GB2466814A

GB2466814A - Conformal liner helmet

Info

Publication number: GB2466814A
Application number: GB0900234A
Authority: GB
Inventors: Joseph Anthony Griffiths
Original assignee: Individual
Current assignee: Individual
Priority date: 2009-01-08
Filing date: 2009-01-08
Publication date: 2010-07-14
Also published as: GB0900234D0; US20100170022A1

Abstract

A helmet 10 suitable for an aircraft pilot comprises an inner shell 12 and a liner (14a, 14b, fig.4) attached to the inner shell, and adjustable tensioning means 16a, 16b disposed at the rear of the helmet configured to tension the inner helmet and liner onto the pilot's head. The tensioning means preferably tensions the inner helmet and liner onto the head between points proximate the left and right of the outward curve of the pilot's skull proximate the nape of the neck, and the forehead. Preferably, the tensioning means comprise first 16a and second 16b tensioning elements attached to the left and right sides of the inner shell respectively, and may be adjustable independently. Also claimed is a method of securing a helmet onto a pilot's head.

Description

Conformal Liner Helmet

Description

The present invention relates to a helmet for use by a combat aircraft pilot and, more particularly, to such a helmet suitable for use iii aircraft capable of high G-force acceleration having a pilot-specific personalised liner.

Modern combat aircraft pilots are provided with advanced flying helmets which generally comprise an inner helmet and an outer helmet. The inner helmet fits on the pilot's head and includes attachment points to which the pilot attaches his breathing mask. The outer helmet fits over and is secured to the inner helmet, and includes instruments and equipment, for example, a helmet mounted display (HMD) for weapons targeting or night vision goggles (NVGs). It is important that the equipment mounted on the outer helmet is positioned accurately with respect to the pilot's eyes in order to function properly. For example, night vision goggles must remain exactly in the pilot's line of sight, and a HMD system, whereby information is projected onto the inside of the pilot's visor, must remain in exactly the correct position for the pilot to be able to read the projected information.

Therefore, once the helmet is fitted and adjusted to the pilot's head in exactly the correct position, it is important the outer helmet does not move during flight relative to the pilot's head. As the outer helmet is rigidly secured to the inner helmet, it is therefore important that the inner helmet does not move relative to the pilot's head.

Modern combat aircraft are capable of very high speed manoeuvres which subject the aircraft and pilot to up to 9G. During such manoeuvres, the mass of the inner and outer helmet, together with the avionic equipment mounted to the outer helmet, cause high forces to be generated and these high forces can cause the inner helmet to move relative to the pilot's head. This is especially problematic when avionic equipment is mounted over the front of the helmet and therefore the forward-positioned mass of such equipment acted upon by the significant downwards and sideways acceleration forces causes the helmet to rotate forwards and sideways relative to the pilot's head. Furthermore, the significant mass of such equipment mounted to the helmet means that if a pilot goes top quickly rotate his head, as he would need to do in a combat situation when tracking an enemy aircraft, the inertia of the mass of the helmet can cause the helmet to be displaced out of position on the pilot's head, thereby misaligning the avionic equipment relative to the pilot's eyes.

It is known to provide a conformal liner which is fitted to the inside of the inner helmet.

Such known liners are produced by laser-scanning an individual pilot's head, and manufacturing a pilot-specific liner having an inner surface that corresponds exactly to the scanned shape of the individual pilot's head, and an outer surface that fits exactly into the inside of the inner helmet. It is intended that such a custom-made snug-fitting liner will prevent the inner helmet from moving relative to the pilot's head during high-G manoeuvres, purely due to the exact shape-fit of the liner on the pilot's head. However, in practice, even these perfectly-fitting custom-made liners cannot reliably prevent helmet movement in all conditions because, despite the exact fit, such known liners and helmets do not apply any tension or tightening onto the pilot's head and so are unable to effectively secure and locate the helmet in a stable position on the pilot's head.

It is therefore an object of the present invention to provide a pilot's helmet, and a liner for such a helmet, that substantially alleviates or overcomes the problems mentioned above.

Accordingly, the present invention provides a helmet for an aircraft pilot comprising an inner shell, a liner attached to the inner shell configured to closely contact the pilot's head, and adjustable tensioning means disposed at the rear of the helmet configured to tension the inner helmet and liner onto the pilot's head, to secure and locate the helmet in place on the pilot's head.

The adjustable tensioning means may be configured to tension the inner helmet and liner onto the pilot's head between points located proximate the left and right of the outward curve of the pilot's skull proximate the nape of the pilot's neck, and at the pilot's forehead.

The adjustable tensioning means may comprise first and second tensioning elements moveably attached to the left and right sides of the inner shell respectively, and in contact with the pilot's head, and operable to be biased against the pilot's head.

The adjustable tensioning means may further comprise an adjustment member operable to cause the first and second tensioning elements to be biased against the pilot's head.

The adjustment member may extend between and be secured to the first and second tensioning elements.

An adjustment member may extend between the first tensioning element and the inner shell, and another adjustment member may extend between the second tensioning element and the inner shell.

The or each adjustment member may comprise a wire or inextensible belt which is adjustable in length.

The first and second tensioning elements may comprise an outer shell layer generally co-extensive with the inner shell, and an inner liner layer generally co-extensive with the liner attached to the inner shell.

The first and second tensioning elements may comprise discrete elements separate from one another.

The first and second tensioning elements may be joined together by a bridging section such that together with said bridging section, the first and second tensioning elements comprise a unitary member.

The first and second tensioning elements may be adjustable independently of each other to independently tension the left and right sides of the inner shell and liner onto the pilot's head.

The rear of the helmet may include an upwardly extending recess for allowing the pilot to tilt his head backwards without the helmet abutting against his neck, said first and second tensioning elements being disposed on the left and right sides of the recess respectively.

The liner may comprise a first portion attached to the front of the inner shell and a separate second portion attached to the rear of the inner shell.

The rear portion of the liner may be divided into two discrete elements respectively disposed on left and right sides of the helmet.

The liner may include recessed sections on its inner surface to provide ventilation to the pilot's head.

The present invention also provides a method of securing a locating a helmet on a pilot's head, the helmet comprising an inner shell, a liner attached to the inner shell configured to closely contact the pilot's head, and adjustable tensioning means comprising first and second tensioning elements at the rear of the helmet moveably attached to the left and right sides of the inner shell respectively, and configured to tension the inner helmet and liner onto the pilot's head, the method comprising placing the helmet on the pilot's head and using the adjustable tensioning means to bias the first and second tensioning elements into contact with the pilot's head to secure and locate the helmet in place on the pilot's head.

The method may further comprises independently adjusting the first and second tensioning elements Preferred embodiments of the present invention will now be described, by way of example only, with reference to Figures 3 -9 of the accompanying drawings, in which: Figure 1 shows an exploded perspective view of a known helmet and liner arrangement; Figure 2 shows a cross-sectional view of the helmet and liner of Figure 1; Figure 3 shows a rear view of an inner helmet and liner of a first embodiment of the present invention; Figure 4 shows a cross-sectional view of the inner helmet and liner of Figure 3; Figure 5 shows a perspective view of one side extension piece of the helmet of Figures 3 and 4; Figure 6 shows a rear view of an inner helmet and liner of a second embodiment of the invention similar to that shown in Figures 3 5, but including alternative adjustment means; Figure 7 shows a rear view of an inner helmet and liner of a third embodiment of the present invention; Figure 8 shows a rear view of an inner helmet and liner of a fourth embodiment of the present invention; and Figure 9 shows a rear view of an inner helmet and liner of a fifth embodiment of the present invention.

Figures 1 and 2 show a known type of pilot's helmet 1 comprising an outer helmet 2, an inner helmet 3 to which the outer helmet 2 attaches, and a liner 4 which fits inside the inner helmet 3. The liner 4 is shaped such that its outer surface 4a conforms to the inside of the inner helmet 3 to make an exact fit therewith, and the inner surface 4b is shaped to conform with the shape of the pilot's head for whom it was manufactured. The exact fit on the pilot's head is achieved by laser-scanning the individual pilot's head and manufacturing the liner 4 so that the inner surface 4b corresponds exactly to the scanned dimensions.

Breathing equipment 6 is mounted to the inner helmet 3, and avionic equipment 7 such as NVGs, HMD, are mounted to the outer helmet 2. In the illustrated embodiment, the HMD comprises an image projection unit 7 mounted on the inside of the outer helmet 2, which projects an image beam 7a onto the inside of the visor 2a, which the pilot can see as it reflects back to his eye. The outer helmet 2 is rigidly secured to the inner helmet 3 and is immovable relative thereto. However, such known helmet arrangements still suffer the drawbacks described above of tilting forward or sideways, or rotating sideways due to the forward mass of the inner and outer helmets 2,3 during high-G manoeuvres, despite the liner 4 being custom made to fit an individual pilot's head.

Referring now to Figures 3 -5, a first embodiment of the present invention is shown and comprises a helmet 10 for use by a pilot of a combat aircraft, comprising an inner helmet or inner shell' 12 (the outer helmet is not shown) and a liner 14A, 14B. The liner is divided into a separate front portion 14A and rear portion 14B (see Figure 4). The front portion 14A is attached to the inside of the inner helmet 12 by conventional means such as snap fasteners, poppers, latches etc., and is in direct contact with the pilot's head. The rear portion I 4B of the liner 14 is attached to the inner helmet 12, again by such known means as described above, and is also in direct contact with the pilot's head. [Alternatively, the front and rear portions 14A, 14B of the liner may be held in place by an inwardly extending lip around the edge of the inner helmet 12.] At the bottom rear of the helmet 10, the bottom edge of the helmet 10 includes an upwardly extending recess 1OA which allows the pilot to tilt his head back without the bottom edge of the helmet abutting against his neck, to increase his range of head movement. The rear of the helmet 10 also includes left and right extension pieces I 6A, 1 6B which extend from the lower left and right side edges of the recess 1 OA respectively. Each extension piece I 6A, 1 6B includes a section of helmet shell 17A, 17B (see Figure 5) co-extensive with the inner shell 12 of the helmet 10, and a section of inner liner 18A, 18B co-extensive with the rear portion 14B of the liner.

Each left and right extension piece I 6A, 1 6B is moveably connected to the rear portion of the helmet 10, and they are spaced from each other (as can be seen in Figure 3) so that a recess 1 OA still exists at the rear of the pilot's head to still allow the pilot to tilt his head back and provide a range of movement of his head. The left and right rear extension pieces 1 6A, I 6B may, for example, be connected to the inner helmet 12 by the shell sections 1 7A, 1 7B being hingedly attached to the inner helmet 12 a the bottom inside edge of the recess I OA.

Each left and right extension piece 1 6A, 1 6B includes a fastening point 22A, 22B on the outer surface of the shell section 17A, 17B which cooperates with an adjustment member 23 to allow the extension pieces 16A, 16B to be adjusted so that they are pressed into contact with the base of the pilot's head underneath the outward curve of his skull proximate the nape of his neck and thereby tension the front portion 14A of the liner against the forehead/hairline of the pilot. In the illustrated first embodiment, the adjustment member 23 comprises an inextensible strap, such as a webbing belt, extending across the back of the pilot's head between the fastening points 22A, 22B of the extension pieces 1 6A, 1 6B. However, the means by which the left and right extension pieces 1 6A, 1 6B are tensioned may vary within the scope of the invention, for example, the adjustment member 23 may comprise a wire extending between each fastening point 22A, 22B, the length of which may be reduced to tension the extension pieces 16A, I6B and thereby the helmet 10 onto the pilot's head. A mechanism 24 by which the wire or strap is adjusted may vary within the scope of the invention, for example, it may comprise a rotatable dial, or a lever and cam arrangement, or a simple ratchet or buckle.

The operation of the helmet 10 of the first embodiment of the present invention is as described hereafter. The inner helmet 12 with attached liner 14A, 14B is placed on the pilot's head with front and rear portions 14A, 14B of the liner fitting snugly against his head. The pilot then tightens the adjustment member 23 using the adjustment mechanism 24 so that the left and right extension pieces 1 6A, 1 6B are pulled together and pivoted forwards, and thereby bias against the rear of the pilot's head to tension the inner helmet 12 and liner 1 4A, I 4B thereon. The extension pieces 1 6A, I 6B are biased against the pilot's head at a point below the outward curved of his skull proximate the nape of his neck. As the pilot adjusts the left and right extension pieces 16A, 16B, the helmet 10 can be tensioned so the helmet 10 is securely located at exactly the correct position with respect to the pilot's eye(s), as required for operation of the avionic equipment, as described above.

As the rear left and right extension piecesl6A, 16B of the helmet 10 are adjusted, they apply a tension between these two rear points of contact proximate the base of his skull and the pilot's forehead/hairline, generally in a plane of tension P (see Figure 4). This tension and the specific location beneath the curve of the rear of the pilot's skull ensures that the inner helmet 12 cannot tilt forwards or sideways, or rotate sideways, relative to the pilot's head, even when an outer helmet (not shown) is secured to the inner helmet 12 with associated heavy avionic equipment secured thereto. Furthermore, the two points of contact of the left and right extension pieces 1 6A, 1 6B at the base of the pilot's skull and the third point of contact of the hairline/forehead, result in the helmet being tensioned about three points of contact in a triangular configuration in plane P (see Figure 4), resulting in a far superior securing configuration than if only two contact points were used.

A second embodiment of the invention is shown in Figure 6, which corresponds largely to that of the first embodiment, and so like features retains the same reference numerals.

However, the second embodiment differs from the first embodiment in that the single adjustment member 23 of the first embodiment is replaced by a pair of adjustment members 33A, 33B comprising inextensible straps, such as a webbing belt, extending from each fastening point 22A, 22B of each extension piece I 6A, I 6B to a central point on the inner helmet 12. Each strap 33A, 33B is adjustable in length by an adjustment mechanism 34A, 34B, which, as described above with reference to the adjustment mechanism 24 of the first embodiment, may vary within the scope of the invention, for example, it may comprise a rotatable dial, a screw barrel, a lever and cam arrangement, or a simple ratchet or buckle. However, it will be appreciated that the adjustment members 33A, 33B are each individually adjustable independently of the other, to individually tension the respective extension pieces I 6A, 1 6B. Therefore, the inner helmet 12 can be precisely adjusted as required to provide a most accurate fit against the rear of the pilot's head, i.e. the left and right sides can be adjusted independently from each other.

As with the first embodiment of the invention, the plane of tension P through which the inner he]met 12 and liner 14A, 14B are secured to the pilot's head, has three main points of contact against the pilot's head (i.e. the front at his forehead/hairline, and two rear left and right extension pieces I 6A, I 6B beneath the curve of his skull proximate the nape of his neck) which lie in a triangular distribution. As described previously, this tension in a triangular distribution, and the specific location beneath the curve of the rear of the pilot's skull, creates a very secure and stable fastening configuration and ensures that the inner helmet 12 cannot tilt forwards relative to the pilot's head, nor tilt sideways, or rotate sideways, even when an outer helmet with associated heavy avionic equipment (not shown) is secured to the inner helmet 12. As well as providing an especially stable helmet-securing configuration, the triangular configuration in this second embodiment also optirnises the pilot's ability to precisely locate the inner helmet 12 on his head by individually adjusting the left and right extension pieces I 6A, 1 6B to independently tension the left and right rear parts of the helmet against his head. Alternatively, the additional member could comprise an adjustable wire or strap.

The adjustment means of the second embodiment is shown in Figure 6 as only comprising the two adjustment members in the form of straps 33A, 33B. However, it is intended to fall within the scope of the invention for an additional member to extend between the left and right extension pieces 16A, 1GB. In such an unillustrated embodiment, such an additional member may comprise a rigid bar or rod 35 (see dashed lines in Figure 6), to keep the left and right extension pieces I 6A, 1GB generally spaced apart laterally by the same distance as the adjustment members 33A, 33B are tensioned. This arrangement could aid in increasing the tension exerted by the left and right extension pieces 1 6A, 11 6B against the rear of the pilot's head proximate the nape of his neck to secure and locate the liner and inner helmet 12 in place on his head.

Third and fourth embodiments of the present invention are shown in Figures 7 and 8, and both comprise a helmet for use by a pilot of a combat aircraft generally as described above with reference to the first and second embodiments, and like components retain the same reference numerals. However, the third and fourth embodiment differ from the first and second embodiments in that the left and right extension pieces 1 6A, I 6B are not discrete separate components, but instead, are connected by a bridging section 1 6C, to form a single unitary component. As can be seen from Figures 7 and 8, the bridging piece 1 6C is configured as an arch to still leave a recess 1OA proximate the pilot's neck to allow the pilot a degree of freedom to tilt his head. Furthermore, the bridging section 1 6C is resilient to allow the left and right extension pieces 1 6A, I 6B to move when acted upon by the tension of the adjustment member 23. The bridging piece 16C can comprise a shell section and a liner section, as each of the extension pieces 1 6A, 1 6B do (see Figure 5), or alternatively, may only comprise an outer shell section, so only the left and right extension pieces 16A, 16B include a section of liner 18A, 18B. In the illustrated third and fourth embodiments, the adjustment member is shown as a single strap 23 extending between fastening points 22A, 22B on the left and right extension pieces 16A, 16B respectively, as with the first embodiment described above. However, the adjustment member may alternatively comprise a pair of straps, one extending from each extension piece 16A, 16B respectively, to a point on the inner shell 12, as described above with reference to the second embodiment of the invention. Furthermore, alternatives other than a strap may be provided, such as wires, and any of the above-described tensioning mechanisms may be included to apply the securing tension to the helmet 10.

The third embodiment shown in Figure 7 illustrates the left and right extension pieces I 6A, 16B being moveably connected to the inner helmet 12 at the lower left and right edges of the upwardly extending recess 1 OA respectively, as in the first and second embodiments.

However, it is intended within the scope of the invention that the bridging section 16C may be connected to the inner helmet 12 at the upper edge of the recess IOA, with the left and right extension pieces I 6A, 1 6B adjacent to, but not connected to, the sides of the inner helmet 12 at the bottom edges of the recess bA. This alternative embodiment is shown in the fourth embodiment of Figure 8. In this fourth embodiment, the left and tight extension pieces 16A, 16B would be moveable relative to the inner helmet 12 upon adjustment of the adjustment member 23 to be biased against the pilot's head, by deflection of the bridging section 16G.

Operation of these third and fourth embodiments of the invention would be similar to that described previously with respect to the first and second embodiments, and so will not be repeated.

A fifth embodiment of the present invention is shown in Figure 9, and comprises a helmet for use by a pilot of a combat aircraft generally as described above with reference to the first and second, and like components retain the same reference numerals. However, the fifth embodiment differs from the first and second embodiments in that the inner helmet 12 includes left and right projections I 9A, 1 9B which extend over and support the left and right extension pieces 16A, 16B. Each of the left and right extension pieces 16A, 16B include shell sections 1 7A, 1 7B which are moveably connected to the inside face of the left and right projections 19A, 19B respectively, and extension pieces 16A, 16B include liner sections 18A, 18B which are attached to the shell sections 17A, 17B. Fastening points 22A, 22B are provided on the shell sections 1 7A, 1 7B of the extension pieces 1 GA, 1 6B and are secured to adjustment means 23 having an adjustment mechanism 24, as described above.

However, any of the configurations of adjustment means described above may be employed. Therefore, the left and tight projections 19A, 19B from the inner helmet 12 provide an alternative mounting configuration for the left and right extension pieces 16A, 1 6B to that described previously. Operation of this fifth embodiment of the invention would be similar to that described previously, and so will not be repeated.

Although the embodiments shown and described above include a liner comprising two separate (front and rear) portions 14A, 14B, it is intended within the scope of the invention and the claims hereafter, that the liner may comprise a single portion attached to the inner helmet or inner shell' 12. Alternatively, the liner may be divided in other ways, for example, the front portion 14A may be sub-divided into left and right sections, and similarly, the rear portion 14B may also be divided into left and right sections, or there may be any other combination of the above configurations.

-11 -Although the]iner 14A, 14B is shown having a continuous solid inner surface, it may be provided with channels formed therein to provide an air gap at portions over the pilot's head to allow air to circulate therethrough and improve cooling of the pilot's head.

Claims

Claims 1. A helmet for an aircraft pilot comprising an inner shell, a liner attached to the inner shell configured to closely contact the pilot's head, and adjustable tensioning means disposed at the rear of the helmet configured to tension the inner helmet and liner onto the pilot's head, to secure and locate the helmet in place on the pilot's head.
2. A helmet according to claim I wherein the adjustable tensioning means is configured to tension the inner helmet and liner onto the pilot's head between points located proximate the left and right of the outward curve of the pilot's skull proximate the nape of the pilot's neck, and at the pilot's forehead.
3. A helmet according to claim I or claim 2 wherein the adjustable tensioning means comprises first and second tensioning elements moveably attached to the left and right sides of the inner shell respectively, and in contact with the pilot's head, and operable to be biased against the pilot's head.
4. A helmet according to claim 3 wherein the adjustable tensioning means further comprises an adjustment member operable to cause the first and second tensioning elements to be biased against the pilot's head.
5. A helmet according to claim 4 wherein the adjustment member extends between and is secured to the first and second tensioning elements.
6. A helmet according to claim 4 wherein an adjustment member extends between the first tensioning element and the inner shell, and another adjustment member extends between the second tensioning element and the inner shell.
7. A helmet according to claim 5 or claim 6 wherein the or each adjustment member comprises a wire or inextensible belt which is adjustable in length.
8. A helmet according to any of claims 3 -7 wherein the first and second tensioning elements comprise an outer shell layer generally co-extensive with the inner shell, and an inner liner layer generally co-extensive with the liner attached to the inner shell.
9. A helmet according to any of claims 3 -8 wherein the first and second tensioning elements comprise discrete elements separate from one another.
10. A helmet according to any of claims 3 -8 wherein the first and second tensioning elements are joined together by a bridging section such that together with said bridging section, the first and second tensioning elements comprise a unitary member.
11. A helmet according to any of claims 3 -10 wherein the first and second tensioning elements are adjustable independently of each other to independently tension the left and right sides of the inner shell and liner onto the pilot's head.
12. A helmet according to any of claims 3 -11 wherein the rear of the helmet includes an upwardly extending recess for allowing the pilot to tilt his head backwards without the helmet abutting against his neck, said first and second tensioning elements being disposed on the left and right sides of the recess respectively.
13. A helmet according to any preceding claim wherein the liner comprises a first portion attached to the front of the inner shell and a separate second portion attached to the rear of the inner shell.
14. A helmet according to claim 13 wherein the rear portion of the liner is divided into two discrete elements respectively disposed on left and right sides of the helmet.
15. A helmet according to any preceding claim wherein the liner includes recessed sections on its inner surface to provide ventilation to the pilot's head. -14-
16. A method of securing a locating a helmet on a pilot's head, the helmet comprising an inner shell, a liner attached to the inner shell configured to closely contact the pilot's head, and adjustable tensioning means comprising first and second tensioning elements at the rear of the helmet moveably attached to the left and right sides of the inner shell respectively, and configured to tension the inner helmet and liner onto the pilot's head, the method comprising placing the helmet on the pilot's head and using the adjustable tensioning means to bias the first and second tensioning elements into contact with the pilot's head to secure and locate the helmet in place on the pilot's head.
17. A method according to claim 16 wherein the method further comprises independently adjusting the first and second tensioning elements.
18. A helmet substantially as hereinbefore described with reference to the accompanying drawings.