Systems for removal of parachute assembly head restraints

A system for translating a head restraint of a parachute assembly away from a head of an occupant supported by the parachute assembly may comprise a chord coupled to the head restraint and at least one of a control line configured to manipulate a canopy of the parachute assembly or a handle coupled to the control line.

FIELD

The present disclosure relates to parachutes, and more specifically, to systems for removal of parachute assembly head restraints.

BACKGROUND

Ejection seats are designed to eject pilots from an aircraft, with the pilot oriented in an generally upright, sitting position. Conventionally, the pilot is released from the ejection seat in response to a main canopy of the ejection seat's parachute assembly deploying. As the canopy catches wind, the pilot may be rotated to orient the pilot in the direction of canopy line stretch. As the pilot is rotated in-line with the force provided by the canopy, there is an increased risk of neck hyperextension and injury due to the change in angular momentum forcing the pilot's head rearward. Head restraints may be provided to limit translation of the pilot's head. However, having the head restraint in place during steady state decent can be uncomfortable and may also restrict a range of motion of the pilot's head, thereby limiting the pilot's sight lines, which can affect his/her ability to look for a clear landing area.

SUMMARY

Disclosed herein is a system for translating a head restraint of a parachute assembly. In accordance with various embodiments, the system may comprise a first control line configured to manipulate a canopy of the parachute assembly, a first handle coupled to the first control line, and a first chord coupled to the head restraint and at least one of the first control line or the first handle.

In various embodiments, the first chord may be located through an opening defined by a riser of the parachute assembly.

In various embodiments, a sleeve may be coupled to a riser of the parachute assembly. The sleeve may be configured to retain the first handle proximate the riser.

In various embodiments, the first control line may comprise a first length extending from the canopy to an attachment point of the first chord to the first control line, and a second length extending from the attachment point to the first handle. In various embodiments, the second length may be configured to be released upon a removal of the first handle from the sleeve. The first chord may be configured to translate the head restraint along the riser upon release of the second length of the first control line.

In various embodiments, a second control line may be coupled to the canopy, and a second chord may be coupled to the head restraint. In various embodiments, the first chord and the second chord may be configured to translate the head restraint along a left shoulder riser and a right shoulder riser of the parachute assembly.

Also disclosed herein is a parachute assembly. In accordance with various embodiments, the parachute assembly may comprise a canopy, a plurality of suspension lines coupled to the canopy, a first riser coupled to a first suspension line of the plurality of suspension lines, a second riser coupled to a second suspension line of the plurality of suspension lines, a head restraint located between the first riser and the second riser, and a head restraint removal system configured to translate the head restraint.

In various embodiments, the head restraint removal system may comprise a cutter configured to sever the head restraint. In various embodiments, a reefing line may be coupled to the canopy, and the head restraint removal system may comprise a coupling between the reefing line and the head restraint.

In various embodiments, the head restraint removal system may be configured to translate the head restraint along the first riser and the second riser. A control line may be configured to manipulate the canopy, and a handle may be coupled to the control line. In various embodiments, the head restraint removal system may comprise a chord coupled to the head restraint and at least one of the control line or the handle.

In various embodiments, the chord may be located through an opening defined by the first riser. In various embodiments, a sleeve may be coupled to the first riser. The sleeve may be configured to retain the handle proximate the first riser. In various embodiments, the control line may comprise a first length extending from the canopy to an attachment point of the chord to the control line, and a second length extending from the attachment point to the handle. The second length may be configured to release upon a removal of the handle from the sleeve. In various embodiments, the head restraint may be configured to translate along the first riser and the second riser in response to the removal of the handle from the sleeve.

Also disclosed herein is a parachute assembly for an ejection seat. In accordance with various embodiments, the parachute assembly may comprise a canopy, a suspension line coupled to the canopy, a riser coupled to the suspension line, and a head restraint configured to translate along the riser.

In various embodiments, a control line may be configured to manipulate the canopy, a handle may be coupled to the control line, and a chord may be coupled to the head restraint and at least one of the control line or the handle.

DETAILED DESCRIPTION

The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosures, it should be understood that other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this disclosure and the teachings herein. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation.

The scope of the disclosure is defined by the appended claims and their legal equivalents rather than by merely the examples described. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to tacked, attached, fixed, coupled, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.

In various embodiments, and with reference toFIG. 1, an aircraft ejection system100is shown, in accordance with various embodiments. Aircraft ejection system100may be installed in aircraft102to safely expel ejection seat106and an occupant110of ejection seat106from a cockpit104of aircraft102. Ejection seat106may be urged from cockpit104by a propulsion system108. Aircraft ejection system100may include a parachute assembly116. In various embodiments, prior to deployment of parachute assembly116, a portion of parachute assembly116may be stored within ejection seat106.

With reference toFIG. 2, parachute assembly116is illustrated in a deployed state, in accordance with various embodiments. Parachute assembly116may be used to increase a drag of, or otherwise decelerate occupant110, in response to occupant110being ejected, jumped, ditched, and/or dropped (collectively, “ejected”) from an aircraft. Parachute assembly116may be configured to deploy upon separation of occupant110from ejection seat106. Stated differently, in various embodiments, deployment of parachute assembly116may be configured to separate occupant110from ejection seat106. Parachute assembly116may comprise a canopy126, suspension lines122, and risers120.

Upon deployment of parachute assembly116, canopy126may open to increase drag, or otherwise decelerate, occupant110. Canopy126may comprise any suitable type of canopy and any suitable type of material, such as, for example, canvas, silk, nylon, aramid fiber (e.g., KEVLAR®), polyethylene terephthalate, and/or the like. Suspension lines122may be coupled to canopy126using any suitable attachment technique, such as, for example, through stitching. Suspension lines122may be configured to at least partially stabilize deployed canopy126. In various embodiments, parachute assembly116may include one or more reefing line(s)124. Reefing line124may be coupled to canopy126proximate a circumferential edge128of canopy126. Reefing line124may also be coupled to suspension lines122. Reefing line124is configured to restrict expansion of canopy126such that canopy126opens in stages. For example, reefing line124may be cut, or otherwise severed, at a preselected time after deployment of canopy126. Prior to cutting reefing line124, canopy126is held at a first, restricted diameter; after reefing line124is severed, canopy126is able to open further and its diameter increases. Opening canopy126in stages may reduce opening shock to parachute assembly116. The time delay between deploying canopy126and severing reefing line124may comprise any suitable time delay based on properties of parachute assembly116, the type of aircraft, and/or the load limitations of the object (e.g., occupant110) being carried by parachute assembly116.

In various embodiments, suspension lines122may be configured to connect canopy126to risers120. Suspension lines122and risers120may comprise any suitable material. For example, suspension lines122may comprise a tubular braided material that constricts in diameter under tension, such as, for example, nylon, aramid fiber (e.g., KEVLAR®), and/or the like. Risers120may comprise a webbing formed from nylon, aramid fiber (e.g., KEVLAR®), and/or the like. Risers120may be configured to attach to a harness130, or other structure, configured to secure occupant110to risers120. In various embodiments, parachute assembly116may comprise a plurality of risers120attached to harness130.

With reference toFIG. 3, in various embodiments, parachute assembly116may comprise left shoulder risers120aand120c, and right shoulder risers120band120d. Left shoulder risers120aand120care attached proximate a left shoulder134of occupant110and/or are configured to be located over left shoulder134of occupant110upon deployment of parachute assembly116. Right shoulder risers120band120dare attached proximate a right shoulder136of occupant110and/or are configured to be located over right shoulder136of occupant110upon deployment of parachute assembly116.

In various embodiments, left shoulder riser120ais located forward of left shoulder riser120c, and right shoulder riser120bis located forward of right shoulder riser120d. Stated differently, left shoulder riser120cand right shoulder riser120dmay be located closer to a backside135of occupant110as compared, respectively, to left shoulder riser120aand right shoulder riser120b. As used herein, “forward” refers to the side of harness130configured to be attached to a front side of an occupant. Backside135of occupant110is generally opposite a front side137of occupant110.

In various embodiments, left shoulder risers120aand120cmay be attached to harness130at an attachment location138, and right shoulder risers120band120dmay be attached to harness130at an attachment location140. Attachment locations138and140are on an end of risers120that is opposite suspension lines122, with momentary reference toFIG. 2. Attachment locations138and140may comprise any suitable attachment mechanism (e.g., stitching, adhesive, etc.) for securing risers120to harness130. In various embodiments, attachment locations138and140may each comprise a hoop, or ring, attached to harness130and located through a loop formed by risers120. In various embodiments, each riser120(e.g., left shoulder riser120a, right shoulder riser120b, left shoulder riser120c, right shoulder riser120d) may have its own attachment location on harness130.

With combined reference toFIG. 2andFIG. 3, in various embodiments, parachute assembly116may comprise a greater number of suspension lines122as compared to the number of risers120. For example, each riser120may couple to multiple suspension lines122, such as, for example 1 to 16 suspension lines122per riser120, 8 to 16 suspension lines122per riser120, etc. In this regard, left shoulder riser120a, right shoulder riser120b, left shoulder riser120c, and right shoulder riser120dmay each couple to its own individual set of suspension lines122.

As canopy126catches wind, occupant110may be rotated in-line with the direction of suspension line stretch. As occupant110is rotated, a rearward force may be exerted on the neck of occupant110. As used herein, “rearward” refers to the side of harness130configured to be attached to a backside of an occupant supported by parachute assembly116. In accordance with various embodiments, parachute assembly116may include a head restraint150(FIG. 3). Head restraint150is configured to be located rearward of the head132of occupant110, upon deployment of parachute assembly116. Head restraint150is configured to limit translation of head132in the rearward direction, thereby reducing a likelihood of head and/or neck injury to occupant110. Head restraint150may limit a range of motion of head132and/or may locate head132in an uncomfortable position. Accordingly, parachute assembly116may include a head restraint removal system configured to translate head restraint away from head132.

Referring toFIG. 4A, a forward view of a head restraint removal system200of parachute assembly116is illustrated, in accordance with various embodiments. Head restraint removal system200includes a first chord202aand a second chord202b. First and second chords202a,202bare each coupled to head restraint150. First and second chords202a,202bmay be coupled to head restraint150using any suitable attachment technique, for example, using stitching, adhesive, friction coupling, etc. First and second chords202a,202bmay comprise any suitable material rope, canvas, silk, nylon, aramid fiber (e.g., KEVLAR®), polyethylene terephthalate, polyvinyl chloride, etc.

First chord202amay be coupled to a left hand (or first) handle206aof parachute assembly116. Second chord202bmay be coupled to a right hand (or second) handle206bof parachute assembly116. Left hand handle206ais also coupled to a first control line204aof parachute assembly116. Right hand handle206bis also coupled to a second control line204bof parachute assembly116. First and second control lines204a,204bare configured to manipulate, and may be coupled to, canopy126, with momentary reference toFIG. 2, of parachute assembly116. For example, occupant110may be able to steer and/or reduce a speed (e.g., increase drag) of parachute assembly using first and control lines204a,204b.

In various embodiments, first control line204aand first chord202amay be located through a first aperture208adefined by left shoulder (or first) riser120d. Second control line204band second chord202bmay be located through a second aperture208bdefined by right shoulder (or second) riser120c.

Referring now toFIG. 4B, after initial deployment of parachute assembly116, for example, after canopy126has fully, or at least substantially, opened, occupant110may grip and pull left and right handles206a,206bin a direction of arrows210to begin steering and/or slowing parachute assembly for descent and landing. Translating left and right handles206a,206bin the direction of arrows210causes head restraint150to translate in the direction of arrow212along left and right shoulder risers120c,120d. Stated differently, occupant110pulling left and right handles206a,206bin the direction of arrows210may translate head restraint150away from head132. Head restraint removal system200is thus configured to have head restraint150limit rearward motion of head132during peak deployment forces to reduce possibility of neck injury, and remove head restraint150during steady state decent and landing to increase a range of motion of head132and/or to increase the comfort of occupant110.

Referring toFIG. 5A, a forward view of a head restraint removal system260for a parachute assembly216is illustrated, in accordance with various embodiments. Parachute assembly216is similar to parachute assembly116and may replace parachute assembly116in aircraft ejection system100, with momentary reference toFIG. 1. Parachute assembly216includes a head restraint250. Head restraint250may be coupled to a left shoulder riser220cand a right shoulder riser220dof parachute assembly216. Left and right shoulder risers220c,220dmay be coupled to a harness230configured to be worn by, or otherwise secured to, an occupant218of parachute assembly216. Head restraint250is configured to be located rearward of a head232of occupant218, upon deployment of parachute assembly216.

In accordance with various embodiments, parachute assembly216further includes head restraint removal system260. Head restraint removal system260includes a first chord262aand a second chord262b. First and second chords262a,262bare each coupled to head restraint250. First and second chords262a,202bmay be coupled to head restraint250using any suitable attachment technique, for example, using stitching, adhesive, friction coupling, etc. First and second chords262a,262bmay comprise any suitable material, for example, rope, canvas, silk, nylon, aramid fiber (e.g., KEVLAR®), polyethylene terephthalate, polyvinyl chloride, etc.

First chord262ais also coupled to a first control line264of parachute assembly216at an attachment point270. First control line264is configured to manipulate the canopy of parachute assembly216. First chord262amay be coupled to first control line264using any suitable attachment technique, for example, using stitching, adhesive, friction coupling, etc. First control line264is coupled to a left hand (or first) handle266aof parachute assembly216. First control line264thus comprises a first length264aextending from attachment point270to the canopy of parachute assembly216and a second length264bextending from attachment point270to left hand handle266a.

Second chord262bis also coupled to a second control line274of parachute assembly216at an attachment point276. Second control line274is configured to manipulate the canopy of parachute assembly216. Second chord262bmay be coupled to second control line274using any suitable attachment technique, for example, using stitching, adhesive, friction coupling, etc. Second control line274is coupled to a right hand (or second) handle266bof parachute assembly216. Second control line274thus comprises a first length274aextending from attachment point276to the canopy of parachute assembly216and a second length274bextending from attachment point276to right hand handle266b.

Referring toFIG. 5B, upon initial deployment of parachute assembly216, left hand handle266ais coupled to left shoulder riser220c. For example, in various embodiments, a first sleeve278amay be attached to left shoulder riser220c. First sleeve278ais configured to receive a tip261aof left hand handle266aand secure left hand handle266ato left shoulder riser220c. First control line264may be configured such that, when left hand handle266ais secured to left shoulder riser220c, second length264bis restricted, or otherwise prevented, from deploying. Stated differently, second length264bof first control line264may be configured to deploy upon removal of tip261afrom first sleeve278a. In this regard, and with momentary combined reference toFIG. 5AandFIG. 5Cwhen left hand handle266ais in a secured to left shoulder riser220c(FIG. 5A), attachment point270is located closer to head232of occupant218(i.e., further from the canopy of parachute assembly216) as compared to after tip261ais removed from first sleeve278a(FIG. 5C).

Returning toFIG. 5A, upon initial deployment of parachute assembly216, right hand handle266bis coupled to right shoulder riser220d. For example, in various embodiments, a second sleeve278bmay be attached to right shoulder riser220d. Second sleeve278bis configured to receive a tip261bof right hand handle266band secure right hand handle266bto right shoulder riser220d. Second control line274may be configured such that, when right hand handle266bis secured to right shoulder riser220d, second length274bis restricted, or otherwise prevented, from deploying. Stated differently, second length264bof second control line274may be configured to deploy upon removal of tip261bfrom second sleeve278b. In this regard, while right hand handle266bis secured to right shoulder riser220d, attachment point276is located closer to 232 head of occupant218(i.e., further from the canopy of parachute assembly216), as compared to after removal of tip261bfrom second sleeve278b.

Referring now toFIG. 5C, after initial deployment of parachute assembly216, for example, after the canopy has fully, or at least substantially, opened, occupant218may grasp and decouple left and right hand handles266a,266bfrom left and right shoulder risers220c,220d, respectively, to begin steering and/or slowing parachute assembly216for descent and landing. Second length264bmay deploy upon removing tip261afrom sleeve278a. Second length274bmay deploy upon removing tip261bfrom second sleeve278b. Deployment of second length264,274bmay allow attachment points270,276to translate generally in the direction of arrow280. Translation of attachment points270,276in the direction of arrow280causes head restraint250to also translate in the direction of arrow280along left and right shoulder risers220c,220d. Stated differently, occupant110removing left and right hand handles266a,266bfrom left and right shoulder risers220c,220d, respectively, may translate head restraint250away from head232. Head restraint removal system260is thus configured to have head restraint250limit rearward motion of head232during peak deployment forces to reduce possibility of neck injury, and remove head restraint250during steady state decent and landing to increase a range of motion of head232and/or to increase the comfort of occupant218.

With reference toFIG. 6Aa forward view of a head restraint removal system300for a parachute assembly316is illustrated, in accordance with various embodiments. Parachute assembly316is similar to parachute assembly116and may replace parachute assembly116in aircraft ejection system100, with momentary reference toFIG. 1. Parachute assembly316includes a canopy326, and suspension lines322. Parachute assembly316includes a head restraint350. Head restraint350comprises a central riser located between left shoulder riser320cand right shoulder riser320dof parachute assembly216. Head restraint350may be coupled to left and right shoulder risers320c,320dand/or to a harness330configured to support an occupant310of parachute assembly316.

In various embodiments, parachute assembly316may include one or more reefing line(s)324. Reefing line324may be coupled to canopy326proximate a circumferential edge328of canopy326. Reefing line324is configured to restrict expansion of canopy326, such that canopy326opens in stages. For example, parachute assembly316may include a cutter380configured to cut, or otherwise sever, reefing line324a preselected time after deployment of canopy326. Prior to cutting reefing line324, canopy326is held at a first, restricted diameter. After reefing line324is severed, canopy326is able to open further and its diameter increases. Opening canopy326in stages may reduce opening shock to parachute assembly316and occupant310. The time delay between deploying canopy326and severing reefing line324may comprise any suitable time delay based on properties of parachute assembly316, the type of aircraft, and/or the load limitations of the object (e.g., occupant310) being supported by parachute assembly316.

Head restraint removal system300comprises a coupling325between head restraint350and reefing line324. In various embodiments, coupling325includes one or more suspension lines coupled to reefing line324and head restraint350.

FIG. 6Billustrates parachute assembly316after a severing of reefing line324. Coupling325may be incorporated into reefing line324such that severing reefing line324releases suspension lines323from canopy326. The released suspension lines323and head restraint350are pulled by gravitational forces toward the ground, thereby removing head restraint350from behind head332. Removing head restraint350from head332may increase a range of motion of head332and/or may allow head332to be oriented at a more comfortable angle. Head restraint removal system300is thus configured to have head restraint350limit rearward motion of head332during peak deployment forces to reduce possibility of neck injury, and remove head restraint350during steady state decent and landing to increase a range of motion of head332and/or to increase the comfort of occupant310.

With reference toFIG. 7A, a forward view of a head restraint removal system360for a parachute assembly356is illustrated, in accordance with various embodiments. Parachute assembly356is similar to parachute assembly116and may replace parachute assembly116in aircraft ejection system100, with momentary reference toFIG. 1.

Parachute assembly356includes a head restraint351. Head restraint351includes a first strap352and a second strap354. First and second straps352,354are each coupled to a left shoulder riser370cand a right shoulder riser370dof parachute assembly356. Left and right shoulder risers370c,370dmay be coupled to a harness371configured to be worn by, or otherwise secured to, an occupant378of parachute assembly356. Head restraint351is configured to be located rearward of a head372of occupant378, upon deployment of parachute assembly356. In various embodiments, first strap352may overlap second strap.

Head restraint removal system360includes a cutter380configured to sever head restraint351, such that first and second straps352,354are no longer limit rearward translation of head372. Cutter380may comprise a sear mechanism that is activated in response to a tension in first strap352and/or in second strap354exceeding a predetermined threshold. The sear mechanism may comprise a trigger mechanism, and/or the like, configured to release a hammer, striker, bolt, blade, shape charge, and/or the like. Once activated, the sear mechanism may release, via an explosive charge, a mechanical spring, and/or the like, the bolt, hammer, striker, bolt, blade, shape charge, and/or the like. The bolt, hammer, striker, bolt, blade, shape charge, and/or the like released from the sear mechanism may sever head restraint351such that first and second straps352,354translate away from head372.

Cutter380may be configured to activate during and/or after the deployment of parachute assembly356. Once activated, a time delay may be initiated before activating the sear mechanism. The time delay may be configured to delay activation of the sear mechanism, and may allow head restraint351to restrict rearward translation of head372during peak deployment forces The time delay may comprise any suitable time delay based on properties of parachute assembly356, the type of aircraft, and/or the load limitations of the object being carried by parachute assembly356. In various embodiments, after the time delay has passed, the sear mechanism in cutter380may activate.

FIG. 7Billustrates parachute assembly356after a severing head restraint351. Removing head restraint351from head372may increase a range of motion of head372and/or may allow head372to be oriented at a more comfortable angle. Head restraint removal system360is thus configured to have head restraint351limit rearward motion of head372during peak deployment forces to reduce possibility of neck injury, and remove head restraint351during steady state decent and landing to increase a range of motion of head372and/or to increase the comfort of occupant370.