AU2020102223B4

AU2020102223B4 - Stretcher loader system

Info

Publication number: AU2020102223B4
Application number: AU2020102223A
Authority: AU
Inventors: David William Chipperfield; Alan Raymond Ross Fear; Gregory Richard Hanlon; Bruce James Robertson; Glenn Newton Secomb
Original assignee: Five Rings Aerospace Pty Ltd
Current assignee: Five Rings Aerospace Pty Ltd
Priority date: 2019-09-13
Filing date: 2020-09-11
Publication date: 2021-06-17
Anticipated expiration: 2028-09-11
Also published as: AU2020102223A4

Abstract

A stretcher loading system for an aircraft is disclosed. The loading system comprises a cabin interface arrangement configured to mount the stretcher loading system to an aircraft cabin, a longitudinal guide arrangement attached to the cabin interface arrangement; and a trolley assembly configured to slidably engage with the longitudinal guide arrangement and moveable along the longitudinal guide arrangement from an extended stretcher receiving position where the trolley assembly engages with a stretcher to a retracted retained position where the stretcher is located in the aircraft cabin and loaded in the aircraft.

Description

STRETCHER LOADING SYSTEM PRIORITY DOCUMENTS

[0001] The present application claims priority from Australian Provisional Patent Application No. 2019903424 titled "STRETCHER LOADING SYSTEM" and filed on 13 September 2019, the content of which is hereby incorporated by reference in its entirety.

TECHNICAL FIELD

[0002] The present invention relates to the transport of patients by stretcher. In a particular form, the present invention relates to a system for loading a stretcher onto an aircraft.

BACKGROUND

[0003] It is often a requirement to transport a sick or injured patient to a medical facility by an aircraft. In many cases, once a patient has been stabilised and placed in a stretcher it is important that they remain in the stretcher during the transport to the medical facility to minimise the risk of further deterioration of the patient. In cases requiring air transport, typically a patient will be placed into a stretcher by ambulance personnel and then transported to the aircraft by the ambulance at which stage the stretcher will then need to be loaded onto the aircraft. When the aircraft arrives at its destination, this process is carried out in reverse requiring the stretcher to be unloaded from the aircraft and then loaded into a waiting ambulance for transport to a medical facility. Alternatively, the aircraft may fly directly to the medical facility and the stretcher will be unloaded into the care of medical personnel.

[0004] Any airborne stretcher loading system will need to meet relevant airworthiness standards for structural integrity and ideally be compatible with stretcher loading systems and stretchers used by ambulances. An important overall consideration for any airborne stretcher loading system is that the weight of system be reduced where possible as the aircraft will often have a restricted payload and it may be necessary to transport additional medical equipment with the patient as well as medical personnel. In addition, reducing the weight of the stretcher loading system potentially allows an aircraft to carry more fuel, as a result increasing the operable range of the aircraft which can be an important consideration when the aircraft is servicing remote areas.

[0005] It is against this background that there is a need for an airborne stretcher loading system having a reduced weight which is compatible with the loading systems and stretchers used by corresponding ambulances.

SUMMARY

[0006] In a first aspect, the present disclosure provides a stretcher loading system for an aircraft, comprising: a cabin interface arrangement configured to mount the stretcher loading system to an aircraft cabin; a longitudinal guide arrangement attached to the cabin interface arrangement; and a trolley assembly configured to slidably engage with the longitudinal guide arrangement and moveable along the longitudinal guide arrangement from an extended stretcher receiving position where the trolley assembly engages with a stretcher to a retracted retained position where the stretcher is located in the aircraft cabin and loaded in the aircraft.

[0007] In another form, the trolley assembly includes a powered lifting arrangement to assist engagement of the trolley assembly with the stretcher for loading the stretcher in the aircraft.

[0008] In another form, the cabin interface arrangement comprises a base plate assembly for direct attachment to a cabin floor of the aircraft cabin.

[0009] In another form, the cabin interface arrangement comprises: a base plate assembly for attachment of the longitudinal guide arrangement; and a turntable assembly for attachment to a cabin floor of the aircraft cabin, and wherein the base plate assembly is rotatable with respect to the turntable assembly.

[0010] In another form, the base plate assembly and the turntable assembly comprise cooperating disc shaped portions to allow rotation of the base plate assembly with respect to the turntable assembly.

[0011] In another form, the turntable assembly is moveable across the cabin floor to translate the position of the stretcher loading system with respect to the cabin floor.

[0012] In another form, the turntable assembly is moveable along track members attached to the cabin floor.

[0013] In another form, the combined weight of the system is less than 105 kg.

[0014] In another form, the combined weight of the system is less than 115 kg.

[0015] Ina second aspect, the present disclosure provides a method of loading a stretcher into an aircraft, using the stretcher loading system of any one of the preceding claims, comprising moving the trolley assembly along the longitudinal guide arrangement to the stretcher receiving position; engaging the stretcher to the trolley assembly; and moving the trolley assembly along the longitudinal guide arrangement to the retracted retained position so that the stretcher is located in the aircraft.

[0016] In another form, engaging the stretcher to the trolley assembly comprises: suspending the stretcher from the trolley assembly to allow a wheel assembly of the stretcher to be retracted for loading in the aircraft.

[0016a] In another aspect, the present disclosure provides an aircraft cabin based stretcher loading system for an aircraft, comprising: a cabin interface arrangement configured to mount the stretcher loading system to the aircraft cabin; a longitudinal guide arrangement attached to the cabin interface arrangement; and a trolley assembly configured to slidably engage directly with the longitudinal guide arrangement and moveable along the longitudinal guide arrangement from an extended stretcher receiving position where the trolley assembly engages with a stretcher to a retracted retained position where the stretcher is located in the aircraft cabin and loaded in the aircraft, wherein the trolley assembly includes a powered lifting arrangement to assist engagement of the trolley assembly with the stretcher for loading the stretcher in the aircraft.

BRIEF DESCRIPTION OF DRAWINGS

[0017] Embodiments of the present disclosure will be discussed with reference to the accompanying drawings wherein:

[0018] Figure 1 is a top perspective view of a stretcher loading system showing a loaded stretcher as mounted to an aircraft cabin in accordance with an illustrative embodiment;

[0019] Figure 2 is a top perspective view of the stretcher loading system illustrated in Figure 1 again showing a loaded stretcher in accordance with an illustrative embodiment;

[0020] Figure 3 is a top perspective view of the stretcher loading system illustrated in Figure 2 without a loaded stretcher in accordance with an illustrative embodiment;

[0021] Figure 4 is an exploded view of the stretcher loading system illustrated in Figure 3 in accordance with an illustrative embodiment;

3a

[0022] Figure 5 is a top perspective view of a base plate assembly forming part of the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment;

[0023] Figure 6 is an underside perspective view of the base plate assembly illustrated in Figure 5;

[0024] Figure 7 is a top perspective view of a turntable assembly arrangement forming part of the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment;

[0025] Figure 8 is an underside perspective view of the turntable assembly illustrated in Figure 7;

[0026] Figure 9 is a top perspective view of a longitudinal guide arrangement forming part of the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment;

[0027] Figure 10 is a underside perspective view of a longitudinal guide arrangement forming part of the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment;

[0028] Figure 11 is a top perspective view of the trolley assembly forming part of the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment;

[0029] Figures 12 through 14 show top perspective views of the stretcher loading system illustrated in Figure 1 being rotated through 90 in accordance with an illustrative embodiment;

[0030] Figure 15 is a top perspective view of the stretcher loading system illustrated in Figure 14 following a lateral translation in accordance with an illustrative embodiment; and

[0031] Figures 16 through 19 show side views demonstrating the loading sequence of a stretcher using the stretcher loading system illustrated in Figures 1 to 4 in accordance with an illustrative embodiment.

[0032] In the following description, like reference characters designate like or corresponding parts throughout the figures.

DESCRIPTION OF EMBODIMENTS

[0033] Referring now to Figures I to 4, there are shown various views of a stretcher loading system 100 for an aircraft according to an illustrative embodiment. Throughout this specification, the term "aircraft" refers to any vehicle capable of flight including, but not limited to airplanes and helicopters.

[0034] Figure 1 depicts stretcher loading system 100 as installed into an aircraft cabin 1000 and being used to secure stretcher 200, wherein in this example stretcher loading system 100 is mounted to laterally extend across cabin floor 1010 between the side walls of the aircraft (not shown). Figure 2 shows stretcher loading system 100 without the aircraft cabin 1000 while Figure 3 shows the stretcher loading system 100 without a stretcher 200 and Figure 4 depicts an exploded view of stretcher loading system 100.

[0035] As will be described below, stretcher loading system 100 is installed by mounting onto aircraft tracks which in this example comprise a series of spaced apart parallel track members 1020 that extend longitudinally along the cabin floor 1010 and which are typically employed for the mounting of seats 300 or cargo and the like. Example seat tracking arrangements that stretcher loading system 100 may be mounted or attached to include seat tracks manufactured by Ancra and Allsafe JungfalkT . In other embodiments, the stretcher loading system 100 may be mounted to customised mounting locations provided on the cabin floor 1010.

[0036] Stretcher loading system 100 comprises a cabin interface arrangement 170 to mount the stretcher loading system 1000 to the aircraft cabin 1000. In this example, cabin interface arrangement 170 includes a base plate assembly 110 which is attached to turntable assembly 120 which in turn is mounted and fixed to cabin floor 1010. In another embodiment, cabin interface arrangement 170 comprises a base plate assembly 110 that is directly attached to the cabin floor 1010.

[0037] Stretcher loading system 100 further comprises a longitudinal guide arrangement or assembly 130 attached to the cabin interface arrangement and a trolley assembly 140 that slidably engages with longitudinal guide arrangement 130 and which is moveable along the longitudinal guide assembly 130 from an extended stretcher receiving position (eg, see Figure 16) where trolley assembly 140 is configured to engage with stretcher 200 (eg, see Figure 17) to a retracted retained position where the stretcher 200 is located in the aircraft cabin 1000 and loaded in the aircraft (eg, see Figures 1, and 19).

[0038] Referring now to Figures 5 and 6, there are shown top and underside perspective views of the base plate assembly 110 forming a component part of the cabin interface arrangement 170 according to an illustrative embodiment. In this example, base plate assembly 110 comprises a rectangular shaped base plate portion 111 having rounded corners 111a and with a length of 1900 mm, a width of 500 mm and a thickness of 13 mm.

[0039] In other embodiments, the base plate portion may have a length of less than 1800 mm, 1800 mm - 1900 mm, 1900 mm - 2000 mm, 2000 mm - 2100 mm, 2100 mm - 2200 mm, or greater than 2200 mm. Similarly, in other embodiments, the base plate portion may have a width less than 480 mm, 480 mm - 490 mm, 490 mm - 500 mm, 500 mm - 510 mm, 510 mm - 520 mm, or greater than 520 mm. Additionally, the base plate portion may have a thickness of less than 12 mm, 12 mm - 12.5 mm, 12.5 mm - 13 mm, 13 mm - 13.5 mm, 13.5 mm - 14.0 mm, or greater than 14.00 mm.

[0040] Base plate assembly 110 further comprises, in this example, four opposed integral seat track or mounting portions 113a, 113b, 113c, 113d spaced to form a rectangular configuration centred at the centre of the base plate portion 111 with a first pair of seat track portions 113a, 113b located at approximately one quarter the length of the base plate portion 111 and on opposed transverse or side edges of base plate portion 111, ie, reflected in a longitudinal mid-line L that divides base plate portion 111 evenly along its width. The second pair of seat track portions 113c, 113d are similarly located at a distance at approximately three quarters the length of the base plate portion 111, effectively reflecting the position of the first pair of seat track portions 113a, 113b about a transverse mid-line T that divides base plate portion 111 evenly along its length (see Figure 5). Seat track portions 113a, 113b, 113c, 113d provide mounting locations to restrain equipment or accessories associated with the stretcher onto the base plate portion 111 such as by use of a restraint strap or other appropriate attachment arrangement.

[0041] Base plate assembly 110 further comprises a centrally disposed spring loaded rotation release actuator 112 located midway along a side edge to control rotation of base plate portion 111 with respect to the aircraft cabin as will be described below. Rotation release actuator 112 in this embodiment includes on its underside two opposed downwardly extending pins or engagement members 112a, 112b (as best seen in Figure 6) which releasably engage with turntable assembly 120 on upward movement of rotation release actuator 112. While in this example, base plate portion 111 has a substantially rectangular shape it would be appreciated that other shapes or profiles may be adopted which accommodate the longitudinal guide arrangement 130.

[0042] In this example, base plate assembly 110 is formed substantially from aluminium or a lightweight aluminium alloy and has a weight of 25 kg. In other embodiments, other lightweight materials may be used including, but not limited to, carbon steel or titanium alloy or other lightweight composite or hybrid materials.

[0043] As can be seen in Figure 6, the underside of base plate assembly 110 comprises a turntable interface portion comprising in this example of a centrally located circular raised disc portion 115 extending downwardly from the underside of base plate portion 111 and opposed part circular or arcuate raised outer guide rails 114 also extending downwardly from the underside of base plate portion and extending laterally between the side edges of base plate portion 111. Raised guide rails 114 are configured to have a common centre to that of circular disc portion 115. Base plate portion 111 further comprises floor pad or support portions 116 located on the underside of each corner of base plate portion 111 and which function to support the stretcher loader by contacting the cabin floor 1010 in operation. In this example, base plate portion 111 further includes reinforcing ribbing members 117 located in each corner region to prevent flexing of base plate portion 111 while maintaining an overall lightweight configuration.

[0044] Referring now to Figures 7 and 8, there are shown top and underside perspective views of turntable assembly 120 which includes a mounting portion 128 for mounting of base plate assembly 110. Turntable assembly 120 in this embodiment has a rectangular or square configuration and includes a central circular disc shape recess 129 sized to receive the raised circular disc portion 115 extending from the underside of base plate portion 111. Turntable assembly 120 further includes a number of lateral extension members 121 extending from the corners of mounting portion 128 for mounting turntable assembly 120 to the cabin floor 1010. In this example, there are six lateral extension members 121 with two of the corners incorporating only a single extension member while the remaining corner members each incorporate pairs of extension members that extend at 90 degrees with respect to each other from the remaining respective corners of mounting portion 128.

[0045] Each of the lateral extension members 121 includes a slot or guide channel 123 that extends across the extension member 121 and which is flared at its ends. Each guide channel 123 is sized and configured to receive the raised arcuate guide rails 114 that extend from the underside of base plate portion 111 of base plate assembly 110. In this example, turntable assembly 120 has an overall substantially square shape with a length of approximately 700 mm and a width of approximately 800 mm.

[0046] Turntable assembly 120 further includes four pairs of engagement apertures 128a, 128b located respectively on the sides of mounting portion 128. Engagement apertures 128a, 128b are sized, shaped and arranged to receive the corresponding engagement members 112a, 112b located on the underside of rotation release actuator 112 located on base plate assembly 110.

[0047] As can be seen from the underside view of Figure 8, each of the lateral extension members 121 includes a series of downwardly extending securing members 126 which engage with track members 1020. In this example, securing members 126 slidably mount within the track members 1020 and prevent upward/downward movement of turntable assembly 120 with respect to the cabin floor 1010 in effect securing turntable assembly 120 to cabin floor 1010.

[0048] In this example, turntable assembly 120 includes a spring loaded translation release actuator 122 extending along one edge of mounting portion 128. Located on the underside of translation release actuator is a pair of opposed downwardly extending locking members or plungers 124 which are configured to lock into respective track members 1020 to prevent forward/aft movement of turntable assembly 120. As will be described below, release of locking members 124 from track members 1020 allows slidable movement of turntable assembly 120 along cabin floor 1010.

[0049] While in this embodiment turntable assembly 120 is configured to span four spaced apart track members 1020, turntable assembly 120 may be configured to suit various aircraft seat track configurations and spacing as required by suitably moving the positions of the securing feet 126 on the underside of turntable assembly 120 to align with the required seat track configuration. Turntable assembly 120 further includes a series of structural reinforcing or ribbing members 127 that provide improved structural rigidity without overly affecting the weight of the system.

[0050] As deployed, turntable assembly 120 is secured to the cabin floor 1010 and the base plate assembly 110 is positioned on top of turntable assembly 110 so that the raised disc portion 115 of the base plate assembly 110 is received within the disc recess 129 of turntable assembly 120. Further, in this example, guide rails 114 that extend from the underside of the base plate portion 111 of base plate assembly 110 are received within corresponding guide channels 123 of turntable assembly 120. In this manner, base plate assembly 110 is rotatable with respect to turntable assembly 120 which in turn is fixed to the cabin floor 1010 via track members 1020.

[0051] In this example, turntable assembly 120 is formed substantially from aluminium or a lightweight aluminium alloy and has a weight of 8 kg. In other embodiments, other lightweight materials may be used including, but not limited to, carbon steel or titanium alloy or other lightweight composite or hybrid materials.

[0052] Referring now to Figures 12 to 14, there is shown the rotational capability of stretcher loading system 100 and in particular the operation of the cabin interface arrangement 170 comprising base plate assembly 110 and turntable assembly 120. As shown in Figure 12, stretcher loader system is deployed in a transverse configuration such as would be expected following loading of the stretcher from a side door of the aircraft. To rotate the stretcher loader system, rotation release actuator 112 is released by an operator which allows the base plate assembly 110 to rotate with respect to turntable assembly 120.

[0053] In this example, rotation release actuator 112 functions by raising or lifting the opposed pins or engagement members 112a, 112b from the corresponding engagement apertures 128a, 128b located on mounting portion 128 of turntable assembly 120 to allow rotation of base plate assembly 110 with respect to turntable assembly 120.

[0054] Figure 13 shows the stretcher loading system 100 in a part rotated configuration having been rotated clockwise approximately 45°. As would be appreciated, rotation of the base plate assembly 110 is governed by the fit between the circular raised disc portion 115 and the disc shaped recess 129 of the turntable assembly 120 as further stabilised by the confinement of the guide rails 114 in the corresponding guide channels 123 of turntable assembly 120. Figure 14 shows the stretcher loading system 100 as rotated through 900 to a longitudinal configuration as aligned with the aircraft fuselage.

[0055] In this example, where each pair of engagement apertures 128a, 128b is oriented at 90° with respect to its neighbour, the engagement members 112a, 112b may be seated in the appropriate engagement apertures 128a, 128b to lock the base plate assembly 110 in four different orientations as required. This can allow for transportation of taller patients in the aircraft by allowing the stretcher to be oriented along the aircraft cabin as desired. As would be appreciated, while the rotation arrangement in the present embodiment is configured to be locked in four positions at 90° with respect to each other, other configurations may allow for additional rotated positions of the base plate assembly.

[0056] While in this embodiment the rotational capability is provided by cooperating disc shaped portions in the base plate assembly 110 and the turntable assembly 120, it will be appreciated that other types of rotating arrangements may be adopted. These include, but are not limited to, axle and bearing arrangements, but these may involve additional weight.

[0057] Referring once again to Figures 7 and 8, cabin interface arrangement 170 in this example also includes a translational capability in addition to the rotational capability referred to above. Considering once again the underside view of Figure 8, turntable assembly 120 incorporates a series of roller elements 125 dispersed across mounting portion 128 and lateral extension members 121. Rollers 121 are all aligned in the same direction to allow translational movement of turntable assembly following actuation of spring loaded translation release actuator 122.

[0058] Referring now to Figures 14 and 15, there is shown the translation capability of stretcher loading system 100 and in particular the ability of the turntable assembly to be moved along track members 1020 across cabin floor 1010. To move stretcher loading system 100 along track members 1020, translation release actuator 122 is manually raised by an operator in the process raising translation locking members or plungers 124 (as best shown in Figure 8) from a respective track member 1020 allowing turntable assembly 120 and as a result stretcher loading system 100 to be manually translated along the track members 1020 due to the slidable engagement between the securing feet 126 and respective track members 1020 as shown in Figure 15.

[0059] As would be appreciated, the capability of the cabin interface arrangement to allow translation of the stretcher loading system 100 along a track member allows an operator to place the stretcher within the aircraft cabin in a convenient location to increase the utility of the aircraft cabin space. In one example, a first stretcher loading system could be loaded and moved to provide space for a second stretcher loading system to be deployed in the aircraft cabin if space permits.

[0060] In another embodiment, cabin interface arrangement 170 is configured to allow tilting of the base plate assembly 110 with respect to the aircraft cabin by incorporating a hinge arrangement between the turntable assembly 120 and base plate portion 111 in order to assist in unloading and loading of a stretcher.

[0061] Referring now to Figures 9 and 10, there are shown detailed top and underside perspectives views of the longitudinal guide arrangement 130 according to an illustrative embodiment. Guide arrangement 130 comprises a guide rail or beam member 131 whose length substantially corresponds to the length of plate member 110 which in this example is at least 1900 mm in length and has a stretcher retracted end 135 and a stretcher receiving end 136. Guide rail 131 is secured to the base plate portion 111 of base plate assembly 110 at multiple locations by longitudinal spaced apart mounting ribs 137 which each extend laterally along the underside of beam member 131. Guide rail 131 includes two vertically oriented opposed channels 132 configured to receive roller wheels of trolley assembly 140 as is described below.

[0062] Longitudinal guide arrangement 130 incorporates a trolley locking arrangement to restrain movement of the trolley assembly 140 at the stretcher retracted end 135 once the stretcher is loaded (eg, see Figure 19) which in this embodiment involves a hook (not shown) that extends upwards from slot 133 to engage with the trolley 140 and prevent forward movement. Guide arrangement 130 further includes a stretcher locking arrangement which in this embodiment comprises locking jaws 134 which engage with a corresponding locking location on the stretcher 200 and similarly prevents forward movement. Both the trolley and stretcher locking arrangements may be released by an actuator 138 located at the stretcher receiving end 136. In this manner, stretcher 200 may be safely stowed and locked once it has been loaded into the aircraft and then released to deliver the patient from the aircraft.

[0063] In this example, longitudinal guide arrangement 130 is formed substantially from aluminium or a lightweight aluminium alloy and has a weight of 30 kg. In other embodiments, other lightweight materials may be used including, but not limited to, carbon steel or titanium alloy or other lightweight composite or hybrid materials. As would be appreciated, the use of a single longitudinal guide arrangement as compared to prior art arrangements involving multiple cooperating sliding members to which the trolley assembly is then attached not only weighs less than these prior art arrangements but has enhanced structural stiffness.

[0064] Referring now to Figure 11, there is shown a detailed top perspective view of a trolley assembly 140 according to an illustrative embodiment. Trolley assembly 140 includes in this example a pair of opposed powered arms 143 extending from the trolley body 141 which may be raised upwardly to support the stretcher to assist engagement of the stretcher 200 with the trolley assembly 140 for loading of the stretcher into the aircraft cabin (eg, see Figure 1). Trolley assembly 140 further includes stretcher latching or locking arrangement 142 arranged on either side of trolley body 141 which together lock the stretcher 200 to the trolley assembly 140. In this example, trolley assembly 140 is electrically powered, but in other embodiments the powered lifting arrangement may be mechanically powered by springs or hydraulically powered or manually powered or any combination of these options.

[0065] Trolley assembly 140 further includes a receiving channel 146 that is configured to cooperate with the side channels 132 of guide rail 131 by the use of four sets of roller wheels (not shown) positioned in receiving channel 146. This provides for direct slidable movement of the trolley assembly 140 along guide rail 131. While in this embodiment, both guide rail 131 and receiving channel 146 have complementary rectangular profiles it would be appreciated that any inter-engagement arrangement between the trolley assembly and the longitudinal guide arrangement 130 that allows movement of the trolley assembly along the longitudinal guide arrangement 130 may be adopted.

[0066] In this example, trolley assembly 140 includes an integral battery indication system 144 to notify operators of the battery status during operations. The battery system can be changed during operations in the event of a battery failure by accessing the battery compartment 145. In this embodiment, trolley assembly 130 may be removed from guide arrangement 130 by removing stoppers 139 that terminate guide channels 132 and moving sliding trolley assembly 140 towards the stretcher receiving end 136 and off the guide rail 131.

[0067] In this example, trolley assembly 140 and longitudinal guide arrangement 130 are configured for operation with stretchers such as the Power-PRO XT available from Stryker Corporation and has a weight of 47 kg. As would be appreciated, trolley assembly 140 may be configured for operation with other stretcher types which are compatible with the Stryker Power-Load TM loading system. In other examples, trolley assembly 140 may be configured for other types of powered stretcher loading systems.

[0068] Referring now to Figures 16 through 19, there are shown side views of the sequence of steps for loading a stretcher 200 into an aircraft (not shown) adopting a stretcher loading system 100 in accordance with the present disclosure.

[0069] In Figure 16, the trolley assembly 140 is moved along longitudinal guide arrangement 130 to the extended stretcher receiving position and the lifting arms 143 are deployed to the lowered position.

[0070] In Figure 17, the end of the stretcher 200 is positioned over trolley assembly 140 and attached to the trolley 140 by stretcher locking arrangement 142. In this example, where the trolley assembly 140 includes a powered lifting arrangement, the lifting arms 143 are raised until they abut and suspend the stretcher 200 so that the wheel assembly 210 of stretcher 200 may be retracted as shown in Figure 18.

[0071] Following retraction of wheel assembly 210 then the trolley 140 in combination with the attached stretcher 200 may be moved from the extended stretcher receiving position along the longitudinal guide arrangement 130 to the retracted retained position where the stretcher is now located in the aircraft cabin and loaded into the aircraft. In order to remove the patient, the sequence of steps illustrated in Figures 15 to 19 is carried out in reverse in order to remove the patient from the aircraft.

[0072] In one example, where the cabin interface arrangement involves the base plate assembly being directly attached to the cabin floor, the combined weight of the stretcher loading system is less than 105 kg. This is a significantly reduced weight as compared to prior art airborne systems having equivalent capability and in particular those loading systems having multiple cooperating sliding members to which the trolley assembly is attached to. In another example, where the cabin interface arrangement also involves a turntable assembly, the combined weight of the stretcher loading system is less than 115 kg, again representing a significantly reduced weight over prior art airborne systems having an equivalent capability.

[0073] A stretcher loading system in accordance with the present disclosure provides an aircraft with the capability of power loading stretchers commonly used by ground ambulances without compromising the weight requirements of an aircraft (eg, a light aircraft or a helicopter). These power assisted stretcher loading systems significantly increase operator safety by minimising the manual handling elements when compared to traditional non-assisted stretcher loading which requires one or more operators to manually lift the stretcher into the aircraft. In some embodiments, the stretcher loading system also provides increased flexibility by allowing the stretcher to be rotated to a desired orientation and/or the position of the loading system to be shifted on the cabin floor as required.

[0074] Throughout the specification and the claims that follow, unless the context requires otherwise, the words "comprise" and "include" and variations such as "comprising" and "including" will be understood to imply the inclusion of a stated integer or group of integers, but not the exclusion of any other integer or group of integers.

[0075] The reference to any prior art in this specification is not, and should not be taken as, an acknowledgement of any form of suggestion that such prior art forms part of the common general knowledge.

[0076] It will be appreciated by those skilled in the art that the invention is not restricted in its use to the particular application described. Neither is the present invention restricted in its preferred embodiment with regard to the particular elements and/or features described or depicted herein. It will be appreciated that the invention is not limited to the embodiment or embodiments disclosed, but is capable of numerous rearrangements, modifications and substitutions without departing from the scope of the invention as set forth and defined by the following claims.

Claims

1. An aircraft cabin based stretcher loading system for an aircraft, comprising: a cabin interface arrangement configured to mount the stretcher loading system to the aircraft cabin; a longitudinal guide arrangement attached to the cabin interface arrangement; and a trolley assembly configured to slidably engage directly with the longitudinal guide arrangement and moveable along the longitudinal guide arrangement from an extended stretcher receiving position where the trolley assembly engages with a stretcher to a retracted retained position where the stretcher is located in the aircraft cabin and loaded in the aircraft, wherein the trolley assembly includes a powered lifting arrangement to assist engagement of the trolley assembly with the stretcher for loading the stretcher in the aircraft.

2. The stretcher loading system of claim 1, wherein the cabin interface arrangement comprises a base plate assembly for direct attachment to a cabin floor of the aircraft cabin.

3. The stretcher loading system of claim 1, wherein the cabin interface arrangement comprises: a base plate assembly for attachment of the longitudinal guide arrangement; and a turntable assembly for attachment to a cabin floor of the aircraft cabin, and wherein the base plate assembly is rotatable with respect to the turntable assembly.

4. The stretcher loading system of claim 3, wherein the turntable assembly is moveable across the cabin floor to translate the position of the stretcher loading system with respect to the cabin floor.

5. A method of loading a stretcher into an aircraft, using the stretcher loading system of any one of the preceding claims, comprising: moving the trolley assembly along the longitudinal guide arrangement to the stretcher receiving position; engaging the stretcher to the trolley assembly; and moving the trolley assembly along the longitudinal guide arrangement to the retracted retained position so that the stretcher is located in the aircraft.