Quick rope assisted deployment and extraction apparatus

A rapid personnel deployment/extraction rope assisting apparatus for an aircraft includes at least one deployment rope support assembly including a main support member adapted for installation in the aircraft, an assembly arm carried by the main support member and a rope securing mechanism carried by the assembly arm, the rope securing mechanism adapted to secure a rapid personnel deployment/extraction rope/cable to the assembly arm.

FIELD OF THE INVENTION

Illustrative embodiments of the disclosure are generally directed to rapid personnel (deployment and extraction) ropes for aircraft. More particularly, illustrative embodiments of the disclosure are directed to a rapid personnel quick rope assisted deployment and extraction apparatus which is readily installable in an aircraft and enables simultaneous rapid deployment and a fixed line extraction of one or more persons from the aircraft.

BACKGROUND OF THE INVENTION

Fast-roping or rappelling is frequently used in military and civilian applications to rapidly deploy personnel from an aircraft to a location below the aircraft. Fast-roping typically involves repelling down a rope which is suspended from a support frame in a helicopter. The personnel may descend the rope either by gripping the rope or by using a brake-assisted descent mechanism. Under some circumstances, such as in various military exercises, for example, deployment of multiple persons in rapid succession from the aircraft to the accessed location may be necessary.

Therefore, a quick rope assisted deployment and extraction apparatus which is readily installable in an aircraft and enables simultaneous rapid deployment of one or more persons from the aircraft may be desirable for some applications. This apparatus may also be used to extract one or more persons connected to a fixed line. Lifting cargo on a fixed line may also be used.

SUMMARY OF THE INVENTION

Illustrative embodiments of the disclosure are generally directed to a rapid personnel deployment and extraction rope assisting apparatus for an aircraft. An illustrative embodiment of the apparatus includes at least one deployment rope support assembly including a main support member adapted for installation in the aircraft, an assembly arm carried by the main support member and a rope securing releasable/mechanism carried by the assembly arm, the rope securing mechanism adapted to secure a rapid deployment or extraction rope to the assembly arm.

DETAILED DESCRIPTION

Referring to the drawings, an illustrative embodiment of the quick rope assisted deployment and extraction apparatus, hereinafter apparatus, is generally indicated by reference numeral1. As illustrated inFIG. 4and will be hereinafter further described, the apparatus1is adapted for installation in an aircraft50such as a helicopter. The apparatus1facilitates suspension of one or more rapid personnel deployment ropes58from the aircraft50to enable one or multiple operators to fast-rope or rappel down the rapid personnel deployment rope or ropes58to a location beneath the aircraft50. The various components of the apparatus1can be fabricated using aluminum, carbon fiber composite, stainless steel, any combination thereof or other materials which are consistent with the functional requirements of the apparatus1. In exemplary application, which will be hereinafter described, the apparatus1may be mounted on an aircraft floor2and attached to an aircraft sidewall10of the aircraft50using existing OEM attachment points.

At least one deployment rope support assembly16is mounted to the aircraft floor2of the aircraft50. In some embodiments, a pair of deployment rope support assemblies16may be provided adjacent, spaced-apart relationship to each other. A walk surface5extends between the deployment rope support assemblies16. Each deployment rope support assembly16may include a generally elongated main support member17which is upward-standing any length from the walk surface5. A main support member foot18may attach the main support member17to the aircraft floor2. An assembly arm19is supported by the main support member17. The assembly arm19may be generally elongated, with a rear arm end20and a front arm end21which is oriented towards the front end of the aircraft floor2. This assembly arm19may also be mounted out either side of the aircraft50. The assembly arm19may be generally perpendicular to the main support member17. The assembly arms19of the respective deployment rope support assemblies may be disposed beneath the ceiling of the aircraft50.

In some embodiments, an assembly arm collar30may extend downwardly from the assembly arm19. The assembly arm collar30receives and accommodates the upper end of the main support member17. In some embodiments, the assembly arm collar30may be attached to the main support member17via pins, mechanical fasteners, welding and/or other suitable attachment technique. A rear arm brace31and a front arm brace31amay extend between the assembly arm19and the assembly arm collar30for reinforcement purposes. In some embodiments, at least one assembly arm connecting cross member44(FIG. 1) may connect the assembly arms19to each other. A handle22may be provided at the front arm end21of the assembly arm19of each deployment rope support assembly16.

In some embodiments, a tensioned rear side anchor cable/link38may attach to and extend between the rear arm brace31and an aircraft wall mount13. The rear-side anchor cable38maintains a downward tension/compression of the assembly arm collar30on the main support member17. A tensioned front anchor cable40may attach to and extend between the front arm brace31aand the floor2. The front anchor cable40may attach to a cable attachment hook41which is threadably or otherwise attached to the aircraft floor2. The front anchor cable40exerts a forward tension on the assembly arm19and reinforces the load-bearing capacity of the assembly arm19.

In some embodiments, a brace member34may angle from the assembly arm19to the aircraft floor2. A brace member foot35may attach the brace member34to the OEM mount location(s) to the aircraft floor2. In some embodiments, the brace member34may be pivotally attached to the brace member foot35. An anchor cable collar36may be provided on the brace member34. A tensioned tensioning cable or link37may attach to and extend between the brace member foot35and the anchor cable collar36. The tensioning cable or link37causes the brace member34to exert a forward tension on the assembly arm19and reinforces the load-bearing capacity of the assembly arm19.

A rope securing mechanism28is provided on the assembly arm19. The rope securing mechanism28may include any type of mechanism which is suitable for attaching the rapid personnel deployment rope58to the assembly arm19in a secure manner. As used herein, “rapid personnel deployment rope” includes but is not limited to a rope, cable, line or wire. In some embodiments, the rope securing mechanism28may include a rope clearance opening23which is provided in the underside of the assembly arm19generally adjacent to the rear arm end20. A rope attachment member24may be provided on the assembly arm19at the rope clearance opening23. The rope attachment member24may be pivotally or slidably attached to the assembly arm19, via a rope attachment member pivot pin26, at a rope attachment member slot25to selectively open and close the rope clearance opening23. A release mechanism attached to handle22to open rope attachment24may have a member lock27that can be detached/or selectively locked so that handle22can be pulled to release attachment24. Accordingly, as illustrated inFIG. 5, in some applications of the apparatus1, the rapid personnel deployment/extraction rope58may terminate in a loop59which engages the rope attachment member24to securely attach the rapid personnel deployment/extraction rope58to the assembly arm19. The rope attachment member24may be unlocked via the rope attachment member lock27and pivoted at the rope attachment member pivot26to open the rope attachment member24and facilitate placement of the loop59around the rope attachment member24. The rope attachment member24may be pivoted and locked in place to secure the loop59to the rope attachment member24as the loop59extends through the rope clearance opening23. In other embodiments, the rapid personnel deployment rope58may be attached to the rope attachment member24via a hook, clamp/ring or other mechanical device which is suitable for the purpose.

Referring next toFIG. 4of the drawings, in exemplary application, the apparatus1is installed in an aircraft50such as an MI-8 or an MI-17 helicopter, for example and without limitation. The aircraft50may include a fuselage51with a rear opening52, runners53and a rotor54. The apparatus1is installed in the aircraft50facing the rear or opening52, at the rear of the fuselage51and the front end4of the aircraft floor2facing the front end of the fuselage51. The deployment rope support assemblies16may be installed to the aircraft floor2and the aircraft sidewall10using existing OEM fixture attachment points (not illustrated) for the main support member feet18, the brace member feet35and the cable attachment hooks41. A pair of rapid personnel deployment ropes58is attached to the assembly arms19of the respective deployment rope support assemblies16typically as was heretofore described with respect toFIG. 5.

The aircraft50is maneuvered over a target location (not illustrated) to which multiple operators are to be rapidly deployed via the rapid personnel deployment ropes58. The rapid deployment ropes58are suspended from the apparatus1through the rear or side opening52of the aircraft50. Each operator who is to descend one of the rapid deployment/extraction ropes58initially walks on the walk surface5of the aircraft floor2between the deployment rope support assemblies16. That operator will deploy out of the aircraft50using the apparatus1to help guide himself or herself safely to the intended target location. Once all personnel are off the rapid deployment rope58, one of the remaining personnel in the aircraft grasps the handle22on the assembly arm19with one hand and then releases the handle22to drop the rapid deployment rope58. The operator then descends the rapid deployment rope58to the target location by either fast roping down the rope58using his or her hands or using a brake-assisted descent (rappelling) mechanism known by those skilled in the art and releases the rope58or mechanism to conduct the operation. Multiple operators may successively descend each rapid deployment rope58in like manner to provide sufficient personnel for the operation. In some embodiments, the dual deployment rope support assemblies16of the apparatus1enables two operators to simultaneously descend each rope to facilitate rapid deployment of the personnel for the operation.

It will be appreciated by those skilled in the art that the apparatus1enables operators to rapidly descend the rapid deployment ropes58using any of a variety of techniques which are known for the purpose. For example, in some applications, each operator can use a bare-handed technique (fast roping) to slide down a rapid deployment rope58. In other applications, each rapid deployment rope58may be a traditional rappel line in which each operator uses a brake-assisted descent mechanism fitted with a harness to insert from the aircraft50to the target location. In some applications, the rapid personnel deployment ropes58may be used to lower cargo, gear or equipment from the hovering aircraft50to the target location. Extraction methods may also be used.

It will be appreciated by those skilled in the art that the apparatus1can be readily installed in an aircraft50without the need to modify the airframe of the aircraft50. The deployment rope support assemblies16can be installed using six (6) internal OEM aircraft anchor points in as little as 10 minutes. The rear “clam-shell” doors of the aircraft50can be re-installed and secured with the apparatus1in the operations position. Rear ingress/egress of the aircraft50is not limited by installation of the apparatus1. The apparatus1can be installed and used with internal AUX fuel tanks installed. The apparatus1requires minimal use of cargo space and does not interfere with aircraft controls.

While the illustrative embodiments of the disclosure have been described above, it will be recognized and understood that various modifications can be made in the disclosure and the appended claims are intended to cover all such modifications which may fall within the spirit and scope of the disclosure.