WO2008037030A1

WO2008037030A1 - Aircraft banner release system

Info

Publication number: WO2008037030A1
Application number: PCT/AU2007/001453
Authority: WO
Inventors: John Andrew Cooper
Original assignee: Itsatruck Pty Ltd
Priority date: 2006-09-29
Filing date: 2007-09-28
Publication date: 2008-04-03
Also published as: AU2007302630A1

Abstract

An aircraft advertising display system includes an emergency drop arrangement, including a ballast release mechanism for releasing ballast which will actuate after the system has been released from an aircraft but prior to the deployment of a deceleration device. Releasing the ballast prior to deployment of the deceleration device will ensure a controlled descent of the system.

Description

Aircraft banner release system

Field of the invention

This invention relates to a banner release system of the type adapted to be deployed between an aircraft and advertising or display banner which hangs below the aircraft and which will permit the display banner and associated fittings and fixtures to be dropped by the aircraft in an emergency.

Background of the invention

Aircraft safety regulations require that an advertising banner connected to an aircraft must be able to be released from the aircraft in the event of an emergency or the like. Thus, the pilot or co-pilot will have some form of release actuator within the cockpit of the aircraft which when actuated will cause the banner, support lines, connection hooks and the like to be released from the aircraft to thereby enable the pilot of the aircraft to deal with the emergency without having to be concerned about the banner connected thereto.

In recent years, one form of advertising in this manner has been to attach a generally vertical banner support line to the underside of a helicopter which is then able to support a relatively large area banner which is attached to that support line. The support line will typically have a ballast filled container attached to the lower end thereof so that the support line hangs vertical and will remain generally vertical as the helicopter flies along its chosen path.

Air safety regulations also require that the system, when dropped, must descend slowly to ensure the safety of persons on the ground. This generally requires the deployment of a deceleration device to slow the descent of the system after release from the aircraft. . In Australia the official air safety body (CASA) require that where this type of system is deployed over water, no special controlled descent arrangement is required, but where the system is deployed over land it is essential that a certified controlled descent arrangement is incorporated into the system to ensure safety of people on the ground. To maximise the use of such systems, that is, to enable them to be used over both land and water, it is thus desirable that all systems are fitted with an appropriate controlled descent arrangement.

Typically, the mass of the ballast is between 50 and 100kg. In order to ensure that the deceleration device does not have to be too large, it is known to form the ballast of a particulate or dispersible material which is released when the system is dropped so that the deployed deceleration device does not need to carry the weight of the ballast during the descent.

One prior art system is described in Australian patent no. 764504 which discloses an emergency drop system which, once it has been deployed, and the deceleration device has opened, will release the ballast, thereby further slowing down the rate of descent of the release system.

One problem with prior art systems such as that disclosed in the aforementioned patent, is that the ballast is not released when the system is detached from the aircraft and the combined weight of the ballast and the banner and associated fixtures and fittings is too great for the size of the deceleration device meant to slow the descent. If the ballast does not release properly the weight of the equipment and ballast will be greater than the design weight of the deceleration device. When this occurs the deceleration device becomes relatively ineffectual and can collapse or tear, may not be able to support the load, or may not deploy properly in the first instance, in which case the entire system, including the ballast, will fall rapidly, which can cause significant damage or injury.

Accordingly, a system which has a reliable ballast release mechanism is desirable and will increase the overall safety of the system.

Summary of the invention According to the invention there is provided an aircraft advertising display system which includes an emergency drop arrangement, said system including a ballast release mechanism for releasing ballast which will actuate after the system has been released from an aircraft but prior to the deployment of a deceleration device which is provided to ensure a controlled descent of the system.

In a preferred form of the invention there is provided an emergency drop system for an aircraft held advertising display, said system comprising:

a banner support line adapted to extend generally vertically below an aircraft and to which a banner may be attached;

a connector at the operatively upper end of the support line for attaching the system to an attachment point on the aircraft, the connector and/or the attachment point being releasable in order to disengage the connector from the aircraft;

a ballast container at the operatively lower end of the support line for containing a flowable ballast material, said ballast container having an opening out of which the ballast material may flow, and a closure mechanism for keeping the ballast material contained in the container;

a deceleration device connected to the support line at or near the upper end thereof;

a deployment arrangement adapted to be connected to the aircraft said deployment arrangement including a deceleration device housing for containing the deceleration device prior to deployment, and a ballast release actuator connected to the closure mechanism on the ballast container, the deployment arrangement configured so that when in use the connector is disengaged from the attachment point on the aircraft the ballast release mechanism will cause the closure mechanism to open to thereby open the ballast container, prior to the deployment of the deceleration device.

The deployment arrangement preferably includes a lanyard which forms a connection between the deceleration device housing and the closure mechanism, the lanyard being connected to the deceleration device housing via a rupturable connection, the rupturable connection adapted to rupture under a rupture load, the rupture load being less than the weight of the drop system and banner.

The rupturable connection may comprise a hook and loop type connection which is configured to separate under the rupture load. One side of the hook and loop connection may be connected to the lanyard, and the opposite side of the hook and loop connection would be connected to the deceleration device housing. This arrangement will ensure that the weight of the system will be for the most part carried by the lanyard during initial deployment which will thus be pulled taut, thereby ensuring that the closure mechanism on the ballast container will be released.

Brief description of the drawings

The following drawings depict a preferred embodiment of the invention but the specific feature shown in the drawings should not be construed as limiting on the invention. In the drawings:

Figure 1 shows a side view of an aircraft with a banner release system according to the invention attached thereto.

Figures 2, 3 and 4 depict three stages in the release of the drop system.

Figure 5 depicts a detail of the release system prior to the deployment of the deceleration device.

Figure 6 depicts the same detail after the deployment of the deceleration device.

Figure 7 depicts the threading arrangement for the release lanyard.

Figure 8 depicts the ballast bag prior to the release of the ballast from the bag.

Figure 9 depicts the ballast bag after it has opened. Figures 10, 11 and 12 depict three stages in the deployment of an alternative drop system.

Detailed description of the embodiments

As shown in Figure 1, an aircraft 10 is shown having a banner system 12 connected to the underside thereof so as to hang vertically below the aircraft. The banner system 12 carries a banner 14 which would typically carry advertising information, event information, political information, or any material which a user wished to display to large numbers of people referred to herein as "advertising material". The banner system 12 includes a tow-line 16 which is held vertical by a ballast filled ballast bag 18 located at the lower end of the tow-line.

The banner system 12 is attached to the underside of the aircraft 10 at two attachment points. The first attachment point 20 is the main attachment point and includes a release mechanism (not shown) operable from within the aircraft to enable the banner system 12 to be dropped in an emergency or like situation. The second attachment point 22 remains permanently attached to the aircraft and a static line 36 is attached to the attachment point 22 so as to provide a means for emptying the ballast bag 18 in the event that the banner system 12 is to be dropped from the aircraft. These aspects are described in more detail below.

As mentioned above, when the banner system 12 is dropped from the aircraft 10 it is important that it descends relatively slowly so that some form of drag device (referred to herein as a "deceleration device") is deployed to allow the entire banner system to float relatively slowly to the ground. In order to achieve this slow descent, the ballast needs to be released from within the ballast bag 18 and the lanyard 24 is employed for this purpose.

The ballast bag 18 has an open lower end 26 which is folded over and held closed by a closure mechanism 28. A lanyard 24 is connected to this closure mechanism 28, the arrangement being such that when the banner system 12 is dropped the tension applied to the lanyard 24 will disengage the closure mechanism 28, thereby allowing the end 26 to fold open and thus release the ballast from the interior of the bag 18. These aspects are described in more detail below.

As shown in Figure 2, the upper end of the banner system 12 has a loop 30 which connects to the attachment point 20 and that loop 30 in turn is attached via static line 36 to a container 32 in which is housed a deceleration device sock or pocket 34, shown in Figure 3. The static line 36 attaches directly to the attachment point 22 and also attaches to the deceleration device pocket 34. The lanyard 24 is releasably connected to the pocket 34 via a releasable mechanism 40.

Thus, when the loop 30 is disengaged from the attachment point 20, as shown in Figure 3, the entire banner system falls some distance away from the aircraft but remains momentarily connected thereto by means of static line 36. When attached, in a condition shown in Figure 3, the deceleration device which is contained within the deceleration device pocket 34 cannot be deployed until it is pulled out of the pocket 34 by the lanyard 24. This, in turn, cannot happen until the release mechanism 40 has disengaged in the manner described below.

Once the release mechanism has been disengaged, as shown in Figure 4, the deceleration device 42 is pulled out of the pocket 34 and can then be deployed in order to slow the descent of the banner system 12. The release mechanism 40 is shown in more detail in Figures 5 and 6 of the drawings. As shown, the release mechanism 40 is formed in two parts, one part 46 remaining attached to the pocket 34, and the other part 48 remaining attached to the lower part of the lanyard 24. In the preferred form of the invention, the parts 46 and 48 of the release mechanism will be formed from a hook and loop type connection arrangement, otherwise known as Velcro™, which is designed to release under the effect of the weight of the banner system when empty.

Thus, when the system is initially released from the aircraft, shown in Figure 3, it will drop a set distance, as allowed by the length of the static line 36, and thereafter the lanyard 24 will tauten so as to cause the closure mechanism 28 on the ballast bag to be opened, allowing the ballast bag to open, and release the ballast. As shown in Figure 7 of the drawings the tow-line 16 includes an outer sheath 50, an inner sheath 52, and a core 54. The lanyard 24 is able to slide between the inner sheath 52 and the outer sheath 50. The banner 14 is connected to the lower end of the tow-line 16 by means of a buckle 56, the banner 14 including a tubular strap 58 which provides strength to the leading edge of the banner and also provides a load carrying portion of the banner. The lower end of the tubular strap 58 is connected to the ballast bag via a lower buckle 60. The lanyard 24 passes down a central passageway of the strap 58, passing into the passageway through eye 61 , and out of the passageway through eye 62, in the manner shown in the drawings. Thus, the lanyard 24 is able to slide freely relative to the banner and the tow-line.

As shown in Figures 8 and 9 of the drawings, the closure mechanism for the ballast bag comprises a two-ring closure 64. The two ring closure 64 includes a main closure ring 61 which is connected via closure cords 61a to the lower part of the bag 18, and when in use will hold the lower end of the bag in its folded, that is closed, configuration. A secondary closure ring 63 is of smaller diameter than the main closure ring 61 , and is adapted to pass through the main closure ring 61. The secondary closure ring 63 is connected to the end of a closure flap 63a. The closure flap 63a carries a retaining lug 65, and in the closed configuration, as shown in Figure 8, the secondary closure ring 63 is engaged behind the retaining lug 65.

A secondary safety clasp 67 formed of a wire or like material is engaged at opposite ends thereof between the bottom of the bag 18, and behind the retaining lug 65, as shown. This secondary safety clasp 67 assists in holding the bag 18 closed, to ensure no ballast leaks out of the bag.

The lower end of the lanyard 24 is connected to a pin 66 which holds the two-ring closure 64 closed. The lanyard is attached to the bag 18 by means of a ring 68 and a fastener 70.

As tension is applied to the lanyard 24, the lanyard will pull the pin 66 out of the closure 28, releasing the secondary safety clasp 67 and allowing the two ring closure 64 to open, thereby allowing the end 26 of the bag to unfold and thereby open fully and dispense the ballast material from the interior of the bag. Typically the ballast material will be some dispersible material such as sand, gravel or the like. As mentioned above, it is envisaged the weight of the ballast material will be between 50 and 100 kg typically, approximately 85kg.

As soon as the bag has opened, as is shown in Figure 9 of the drawings, the weight of the banner system absent the sand will be sufficient to cause the release mechanism 40 to disengage. It is envisaged that the banner system will weigh approximately 85kg and thus the release mechanism 40 will be designed to release at a weight of significantly below 85kg, that is, it will release when a weight of greater than between about 40kg and 50 kg is applied to the release mechanism 40.

However, it will be appreciated that the release mechanism will hold the banner system to the aircraft for a period which is sufficient to ensure that the ballast bag has been fully opened and that the ballast material has at least started to dispense from the bag prior to the deployment of the deceleration device. Thus, whilst the system is still connected to the aircraft the opening of the ballast bag will take place. It is envisaged that it will be a relatively sharp jerk by the lanyard 24 on the pin 66, thus ensuring that the pin instantaneously releases thereby ensuring quick opening of the bag and almost instantaneous dispersion of the ballast material from the bag. Once released, the ballast will disperse harmlessly. Free-flowing dry sand is the preferred ballast.

Reference may now be made to an alternative version of the drop system as shown in Figures 10 to 12 in which the connection between the aircraft and the ballast release mechanism, and between the aircraft and the deceleration device, are somewhat different. In this embodiment a lanyard 74 connects the Velcro release mechanism 40 directly to the ballast closure mechanism 28. The deceleration device 42 is linked to the banner and ballast container via a sturdy strap or webbing 76. The relative lengths of the lanyard 74 and webbing 76 are selected such that on release the lanyard 74 will pull taught and cause the closure member 28 to open, prior to the deceleration device being deployed. That is, the lanyard 74 will be pulled taught, the closure member will open, and the banner and ballast container will begin to fall away from the aircraft, causing the Velcro release mechanism 40 to rupture, prior to the webbing 76 being pulled taught, thereby ensuring that the deceleration device 42 is not deployed until the ballast container has been completely opened, and the ballast released. The high strength webbing 76 will be selected to ensure that it can carry the load of the drop system below the deceleration device, as it descends from the aircraft.

It will be appreciated that by having the lanyard 74 dedicated to. opening the closure mechanism 28, and the webbing 76 having strength characteristics necessary to support the load, each component can be selected so as to ensure it performs its requisite task, without being over or under engineered. The lanyard 74 will not carry any significant load. The lanyard needs to be able to slide easily relative to the banner in order to open the closure mechanism. The lanyard will typically be a lightweight high strength cord, whereas the webbing 76 needs to be of higher strength and specifically envisaged is a woven strap-like material.

In the short delay which occurs before the release mechanism 40 disengages, the weight of the system will be reduced by the loss of the ballast material, and thus the deceleration device itself will not need to support the weight of the ballast material once it is deployed. Accordingly, it is envisaged that the release of the ballast material will occur more reliably, and also failure of the deceleration device is not likely to occur since the deceleration device will not be required to momentarily support a load which is well in excess of its design load.

The term "deceleration device" used herein should be interpreted broadly and will include within its scope devices such as parachutes, wind socks, drogues, and other drag devices.

Other forms of release mechanisms in 40 are envisaged. The example, a shear pin type mechanism could be used, or a tie member of known breaking strength, or other forms of rupturable or severable devices.

It will be understood that the invention disclosed and defined in this specification extends to all alternative combinations of two or more of the individual features mentioned or evident from the text or drawings. All of these different combinations constitute various alternative aspects of the invention.

It will also be understood that the term "comprises" (or its grammatical variants) as used in this specification is equivalent to the term "includes" and should not be taken as excluding the presence of other elements or features.

Claims

1 An aircraft advertising display system which includes an emergency drop arrangement, said system including a ballast release mechanism for releasing ballast which will actuate after the system has been released from an aircraft but prior to the deployment of a deceleration device which is provided to ensure a controlled descent of the system.

2 An aircraft display system according to claim 1 comprising:

a deployment arrangement adapted to be connected to the aircraft said deployment arrangement including a deceleration device housing for containing the deceleration device prior to deployment, and a ballast release actuator connected to the closure mechanism on the ballast container, the deployment arrangement configured so that when in use the connector is disengaged from the attachment point on the aircraft the ballast release mechanism will cause the closure mechanism to open to thereby open the ballast container, prior to the deployment of the deceleration device. 3 An aircraft display system according to claim 2 wherein the deployment arrangement includes a lanyard which forms a connection between the deceleration device housing and the closure mechanism, the lanyard being connected to the deceleration device housing via a rupturable connection, the rupturable connection adapted to rupture under a rupture load, the rupture load being less than the weight of the drop system and banner.

4 An aircraft display system according to claim 3 wherein the rupturable connection comprises a hook and loop type connection which is configured to separate under the rupture load.

5 An aircraft display system according to claim 4 wherein one side of the hook and loop connection is connected to the lanyard, and the opposite side of the hook and loop connection is connected to the deceleration device housing.

6 An aircraft display system according to any one of claims 2 to 5 wherein the ballast container comprises an open ended cylindrical bag, the lower end of which is folded close to contain the ballast material.

7 An aircraft display system according to any one of claims 2 to 6 wherein the ballast material is one of sand, gravel or water.

8 An aircraft display system of according to any one of claims 2 to 7 wherein the deceleration device is a parachute.

9 An aircraft display system according to any one of claims 2 to 8 wherein the ballast release actuator comprises a two ring closure held by a pin, said actuator being actuated when the pin is disconnected from the two ring closure.

10 An aircraft display system substantially as hereinbefore described with reference to the accompanying drawings.