A number of parachute retardation or shock absorption devices are known, for example those disclosed in USA patents 4,127,246; 4,333,621; and 6,050,524. USA patent number 6,050,524 discloses a device for reducing the impact velocity of a parachutist by a length-shortening retraction device. The retraction device is operated by a gas generator, which is activated by a ground proximity sensor.

The retraction device is mounted between the load and the conventional suspension lines and a disadvantage of the known device is that a substantial force has to be applied to shorten the suspension lines. High stress forces are thus generated in the suspension lines and the device is not suitable for use with heavy loads.

OBJECT OF THE INVENTION It is therefore an object of the present invention to provide a parachute retardation device with which the aforesaid disadvantage can be overcome or at least minimised.

SUMMARY OF THE INVENTION According to a first aspect of the invention there is provided a parachute retardation device for retarding the downward velocity of a load carried by a parachute, the retardation device comprising increasing means for increasing the effective surface of the parachute.

Further according to the invention the increasing means includes: a retraction device connectable to the load for moving the load and the parachute towards each other; and connecting means for connecting the retraction device to the parachute, the connecting means comprising a plurality of elongate members, a first end of each member being connected to the retraction device and a second end of each elongate member being connected to a region of the parachute towards but inwards from the periphery of the parachute.

The parachute retardation device may further include a sensing means for sensing the approach of the load to the ground.

The parachute retardation device may even further include an activating mechanism for activating the retraction device in response to a signal received from the sensing means.

The first ends of the elongate members may be connected to each other.

The elongate members may be in the form of a plurality of secondary cables and the first ends of the secondary cables may further be connected to the retraction device by a primary cable.

The parachute may be in the shape of a dome and for optimum performance, the second end of each secondary cable may be connected to the dome- shaped parachute in the region of the outer middle annular quarter of the dome.

The retraction device may be in the form of a servo-mechanism including a piston and cylinder assembly and two sets of pulleys, each set being connected to either the piston or the cylinder. The primary cable may be suspended over the pulleys, with the operatively lower end of the primary cable being connected to either the piston or the cylinder.

The retraction device may further include a gas expansion device disposed inside the cylinder to be activated by the activating mechanism, for moving the piston outwardly relative to the cylinder, to expand the retraction device and thus to draw in the primary cable.

According to a second aspect of the invention there is provided a parachute having a retardation device according to the first aspect of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS The invention will now be described further by way of a non-limiting example with reference to the accompanying drawings wherein: figure 1 is a longitudinal-sectional side view of a parachute provided with a retardation device according to a preferred embodiment of the invention in a pre-retarded condition; figure 2 is the same view as that of figure 1, with the retardation device in a retarded condition; figure 3 is a longitudinal-sectional side view of the retardation device of figure 1; and figure 4 is a top view of the parachute of figure 1.

DESCRIPTION OF A PREFERRED EMBODIMENT OF THE INVENTION Referring to figures 1 and 2, a parachute 10 according to a preferred embodiment of the invention is provided with a retardation device 12 (shown in more detail in figure 3). The retardation device 12 is particularly suitable for retarding the downward velocity of a load 14 carried by the parachute 10.

The retardation device 12 includes an increasing means for increasing the effective surface of the parachute 10, comprising a retraction device 12.5 connectable to the load 14 for moving the load 14 and the parachute 10 towards each other. The increasing means further includes connecting means for connecting the retraction device 12.5 to the parachute 10. The connecting

means comprises a primary cable 18 and a set of between eight and fourteen, preferably twelve secondary cables 20. A first or lower end of each secondary cable 20 is connected to the retraction device 12.5 via the primary cable 18, and a second or upper end of each is connected to a region R of the parachute 10 towards but inwards from the periphery of the parachute 10.

The parachute 10 is dome shaped and could be divided into annular quarters by imaginary lines depicted in figure 4 comprising a middle quarter 23, inner middle quarter 24, outer middle quarter 25 and a peripheral quarter 26. The region R is the outer middle annular quarter 25 of the dome shaped parachute 10.

The retardation device 12 further includes a proximity sensor 22 for sensing the approach and close proximity of the load 14 to the ground.

Referring to figure 3, the retraction device 12.5 is in the form of a servo- mechanism including a piston and cylinder assembly 12.1 and 12.2 respectively, and two sets of pulleys 12.3. One set of pulleys 12.3 is mounted on the outside end of the cylinder 12.2 and the other set of pulleys is mounted on the rod of the piston 12.1.

The primary cable 18 is suspended over the pulleys 12.3, with the operatively lower end of the primary cable 18 being connected to the rod of the piston 12.1.

The retardation device 12 even further includes an activating mechanism for activating the retraction device 12.5 in response to a signal received from the sensor 22. The activating mechanism comprises a gas expansion device 12.4 disposed inside the cylinder 12.2 and which is activated by a signal from the sensor 22, to move the piston 12.1 outwardly relative to the cylinder 12.2 as indicated by arrows A and B in figure 3, to expand the retraction device 12.5 and thus to draw in the primary cable 18. The primary cable 18 pulls the secondary cables 20 in the direction of arrows C in figure 1, which causes the air inside the parachute to accelerate and the portion of the parachute towards but inwardly from the periphery of the parachute 10 is pulled downwards by the secondary cables 20, to increase the effective surface of the parachute 10.

The downward speed of the load 14 is thus retarded just before it hits the ground.

It will be appreciated that variations in detail are possible with a parachute retardation device according to the invention without departing from the scope of the appended claims.