GB2071030A

GB2071030A - Parachute deployment apparatus

Info

Publication number: GB2071030A
Application number: GB8005164A
Authority: GB
Original assignee: Individual
Current assignee: Individual
Priority date: 1980-01-25
Filing date: 1980-02-15
Publication date: 1981-09-16

Abstract

Particularly for use in a hangglider, a parachute is deployed out of a housing (1) in case of emergency by the pilot firing a rocket (3) which is attached to the parachute by a lead line. The parachute rigging is attached to an anchor point on the glider to which the pilot's harness is also attached. <IMAGE>

Description

SPECIFICATION Parachute deployment apparatus This invention relates to a parachute deployment apparatus and particularly, although not exclusively, to such an apparatus when mounted on a hangglider.

The sport of hang-gliding is a rapidly growing one but there have been accidents where a glider has folded or collapsed whilst in the air, leading to death or injury for the pilot. The successful deployment of a parachute depends on the pilot being able to deploy his parachute into unobstructed air. This invention seeks to simpiify this operation for him.

According to an embodiment of the present invention, a parachute deployment apparatus includes a housing, containing a parachute, concentric with, or, adjacent to a tube containing a rocket connected to the parachute canopy with a leader line; whose base is located adjacent to an igniter, the apparatus also including a means whereby the igniter can be remotely actuated.

In a preferred version of the invention the housing is cylindrical, although it will be understood that the housing need not be cylindrical, it could be of rectangular shape for example.

The rocket tube may be located concentrically within the parachute housing. Of course it will be understood that the rocket tube could be externally adjacent to the parachute housing. The parachute housing maybe open ended. The rocket may be connected to the canopy of the parachute with a leader line of sufficient length to protect the parachute from hot emissions to the rocket. There may be a weak-link in series with the leader line to release the rocket upon full extension of the parachute.

There maybe a dust and moisture cover on the open end of the housing which may have an 'open sesame' type latch to secure it in position. The igniter maybe connected to the cable of a Bowden cable type of mechanism leading to a pull handle near the pilot. When the pilot pulls the handle, the igniter ignites the rocket which then bears upon the open sesame latch, so releasing the dust and moisture cover and the rocket escapes the apparatus towing the parachute after it.

The invention will be better understood from the following description of a non-limiting and illustrative example thereof, given with reference to the accompanying drawings, in which: Figure 1 is a perspective view of a hang-glider including a parachute deployment apparatus in accordance with one example of the present invention; Figure 2 is an axial cross-section of one form of parachute deployment apparatus illustrated at (1) in Figure 1, with an accompanying end - elevation; Figure 3 is an end - elevation illustrating a second rocket-tube arrangement.

Figure 4 is a sectional view of the sesame latch illustrated at (9) in Figure 2; Figure 5 is a sketch illustrating a weak-link device usable in the apparatus according to the invention.

The illustrated parachute deployment apparatus includes a cylindrical housing (1) concentric with a rocket tube (2) containing a rocket (3) whose base is deposed adjacent to an igniter device, generally indicated at (6). The term 'igniter' shall be deemed to include an explosive cap and spring urged firing pin, or, any other suitable means of igniting the rocket (3). Instead of a tube, the rocket may be supported relative to the housing by other support structure such as a spike or a skeleton framework.

Of course it will be appreciated that the housing (1) need not be cylindrical but a cylindrical housing is ultilised in the presently preferred version of the invention. It will also be appreciated that the rocket tube (2) need not be within the housing (1) but may be adjacent to it, as illustrated on the front elevation shown in Figure 3.

The housing (1) has an open end which is covered by a dust and moisture cover (8), and its opposite end is blanked off with a back plate (5), thus defining together with the outer wall of the housing, a space (4) within which the paracute, together with its rigging lines can be contained. The grouped ends of the rigging lines are connected to a connecter (7) which connects them to a webbing strap (11) which extends out of the back of the housing and connects to the central anchor point on the hang-glider, thereby also coupling to the pilot's harness anchor.

The back of the housing contains an igniter generally indicated at (6). The igniter (6) is connected to a pull handle (15) by a Bowden type cable (10). The pull handle (15) is located near the pilot so that a sharp pull on it will fire the rocket. There will be a safety pin, locking the igniter actuator, which will be externally accessible. This will be protect against inadvertent firing of the rocket, and it will be understood that before taking off the pilot removes the safety pin, and upon landing, replaces it As seen in Figure 2a,the handle (15) is encased within an actuating handle pocket, which may have a flap thereon, secured by 'Velcro' (Registered Trade Mark) or in any other suitable way, thereby protecting the handle against accidental actuation.

The leader line interposed between the rocket (3) and the parachute canopy may include a weak-iink illustrated Figure 5, of a caiculated separation Force to release rocket (3) from the parachute upon full extention of the latter. The function of the leader line is such that by virture of it's length, it will protect the parachute canopy from hot emissions of the rocket.

The rocket (3) may, itself, be fitted with a parachute to render it safe after separation.

The "sesame" latch generaliy illustrated at (9) Figure 2, may be of such form as illustrated by a sectional view in Figure 4 where :- (3) is the rocket: (2) is the rocket tube; (8) is the dust and moisture cover and (14) are sprung latch limbs. The rocket (3) upon ignition will move in the direction indicated by the arrow and depress the limbs (14) thereby removing the sear portion of the limbs from their respective holes in the rocket tube (2) and releasing dust and moisture cover (8). The rocket (3) will then escape the apparatus towing the parachute after it.

It will be understood that modifications may be made without departing from the invention. As illustrated in Figure 1 the parachute deployment apparatus is located at the rear end of the main boom of a hang-glider, but it will be appreciated that it could be suitably placed elsewhere on the hangglider. For example, it could be placed at any position thereon where there is a deployment window, i.e. a clear space which is likely to be kept clear even in the event of the glider structure folding up or collapsing.

It will be also realised that this invention is distinguished from the known pilot ejector seats where the parachute is deployed by explosive, as these are directed to a completely different set of problems, and for many reasons would be completely unsuitable for use on light flying craft such as a hang-glider.

Claims

1. A parachute deployment apparatus which includes a housing defining a space within which a parachute and its rigging lines can be contained, a means of mounting a rocket contained within or adjacent to the housing, an igniter device within or adjacent to the housing for igniting the rocket, and means for remote actuation of the rocket.

2. An apparatus according to claim 1 in combination with a rocket and a parachute, there being a leader line connecting the rocket and the parachute canopy.

3. Apparatus accoring to claim 1 or 2 in which the housing is open ended.

4. Apparatus according to claim 3 in which there is a dust and moisture cover or the like over the open end ofthe housing.

5. Apparatus according to claim 4 in which the dust cover inludes a latch co-operating with the rocket to achieve it's detachment.

6. Apparatus to according to any preceding claim in which the parachute rigging lines are connected to a non-rigid member of known breaking strain which is in turn connected to the central anchor point of a hang-glider.

7. Apparatus according to claim 1,2,3,4 or 5 in which the parachute rigging lines are connected to a webbing strap which in turn is connected to the central anchor point of a hang-glider.

8. Apparatus according to any preceding claim in which the means of ignition is connected to a Bowden type cable for remote actuation.

9. Parachute deployment apparatus substantially as herein described with reference to and as illustrated in the accompanying drawings.

10. A hang-glider having parachute deployment apparatus according to any one of claims 1 - 9.