AU2011200503A1 - Aircraft strecher assembly - Google Patents

Abstract

An aircraft stretcher assembly including: a mounting assembly mountable to a deck of the aircraft in juxtaposition with an opening in the fuselage; a stretcher supporting 5 platform mounted to the mounting assembly for relative sliding movement with respect to said mounting assembly; and said stretcher supporting platform having stretcher securing means for securing a stretcher to said stretcher supporting platform. 21' 18 < Figi , N 16 .~NI, Fig2

Description

AIRCRAFT STRETCHER ASSEMBLY FIELD OF INVENTION THIS INVENTION relates to an aircraft stretcher assembly. The invention is primarily directed to an aircraft stretcher assembly for loading stretchers onto helicopters and securing such stretchers for transport. However, the invention may have application to other types of aircraft that have a hovering capability. BACKGROUND ART Stretchers used in helicopters for transporting patients such as, for example, from rescue sites to hospital, may be winched to and from a helicopter from a boom extending abeam the cockpit of the helicopter. In order to load the stretcher onto the helicopter, rescue personnel normally lean outward from the cockpit to manhandle the stretcher from outboard of the helicopter onto the cockpit. Such a procedure is dangerous for the rescue personnel. If the aircraft is landed, the stretcher may be brought to and loaded into the cockpit which may require rescue personnel to lean inward from the ground into the cockpit. Such a procedure can pose a problem from a workplace health and safety point of view. Additionally, considerable physical strength may be required if the patient and/or support equipment are heavy.

2 The present invention aims to provide an aircraft stretcher assembly which alleviates one or more of the problems associated with the prior art. Other aims and advantages of the invention may become apparent from the ) following description. With the foregoing in view, the present invention in one aspect resides broadly in an aircraft stretcher assembly including: a mounting assembly mountable to a deck of the aircraft in juxtaposition with an opening in the fuselage; a stretcher supporting platform mounted to the mounting assembly for relative sliding movement with respect to said mounting assembly; and said stretcher supporting platform having stretcher securing means for securing a stretcher to said stretcher supporting platform. In another aspect, the present invention resides broadly in a method of loading a stretcher onto an aircraft including: providing an aircraft stretcher assembly having a mounting assembly mounted to a deck of the aircraft in juxtaposition with an opening in the fuselage, a stretcher supporting platform mounted to the mounting assembly for relative sliding movement with respect to said mounting assembly and securing 3 means on said stretcher supporting platform for securing a stretcher thereto; sliding said stretcher supporting platform outward from the aircraft through the opening in the fuselage to an 5 outboard position substantially outside of the aircraft; receiving a stretcher onto said stretcher supporting platform when in said outboard position; securing said stretcher to said stretcher supporting platform; and sliding said stretcher supporting platform back through J the opening to a position inboard of the aircraft. Preferably, the relative sliding movement is provided by sliding means formed onto or into said mounting assembly and arranged for sliding of the stretcher supporting platform across the aircraft along a beam axis. Preferably, the mounting assembly also includes pivoting means formed to provide relative pivoting movement between the mounting assembly and the stretcher supporting platform about an axis substantially perpendicular to the deck to which the mounting assembly is mounted. 0 Preferably, the mounting assembly includes deck fixing formations for fixing the mounting assembly to the deck. Preferably, the deck fixing formations are formed for mounting the mounting assembly to the seat mounting tracks of the aircraft.

4 Preferably, the stretcher supporting platform includes a substantially planar portion on which a stretcher may be supported. In such form, it is preferred that said stretcher securing means be moveable between a retracted position 5 substantially below the plane of the planar portion and a securing position whereat at least some of the stretcher securing means is above the plane of the planar portion whereby the stretcher may be secured onto the planar portion by operative engagement of complementary securing means on the 0 stretcher with the securing means of the stretcher supporting platform. In order that the invention may be more readily understood and put into practical effect, two preferred embodiments of the present invention will now described with reference to the 5 following drawings, and wherein: Fig. 1 is a pictorial view of a pivotable aircraft stretcher assembly according to the invention in a keel wise orientation. Fig. 2 is a pictorial view of the stretcher assembly of 0 Fig. 1 in an intermediate orientation; Fig. 3 is a pictorial view of the stretcher assembly of Fig. 1 in an abeam orientation; Fig. 4 is a pictorial view of a non-pivoting aircraft stretcher assembly according to the invention; 5 Fig. 5 is a pictorial view of the stretcher assembly of Figs. 1 to 3 with a stretcher disconnected from the remainder of the stretcher assembly; Fig. 6 is a pictorial view of the stretcher assembly of 5 Fig. 4 with the stretcher disassembled from the remainder of the stretcher assembly; Fig. 7 is a detailed view of the pivoting action of the pivotable aircraft stretcher assembly of Fig. 1; Fig. 8 is a detailed pictorial view of a stretcher locking 9 mechanism in an unlocked position; Fig. 9 is a pictorial view of the stretcher locking mechanism of Fig. 8 in an intermediate position; Fig. 10 is a pictorial view of the stretcher locking mechanism of Fig. 8 in a locked position; 5 Fig. 11 is a pictorial view showing detail of. the stretcher assembly of Fig. 4 at an inboard position; Fig. 12 is a pictorial view of a stretcher assembly of Fig. 1 detailing its mounting to the seat rails of an aircraft; 0 Fig. 13 is a pictorial view of the stretcher assembly of Fig. 4 showing detail of its mounting to the floor of an aircraft; 6 Fig. 14 is a pictorial view of the stretcher assembly of Fig. 12 with the stretcher removed from the remainder of the assembly; Fig. 15 is a pictorial view of the stretcher assembly of 5 Fig. 12 with a stretcher and a stretcher support removed from the remainder of the stretcher assembly; Fig. 16 is a view of the underside of the remainder of the stretcher assembly shown in Fig. 15; Fig. 17 is a pictorial view of the stretcher assembly of ) Fig. 13 with the stretcher and a stretcher support removed from the remainder of the stretcher assembly; Fig. 18 is a view of the underside of a stretcher support platform for the aircraft stretcher assembly of Figs. 1 and 4; Fig. 19 is a detailed end view of the stretcher support platform of Fig. 23; Fig. 20 is a pictorial view of a ground interface assembly for the pivotable aircraft stretcher assembly of Fig. 1; Fig. 21 is a pictorial view of the ground interface of 0 Fig. 20 in a folded attitude; Figs. 22 and 23 are a pictorial and elevation views of the ground interface showing its use with the pivotable 7 aircraft stretcher assembly of Fig. 1 with respect to an aircraft; and Figs. 24 to 27 are four comparative pictorial views showing the pivotable aircraft stretcher assembly of Fig. 1 with a range of different loads. The pivotable aircraft stretcher assembly 10 shown in Fig. 1 includes a stretcher 11 mounted to a stretcher supporting platform 12 which in turn is mounted to a pivotable mounting assembly 13. The pivotable mounting assembly is fixed to the deck 14 of an aircraft shown diagrammatically at 15. The stretcher has a head end 16 heading towards the forward end of the aircraft and a foot end at the opposite end of the head end towards the arc of the aircraft, the forward direction of the aircraft being indicated by arrow 18. The pivotable aircraft assembly is shown in Figs. 2 and 3 pivoted from the travelling attitude shown in Fig. 1 to an intermediate attitude shown in Fig. 2 and further to a loading attitude shown in Fig. 3. The non-pivotable aircraft stretcher assembly 20 shown in Fig. 4 has the same stretcher 11 and stretcher supporting platform 12 as the pivotable aircraft stretcher assembly shown in Figs. 1 to 3. However, the stretcher supporting platform is mounted to a non-pivotable mounting assembly 23, the stretcher being aligned the aircraft for both loading and transport.

8 Since the stretcher assembly is non-pivotable, two forward facing passenger seats 21 may be provided as opposed to a single forward facing passenger seat in the case of the pivotable aircraft stretcher assembly shown in Figs. 1 to 3. 5 The aircraft stretcher assembly shown in Figs. 5 and 6 have the stretcher removed from the stretcher supporting platform by sliding in the direction of arrow 19 in a direction the aircraft. The stretcher is constrained for sliding movement with J respect to the stretcher supporting platform by a pair of slide rails 24 extending part way along the side edges of the stretcher platform, ending about one quarter the length of the stretcher supporting platform from each end. A stretcher locking mechanism 25 is provided at each end of the stretcher 5 supporting platform and is shown in more detail in Fig. 8. Each stretcher locking mechanism includes an end plate 26 which has two apertures 27 spaced inwardly from its edges spaced from one another a distance equivalent to the distance between two locking lugs 28 provided at each end of the 0 stretcher, the locking lugs being sized for insertion into the apertures. The end plates are pivotable between an upright attitude shown at the head end of the stretcher supporting platform and a flat attitude shown at the foot end of the stretcher 9 supporting platform, the locking mechanism at the foot end of the stretcher mounting platform being so oriented to permit the sliding of the stretcher along the stretcher supporting platform in the direction of arrow 19 as previously described. The end plate pivots along a pivot edge 29 whereby the stretcher maybe slid out from engagement on the stretcher mounting platform by the side rails either towards the foot end or the head end. The detail shown in Fig. 7 shows the pivot assembly for pivoting the stretcher supporting platform about an axis normal to the deck. A pivot lock lever 31 locks the stretcher supporting platform at indexed locations angularly between the beam attitude and the travelling attitude. The pivoting of the stretcher supporting platform is effected by lifting the pivot lock lever in the direction of arrow 32. The locking mechanism is shown in more detail in Figs. 8, 9 and 10 where it can be seen that the hinge permits pivoting of the end plate with respect to the remainder of the stretcher supporting platform is in two parts, each part being aligned axially to provide the hinge pivoting movement of the end plate. The aircraft stretcher assembly shown in Fig. 11 has been moved from the outboard position shown in Figs. 8, 9 and 10 to an inboard position by relative movement with respect to the 10 aircraft in the direction of arrow 33. The lateral movement of the stretcher supporting platform (and the stretcher when mounted thereto) is common to both the pivoting and non pivoting versions of the aircraft stretcher assembly. 5 The pivotable stretcher assembly shown in Fig. 12 is mounted to the deck of the aircraft by four seat track studs 34 (two of which can be seen in Fig. 12) . Respective pairs of seat track studs engage with a seat track 35, two being shown in Fig. 12, being seat tracks mounted typically in the deck of an aircraft for mounting seats thereby. The non-pivotable mounting assembly has four seat track studs being the same in every respect as the seat track studs of the pivotable mounting assembly, but being spaced further apart for engagement with respective parallel seat tracks being further apart then the seat tracks illustrated in the case of the pivotable aircraft stretcher assembly shown in Fig. 12. The stretcher supporting platform shown in Fig. 14 shown in greater detail the side rails. The side rails are connected to a platform base 30 by a pair of spaced side rail hinges near the respective ends of each side rail, the pivoting action of the side rails being controlled by a side rail lock 22 substantially in the middle of the length of the side rails for locking the side rails in a stretcher securing attitude shown in Fig. 14 with the side rails extending above the platform base.

11 The pivotable mounting assembly 13 shown in Fig. 15 has a frame assembly 37 of rectangular form mounted to a base plate 38. Three pairs of rollers 39 are mounted to extend beyond the longitudinal side edges of the base plate. The longitudinal 5 side edges of the stretcher supporting platform include C shaped rails spaced at sufficient distance for the open size of each C-section to face one another for engagement with the aligned pairs of rollers on the frame assembly. Two pairs of rollers are mounted at or near the ends of the frame assembly and the remaining pair mounted intermediate the end rollers, but offset from the centre of the side edges. The pivot mounting assembly 13 shown from beneath in Fig. 16 has a circular pivot base 40 which permits pivoting of the base place with respect to the seat tracks. The non-pivoting mounting assembly shown in Fig. 17 includes a frame assembly which is the same in every respect as the frame assembly of the pivotable mounting assembly with the exception that the base plate and pivot base are not provided, the frame assembly being fixed directly to the seat tracks by the four seat track studs mounted to a rail mounting assembly 41 interposed between pairs of the seat track studs and the ends of the frame assembly. When viewed from the underside as shown in Fig. 18 and end as shown in detail in Fig. 19, it can be seen that the 12 stretcher locking mechanism includes a release button 42 mounted for depression to release the end plate from its locked upright attitude. The release button also acts against a transfer rod 43 which transfers its action to the release button of the other stretcher locking mechanism on the other end of the stretcher supporting platform through a transfer hub 44 which has another transfer rod connected to another release button on the other end of the stretcher supporting platform. Such an arrangement permits both stretcher locking mechanisms to be released at the same time by depressing one of the release buttons. The ground interface 50 shown in Figs. 20 and 21 includes a top frame 51 rectangular in form formed from two side bars 63 in spaced parallel relationship with one another, an end bar 61 between the one end of the side bars and an intermediate cross bar 62 extending from one side bar to the other, but spaced from the other ends of the side bars. For convenience, the end of the ground interface at the end bar will be referred to as the proximal end and the other end will be referred to as the distal end. A sliding pivot leg 53 is attached to the side bars of the frame by a sliding pivot 52. A fixed pivot leg 55 is attached to the side bars at the distal end by a fixed pivot 54. As the ground interface is lowered to its folded attitude illustrated 13 in Fig. 21, the sliding pivots move towards the proximal ends of the side bars. The fixed pivot legs each terminate at their lower ends with a fixed wheel assembly 56. The sliding pivot legs each terminate at their lower ends with a castor wheel assembly 57 which further includes a wheel brake 58. A pair of guide rollers 60 is provided at the proximal end of the top frame, one on the end of each side bar. Six support rollers 59 are provided on the outer edges of the side bars for supporting a platform for the stretcher loader system according to the invention. As illustrated in Figs. 22 and 23, the ground interface may be used to support a platform for the pivotable aircraft stretcher assembly for transport across a floor or ground surface. The height of the top frame of the ground interface is commensurate with the ground clearance of the aircraft 15 such that the guide rollers may engage with the deck of the aircraft and support the weight of the platform and its load when it is slid along the support rollers into the aircraft. The comparative pictorial views showing different loads illustrated in Figs. 24 to 27 show firstly a ground interface with a bare platform 12 supported thereon in Fig. 24, a rescue basket 65 is shown supported on the platform in Fig. 25. A humidicrib 66 is shown supported on the platform in Fig. 26 14 and the stretcher 11 is shown with a bridge assembly 67 across the foot end in Fig. 27. In use, the aircraft stretcher loading system according to the invention has been designed as an effective way of managing the loading, positioning and restraint of a stretcher, patient and equipment within medium sized helicopters such as, for example, the Agusta Westland 139 aircraft. The system provides crew with a stable loading platform which can traverse laterally for loading beyond the aircraft doorway, allowing clear access for lifting and manoeuvring. The design includes two deck interfacing options to allow for either fixed mounting or turntable mounting of the system. Both interface options require no modifications to the aircraft structure and connect directly to existing seat tracking on the cabin floor or deck. Beyond carriage of the standard stretcher, the system has been designed with the consideration of being able to carry other mission specific equipment such as basket stretchers and humidicribs. The Multi-Deck system consists of three major assemblies. These are: a stretcher, a stretcher deck, and a floor interface. The floor interface can exist as either a fixed interface or a turntable interface.

15 The floor interface serves the function of providing direct connection to the airframe and also provides the necessary base features which to allow the stretcher deck to traverse laterally in either direction for the purpose of 5 loading and unloading stretchers or equipment from either side of the aircraft. The interface consists of a composite sandwich panel which contains threaded internal inserts to provide fastening locations for all externally mounted machined fittings. On the upper face of the panel, there are D there are six fittings fastened in place. These fittings perform the function of providing mounting positions for rollers and latch stops as required for the traversing operations of the stretcher deck. On the lower face of the panel, there is provision for the mounting of fittings to suit either a fixed interface or turntable interface. In the instance of the fixed floor interface, the underside of the panel has a foot assembly fastened at each end to facilitate connection to two parallel lengths of seat track running longitudinally in the deck of the aircraft. The ) track interface consists of four groups of seat track studs and four spring loaded track stops. The spring loaded stops are operated via two latch bars (one at each end), which allow the stops to be retracted for the purpose of installation to and removal from the seat track. Each stud and stop grouping (four in total) has an adjacently mounted roller to assist 16 with longitudinal positioning of the assembly (relative to the seat tracks). In the instance of the turntable interface, the interface panel has a turntable assembly fastened to the underside in 5 lieu of the foot assemblies for the fixed interface. The turntable assembly consists primarily of a turntable top, a turntable bearing, and a turntable base. The turntable top utilizes a spring loaded index pin operated by a lifting leaver to provide rotational positioning relative to pre-set ) stops located around the turntable base. In similar fashion to the foot assemblies of the fixed interface, the turntable base facilitates connection to two parallel lengths of seat track running longitudinally in the aircraft. The track interface again consists of four groups of seat track studs and four spring loaded track stops, where each stud and stop grouping (four in total) has an adjacently mounted roller. The spring loaded stops are again operated via two latch bars for the purpose of installation to and removal from the seat track. ] The stretcher deck provides a flat durable surface upon which stretchers or other equipment can be loaded and secured. The stretcher deck consists of a main composite sandwich panel (deck panel) to which numerous machined fittings and assemblies are incorporated. On the top surface of the deck 17 panel, two machined tracks run the full length of the outside edge to provide a means for interfacing future additional equipment to the deck using standard track fittings. The tracks run directly above two (x2) machined rails 5 located on the panel underside and are through fastened in position. The machined rails provide the required running surfaces for traversing along the six floor interface rollers located on the upper side of the interface panel mounted to the aircraft floor as hereinbefore described. o A folding fitting ("centre restraint") provides a connection point for the stretcher centre hardpoints in the centre of each run of track in two locations. Along each side edge of the deck panel, there are two externally mounted composite loading guides ("wing panels") which are profiled to 5 ensure correct positioning of the standard stretcher during loading and unloading operations. All guides and fittings which protrude above the deck surface can be folded or stowed to provide a clear and flat mounting platform suitable for carriage of basket stretchers and other equipment. o Restraint of the stretcher ends is provided by two machined end housings located at each end of the deck panel. The end housings each incorporate a handle operated, hinging end plate assembly, which provides clear loading access and additional loading extension beyond the edge of the deck panel 18 when folded flat about the hinge axis outwards. The folding assembly also provides a means of locking the two barbed pins at located each end of the standard stretcher frame. Each end assembly is interconnected such that operation of the 5 stretcher release handle from either end will release the stretcher pins at both ends simultaneously, allowing the stretcher to be loaded and unloaded from either side of the aircraft. On the underside of the deck panel, two machined rails (as 0 previously described) run the full length of long edges of the panel. In the centre of the lower surface, a spring loaded latching mechanism ("centre latch assembly") is provided which provides a locking connection to fittings located on the previously described interface panel. The centre latch assembly is connected to and operated by any of four push buttons ("traverse buttons") which are located at each corner of the stretcher deck. The buttons are incorporated as part of the two previously described end housings. On the underside of the panel, machined rails run the full 0 length along each side. In the centre of the lower surface, there is a spring loaded latching mechanism (center latch assembly), which provides a locking connection to fittings located on the previously described interface panel. The centre latch assembly is connected to and operated by any of 5 four push buttons (traverse buttons) which are located at each 19 corner of the stretcher deck. The buttons are incorporated as part of the two previously described end housings. The standard stretcher for mounting onto the stretcher deck is based upon conventional tubular stretchers with some 5 additional features incorporated to increase utility and load carrying capabilities. The stretcher has four barbed pins in total, with two located at each end of the stretcher frame to facilitate connection to the previously described end restraints. The stretcher also has two additional centre hard points which connect into the previously described folding fittings located in the middle of the stretcher deck tracks. The stretcher has castor wheels on the underside to allow it to move along the stretcher deck surface as required. There is an adjustable backrest to allow the head of the patient to be elevated as required. The stretcher is provided with a removable four-point shoulder harness for restraint of the upper body of the patient, and an additional leg belt for restraint of the lower body. Additional cut-outs have been placed in the stretcher pans to allow additional chest and crotch belts to be fitted if required. For the purpose of stowage, the stretcher can fold about two hinge lines located intermediate the ends. Although the invention has been described with reference to a specific example, it will be appreciated by those skilled 20 in the art that the invention may be embodied in other forms within the broad scope and ambit of the invention as herein set forth and defined by the following claims.

Claims (9)

1. An aircraft stretcher assembly including: a mounting assembly mountable to a deck of the aircraft in juxtaposition with an opening in the fuselage; 5 a stretcher supporting platform mounted to the mounting assembly for relative sliding movement with respect to said mounting assembly; and said stretcher supporting platform having stretcher securing means for securing a stretcher to said stretcher supporting platform.

2. The stretcher assembly according to Claim 1, wherein the mounting assembly also includes pivoting means formed to provide relative pivoting movement between the mounting assembly and the stretcher supporting platform about an axis substantially perpendicular to the deck to which the mounting assembly is mounted.

3. The stretcher assembly according to Claim 1 or Claim 2, wherein the mounting assembly includes deck fixing formations for fixing the mounting assembly to the deck. 0

4. The stretcher assembly according to Claim 3, wherein the deck fixing formations are formed for mounting the mounting assembly to the seat mounting tracks of the aircraft. 22

5. The stretcher assembly according to any one of the preceding claims, wherein the stretcher supporting platform includes a substantially planar portion on which a stretcher may be supported. 5

6. The stretcher assembly according to Claim 5, wherein said stretcher securing means is moveable between a retracted position substantially below the plane of the planar portion and a securing position whereat at least some of the stretcher securing means is above the plane of the planar portion 0 whereby the stretcher may be secured onto the planar portion by operative engagement of complementary securing means on the stretcher with the securing means of the stretcher supporting platform.

7. A method of loading a stretcher onto an aircraft including: providing an aircraft stretcher assembly having a mounting assembly mounted to a deck of the aircraft in juxtaposition with an opening in the fuselage, a stretcher supporting platform mounted to the mounting assembly for relative sliding movement with respect to said mounting assembly and securing means on said stretcher supporting platform for securing a stretcher thereto; 23 sliding said stretcher supporting platform outward from the aircraft through the opening in the fuselage to an outboard position substantially outside of the aircraft; receiving a stretcher onto said stretcher supporting 5 platform when in said outboard position; securing said stretcher to said stretcher supporting platform; and sliding said stretcher supporting platform back through the opening to a position inboard of the aircraft.

8. The method according to Claim 7, wherein the relative sliding movement is provided by sliding means formed onto or into said mounting assembly and arranged for sliding of the stretcher supporting platform across the aircraft along a beam axis.

9. A stretcher assembly substantially as hereinbefore described with reference to Figs. 1 to 19, 22 and 23. Dated this 5 th day of February, 2011 HELIMODS PTY LTD By its Patent Attorneys AHEARN FOX