal.

In one embodiment, the first blade set is rigidly connected to a central axis.

In one embodiment, the first blade set and the hollow formation are concentric.

In one embodiment, the gyrochute includes a second blade set of primarily rotation force inducing blades.

In one embodiment, the rotation inducing blades are configured to present a pitch of between <NUM>° and <NUM>° downwardly from the horizontal.

In one embodiment, the rotation inducing blades are configured to vary their pitch along their length.

In one embodiment, the rotation inducing blades are configured to vary their pitch along the length to present a pitch of between <NUM>° and <NUM>° downwardly from the horizontal.

In one embodiment, the plurality of rotation inducing blades are attached at a hub.

In one embodiment, the plurality of rotation inducing blades extend radially from the hub.

In one embodiment, the second blade set is fixed in position relative to the cylindrical formation.

In one embodiment, the first blade set and the second blade set are concentric.

In one embodiment, the second blade set and the cylindrical formation are concentric.

In an alternative embodiment, the gyrochute includes a plurality of counter rotating blade sets.

In one embodiment, at least one or more of the plurality of counter rotating blade sets are freely rotatable about a central axis.

In one embodiment, at least one or more of the plurality of counter rotating blade sets includes primarily lift force inducing blades.

In one embodiment, the foldable blades include a plurality of folding blade portions and a folding mechanism.

In one embodiment, the folding mechanism is spring-loaded.

In one embodiment, the blades are configured to be removable from the body.

In one embodiment, the blades are configured to be removably connectable to the body by a connector arrangement.

In one embodiment, the blades include connector formations for removable connection to the body.

In one embodiment, the connector arrangement includes one or more selected from:.

In one embodiment, the communications module is configured for wireless communication in one or more selected from:.

In one embodiment, the communications module includes at least one or more antennaes.

In one embodiment, the controller includes at least one or more selected from:.

In one embodiment, the digital storage media is configured with software instructions for directing operation of the processor.

In one embodiment, the communications module includes at least one receiver.

In one embodiment, the communications module includes at least one transmitter.

In one embodiment, the communications module includes at least one or more sensors.

In one embodiment, the at least one or more sensors include one or more selected from:.

In one embodiment, the communication module includes a dehumidifier.

In one embodiment, the communication module includes a water purification device.

In one embodiment, the dehumidifier is configured for generating water from humidity in the air.

In one embodiment, the communication module includes a storage tank for storing water generated by the dehumidifier.

In one embodiment, the communication module includes a visual alert generator.

In one embodiment, the visual alert generator is a light source.

In one embodiment, the light source is an LED light.

In one embodiment, the communication module includes an audial alert generator.

In one embodiment, the audial alert generator is one or more selected from a speaker, a whistle and a buzzer.

In one embodiment, the aerially distributable communications device includes a power source.

In one embodiment, the power source is one or more selected from a battery and a capacitor.

In one embodiment, the aerially distributable communications device includes a power generation arrangement.

In one embodiment, the power generation arrangement is at least one or more solar panels.

In one embodiment, the controller is configured to control recharging of the power source by the solar panel.

In one embodiment, the controller is configured for control communications to a gateway communication device.

In one embodiment, the software instructions are configured for directing the processor to:.

In one embodiment, the received communication signal includes an associated timestamp, and the step of storing and transmitting the received communication signal includes the step of storing and transmitting the associated timestamp, respectively.

In one embodiment, the wireless transmitter and/or receiver (the "transceiver") is configured for low-power and/or short-range wireless communication using one or more selected from the following protocols:.

In one embodiment, the wireless transmitter and/or receiver is configured for high-power and/or long-range wireless communications using one or more selected from the following protocols:.

In one embodiment, the aerially distributable communications device is configured for deployment from one or more selected from a spacecraft and a satellite.

In one embodiment, the aerially distributable communications device includes a heat shield for shielding one or more selected from the gyrochute and the communications module on re-entry into an atmosphere in use.

In one embodiment, the heat shield is composed of a plurality of portions.

In one embodiment, the plurality of portions together enclose the gyrochute and applications module.

In one embodiment at least one or more of the plurality of portions are heat resistant.

In one embodiment, the heat shield comprises an upper portion and a lower portion.

In one embodiment, the heat shield comprises a plurality of side portions.

In one embodiment, the plurality of side portions are configured to engage with each other to enclose one or more selected from the gyrochute and the communications module.

In one embodiment, the lower portion includes a heat resistant layer.

In one embodiment, the resistant layer is composed of ceramic.

In one embodiment, the heat shield is configured for being disposed of after re-entry.

In one embodiment, the heat shield is configured for inducing autorotation.

In one embodiment, the plurality of portions of the heat shield are coupled together by a fastening arrangement.

In one embodiment, the controller is configured for operating the fastening arrangement to decouple the plurality of portions of the heat shield.

In one embodiment, the controller is configured for receiving information from sensors indicative of one or more selected from:.

In one embodiment, the controller is configured for operating the fastening arrangement in accordance with information received from the sensors, in order to determine when to decouple the plurality of portions of the heat shield.

In one embodiment, the heat shield is configured for being thrown outwardly on the coupling of the plurality of portions.

In one embodiment, the heat shield includes at least one or more explosive arrangements for pushing the heat shield away from the gyrochute and/or the communications module.

In one embodiment, the heat shield is configured for being thrown outwardly on the coupling of the plurality of portions by the centrifugal force generated by autorotation of the aerially distributable communications device.

In one embodiment, the fastening arrangement includes at least one frangible fastening member configured for breaking if forces acting on the aerially distributable communications device exceed a threshold limit.

In one embodiment, the plurality of portions of the heat shield are engageable with each other at a labyrinth seal.

In one embodiment, the fastening arrangement includes a locking pin.

In one embodiment, the login pin is receivable within locking formations in the portions, the locking pin being configured for locking the portions together.

In one embodiment, the controller is configured for removing the locking pin from the locking formations.

In one embodiment, the aerially distributable communication device includes a plurality of gyrochutes.

In one embodiment, the aerially distributable communication device includes a frame connecting the plurality of gyrochutes.

In one embodiment, the frame includes supporting formations for supporting a payload.

According to claim <NUM>, in a a further aspect, the present invention may be said to comprise a communication network, comprising a plurality of devices according to claim <NUM>.

In one embodiment, the communication network is one or more selected from the following network topologies:.

In one embodiment, the communication network includes a gateway communication module is configured for communication to communication nodes outside of the communication network.

In one embodiment, the gateway communication module is configured for satellite communication to a satellite via a satellite communication network.

In one embodiment, the gateway communication module is configured for communication via medium to long range communication protocols.

In one embodiment, the medium to long range communication protocols include one or more selected from:.

According to a further aspect, the present invention according to claim <NUM> comprises a method of deploying communications nodes, the method comprising:.

The following example embodiments are not claimed.

In one embodiment, the step of deploying the at least one or more aerially distributable communication devices comprises the step of launching the at least one or more aerially distributable communication nodes from an aircraft with an initial angular velocity about the centre of the at least one or more set of blades.

In one embodiment, the step of deploying the at least one or more aerially distributable communication devices comprises the step of launching the at least one or more aerially distributable communication devices or nodes from an aircraft with the at least one or more set of blades aligned substantially in a horizontal plane.

In one embodiment, the step of deploying the at least one or more aerially distributable communication devices comprises the step of wirelessly controlling the control surfaces of at least one of the aerially distributable communication nodes to thereby guide the aerially distributable communication node to a preferred area.

In addition, albeit not claimed, a heat shield is provided, which is configured for shielding an aerially distributable communications device as described after being deployed from a spacecraft, and during re-entry into the atmosphere.

To those skilled in the art to which the invention relates, many changes in construction and widely differing embodiments and applications of the invention will suggest themselves without departing from the scope of the invention as defined in the appended claims. The disclosures and the descriptions herein are purely illustrative and are not intended to be in any sense limiting.

Other aspects of the invention are also disclosed.

Notwithstanding any other forms which may fall within the scope of the present invention, preferred embodiments of the invention will now be described, by way of example only, with reference to the accompanying drawings in which:.

It should be noted in the following description that like or the same reference numerals in different embodiments denote the same or similar features.

An aerially distributable communications device according to a first aspect of the invention is generally indicated by the numeral <NUM>. A communications network according to a second aspect of the invention is generally indicated by the numeral <NUM>.

In <FIG>, <FIG>, <FIG> and <FIG>, airflow is shown by broken arrows.

Now described with reference to the figures, there is provided an aerially distributable communications device <NUM>. The aerially distributable communications device <NUM> includes a gyrochute <NUM> and a communications module <NUM>.

The gyrochute <NUM> includes a body <NUM> and one or more sets of blades. The body <NUM> can include a hub <NUM>, and may include a hollow formation surrounding the set of blades. The hollow formation acts as a vertical stabiliser and acts to reduce wingtip vortices, thereby increasing the lift generating efficiency of the blades.

The aerially distributable communications device <NUM> is configured for deployment from an aircraft (not shown) as will be described in more detail below. In order to facilitate such deployment, the gyrochute <NUM> is configured for providing lift force in order to slow the rate of fall of the aerially distributable communications device <NUM>. In order to generate lift force, the gyrochute <NUM> is configured for inducing autorotation of the gyrochute <NUM> as it falls during deployment, as will be described in more detail below. The autorotation of the gyrochute could be clockwise or counterclockwise according to design preference.

As shown in <FIG>, the gyrochute includes a single set of three blades <NUM> connected to each other at a central hub <NUM>. The gyrochute also includes an open-ended hollow formation in the form of a cylindrical formation <NUM> extending around the outer periphery of the blades <NUM>. Each of the blades <NUM> are rigidly connected to the cylindrical formation <NUM> at their outer periphery.

The cylindrical formation <NUM> is configured for guiding airflow through the centre of the cylindrical formation as a main column of airflow (shown as arrow A in <FIG>, <FIG>, <FIG> and <FIG>). The cylindrical formation <NUM> includes a cylindrical wall <NUM> that defines an inner surface <NUM> and an outer surface <NUM>. The blades <NUM> are connected to the inner surface <NUM> of the cylindrical wall <NUM> at a point about midway between the open ends of the cylindrical formation <NUM>. In alternative embodiments, the blades <NUM> may be connected at any point along the length of the inner surface.

The blades <NUM> each include an autorotation portion <NUM> in the form of an aerofoil portion <NUM> and a preferably planar extended trailing edge <NUM>. Preferably the extended trailing edge <NUM> extends in parallel with the general plane of the gyrochute <NUM>, and also in parallel with the upper edge of the cylindrical formation <NUM>. Preferably the extended trailing edge extends perpendicularly to the vertical column of air A when the aerially distributable communications device <NUM> is in stable flight. In this way, the extended trailing edge provides the greatest resistance to the flow of the vertical column of air A.

Preferably, the pitch of the aerofoil portion (when the aerially distributable communications device <NUM> is being deployed in stable flight/equilibrium in use) extends downwardly below the horizontal, while the extended trailing edge <NUM> extends substantially horizontally.

The intended functionality of the extended trailing edge <NUM> is to provide a drag force (shown as arrow D in <FIG>) in a vertical direction on the main column of air passing through the cylindrical formation.

The intended functionality of the autorotation portion in the form of aerofoil portion <NUM> is to generate lift force (shown as arrow L in <FIG>) from air passing over the aerofoil portion. This lift And to induce an autorotation effect in the gyrochute <NUM> during deployment when it is falling through the air. The lift force L has an azimuthal rotational component Lh that extends horizontally to induce autorotation of the gyrochute. The lift force L also has a vertical component LV that increases further serves to reduce the rate of fall of the aerially distributable communications device <NUM> during deployment. Preferably the pitch of the aerofoil portion <NUM> is between <NUM>° and <NUM>° in use when the aerially distributable communications device is generally aligned in a horizontal plane and falling in stable flight or equilibrium. Each aerofoil portion of the blade preferably has a pitch distribution that varies over its length depending on its radius from the hub in order to optimise the effect of the aerofoil portion. As air travelling over the aerofoil portion <NUM> will be foster towards the outer extents of the, the relative wind angle will be more horizontally inclined, and the pitch of the aerofoil portion is not required to be as downwardly inclined.

It is envisaged that initially once the aerially distributable communications device <NUM> is deployed, for example from an aeroplane, the total incident air velocity will start off being directly vertically upwardly. In this state, it is envisaged that the aerofoil portion <NUM> will generating relatively small amounts of vertical lift Lv while it is in a state of stall. However vertical airflow A moving over the aerofoil portion <NUM> will generate lift L. The horizontal or azimuthal rotational component Lh of the lift L will cause an increased angular velocity of autorotation. As autorotation speeds up, the relative direction of the airflow moves from being directly vertically to being more angled, as shown by arrow B in <FIG>. This angled airflow is more conducive to the generation of lift L by the aerofoil portion <NUM>, causing it to generate increased azimuthal rotational component Lh , causing increased autorotation, and also increased vertical lift Lv, serving to slow fall of the gyrochute. Eventually, the lift forces L, Lh, Lv will be balanced by the increase drag forces from the increased airflow, and the system will reach equilibrium or stable flight.

In alternative embodiments (not shown), it is envisaged that the blades could be pivotably connected to the cylindrical formation and/or hub, so as to be able to vary the pitch of the blades. It is further envisaged that controllable motors may be provided to allow the pitch of the blades to be controlled remotely. Such motors could be located in the hub, or built into the cylindrical formation. The blades could be pivotable on an axle extending into the hub/cylindrical formation.

It is envisaged that the blades <NUM>, hub <NUM> and cylindrical formation <NUM> will preferably be integrally formed, for example by a moulding process such as injection moulding, blow moulding, rotary moulding, or the like. In this regard, it is also envisaged that the gyrochute <NUM> will preferably be composed of lightweight material (such as plastic, a resin fibre composite such as carbon fibre, glass fibre or the like) so that the lift generated by the gyrochute <NUM> will have a greater effect in slowing down the fall of the aerially distributable communications device <NUM> during deployment. Preferably, the materials chosen for construction of the gyrochute will be less dense than water, allowing the aerially distributable communications device to float if it happens to land in water. Alternatively and/or additionally, it is envisaged that any portion of the gyrochute could include a sealed hollow portion enabling the aerially distributable communications device to float in water. It is further envisaged that in an alternative embodiment (not shown) the aerially distributable communications device could include an inflatable bladder and a compressed gas source that causes the inflatable bladder to be inflated if it is detected that the aerially distributable communications device has landed in water. Such detection on actuation can be provided by the controller and/or sensors as discussed in further detail below.

It is the intention that the aerially distributable communications devices <NUM> will be deployed in mass, and once deployed (for example in the case of a natural disaster) they will be picked up by locals and preferably kept by them. In this way, it is expected that there will be taken to areas of highest concentration of population density, and the communication functionality provided by the aerially distributable communications devices <NUM> will in this way be increased. For this reason, it is preferable that the aerially distributable communications devices <NUM> be manufactured as cheaply as and conveniently as possible.

In the embodiments shown in <FIG> and <FIG>the gyrochute <NUM> further includes an annular flange <NUM> or lip extending outwardly from an upper edge of the cylindrical formation <NUM>. The annular flange <NUM> includes a curved upper surface <NUM>, and a curved lower surface <NUM>. The upper surface <NUM> and the lower surface <NUM> meet at an outer edge <NUM>. The curved upper surface <NUM> curves downwardly towards the blades from the outer edge <NUM> to meet with the inner surface <NUM> of the cylindrical formation <NUM> at inner edge <NUM>. The curved lower surface <NUM> similarly extends downwardly from the outer edge <NUM> to engage tangentially with the outer surface <NUM> of the cylindrical formation <NUM>.

In an alternative embodiment, the upper surface and/or lower surface need not be curved, and can be planar or flat in configuration, however this is not preferred as the applicant believes that this will not generate the same amount of stabilising effect as will be described in more detail below. In another embodiment (not shown), the annular flange can be pivotably attached to the cylindrical formation to be stowed out of the way for storage and/or transport. It is further envisaged that any aspect of the body and/or blades can be modifiable to be foldable/removable/reconfigurable to allow for reduced space requirements during transport and/or storage.

The curved upper surface of the annular flange <NUM> is configured for inducing the main column of airflow within the cylindrical formation to flow radially outwardly over the aerofoil shape of the radial cross-section of the curved upper surface in use during deployment of the aerially distributable communications device <NUM> from an aircraft. This helps to generate additional lift force and slow down the rate of descent of the aerially distributable communications device <NUM>.

Similarly, airflow over the outer surface <NUM> of the cylindrical formation <NUM> will continue upwardly and outwardly along the lower surface of the <NUM>. This has an effect on the stability of the aerially distributable communications device <NUM> during aerial deployment as will be described in more detail below.

It is envisaged that during deployment, while the aerially distributable communications device <NUM> is falling from an aircraft, it may be subject to buffeting forces, or could be incorrectly deployed. For this reason, the gyrochute <NUM> is preferably configured to self-stabilise. Such self-stabilisation is explained below with reference to <FIG>.

Airflow A in the main column passing through the cylindrical formation (shown as arrow A in <FIG>, <FIG>, <FIG> and <FIG>) nearby the inner surface <NUM> of the cylindrical formation <NUM> is drawn outwardly over the upper surface <NUM>, generating lift force. When the cylindrical formation <NUM> and annular flange <NUM> is aligned horizontally, lift force is generated equally around the periphery of the cylindrical formation.

However, when the cylindrical formation <NUM> and annular flange <NUM> are not aligned with the horizontal (as shown in <FIG> and <FIG>), and are instead aligned at an angle α to the horizontal, airflow shown as arrow C over the lowest portion of the upper curved surface <NUM> will generate an increased amount of lift force relative to the airflow C flowing over the highest portion of the upper curved surface <NUM>. This is shown in <FIG>, where L<NUM> is the lift force generated by the lowest portion, L<NUM> is the lift force generated by the highest portion, and L<NUM>>L<NUM>. The difference between L<NUM> and L<NUM> serves to slow the fall of the lowest portion more than the fall of the highest portion, causing the lowest portion to rise relative to the highest portion, and eventually stabilising both the highest and lowest portions of the annular flange <NUM> at equal heights.

Further, airflow (shown as arrow D) travelling over the outer surface <NUM> of the cylindrical formation <NUM> is deflected outwardly by the curved lower surface <NUM> of the annular flange <NUM>. As may be seen from <FIG> and <FIG>, the deflection of this airflow outwardly is more pronounced for the lowest portion of the curved lower surface <NUM> than the highest portion. This will mean that the airflow D over the lowest portion of the curved lower surface <NUM> will generate a greater upward force on the lower portion of the curved lower surface than on the highest portion. This generates a finite moment that corrects the angle of tilt to an equilibrium position, when the forces on opposing sides are balanced.

In another embodiment shown in <FIG> the gyrochute <NUM> is provided with two sets of blades. A first set of blades are three autorotation inducing blades <NUM>, and the second set of blades are a set of three lift force inducing blades <NUM>. The first set of three autorotation inducing blades <NUM> are rigidly connected to a central hub <NUM>, and to a cylindrical formation <NUM> at their outer periphery, similarly to the previous embodiment shown in <FIG>. However, in the embodiment shown in <FIG>, the autorotation inducing blades <NUM> present a steep downward pitch when the gyrochute is in equilibrium during deployment relative to the pitch presented by the set of three lift force inducing blades <NUM>. The autorotation inducing blades <NUM> present the relatively steeper downward pitch with a view to primarily generating autorotation forces La (shown in <FIG>) over their aerofoil shape to cause autorotation of the gyrochute <NUM> during deployment. This autorotation force La has a larger azimuthal rotational component Lh force component, relative to vertical lift component Lv causing the blades <NUM> (and hence the gyrochute) to accelerate quicker horizontally in a rotational motion, in order to induce autorotation faster. In a preferred embodiment, the autorotation inducing blades <NUM> are configured to present a variation in their pitch of between <NUM>° to <NUM>° downwardly from the horizontal. The variation in the pitch of the autorotation inducing blades preferably varies over their length or radius from the hub.

The gyrochute <NUM> further includes a second set of three lift force inducing blades <NUM> that are preferably rigidly coupled to each other to extend radially from the hub <NUM>. The lift force inducing blades <NUM> are rigidly connected to the hub <NUM> and to the cylindrical formation <NUM>. The lift force inducing blades <NUM> have an axis of rotation preferably concentric with the centre or axis of the cylindrical formation <NUM>. The lift force inducing blades <NUM> present a pitch that varies over their radius from the hub of between <NUM>° to <NUM>° downwardly from the horizontal in use when the aerially distributable communications device <NUM> is being deployed and is in equilibrium. Airflow incident on the lift force inducing blades (shown in <FIG> as arrow I) will have both a vertical component Iv related to the downward velocity of the gyrochute <NUM>, as well as a horizontal component Ih related to the angular velocity of the autorotation. The faster the angular velocity of the autorotation, the more horizontal the incident angle of airflow I.

The lift force inducing blades <NUM>, the autorotation inducing blades <NUM> and the cylindrical formation <NUM> are all preferably concentric, extending radially from the hub. The lift force inducing blades <NUM> present with a more horizontal pitch than the autorotation inducing blades <NUM>, so that incident airflow during autorotation will pass over the lift force inducing blades <NUM> creating a lift force LL acting mainly vertically upwards, helping to slow the fall of the aerially distributable communications device <NUM> during deployment. The autorotation inducing blades <NUM> will deflect airflow passing over them to become incident airflow for the lift force inducing blades <NUM>.

In another embodiment shown in <FIG>, it is envisaged that the aerially distributable communications device <NUM> can be provided with preferably lightweight leg structures <NUM>. The leg structures <NUM> shown in <FIG> are curved elongate members <NUM> composed of resilient material such as spring steel, plastic, resin fibre material, or the like. The leg structures <NUM> preferably extend outwardly from the cylindrical formation.

The leg structures <NUM> can serve several functions in that they serve to cushion the impact of the aerially distributable communications device <NUM> on landing, provide ground clearance of the communications module <NUM> to allow for increased communication range, and can extend outwardly of the cylindrical formation <NUM> (without unduly interfering with the airflow during deployment) to increase the area coverage when viewed from the top, and help to ensure that the aerially distributable communications node <NUM> only lands the right way up. It is envisaged that such landing or leg structures can be provided in a wide variety of configurations and/or shapes that will be apparent to person skilled in the art.

In another embodiment shown in <FIG>, the aerially distributable communications device <NUM> further includes a power generation arrangements in the form of solar panels <NUM>. The solar panels <NUM> shown as being distributed over the upper surface of blades <NUM>, however it is envisaged that the solar panels could also be distributed over the upper surface <NUM> of the annular flange <NUM>.

The solar panels <NUM> are preferably configured for charging a power storage device such as a battery or capacitors. In turn, the power storage device will be used to power operation of the communications module <NUM> as will be described in more detail below.

In the embodiment shown in <FIG>, the communications module <NUM> is further provided with an externally extending antenna <NUM> for increasing the communication range of the communications module. It is further envisaged that an external antenna can be built or moulded into the cylindrical formation <NUM> and/or the blades.

As shown in <FIG>, in a further embodiment it is envisaged that autorotation inducing blades <NUM> and/or lift force inducing blades <NUM> can be pivotably movable about their longitudinal axis to thereby change their pitch. Preferably, each of the autorotation inducing blades <NUM> and the lift force inducing blades <NUM> are rotatable about a central axle <NUM>, <NUM> respectively, with their pitches being variable between <NUM> and <NUM> from the horizontal. Electrical control motors <NUM> and <NUM> are provided for pivoting the autorotation inducing blades <NUM> and/or the lift force inducing blades <NUM>, respectively. Such electrical control motors <NUM> and <NUM> can be controlled by a controller <NUM>, which is preferably controlled remotely from a remote controller by wireless radio frequency control. Alternately, the controller can be preprogramed before deployment to control the autorotation inducing blades <NUM> and/or lift force inducing blades <NUM> to steer movement of the aerially distributable communications device <NUM> to a predetermined destination or zone.

It is further envisaged that additional control surfaces, such as a tail or any other suitable configuration aerofoil or formation can be provided, for steering of the aerially distributable communications device <NUM> during deployment to guide it to a preferred landing area. In another alternative embodiment (not shown) it is envisaged that at least part of the annular flange, or portions thereof may be rotatable about the upper edge of the cylindrical formation, to thereby act as control surfaces for the guidance of the aerially distributable communications device. Such steering portions may similarly be controlled by electric motors by the controller or remotely.

In alternative embodiments (not shown), the external antenna can also be spring released for example as a sprung telescopic arrangement, electrically driven by electrically motors between a deployed and a retracted position, or launched into the air via balloon, preferably using the same compressed gas cannister that would be used for inflation of the inflatable bladder described above.

It is further envisaged that the power storage device can be used to power external devices such as phones via a charging port (not shown).

In alternative embodiments (not shown), it is envisaged that the gyrochute can have any number of blades or blade sets, as long as the blades are configured to, whether in combination and/or individually, generate autorotation and lift force and/or drag force during deployment of the aerially distributable communications device <NUM>. For example, in an alternative embodiment (not shown) it is envisaged that two pairs of counter rotating pivoting blades may be provided for producing lift force, as well as a further fixed set of blades for autorotation. It is further envisaged that a pair of counter rotating blade sets may be provided that rotate relative to a central hub which does not rotate. It is envisaged that this may allow for sensitive electronics that will be affected by acceleration to be provided on the hub.

It is envisaged that aerially distributable communications devices can be provided in substantial sizes, ranging from <NUM> to <NUM> in diameter, allowing for additional componentry to be added. For example, in a further embodiment (not shown), it is envisaged that a dehumidifier apparatus and/or water purification device may be provided in the central hub, or slung underneath the gyrochute <NUM>. The dehumidifier apparatus may be powered by the battery and serve to generate clean water from the atmosphere. Water generated by the dehumidifier apparatus can be distributed continuously from an outlet into a storage tank provided.

As aerially distributable communications devices <NUM> of larger diameter may be hazardous to people on the ground during deployment, it is further envisaged that a visual and/or audial alert device will be provided to alert people on the ground that one is approaching. An example of a visual alert may be a flashing light or lights, or mirrors located on the cylindrical formation. An example of an audial alert may be a speaker, buzzer, or alternatively a whistle that is actuated by airflow.

Another embodiment is shown in <FIG> and <FIG>. In this embodiment, the cylindrical formation does not include an annular flange, and instead only presents a hollow formation in the form of a cylindrical wall. The blades are the same as the blades shown in <FIG>, and are fixed to the cylindrical formation and the hub.

<FIG> show an embodiment of an aerially distributable communications device <NUM> that includes foldable blades <NUM>. The profile of the blades <NUM> are similar to the blades shown in <FIG>, however a pivoting mechanism is provided in the form of hinge <NUM> including pivot pin <NUM>. The blades <NUM> are movable between a folded position and deployed position. In another embodiment (not shown) the pivoting mechanism may be spring loaded, including an over centre spring mechanism to hold the blade in either its folded position or deployed position, once it has been manually moved into either of the positions.

A supporting flange <NUM> extends from the hub <NUM> to support the foldable blade <NUM> when it is in the deployed position, in order to prevent it from pivoting further upwardly, for example by forces applied to the blade <NUM> by airflow when it is in flight. The pivot pin <NUM> of the hinge <NUM> is slidably movable in slot <NUM> in the blade <NUM>. By sliding the pivot pin <NUM> through slot <NUM> when the blade <NUM> is in its folded position, the height of the aerially distributable communications device <NUM> can be reduced during transport and/or storage. In order to deploy the aerially distributable communications device <NUM>, the pivot pin will be moved to the top of the slot, and the blade <NUM> folded over into a horizontal position. The blade <NUM> will then be inserted into the receiving slot <NUM> in the hub <NUM>. The blade <NUM> includes a snap fit connecting formation <NUM>. As the pointed end of blade <NUM> is inserted into receiving slot <NUM>, the snap fit connecting formation <NUM> engages securely with complementary snap fit connecting formation (not shown) within receiving slot <NUM>. It will be appreciated by those skilled in the art that a large variety of other connecting arrangements could be used in alternative embodiments (not shown) for connecting of the blade to the hub. For example, alternative connecting arrangements could include spigot and socket type arrangements utilising friction or interference fit to secure the blade to the hub, bayonet type connecting arrangements, locking pin type arrangements, for example including a spring loaded locking pin is receivable into a recess; and a wide variety of other connecting arrangements.

<FIG> shows the aerially distributable communications device <NUM> with the blades <NUM> inserted into receiving slots <NUM> in their deployed position. <FIG> shows the blades <NUM> in their folded position, with the pivot pin <NUM> at the top of slot <NUM>.

It is further envisaged that in another embodiment (not shown) a spring loaded locking pin can be provided that may be receivable into a recess associated with the hub <NUM> in order to lock the foldable blade <NUM> in its deployed position, and to prevent it from folding back to its folded position.

In the embodiment shown in <FIG>, the hollow formation is segmented into separate fins <NUM> located at the end of each of the blades <NUM>. The fins <NUM> of this embodiment are shown as being planar, however in alternative embodiments as will be described below, the fins can be aerofoil shaped in order to streamline the movement of the blades <NUM> through the air.

Another embodiment is shown in <FIG>, wherein the hollow formation is segmented into separate fins <NUM>, however the fins <NUM> in this instance include an outwardly extending segmented flange <NUM> at an upper edge, the segmented flanges <NUM> of all of the blades <NUM> making up a segmented annular flange as described above.

In the embodiment shown in <FIG>, an upwardly extending antenna <NUM> is shown extending from the hub <NUM>.

Another embodiment of an aerially distributable communications device <NUM> is shown in <FIG>. In this embodiment, the plurality of gyrochutes <NUM> are provided. The gyrochutes are connected together by a frame <NUM>. The frame includes supporting formations <NUM> on which a large payload may be supported. In the embodiment shown in <FIG>, the support information is in the form of a large carabiner type clip, however it will be appreciated by person skilled in the art that a wide variety of supporting formations <NUM> may be used. In this embodiment, it is envisaged that the blades <NUM> will be freely rotating about hubs <NUM>.

As discussed above, another embodiment of a blade <NUM> is shown in <FIG>. In this embodiment, the fin <NUM> is shown as aerofoil shaped in cross-section. In this embodiment, the aerofoil is streamlined in the vertical direction. A close up of the fin <NUM> shown in <FIG> is shown in <FIG>, illustrating the streamlining in the vertical direction.

Another embodiment of a fin <NUM> is shown in <FIG>, showing the aerofoil shape being streamlined for movement in the horizontal or rotational direction.

It is further envisaged that the fins <NUM> may be removably connectable to the blades <NUM>, for example by means of a snap fit type connection. It will be appreciated by person skilled in the art that a wide variety of connecting arrangements could be used to connect a fin to a blade.

Now described with reference to <FIG>, a communications module <NUM> is provided. The communications module <NUM> is preferably located in the hub <NUM>, however it is also envisaged that it could be slung underneath and/or above the gyrochute <NUM>. The communications module <NUM> includes a computer processing unit (CPU) or processor <NUM> and digital storage memory <NUM> configured for storing data and/or software instructions. It is envisaged that the communications module <NUM> may be provided as a system on a chip (SOC), or could be provided on any combination of circuitry boards <NUM>. Such secondary boards may be provided with secondary support componentry (not shown) such as read-only memory (ROM), random access memory (RAM), and other known requirements for the circuitry to operate.

In a preferred embodiment, the processor <NUM> and digital storage memory <NUM> can also be configured for and function as the controller <NUM> for the gyrochute <NUM>. In an alternative embodiment, it is envisaged that a separate controller <NUM> may be provided.

Further, software stored on the digital storage memory <NUM> preferably includes software modules for controlling operation of the communications module <NUM>, which may access stored software libraries such as. dll libraries for use by the various software modules.

The communications module <NUM> further includes preferably a plurality of transceivers in the form of communications chips and associated antennas as will be described below. The communications chips and their associated antennas are preferably configured for both low-power/low range wireless communications, as well as relatively higher power/longer range wireless communications.

In the embodiment shown in <FIG>, the communications module <NUM> includes a Bluetooth™ enabled chip <NUM> and associated Bluetooth™ antenna <NUM> for low-power, low range communication with other similar communications modules <NUM>, as well as for communication with communication devices of users on the ground after it is deployed.

In addition, the communications module <NUM> includes a near field communication (NFC) read/write chip <NUM> and associated NFC antenna <NUM>. It is envisaged that the NFC read chip <NUM> and associated NFC antenna <NUM> will also be used for close range, low power communication with mobile phones of users on the ground.

Further, the communications module <NUM> includes a Wi-Fi/WiMax enabled chip <NUM> and associated Wi-Fi/WiMax antenna <NUM> for medium to longer range communications, at relatively higher power.

Lastly, it is envisaged that the communications module <NUM> can include very long range (and generally higher power) communications chips for communication over longer ranges using protocols such as satellite communications protocols, or cellular communications protocols such as <NUM>, <NUM>, LTE, <NUM>, or the like. In this regard, the communications module <NUM> shown in <FIG> includes a satellite communications chip <NUM> and associated antenna <NUM>, enabling it to communicate directly with satellites <NUM> using known protocols. In addition, the communications module <NUM> includes a cellular communications chip <NUM> and associated cellular communications antenna <NUM> for communication with, for example, cellular communication towers <NUM> that may still be in operation.

It will be appreciated that many alternative protocols may be possible which can offer a wide variety of communication types, ranging from text only (in order to conserve power usage), SMS and MMS, to voice over IP (VOIP), sending of pictures or photos, to video calls (although this is not preferred as it is power hungry).

It is envisaged that most aerially distributable communications devices <NUM> will not be provided with a satellite communications chip <NUM> and associated antenna <NUM>. However, it is envisaged that a large number of aerially distributable communications devices <NUM> may be provided, which will set up a communication network <NUM> as will be described in more detail below.

A relatively small proportion of the aerially distributable communications devices <NUM> will preferably be configured as a gateway communications device <NUM> operable as a gateway node in the communications network <NUM>, enabling long-range communications from users phones via the communications network to a distant antenna and/or satellite. It is envisaged that an aerially distributable communications device <NUM> having the functionality to operate as a gateway communications device will also be provided with increased power storage and charging abilities, as such long-range communications are expected to require increased power usage.

In an alternative embodiment, it is envisaged that a dedicated gateway node, such as a preferably generator powered gateway communication device <NUM>, preferably with its own mast antenna, may be set up for communication with the communication network <NUM> utilising a plurality of aerially distributable communications devices <NUM> as nodes of the communication network <NUM>.

The communications module <NUM> further includes a power source in the form of a battery <NUM>. The battery <NUM> is preferably configured to be charged by the solar panel and/or generator <NUM> via battery charger <NUM>.

The communications module <NUM> further includes a clock device <NUM> on which time can be set and measured. The clock device is used for time stamping any communications moving through the communications module <NUM>.

The communications module <NUM> further includes a GPS chip <NUM> and associated GPS antenna <NUM>. It is envisaged that the processor <NUM> may be configured by software stored on the digital storage media <NUM> to act as a geo-positioning device, using signals received from geo-positioning satellites to determine the location of the aerially distributable communications device <NUM>.

The communications module <NUM> further includes an input/output interface <NUM>, to which external devices can be connected. Examples of such external devices include output devices such as visual indicator than the form of LED lights <NUM>, audio indicators in the form of a speaker or buzzer <NUM>, and input devices such as a pushbutton <NUM> and/or touchscreen <NUM>.

Also connected via the input/output interface <NUM> may be an array of sensors. The sensors can include vibration sensors <NUM>, one or more accelerometers <NUM>, pressure sensors <NUM>, humidity sensors <NUM>, temperature sensors <NUM>, (preferably ambient) light sensors <NUM>, an altimeter <NUM>, wind speed sensors <NUM> and an array of gas sensors <NUM>, such as a carbon dioxide sensor, oxygen sensor, nitrogen sensor, and methane sensor.

Also envisaged but not shown are sound sensors; proximity sensors; gyroscopes; infrared sensors; ultrasonic sensors; smoke sensors; alcohol sensors; touch sensors; colour sensor; tilt sensor; flow sensors; level sensors; or the like.

The sensors need not be physically connected to the aerially distributable communications devices <NUM>, and may be configured to be distributed by the aerially distributable communications devices <NUM> on deployment. The sensors could be launched from the aerially distributable communications device <NUM> at a set height detected by an altimeter, or on landing. The sensors could be launched away from the aerially distributable communications device <NUM> by being spring loaded, or by using the rotating action of the aerially distributable communications device <NUM> during deployment to generate centripetal forces to push the sensors away. In this regard it is envisaged that the sensors may be attached to the annular flange, or to an external surface of the cylindrical formation.

It is envisaged that the sensors will be able to provide feedback to the outside world of conditions on the ground in the area. In addition, the sensors can be used by the processor <NUM> in order to perform a wide variety of useful functions such as, for example, initiating the production of clean water using the dehumidifier and/or water purification device, or monitoring weather and/or geological events using the wide array of sensors.

In addition, it is envisaged that the aerially distributable communications device <NUM> can include an ultrasound emitter (not shown) to attract or repel creatures. Further, the aerially distributable communications device <NUM> can be provided with ultrasonic vibrators to remove dust and dirt from solar panels or to otherwise keep its componentry clean. It is further envisaged that a secondary active or passive deceleration device (not shown) may be provided, such as a small rocket or jet engine or parachute, for facilitating the soft landing of the aerially distributable communications device <NUM>.

It is envisaged that, on establishing that there is a requirement for communications to be set up in an area where communications is not currently available, a plurality of aerially distributable communications devices <NUM> will be loaded on board an aircraft (not shown). The aircraft will then be flown over the affected region, and the aerially distributable communications devices <NUM> will be deployed from the aircraft. It is envisaged that, depending on the size of the aerially distributable communications devices <NUM>, may be deployed from the aircraft in a spinning horizontally aligned condition, in order to facilitate autorotation, and in order to facilitate stability of the aerially distributable communications device <NUM> in flight.

Alternatively, it is envisaged that the aerially distributable communications devices <NUM> can be deployed from a much higher level craft such as a spacecraft or satellite (not shown). In order to facilitate the deployment from high altitudes, is envisaged that the aerially distributable communications devices can include a heat shield <NUM> to shield it from heat generated from friction during re-entry into an atmosphere. The heat shield <NUM> is preferably covered at least on its downward facing surfaces <NUM> (in use) with heat resistant materials, such as ceramic tiles, or the like. Once the speed of re-entry has sufficiently slowed from the increased density of the atmosphere, the heat shield may be released, allowing the gyrochute <NUM> to slow the descent.

In the embodiment shown in <FIG> and <FIG>, the heat shield comprises an upper portion <NUM> and a lower portion <NUM> that together preferably enclose the gyrochute <NUM> and communications module <NUM>. It is envisaged that the upper portion <NUM> will be separable from the lower portion <NUM>, and preferably will fall away after insulating the gyrochute <NUM> and communications module <NUM> during re-entry. In order to separate the upper portion <NUM> and lower portion <NUM>, it is envisaged that they may be held together preferably internally by a fastening arrangement, for example by a threaded fastener or similar, and an electrical motor (not shown) may be used to turn the threaded fastener to decouple the upper portion <NUM> from the lower portion <NUM>. The electrical motor used to decouple the portions of the heat shield may be actuated by the processor <NUM> acting as a controller, or may be provided with its own controller, which may in turn be guided by instructions for receiving information from sensors. This information received from the sensors may be indicative of the correct altitude and/or speed and/or acceleration and/or windspeed at which the heat shield <NUM> is to be dispensed with.

In an alternative embodiment (not shown) the fastening arrangement may be provided externally. However this is not preferred as the heat of re-entry may affect the operation of the fastening arrangement.

In an alternative embodiment (not shown), any number of portions or pieces may be used to enclose the gyrochute and communications module. The portions need not necessarily be upper or lower portions, and could be a plurality of side portions that enclose the gyrochute and communications module from the side, as shown in <FIG>. However a dedicated lower portion is preferred as this allows for the thermal integrity of the underside to be maintained.

Alternatively, it is and /or additionally, it is envisaged that a wide variety of mechanisms could be used to separate the heat shield portions from each other to cause them to fall away from the gyrochute and communications module. For example, a small explosive device could be used to decouple the portions of the heat shield. However this is not preferred as it may cause damage to the communications module.

In the embodiment shown in <FIG>, the heat shield includes a pair of side portions <NUM> that are engageable with each other at a labyrinth seal <NUM> extending around the engaging outer periphery of the side portions. The fastening arrangement includes a locking pin <NUM> receivable within apertures (not shown) through the labyrinth seals. The locking pin is preferably connected to an electrical motor that is actuated by the controller to remove the locking pin. The lower surface of the heat shield is configured with aerodynamic formations <NUM> configured for inducing autorotation. Once the correct altitude has been reached, it is envisaged that the controller will actuate a solenoid (not shown) to remove the locking pin from the apertures, and the centrifugal forces generated by autorotation will cause the side portions to move apart from each other and be flung outwardly and away from the gyrochute.

In the embodiment shown in <FIG>, the heat shield is configured with aerodynamic formations <NUM> in the form of ridges on its lower surface in the extending from the centre transverse to the radial direction on the underside of the lower portion of the heat shield, in order to induce autorotation. Once autorotation has been established, then on being decoupled, the gyroscopic forces caused by the autorotation of the heat shield would urge the portions of the heat shield outwardly and away from the gyrochute and communications module. In addition, the gyrochute would already be spinning once the heat shield is released, and would be generating better lift forces than if it was starting from a non-rotating condition.

It is further envisaged that a fastener holding the plurality of portions of the heat shield together can be a frangible fastener (not shown) that is designed to break if autorotation has been induced and the gyroscopic forces are strong enough to reach a predetermined threshold limit.

The aerially distributable communications devices <NUM> can be guided to move towards a predetermined area or zone, either by controlling the control surfaces of the gyrochute <NUM> to steer the aerially distributable communications device <NUM>, or by having the aerially distributable communications device <NUM> steer itself using the controller, towards areas or zones that have been pre-input for each aerially distributable communications device <NUM>. It is envisaged that where the controller is used to steer the aerially distributable communications device <NUM>, the GPS chip can be used to provide geolocation data to determine the correct landing site.

Alternatively, sufficient numbers of aerially distributable communications devices <NUM> can be deployed to ensure density of coverage over a predetermined area, without guiding of the aerially distributable communications device <NUM> to a predetermined or designated area. Since it is envisaged that the aerially distributable communications devices <NUM> will be recovered by people on the ground, and taken to areas of higher density population, this method is preferred.

On landing at the designated area or zone, the generator <NUM> can be coupled to the rotating blade set <NUM>, either by controlling of the coupling remotely via the controller, or by automatic actuation by impact on landing.

As the aerially distributable communications device <NUM> approaches the landing zone, it is envisaged that the controller can cause audible and visual alert signals to be issued. Alternatively, the whistle that is actuated by airflow during the descent will make a noise, alerting people to the falling device <NUM>.

After deployment, the communications module <NUM> is configured for connecting with other similar aerially distributable communications devices <NUM> in a locally located communications network <NUM>, as well as to connect with a gateway communication device <NUM> that is preferably able to communicate to the outside world, thereby enabling important communications for management of, for example, natural disasters. The communications network <NUM> can have a network topology that may be a mesh topology network; a point-to-point network; a point to multipoint network; a star topology network; and any other suitable topology network.

It is envisaged that each aerially distributable communications device <NUM> will be able to cover an area of between <NUM><NUM> and <NUM>,<NUM>,<NUM><NUM>, depending on factors such as terrain, foliage and environmental conditions, as well as the radio technology being used.

As shown in <FIG> and <FIG>, it is further envisaged that a rotating blade set such as the pivoting lift inducing blade set <NUM> can be configured with extension portions <NUM> to be driven by wind once the aerially distributable communications device <NUM> has been deployed and has landed on the ground. The blade set <NUM> can be coupled to a generator <NUM> so that, as it is turned by the wind, it will generate electricity for recharging the battery. It is envisaged that the blade set <NUM> can be selectively coupled to the generator <NUM>, so that it is only coupled to the generator <NUM> on landing. It is envisaged that coupling can be actuated either remotely via the controller, or alternatively the impact of landing could be used to actuate coupling of the blade set to the generator.

Preferably the leg structures <NUM> will dampen the impact on landing where the impact is not required to actuate the coupling of the blade set to the generator. Further, the leg structures <NUM> will serve to elevate the communications module <NUM> for better coverage.

On landing, the communications modules <NUM> will set up communications with the communications modules <NUM> of nearby aerially distributed to indications devices <NUM>. The communication modules <NUM> will each become a node in a distributed mesh network. In this configuration, any information transmitted by one of the communication modules <NUM> will be received by adjacent communication modules and transmitted on through the communication network <NUM> until information is received by a gateway communication device <NUM> (shown in <FIG>). Each of the communications that are received and/or transmitted preferably time stamped. Further, each of the communications that are received and/or transmitted can be stored either persistently or temporarily on the digital storage media <NUM>, until the information is able to be transmitted. The gateway communication device <NUM> can be one or more of the aerially distributable communications devices <NUM>, or can be set up as a purpose-built gateway communication device, for example with a large mast antenna allowing for communication over wide area networks, and preferably including its own relatively high power sources such as a generator or mains power supply (if available). Such a purpose built gateway communications device may be ground, sea or air based.

Users on the ground with communications devices such as mobile phones will be able to connect to the transceivers of the communications module <NUM>, either through NFC, Bluetooth, or Wi-Fi, setting up a communications infrastructure for communicating information to the gateway device <NUM>. From the gateway communication device <NUM>, the information can be transmitted to and/or received from the outside world.

For the purposes of the present invention, additional terms are defined below. Furthermore, all definitions, as defined and used herein, should be understood to control over dictionary definitions, and/or ordinary meanings of the defined terms unless there is doubt as to the meaning of a particular term, in which case the common dictionary definition and/or common usage of the term will prevail.

As used herein, the singular articles "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise and thus are used herein to refer to one or to more than one (i.e. to "at least one") of the grammatical object of the article. By way of example, the phrase "an element" refers to one element or more than one element.

The term "about" is used herein to refer to quantities that vary by as much as <NUM>%, preferably by as much as <NUM>%, and more preferably by as much as <NUM>% to a reference quantity. The use of the word 'about' to qualify a number is merely an express indication that the number is not to be construed as a precise value.

Throughout this specification, unless the context requires otherwise, the words "comprise", "comprises" and "comprising" will be understood to imply the inclusion of a stated step or element or group of steps or elements but not the exclusion of any other step or element or group of steps or elements.

The term "real-time" for example "displaying real-time data," refers to the display of the data without intentional delay, given the processing limitations of the system and the time required to accurately measure the data.

As used herein, the term "exemplary" is used in the sense of providing examples, as opposed to indicating quality. That is, an "exemplary embodiment" is an embodiment provided as an example, as opposed to necessarily being an embodiment of exemplary quality for example serving as a desirable model or representing the best of its kind.

Thus, as a non-limiting example, a reference to "A and/or B", when used in conjunction with open-ended language such as "comprising" can refer, to A only (optionally including elements other than B); in another embodiment, to B only (optionally including elements other than A); in yet another embodiment, to both A and B (optionally including other elements); etc..

Only terms clearly indicated to the contrary, such as "only one of" or "exactly one of," or, when used in the claims, "consisting of" will refer to the inclusion of exactly one element of a number or list of elements.

Thus, as a non-limiting example, "at least one of A and B" (or, equivalently, "at least one of A or B," or, equivalently "at least one of A and/or B") can refer, to at least one, optionally including more than one, A, with no B present (and optionally including elements other than B); in another embodiment, to at least one, optionally including more than one, B, with no A present (and optionally including elements other than A); in yet another embodiment, to at least one, optionally including more than one, A, and at least one, optionally including more than one, B (and optionally including other elements); etc..

As described herein, 'a computer implemented method' should not necessarily be inferred as being performed by a single computing device such that the steps of the method may be performed by more than one cooperating computing devices.

Similarly objects as used herein such as 'web server', 'server', 'client computing device', 'computer readable medium' and the like should not necessarily be construed as being a single object, and may be implemented as a two or more objects in cooperation, such as, for example, a web server being construed as two or more web servers in a server farm cooperating to achieve a desired goal or a computer readable medium being distributed in a composite manner, such as program code being provided on a compact disk activatable by a license key downloadable from a computer network.

In the context of this document, the term "database" and its derivatives may be used to describe a single database, a set of databases, a system of databases or the like. The system of databases may comprise a set of databases wherein the set of databases may be stored on a single implementation or span across multiple implementations. The term "database" is also not limited to refer to a certain database format rather may refer to any database format. For example, database formats may include MySQL, MySQLi , XML or the like.

In addition, where features or aspects of the invention are described in terms of Markush groups, those skilled in the art will recognise that the invention is also thereby described in terms of any individual member or subgroup of members of the Markush group.

For the purpose of this specification, where method steps are described in sequence, the sequence does not necessarily mean that the steps are to be carried out in chronological order in that sequence, unless there is no other logical manner of interpreting the sequence.

The invention may be embodied using devices conforming to other network standards and for other applications, including, for example other WLAN standards and other wireless standards. Applications that can be accommodated include IEEE <NUM> wireless LANs and links, and wireless Ethernet.

In the context of this document, the term "wireless" and its derivatives may be used to describe circuits, devices, systems, methods, techniques, communications channels, etc., that may communicate data through the use of modulated electromagnetic radiation through a non-solid medium. In the context of this document, the term "wired" and its derivatives may be used to describe circuits, devices, systems, methods, techniques, communications channels, etc., that may communicate data through the use of modulated electromagnetic radiation through a solid medium. The term does not imply that the associated devices are coupled by electrically conductive wires.

Unless specifically stated otherwise, as apparent from the following discussions, it is appreciated that throughout the specification discussions utilizing terms such as "processing", "computing", "calculating", "determining", "analysing" or the like, refer to the action and/or processes of a computer or computing system, or similar electronic computing device, that manipulate and/or transform data represented as physical, such as electronic, quantities into other data similarly represented as physical quantities.

A "computer" or a "computing device" or a "computing machine" or a "computing platform" may include one or more processors.

The methodologies described herein are, The aerially distributable communications device as claimed in claim <NUM>, wherein performable by one or more processors that accept computer-readable (also called machine-readable) code containing a set of instructions that when executed by one or more of the processors carry out at least one of the methods described herein. Any processor capable of executing a set of instructions (sequential or otherwise) that specify actions to be taken are included. Thus, one example is a typical processing system that includes one or more processors. The processing system further may include a memory subsystem including main RAM and/or a static RAM, and/or ROM.

Furthermore, a computer-readable carrier medium may form, or be included in a computer program product. A computer program product can be stored on a computer usable carrier medium, the computer program product comprising a computer readable program means for causing a processor to perform a method as described herein.

In alternative embodiments, the one or more processors operate as a standalone device or may be connected, e.g., networked to other processor(s), in a networked deployment, the one or more processors may operate in the capacity of a server or a client machine in server-client network environment, or as a peer machine in a peer-to-peer or distributed network environment. The one or more processors may form a web appliance, a network router, switch or bridge, or any machine capable of executing a set of instructions (sequential or otherwise) that specify actions to be taken by that machine.

Note that while some diagram(s) only show(s) a single processor and a single memory that carries the computer-readable code, those in the art will understand that many of the components described above are included, but not explicitly shown or described in order not to obscure the inventive aspect. For example, while only a single machine is illustrated, the term "machine" shall also be taken to include any collection of machines that individually or jointly execute a set (or multiple sets) of instructions to perform any one or more of the methodologies discussed herein.

Thus, one embodiment of each of the methods described herein is in the form of a computer-readable carrier medium carrying a set of instructions, e.g., a computer program that are for execution on one or more processors. Thus, as will be appreciated by those skilled in the art, embodiments of the present invention may be embodied as a method, an apparatus such as a special purpose apparatus, an apparatus such as a data processing system, or a computer-readable carrier medium. The computer-readable carrier medium carries computer readable code including a set of instructions that when executed on one or more processors cause a processor or processors to implement a method. Accordingly, aspects of the present invention may take the form of a method, an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of carrier medium (e.g., a computer program product on a computer-readable storage medium) carrying computer-readable program code embodied in the medium.

The software may further be transmitted or received over a network via a network interface device. While the carrier medium is shown in an example embodiment to be a single medium, the term "carrier medium" should be taken to include a single medium or multiple media (e.g., a centralized or distributed database, and/or associated caches and servers) that store the one or more sets of instructions. The term "carrier medium" shall also be taken to include any medium that is capable of storing, encoding or carrying a set of instructions for execution by one or more of the processors and that cause the one or more processors to perform any one or more of the methodologies of the present invention. A carrier medium may take many forms, including but not limited to, non-volatile media, volatile media, and transmission media.

It will be understood that the steps of methods discussed are performed in one embodiment by an appropriate processor (or processors) of a processing (i.e., computer) system executing instructions (computer-readable code) stored in storage. It will also be understood that the invention is not limited to any particular implementation or programming technique and that the invention may be implemented using any appropriate techniques for implementing the functionality described herein. The invention is not limited to any particular programming language or operating system.

Furthermore, some of the embodiments are described herein as a method or combination of elements of a method that can be implemented by a processor of a processor device, computer system, or by other means of carrying out the function.

Similarly, it is to be noticed that the term connected, when used in the claims, should not be interpreted as being limitative to direct connections only. Thus, the scope of the expression a device A connected to a device B should not be limited to devices or systems wherein an output of device A is directly connected to an input of device B. It means that there exists a path between an output of A and an input of B which may be a path including other devices or means. "Connected" may mean that two or more elements are either in direct physical or electrical contact, or that two or more elements are not in direct contact with each other but yet still co-operate or interact with each other.

Similarly it should be appreciated that in the above description of example embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects. Thus, the claims following the Detailed Description of Specific Embodiments are hereby expressly incorporated into this Detailed Description of Specific Embodiments, with each claim standing on its own as a separate embodiment of this invention.

As used herein, unless otherwise specified the use of the ordinal adjectives "first", "second", "third", etc., to describe a common object, merely indicate that different instances of like objects are being referred to, and are not intended to imply that the objects so described must be in a given sequence, either temporally, spatially, in ranking, or in any other manner.

In describing the preferred embodiment of the invention illustrated in the drawings, specific terminology will be resorted to for the sake of clarity. However, the invention is not intended to be limited to the specific terms so selected, and it is to be understood that each specific term includes all technical equivalents which operate in a similar manner to accomplish a similar technical purpose. Terms such as "forward", "rearward", "radially", "peripherally", "upwardly", "downwardly", and the like are used as words of convenience to provide reference points and are not to be construed as limiting terms.

For the purposes of this specification, the term "plastic" shall be construed to mean a general term for a wide range of synthetic or semisynthetic polymerization products, and generally consisting of a hydrocarbon-based polymer.

For the purposes of this specification, any reference to the term "pitch" of an aerofoil in a gyrochute shall be construed to be the angle between the chord of an aerofoil and the horizontal when the gyrochute is in stable flight.

For the purpose of this specification, the term "horizontal" in reference to the direction of any features of the aerially distributable communications device shall be construed to refer to the direction relative to the aerially distributed communications device when it is in equilibrium and/or stable flight, unless otherwise specified, or the context makes it clear that this is not the case.

For the purposes of this specification, the term "gyrochute" shall be construed to include a gyrochute, rotary chute, unpowered autogyro and any other aircraft that includes unpowered blades that automatically generates lift force to slow their descent on falling through the air.

For the purposes of this specification, the term "aircraft" shall be construed to include but not be limited to an airplane, helicopter, balloon, spacecraft, satellite, missile, rocket or similar craft.

In the claims which follow and in the preceding description of the invention, except where the context requires otherwise due to express language or necessary implication, the word "comprise" or variations such as "comprises" or "comprising" are used in an inclusive sense, i.e. to specify the presence of the stated features but not to preclude the presence or addition of further features in various embodiments of the invention.

Any one of the terms: including or which includes or that includes as used herein is also an open term that also means including at least the elements/features that follow the term, but not excluding others.

Thus, while there has been described what are believed to be the preferred embodiments of the invention, those skilled in the art will recognize that other and further modifications may be made thereto without departing from the the scope of the invention, as defined by the appended claims.

For example, any formulas given above are merely representative of procedures that may be used. Functionality may be added to the block diagrams and operations may be interchanged among functional blocks. Steps may be added to methods described within the scope of the present invention.

Although the invention has been described with reference to specific examples, it will be appreciated by those skilled in the art that the invention may be embodied in many other forms.

Claim 1:
An aerially distributable communications device (<NUM>) for aerial deployment as a node of a communications network (<NUM>), the aerially distributed communications module including:
a. a gyrochute (<NUM>) including at least one or more set of blades, wherein the at least one or more set of blades includes an autorotation portion (<NUM>) that is configured for inducing autorotation of the gyrochute (<NUM>), and wherein the pitch of the autorotation portion (<NUM>) is configured with an angle of attack below the horizontal; and
b. a communications module (<NUM>) configured for wireless communication with external communication nodes,
wherein the blades (<NUM>) of the set of blades at least partly define an aerofoil shape (<NUM>) along their length, and the pitch of the aerofoil shape (<NUM>) is variable along the length of the blade (<NUM>).