Systems and methods for accelerating the inflation of a parachute canopy

Abstract

A system for accelerating the inflation of a parachute canopy ejected or extracted from an airborne aerial object includes a thrust generator operatively attached to a load-bearing bridle of the parachute canopy, and is configured to pull the canopy toward the airborne aerial object to accelerate inflation of the canopy.

Description

[0001] SYSTEMS AND METHODS FOR ACCELERATING THE INFLATION OF A PARACHUTE CANOPY

[0002] REFERENCE TO RELATED APPLICATIONS

[0003] This application claims priority to and the benefit of U.S. Provisional Patent Application No. 63 / 515,950, filed on July 27, 2023, the contents of which are incorporated by reference in their entirety as if fully set forth herein.

[0004] TECHNICAL FIELD

[0005] This disclosure relates to systems and methods for deploying an emergency parachute from an airborne aerial object such as an aircraft. In particular, this disclosure relates to systems and methods for pulling an inflating parachute canopy back toward the aerial object from which it was deployed, in order to accelerate parachute canopy inflation.

[0006] BACKGROUND

[0007] The aviation industry has continuously prioritized safety, leading to the development of various technologies aimed at mitigating risks during flight. One such technology is the aircraft emergency parachute system, which has been integrated into various types of aircraft, from small private planes to larger commercial jets. These systems are designed to deploy in critical situations, such as engine failure or structural damage, providing an additional layer of safety for both passengers and crew.

[0008] Despite the progress in parachute technology, significant challenges remain in ensuring the rapid and reliable deployment of these life-saving devices. Traditional parachute systems typically operate by deploying the canopy into the airstream, retying on natural airflow and gravitational forces to achieve full inflation. This process can sometimes be slow and inconsistent, particularly in turbulent or low-speed scenarios, where airflow patterns may not be conducive to quick inflation. The time it takes for a parachute canopy to fully deploy and become effective is crucial; even a delay of a few seconds can mean the difference between life and death in an emergency.

[0009] Environmental conditions can also play a significant role in the effectiveness of parachute deployment. Factors such as wind speed, direction, and atmospheric pressure can all influence the speed and manner in which a parachute inflates. In adverse weather conditions, such as heavy rain or strong crosswinds, the deployment process can be further compromised. These variables introduce a level of unpredictability that current systems are not always equipped to handle, potentially putting lives at risk. The impact of a delayed or failed parachute deployment extends beyond the immediate threat to human life. The quicker a parachute can fully inflate, the sooner it can arrest the descent of an aircraft, thereby reducing the potential for severe damage upon impact. This reduction in impact force can mean the difference between a survivable crash landing and a catastrophic event. Faster canopy inflation can also prevent the aircraft from reaching critical speeds that exacerbate damage, ensuring a more controlled and less destructive descent.

[0010] While current aircraft emergency parachute systems have undoubtedly saved lives, there is a pressing need to increase the speed at which such parachute canopies inflate, to maximize survivability and minimize structural damage resulting from an aircraft emergency. With the proliferation of low- and slow-flying aircraft such as vertical take-off and landing (VTOL) aircraft, such needs are becoming increasingly urgent. A system that can inflate emergency parachute canopies more quickly and reliably under a wide range of conditions is a significant unmet need in aviation safety. Faster canopy inflation can not only save lives but also minimize damage to aircraft, contributing to better overall outcomes in emergency scenarios.

[0011] SUMMARY

[0012] In general, systems and methods for increasing the inflation speed of an emergency parachute canopy are disclosed. Across multiple embodiments, the systems and methods utilize a thrust generator to pull a canopy back toward the aerial object from where it originated as it is inflating, so as to increase the under-canopy air pressure during deployment and accelerate canopy inflation.

[0013] In a first general aspect, a system for accelerating the inflation of a canopy of a parachute assembly deployed from an airborne aerial object includes a thrust generator storing a potential energy, the thrust generator being contained in or mounted on the aerial object and connected to a load-bearing suspension component of the parachute assembly between the canopy and the aerial object. The thrust generator is configured to draw the canopy toward the aerial object after the parachute assembly has been deployed from the aerial object.

[0014] The load-bearing suspension component can be. for example, a reefing bridle of the parachute or a load-bearing suspension component is keeper that serves as a unifying anchor point for a confluence of suspension lines of the parachute.

[0015] In one embodiment, the thrust generator is a rocket.

[0016] In one embodiment, the thrust generator is configured to activate in response to a predetermined condition. In this and other embodiments, the aerial object is a fixed-wing aircraft, a rotary-wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

[0017] In a second general aspect, a system for accelerating the inflation of a canopy of a parachute assembly’ deployed from an aerial object includes a thrust generator storing a potential energy, the thrust generator being contained in, or mounted on the aerial object and connected to a load-bearing suspension component of the parachute assembly between the canopy and the aerial object. The thrust generator is configured to convert the potential energy to a kinetic energy to extract or jettison the parachute assembly into an atmosphere surrounding the aerial object. The load-bearing suspension component is routed so as to engage a redirection assembly that is secured to the aerial object. After the parachute assembly is extracted or jettisoned into the surrounding atmosphere, the thrust generator exerts an urging force on the load-bearing suspension component that urges the canopy toward the aerial object by way of the redirection assembly.

[0018] In one embodiment, the redirection assembly includes one or more sheaves, wheels or pulleys.

[0019] In one embodiment, the thrust generator is configured to activate in response to a predetermined condition such as a stall of the aerial object, or a loss of altitude of the aerial object within a predetermined amount of time.

[0020] In one embodiment, the thrust generator is configured for manual activation.

[0021] In one embodiment, the thrust generator is a rocket.

[0022] In one embodiment, the redirection assembly engages the load-bearing suspension component between the thrust generator and the canopy.

[0023] In one embodiment, the potential energy of the thrust generator is sufficient to both extract or jettison the parachute assembly and urge the canopy toward the aerial object after the parachute assembly has been extracted or jettisoned.

[0024] In one embodiment, the aerial object is a fixed-wing aircraft, a rotary-wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

[0025] In a third general aspect, a system for accelerating the inflation of a canopy of a parachute assembly deployed from an aerial object includes a thrust generator mounted on the aerial object that is configured to activate upon an activation event to extract or jettison at least the canopy of the parachute assembly, a redirection assembly mounted on the aerial object, a bridle, operatively connected to the canopy at a first end portion, and connected to the thrust generator at a second end portion, and wherein the bridle is routed through or around the redirection assembly between the first and the second bridle end portions. Upon activation, the thrust generator is launched from the aerial object, thereby extracting at least the canopy and the second end portion of the bridle into an atmosphere surrounding the aerial object. A thrust of the thrust generator urges the second portion of the bridle away from the aerial object while simultaneously urging the first portion of the bridle and the canopy toward the aerial object by way of the redirection assembly to accelerate inflation of the canopy.

[0026] In one embodiment, the thrust generator is a rocket.

[0027] In one embodiment, the redirection assembly includes at least one sheave, wheel or pulley.

[0028] In one embodiment, the aerial object is a fixed-wing aircraft, a rotary-wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

[0029] In one embodiment, the system further includes at least one bridle brake or arresting assembly operative to prevent the first end portion of the bridle from shifting away from the aerial object after the canopy is inflated.

[0030] In a fourth general aspect, a system for accelerating the inflation of a parachute canopy ejected or extracted from an airborne aerial object includes a thrust generator operatively attached to a load-bearing bridle of a parachute canopy that is configured to pull the canopy toward the airborne aerial object to accelerate inflation of the canopy.

[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. Although methods and materials similar or equivalent to those described herein can be used in the practice or testing of any described embodiment, suitable methods and materials are described below. In addition, the materials, methods, and examples are illustrative only and not intended to be limiting. In case of conflict with terms used in the art, the present specification, including definitions, will control.

[0032] The foregoing summary is illustrative only and is not intended to be in any way limiting. In addition to the illustrative aspects, embodiments, and features described above, further aspects, embodiments, and features will become apparent by reference to the drawings and the following detailed description and claims.

[0033] BRIEF DESCRIPTION OF DRAWINGS

[0034] The present embodiments are illustrated by way of the figures of the accompanying drawings, which may not necessarily be to scale, in which like references indicate similar elements, and in which:

[0035] FIG. 1 is an illustration of a system for accelerating the inflation of a parachute canopy according to one embodiment; FIG. 2 is an illustration of a system for accelerating the inflation of a parachute canopy according to a second embodiment;

[0036] FIG. 3 is a bridle redirection assembly according to one embodiment;

[0037] FIG. 4 is an embodiment of a system for accelerating the inflation of a parachute canopy incorporating a dual-rocket system;

[0038] FIGS. 5 A and 5B illustrate front and side views respectively of a bridle redirection assembly incorporating a spring-loaded system according to one embodiment; and

[0039] FIG. 6 is a system diagram for a system for accelerating the inflation of a parachute canopy system according to one embodiment.

[0040] DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

[0041] In general, systems and methods for accelerating the inflation of a parachute canopy are disclosed. Throughout the present disclosure, the term ‘aerial object’ is used to denote any type of flying craft or airborne object, including, but not limited to fixed-wing aircraft, rotary-wing aircraft, balloons, airships, gliders, drones, unmanned aerial vehicles, helicopters, auto-gyros, blimps, Zeppelins, personal jet packs, skydiving parachute assemblies, powered ram-air style parachutes, conventional or cargo aircraft, vertical takeoff and landing (VTOL) aircraft, jetpacks (including personal jetpacks), rocket belts, flying or airborne platforms, and cargo or package drops (e.g.. dropped from an aircraft), even though the description and drawings may refer to a certain kind of aircraft in the examples that follow . Similarly, the phrase ‘thrust generator’ is used to describe any object, assembly or system capable of producing thrust or imparting a thrust or kinetic energy of motion to an object - particularly a parachute assembly bridle, such as, but not limited to rockets and rocket motors, winches, flywheels, electric motors, engines, mortars, springs, bungees, catapults, pneumatic cylinders, hydraulic actuators, electromagnetic launchers, gas thrusters, solid rocket boosters, air cannons, compressed gas cartridges, and chemical propulsion systems.

[0042] In general, the systems and methods described herein for accelerating the inflation of a parachute canopy involve a mechanism for jettisoning or extracting a parachute assembly, including a parachute canopy from an initially stored configuration on or in an aerial object, into the surrounding atmosphere away from the aerial object. After being jettisoned or extracted, a thrust generator is used to pull the inflating canopy back toward the aerial object, thereby increasing the rate of canopy inflation. In some cases, the thrust generator plays a dual role, also being the mechanism for jettisoning or extracting the parachute system from the aerial object.

[0043] By accelerating the canopy inflation speed of an emergency parachute, loss of life and structural damage of aerial objects can be reduced or eliminated, in particular, for aerial objects at low altitudes or those that incorporate low- or no forward speed as an element of their flight characteristics, e.g., in the case of helicopters or VTOL aircraft. Furthermore, the systems and methods described herein for accelerating the inflation of an emergency parachute canopy can be particularly beneficial in emergencies such as stalls, unrecoverable spins, mid-air collisions with other aircrafts, birds, drones or stationary objects, engine or motor failure, structural failure, jammed or failed aircraft controls, pilot incapacitation, pilot disorientation or drone guidance or communication failure, among others.

[0044] In one example, a thrust generator, such as a rocket, is connected to a deployable, packed parachute assembly of an aerial object, e.g., an aircraft. In this and other described examples, the canopy and suspension lines of the packed parachute assembly can be contained within a deployment bag, as is common in parachute design and operation. A bridle of the parachute assembly includes a proximal end portion securely connected to a confluence point of the suspension lines of the parachute canopy. The bridle extends through or around a redirection assembly attached to the aerial object, with the distal end portion of the bridle securely attached to the rocket. The purpose of the redirection assembly is to redirect the motion of the bridle from being carried or urged away from the aerial object during deployment back to the aerial object as the canopy is inflating. In other words, the thrust generator and redirection assembly cooperate to draw the bridle of the parachute assembly toward the aerial object after the canopy, suspension lines and other components of the parachute assembly have been extracted or jettisoned into the atmosphere surrounding the aerial object.

[0045] In this example, when the rocket is activated, it launches from the aerial object, extracting the packed parachute assembly and releasing it into the surrounding atmosphere. The rocket also carries the connected distal end portion of the bridle into the atmosphere. As the bridle becomes taut — whether from the parachute canopy catching air and beginning to inflate, from the rocket carrying the parachute assembly away from the aerial object, or both — the rocket continues to exert a thrusting force on the distal end portion of the bridle. This thrusting force rapidly urges the canopy toward the aerial object via the redirection assembly, thereby accelerating the canopy inflation process.

[0046] Referring now to FIG. 1, a system 100 and related method for accelerating the inflation of a canopy of a parachute assembly deployed from an aerial object is illustrated according to one embodiment. In this example, the x-axis of the illustration represents time, and the v-axis illustrates altitude; the illustration is not necessarily to scale.

[0047] The left-most depiction (section “A”) of FIG. 1 illustrates an aerial object, in this example an aircraft Ac at an altitude Al that is experiencing an emergency such as an engine failure, such that the aircraft is unable to maintain its altitude. The aerial object is outfitted with an emergency parachute assembly that includes, inter alia, a bridle 110, suspension lines 121, and a parachute canopy 123. The bridle 110, suspension lines 121 and canopy 123 can be stowed in a deployment bag 115 within the aircraft as is a common practice for aircraft emergency parachutes.

[0048] Section A of FIG. 1 shows the aircraft Ac having deployed the emergency parachute assembly at altitude Al. In this example, the emergency parachute assembly uses a first rocket 105 to extract the deployment bag 115 utilizing tether 114. As the rocket 105 is launched, it carries the deployment bag 115 away from the aircraft Ac until the bridle 110 and suspension lines 122 are fully extended (commonly referred to as having achieved Tine stretch’), as illustrated in middle section B of FIG. 1, where the aircraft has now descended or fallen to altitude A2, which is less than altitude Al. The distance DLS between the top of the aircraft and the confluence point of the suspension lines 121 is maximized when the bridle 110 reaches full line stretch and the parachute canopy 123 begins to inflate.

[0049] In this embodiment, the assembly 100 includes a thrust generator that is operative to pull the parachute canopy 123 back toward the aircraft Ac via bridle 1 10 as it is in the process of inflating, in order to accelerate the canopy inflation process. In this example, the thrust generator is a second rocket 112 that is coupled to the bridle 110. The secondary rocket 112 is housed in, and operative to launch from the bottom of the aircraft Ac in a downward direction, so as to oppose the upward pull of the bridle caused by the drag of the inflating parachute canopy as the aircraft Ac descends under the force of gravity. In this embodiment, the bridle 110 is routed from the top portion of the aircraft Ac where it connects to the emergency parachute assembly, through the fuselage, and connects to the secondary rocket 112. When activated, the secondary rocket 112 rapidly urges the bridle 110 downward, in a direction opposing the pull of the inflating parachute canopy 123. This action forces surrounding air into the canopy 123, greatly accelerating the inflation rate of the canopy 123 compared to that if the aircraft were in freefall alone.

[0050] Referring to sections “B” and “C” of FIG. 1. in this embodiment, bridle 110 includes a bridle stop member for stopping the downward translation of the bridle at a predetermined bridle location. The bridle stop member effectively prevents the secondary rocket 112 from pulling the parachute canopy too close to the aircraft Ac or pulling the suspension lines and canopy into the aircraft. In this example, a cross-bar 140 (described in greater detail below) is integrated with, or securely attached to the bridle 110 that stops the bridle 110 from shifting through the aircraft Ac at a pre-selected position. The pre-selection position of bar 140 can be a distance Di that is selected so that there is ample space betw een the inflated canopy 123 and the aircraft Ac. Referring to the right side portion of FIG. 1 (section "C”). in this illustration the secondary rocket 112 has pulled bridle 110 downward until bar 140 has seated against the aircraft or a catch 142 (described in greater detail below). At this point, the parachute canopy 123 has become fully inflated where the aircraft is at altitude A3, which is less than altitudes Al and A2. The secondary rocket 112 may continue to hang from the aircraft after its thrust is expended, or, in an alternative approach, the secondary rocket may break free. As illustrated in FIG. 1, the bridle distance Di is less than the line stretch distance DLS between the time that the canopy 123 begins to inflate (section “B” of FIG. 1) and full canopy inflation (section “C” of FIG. 1).

[0051] Referring now to FIG. 2, a system 200 for accelerating the inflation of a parachute canopy is illustrated according to a second embodiment. In this example, the x-axis of the illustration represents time, and the y-axis illustrates altitude. The illustration is not necessarily to scale and incorporates some of the features and elements of the system 100 shown and described with respect to FIG. 1.

[0052] In this embodiment, the left-most section (’‘A”) of FIG. 2 illustrates an aerial object, in this example an aircraft Ac at an altitude Al that is experiencing an emergency such as an engine failure such that the aircraft is unable to maintain its altitude. The aircraft Ac is equipped with the system 200 that includes, inter alia, a rocket 105 acting as a thrust generator, an emergencyparachute assembly 120, including a parachute bridle 110, canopy 123, and suspension lines 121 contained in a deployment bag 1 15, and a sheave assembly 125 acting as a bridle redirection assembly.

[0053] In this embodiment, a rocket 105 is configured to be launched from the aircraft Ac in order to deploy the emergency parachute assembly. The ignition of the rocket 105 can be initiated, e.g., by a pilot of the aircraft, wherein the pilot may be within the aircraft itself or in a remote location flying the aircraft by remote control, as is the case for drone piloting. The rocket 105 may also be launched automatically by a monitoring system that analyzes flight data such as, but not limited to speed, altitude, attitude, weather conditions, terrain and other data. This system 200, as well as others described herein, may be utilized in military aircraft, where the monitoring system can further analyze threat information.

[0054] In this embodiment, the rocket 105 is operative to extract the deployment bag 115 from the aircraft into the surrounding atmosphere by way of tether 114; however, it should be understood that the rocket 105 can be configured to extract the deployment bag 115 from the aircraft Ac using alternative methods. In this embodiment, the deployment bag 115 keeps the stowed canopy 123, suspension lines 121 and bridle 110 of the parachute assembly 120 in an orderly configuration until it is extracted or jettisoned from the aircraft Ac. When the rocket 105 is launched, it lifts the deployment bag away from the aircraft Ac and allows the suspension lines 121 and canopy 123 to be freed, as illustrated.

[0055] Referring now to the middle depiction “B’‘ of FIG. 2, unable to maintain its altitude, the aircraft has fallen to an altitude A2, which is less than altitude Al. In this embodiment, the bridle 110 includes proximal (130) and distal (135) end portions. The proximal end portion 130 is connected to a confluence point 137 of the canopy suspension lines 121 utilizing, for example, a ring, buckle, or other suitable hardware. The distal end portion 135 of the bridle is securely coupled to the rocket 105. The bridle 110 is routed through or around the sheave assembly 125 between the proximal (130) and distal (135) end portions. In this example, the bridle 110 is routed through a central open aperture or vent 133 of the parachute canopy 123 as illustrated; however, in an alternative embodiment, the bridle can be routed to the outside of the canopy instead of through the vent 133.

[0056] In this embodiment, the rocket 105 is configured to remain attached to the bridle 110 and continue its upward trajectory after the parachute is released from the deployment bag 115, the bridle 110 has reached initial line stretch and the parachute canopy 123 begins to inflate. In the exemplary illustration of FIG. 2, as the distal end portion (135) of the bridle 110 is pulled upward by the rocket 105, the proximal portion (130) of the bridle 110 and thereby the canopy 123 is rapidly pulled toward the aircraft Ac as illustrated.

[0057] Continuing the present example and now referring to the right-most section (‘"C”) in FIG. 2, the aircraft Ac has fallen to an altitude A3, which is less than altitudes Al and A2. At this time, the parachute canopy 123 is fully inflated. From the time of the initial emergency (section “A” of FIG. 2) at altitude Al, the aircraft has fallen to altitude A3. However, the canopy 123 reaches full inflation faster than if the parachute had been deployed in a corresponding freefall from altitude Al to A3, because the rocket 105 has effectively advanced the parachute toward the aircraft via the combination of rocket 105 and redirection assembly 125 faster than the aircraft descends. Accordingly, the under-canopy air pressure increases faster than would occur if the rocket simply deployed the parachute and did not additionally rapidly advance it toward the aircraft, as is the case with respect to the embodiment shown and described with respect to FIG. 1.

[0058] The speed at which a parachute canopy becomes fully inflated can depend on several factors, including, but not limited to the canopy size, atmospheric conditions (e.g., density altitude), the way in which the parachute assembly is packed in the deployment bag and other factors. In the event of an aircraft emergency where the aircraft is falling, especially in a spin, the aircraft itself can create a column of still air in its wake which can reduce the available surrounding air to fill the canopy. In such cases, the canopy may not inflate ('streamer') for a considerable distance before enough air enters the canopy to cause it to inflate. Thus, the use of a thrust generator, such as rocket 105, to pull the inflating parachute canopy toward the aircraft can significantly increase the under-canopy air pressure, leading to considerably faster canopy inflation.

[0059] Referring now to FIG. 3, a side elevation view of a redirection assembly, in this case a sheave assembly 125, is shown according to one embodiment. In this embodiment, the sheave assembly 125 includes a housing 126 that is configured to be securely attached to the frame of the aircraft Ac. Preferably, the sheave assembly 125 is attached to a portion of the aircraft frame that is capable of withstanding support of the aircraft by the parachute, as well as opening forces of the parachute as it deploys. The sheave assembly 125 can be attached to an interior or exterior portion of the aircraft as desired or as suitable for the type of aerial object to which it is attached.

[0060] In this embodiment, the sheave assembly 125 includes a rotatable sheave 127 around which the bridle 110 is routed. In the example of FIG. 3, the portion of the bridle leading to the proximal end (1 lOp, the portion leading to the parachute assembly 120) enters the housing 126, extends around the sheave 127 and exits the housing. The portion of the bridle leading to the distal end (1 lOd) extends to the rocket assembly 105.

[0061] When the rocket 105 is launched, it draws both the proximal (130) and distal (135) end portions of the bridle 110 with it from the aircraft Ac at the same time; thus, the sheave 127 can be considered an anchor point of the bridle 110 as it is deployed into the atmosphere surrounding the aircraft Ac. Once the canopy is freed from the deployment bag 115, it will begin to inflate, causing the bridle and suspension lines will begin to become taut. Now, as the rocket continues its thrust, distal bridle portion HOd is urged upward, according to the convention shown in FIG. 3. causing proximal bridle portion 1 lOp to be urged downward, pulling the canopy toward the sheave assembly 125 and the aircraft. In this embodiment, sheave 127 rotates in the direction of the curved dashed arrow to facilitate frictionless movement of the bridle 110. However, the redirection assembly can utilize any type of bridle redirection system, including but not limited to wheels, pulleys, cross-bar members, and others.

[0062] In this embodiment, a bridle brake or arresting assembly, in this case, a pawl 129 is located within the housing 126 that is biased against bridle portion 1 lOd, preventing the bridle 110 from reversing direction after the parachute canopy has been pulled toward the aircraft. In alternative embodiments, two or more pawls can be used in series so as to ensure that bridle portion 1 lOd only translates in the direction imposed by the rocket and does not reverse or slip in the opposite direction. In an alternative embodiment, sheave 127 can include a pawl, clutch or other mechanism that prevents the sheave 127 from rotating in a reverse direction (counterclockwise according to the convention of FIG. 3). Other mechanisms for preventing bridle portion 1 lOp from shifting away from the aircraft, thereby increasing the distance of the parachute canopy 123 from the aircraft, can be used.

[0063] In this and other embodiments, the distance Dp between the fully-inflated parachute canopy 123 and the aircraft Ac can be set using a bridle stop member or assembly as previously described. The bridle stop member or assembly can be used to prevent the rocket from pulling the parachute all the way to the aircraft or through the sheave assembly 125, and ensures that the parachute canopy is operated at an effective distance from the aircraft.

[0064] Still referring to FIG. 3, one exemplary and non-limiting bridle stop member includes a bar 140 integrated into, or otherwise securely attached to bridle portion 1 lOp. As bar 140 is drawn to the sheave assembly 125, it engages a catch 142 that prevents bridle portion 1 lOp from translating further into the sheave assembly 125, according to the convention of FIG. 3. Accordingly, a preferred aircraft-to-deployed parachute canopy distance may be precisely set by selective placement of the bar 140 on bridle portion 1 lOp.

[0065] In this and other embodiments, the distal end portion (135) of bridle 110 can be routed through the vent opening 133 of the parachute canopy 123 as illustrated. However, in an alternative embodiment, the bridle 110 can be positioned outside of the parachute canopy 123 to reduce possible entanglement with the canopy suspension lines 121. In this and other embodiments, if the bridle is not routed through the center of the canopy, the redirection assembly - e.g., sheave assembly 125 - can be rotatable about an axis substantially perpendicular to the top portion of the aircraft to accommodate any drift that the rocket might follow during launch. In doing so, even if the rocket were to launch sideways, the parachute assembly would still be drawn toward the aircraft during deployment as previously described, leading to quicker inflation compared to a freefall deployment.

[0066] Referring now to FIG. 4, in an alternative embodiment, a system for accelerating the inflation of a canopy of a parachute assembly can incorporate a dual-rocket configuration. In this embodiment, a first rocket 402 deploys the emergency parachute assembly PA from the aircraft as described previously with respect to rocket 105, including the deployment bag, parachute canopy and suspension lines. However, in this embodiment, once the suspension lines reach full line stretch after being deployed from the aircraft, a second rocket 405 is launched to pull the inflating canopy back toward the aircraft. The second rocket 405 is attached via a linkage 420 to a bridle 401, which itself is attached to the confluence point of the suspension lines of the parachute. In this embodiment, the bndle 401 is routed around a sheave 410 that acts to pull the parachute canopy toward the aircraft - specifically toward the sheave 410 - even though the rocket 405 is launched at an angle relative to the bridle 401. A one-way pawl assembly 415 prevents the bridle 401 from reversing and allowing the parachute to move away from the aircraft. In this and other embodiments, the rocket 405 can be launched from a tube 403 disposed on the interior or exterior of the aircraft frame A as desired.

[0067] In this embodiment, the second rocket 405 can be triggered in several ways. For example, and without limitation, the second rocket 405 can include a firing pin that, when removed, causes the rocket 405 to ignite. The firing pin can be attached to a tether (not shown in FIG. 4) or a portion of the bridle 401, such that the pin is extracted when the suspension lines of the parachute assembly become taut.

[0068] In another example, a tensiometer (not shown in FIG. 4) can monitor the tautness of the bridle 401 and cause the second rocket to launch when a threshold tautness value is met or exceeded. In yet another example, a so-called 'dead-reckoning’ timer can be employed to fire the second rocket 405 after a certain amount of time has elapsed after the first rocket is deployed. It should be appreciated that other mechanisms and approaches can be used to fire the second rocket after the first in order to pull the deploying parachute canopy toward the aircraft.

[0069] Referring now to FIGS. 5A and 5B, a spring assembly is shown that can be used as an alternative thrust generator to a rocket. In this example, a single parachute-deployment rocket (e.g., rocket 105) can deploy the parachute assembly PA from the aircraft during an emergency. In this embodiment, a first end of bridle 530 extends to the confluence point of the suspension lines of the parachute assembly (similar to bridle 110 previously described), and the second, opposite end is attached to a spring assembly 501. For reference, FIG. 5 A is a front elevational view, and FIG. 5B is a left side elevational view of the spring assembly 501.

[0070] In this embodiment, the spring assembly 501 includes a post 520 onto which the bridle 530 is secured. The post 520 is connected to a center area of spring member 510. As the post 520 is rotated in a first direction, the spring member 510 is wound and loaded with potential spring energy. When the suspension lines have reached full stretch, the spring member 510 can be triggered to release its potential spring energy, rapidly drawing the parachute back toward the aircraft to accelerate canopy opening and inflation time as previously described. In this embodiment, the spring member can be triggered by, for example and without limitation, incorporating a tensiometer that monitors the tension of the bridle 530, a timer, or any other triggering mechanism.

[0071] In this embodiment, the spring member and post can be chosen according to the characteristics of the aircraft, e.g., size, weight, etc. and can employ multiple springs attached to post 520 as necessary. Furthermore, in an alternative embodiment, spring member 510 may be stored in a pre-wound, or “loaded” configuration, storing enough potential energy to be converted to kinetic energy' for retracting the inflating canopy back toward the aircraft. In this embodiment, when the suspension lines of the parachute assembly reach line stretch, the spring member 510 can be triggered to release its potential energy, unwinding and drawing the parachute toward the aircraft via bridle 530.

[0072] In an alternative embodiment, the systems and methods disclosed herein can utilize a resiliently-stretchable bridle portion or component as the bridle redirection element. In such an embodiment, the resiliently-stretchable bridle component can be, for example, a length of bungee cord. Bungee cords, also known as an elastic or shock cords, are flexible cords composed of one or more elastic strands forming a core, typically covered by a woven sheath. The elasticity of the core material gives the cord a unique ability to stretch and then return to its original length, allowing it to absorb and release energy. Accordingly, in lieu of a rocket pulling back on the bridle after an emergency parachute has been deployed, a system of the type described herein can utilize the properties of a bungee cord element for retracting the parachute canopy after it has been deployed from an aerial object and attained line stretch.

[0073] In such a system, a deployment rocket, such as rocket 105 described with respect to FIG.

[0074] 1 can be used to extract the emergency parachute assembly. As the rocket pulls the emergency parachute assembly to line stretch, it can stretch the bungee component of the bridle, imparting thereto a potential energy' for kinetically pulling the inflating canopy of the parachute system back toward the aerial object after the rocket disconnects from the parachute assembly or otherwise ceases to produce thrust away from the aerial object. As with other embodiments described herein, such a system can utilize a bridle brake or arresting assembly that is operative to prevent the bridle from extending away from the aerial object after it has pulled the inflating canopy toward it. Such a system can utilize, for example, a bungee component integral with the bridle, a separate bungee component connected inline with the bridle or a combination thereof. It should be understood that other bungee-like materials can be used in place of a bungee cord, for example, and without limitation, elastic bands, rubber tubing, shock cords, and elastic webbing.

[0075] Referring now' to FIG. 6, a system diagram 600 for the emergency parachute deployment system described herein is shown according to one embodiment. In this embodiment, the system 600 includes a thrust generator trigger 605. The thrust generator trigger 605 is configured to cause the thrust generator to activate, depending on the type of thrust generator used. For example, in the case of a rocket, e.g., rocket 105, there are multiple w ays that rockets can be launched, such as, and without limitation, electronic triggering that ignites a fuel or other propellant contained within the rocket.

[0076] In this embodiment, the thrust generator trigger 605 is in wired or wireless signal communication with a manual activator 610 and a systems monitor 615. The manual activator 610 can be, for example, a pilot control within the aircraft, preferably the cockpit, where the pilot can lift a lever, press a button, toggle a switch or otherwise activate a control that will cause immediate activation of the thrust generator trigger 605. In the case of a remotely-controlled aircraft, the manual activator can also be remotely controlled by a controller or pilot.

[0077] In this embodiment, the systems monitor 615 can monitor one or more attributes of the aerial object in flight. In this example, the systems monitor is configured to receive data from an attitude sensor 620, an altitude sensor 625. an airspeed / stall sensor 630. an airframe integrity sensor 635 and an engine sensor 640. The systems monitor 615 is configured to send an ignition signal to the thrust generator trigger 605 under predetermined emergency conditions; the systems monitor can also combine data from multiple systems to determine an emergency. For example, data from the attitude sensor 620 can be combined with data from the altitude sensor or the airspeed / stall sensor to determine that the aerial object is in an unrecoverable spin, dive or stall close to the ground. Likewise, data from the airspeed / stall sensor 630 and altitude sensor 625 can be combined to determine a stall condition after takeoff or during landing. In another example, the systems monitor 615 can determine from at least the altitude sensor that the aerial object is approaching a pre-determined altitude at an unsafe descent velocity at which time the parachute should be deployed to prevent the aerial object from crashing into the ground or other terrain.

[0078] In this embodiment, the engine sensor 640 can determine rough performance or engine failure of the aerial object. In combination with the altitude sensor 625, the systems monitor 615 can determine an emergency - e.g., low altitude engine failure on takeoff or landing approach and initiate the thrust generator trigger 605.

[0079] In another example, the airframe integrity sensor can determine, for example, structural damage to the aerial object, rapid depressurization or other events that may otherwise lead to catastrophic failure of the airframe and / or control surfaces. The systems monitor 615 can then activate the thrust generator trigger to deploy the parachute immediately to prevent freefall and ultimately a crash.

[0080] In each of the above embodiments and others, the systems monitor can oftentimes detect an imminent threat to the aircraft before the pilot can ascertain the situation and manually activate the thrust generator trigger 605. However, the systems monitor can be switched off if preferred; in other embodiments, the system may exclude the systems monitor altogether and rely solely on the manual activator 610.

[0081] A number of illustrative embodiments have been described. Nevertheless, it will be understood that various modifications may be made without departing from the spirit and scope of the various embodiments presented herein. For example, the attributes of the parachute assembly 120 can be chosen for characteristics of the aircraft; for example, the overall design of the parachute system, including, but not limited to the size of the canopy and strength of the suspension lines can be selected according to the weight, size and other features of the aircraft. In addition, while embodiments showing a single rocket used as the thrust generator have been shown, it should be understood that the systems and methods described herein can be adapted or configured for use with a plurality of rockets. Accordingly, other embodiments are within the scope of the following claims.

Claims

WHAT IS CLAIMED IS:1 . A system for accelerating the inflation of a canopy of a parachute assembly deployed from an aerial object, comprising: a thrust generator storing a potential energy', said thrust generator being contained in or mounted on said aerial object and connected to a load-bearing suspension component of said parachute assembly between said canopy and said aerial object; wherein said thrust generator is configured to draw said canopy toward said aerial object after said parachute assembly has been deployed from said aerial object.

2. The system of claim 1, wherein said load-bearing suspension component is a reefing bridle of said parachute.

3. The system of claim 1, wherein said load-bearing suspension component is keeper that sen es as a unifying anchor point for a confluence of suspension lines of said parachute.

4. The system of claim 1, wherein said thrust generator is a rocket.

5. The system of claim 1, wherein said thrust generator is configured to activate in response to a predetermined condition.

6. The system of claim 1, wherein said aerial object is a fixed-wing aircraft, a rotary -wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

7. A system for accelerating the inflation of a canopy of a parachute assembly deployed from an aerial object, comprising: a thrust generator storing a potential energy', said thrust generator being contained in, or mounted on said aerial object and connected to a load-bearing suspension component of said parachute assembly between said canopy and said aerial object; wherein said thrust generator is configured to convert said potential energy to a kinetic energy to extract or jettison said parachute assembly into an atmosphere surrounding said aerial object; wherein said load-bearing suspension component is routed so as to engage a redirection assembly that is secured to said aerial object; wherein, after said parachute assembly is extracted or jettisoned into said surrounding atmosphere, said thrust generator exerts an urging force on said load-bearing suspension component that urges said canopy toward said aerial object by way of said redirection assembly.

8. The system of claim 7. wherein said redirection assembly comprises one or more sheaves, wheels or pulleys.

9. The system of claim 7, wherein said thrust generator is configured to activate in response to a predetermined condition.

10. The system of claim 9. wherein said predetermined condition is a stall of said aerial object, or a loss of altitude of said aerial object within a predetermined amount of time.

11. The system of claim 7, wherein said thrust generator is configured for manual activation.

12. The system of claim 7, wherein said thrust generator is a rocket.

13. The system of claim 7, wherein said redirection assembly engages said load-bearing suspension component between said thrust generator and said canopy.

14. The system of claim 7, wherein said potential energy of said thrust generator is sufficient to both extract or jettison said parachute assembly and urge said canopy toward said aerial object after said parachute assembly has been extracted or jettisoned.

15. The system of claim 7, wherein said aerial object is a fixed-wing aircraft, a rotary-wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

16. A system for accelerating the inflation of a canopy of a parachute assembly deployed from an aerial object, comprising: a thrust generator mounted on said aerial object, configured to activate upon an activation event to extract or jettison at least said canopy of said parachute assembly; a redirection assembly mounted on said aerial object; a bridle, operatively connected to said canopy at a first end portion, and connected to said thrust generator at a second end portion, and wherein said bridle is routed through or around said redirection assembly between said first and said second bridle end portions; wherein, upon activation, said thrust generator is launched from said aerial object, thereby extracting at least said canopy and said second end portion of said bridle into an atmosphere surrounding said aerial object; and wherein a thrust of said thrust generator urges said second portion of said bridle away from said aerial object while simultaneously urging said first portion of said bridle and said canopy toward said aerial object by way of said redirection assembly to accelerate inflation of said canopy.

17. The system of claim 16, wherein said thrust generator is a rocket.

18. The system of claim 16, wherein said redirection assembly comprises at least one sheave, wheel or pulley.

19. The system of claim 16, wherein said aerial object is a fixed-wing aircraft, a rotary-wing aircraft, balloon, airship, glider, drone, unmanned aerial vehicle, or vertical takeoff and landing aircraft.

20. The system of claim 16, further comprising at least one brake assembly operative to prevent said first end portion of said bridle from shifting away from said aerial object after said canopy is inflated.

21. A system for accelerating the inflation of a parachute canopy ejected or extracted from an airborne aerial object, comprising: a thrust generator operatively attached to a load-bearing bridle of a parachute canopy and configured to pull said canopy toward said airborne aerial object to accelerate inflation of said canopy.

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