Abstract: A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio/video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

Abstract: A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

Abstract: A system for enabling the safe landing of an aircraft during an in-flight emergency is provided. The system includes a plurality of onboard devices for releasably securing a plurality of wings to a fuselage, and a non-electric module for activating said onboard devices. Said onboard devices are released to separate said wings from the fuselage.

Abstract: An unmanned aerial vehicle mounts a payload section to an air delivery vehicle. The air delivery vehicle includes deployable wings and tail fins for gliding or powered flight. A set of propeller blades are provided for powered flight. The propeller blades are mounted for movement from a stowed position to deployed position extending radially from the fuselage for powered flight.

Abstract: A method performed by an aircraft, the aircraft including a wing, aircraft fuel, and a whole-aircraft parachute that is coupled to the aircraft. The method comprises: deploying the whole-aircraft parachute while the aircraft is in flight; and after deploying the parachute, but before the aircraft contacts the earth or any object coupled to the earth, discharging at least a portion of the aircraft fuel from the wing of the aircraft.

Abstract: An aircraft, the aircraft including a whole-aircraft ballistic parachute that is coupled to the aircraft. The aircraft determines if a pre-activation action needs to be performed before activation of the whole-aircraft ballistic parachute. The aircraft also receives a whole-aircraft ballistic parachute activation request. The aircraft then issues a command to perform the pre-activation action and then activates the deployment of the whole-aircraft ballistic parachute. The aircraft then issues a command to perform a post-activation action.

Abstract: An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

Abstract: A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio/video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

Abstract: A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio/video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

Abstract: An aircraft has an emergency landing system which includes a paraglider for the emergency landing phase of the aircraft and an attitude positioning parachute for decelerating and subsequently swiveling the aircraft with respect to the flight direction. The vertical axis essentially corresponds to the direction of pull from the attitude positioning parachute.

Abstract: An aircraft has an emergency landing system which includes a paraglider for the emergency landing phase of the aircraft and an attitude positioning parachute for decelerating and subsequently swiveling the aircraft with respect to the flight direction. The vertical axis essentially corresponds to the direction of pull from the attitude positioning parachute.

Abstract: A parachute-landing device for whole airplane, comprising at least one parachute compartment (4) on the airplane (1), which has a cover (5) who can be controlled to open, and in which there set a parachute (2) with a guiding parachute (3) which is set in the space formed by the parachute compartment (4) and its cover (5), and the end of the sling (21) of which is fixed relatively to the parachute compartment (4), characterized in that a wind-guiding pipe (11) is set on the windward side of the parachute compartment (4), the front end and the rear end of the wind-guiding pipe (11) are respectively the air inlet (12) and the air outlet (13), and the air inlet (12) will be covered by the cover (5) of the parachute compartment (4) when the cover (5) is closed, while the air outlet (13) is in the parachute compartment (4) and the guiding parachute (3) of the parachute (2) covers the air outlet (13). The parachute of the present invention can be opened without power.

Abstract: A system for enabling the safe landing of an aircraft during an in-flight emergency is provided. The system includes a plurality of onboard devices for releasably securing a plurality of wings to a fuselage, and a non-electric module for activating said onboard devices. Said onboard devices are released to separate said wings from the fuselage.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: A cruise missile recovery system, for capturing a flying cruise missile and for guiding the cruise missile to a landing spot. The cruise missile recovery system has an intercept device for capturing the flying cruise missile, a radio-controlled parafoil connected to the intercept device for allowing the intercept device and cruise missile to be guided to the landing spot during descent of the intercept device and cruise missile, after capture of the flying cruise missile by the intercept device, and a position-stabilized suspension vehicle for suspending the radio-controlled parafoil device and the intercept device at a stable location above the earth, prior to capture of the flying cruise missile by the intercept device.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: A parafoil recovery system capable of autonomously controlling the descent profile of a payload to a recovery area and maneuvering the parafoil to execute a soft landing in the recovery area is disclosed. A descent profile management system determines wind speed and direction, altitude, heading, and position of the payload based on sensor input. The descent profile management system also determines a gliding flight path profile from the launch point to the desired recovery area. A flare and stall maneuver is executed at the end of the landing sequence by braking the parafoil to slow the vertical descent speed and groundspeed for a soft landing. The pitch attitude of the payload can be adjusted by the descent profile management system to prevent nose-first impact with the ground. The parafoil canopy is released from the payload upon touchdown to prevent the canopy from dragging the payload on the ground after landing.

Abstract: An improved pack for parachutes for powered parachute aircraft breaks down to lie flat against the ground providing a staging area for folding the parachute and full access to the parachute to remove entrapped air. Flaps of the pack fold up around the parachute to create an enclosure. The pack may include attached bungee cords for tying it to the frame of the cockpit and may be part of a kit including line socks and frame attachment hooks.

Abstract: An aircraft has a fuselage with a cockpit and a tail, and jet or propeller propulsion. The improved aircraft has a fuselage with one or more modules located between the cockpit and the tail. The modules include passenger seating, means to seal the modules, and means to detach the modules from the fuselage. One or more parachutes connect to the modules for use during an in-flight emergency, and the modules have a means to store the parachutes. Also, modules allow an airline to load passengers by groups onto an aircraft and to change the configuration of aircraft readily.

Abstract: An aircraft has an aircraft part with driving means and a body, and an impact reducing device which is movable between an inoperative position in which it is located close to the body and an operative position in which it is moved away from the body so as to first be subjected to impact against the ground and to dampen the impact, wherein the impact reducing device is formed as a plate-shaped element extending in a longitudinal direction of the body in a direction from a rear end to a front end, the plate-shaped element being pivotally connected with the aircraft body at one end so that it can pivot about a substantially horizontal axis and the other end of the plate-shaped element in the inoperative position is located near the aircraft body, while in the operative position it moved away from the aircraft body.

Abstract: An aircraft, comprising a body; a structure providing flying of the aircraft; and a structure for preventing or at least reducing chances of crash of the aircraft in the event of malfunction, the preventing and reducing structure include a structure for preventing a direct hit of the body of the aircraft against a surface.

Abstract: A miniature, unmanned aircraft having a parachute which deploys automatically under certain conditions. The aircraft has a flight control system based on remotely generated signals, potentially achieves relatively high altitude flight for a remotely controlled aircraft, and can thus operate well beyond line-of-sight control. For safety, an automatically deployed parachute system is provided. The parachute deployment system includes a folded parachute and a propulsion system for expelling the parachute from the aircraft. Preferably, a microprocessor for flight management sends intermittent inhibitory signals to prevent unintended deployment. A deployment signal is generated, illustratively, when the microprocessor fails, when engine RPM fall below a predetermined threshold, and when the aircraft strays from predetermined altitude and course.

Abstract: There is provided a store ejection system, store, and method for mounting a jettisonable store on an aircraft. The system uses a pressurized non-pyrotechnic fluid from a pressure vessel integral to the store and sealed by a releasable seal as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure vessel, a dump valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the dump valve to an open position in response to a control signal to jettison the store. The seal is configured to hermetically seal the pressure vessel before the actuation system is connected to the pressure vessel, and the actuation system is configured to be fluidly connected to the pressure vessel upon release of the releasable seal.

Abstract: An urgent purpose for solving the lost of life issue during airplane travel. This device comprises an integration of three pressurized parachutes, which are determined by the weight of each section of the airplane, also comprising an air compressor battery or generator that controls the constant air pressure and release valve of this system. However this system functions on its own by pushing the switch in the cockpit, then it releases the system. This system also runs off its own airflow system, not the airplanes pressurized functions. When releasing the system, pressurized air is released from holding the Air, Spring Rod Locking Shoes, this frees the arrow dynamic pressurized doors which are connected and manufactured with the fire proof parachute. This allows the parachute to spring out and do their job, also there can be another switch hooked to the system for a floatation on device that works the same way underneath the plane.

Abstract: A parachute system for a miniature aircraft having a storable parachute mounted on an upper surface of the aircraft. The system includes a canopy having a stored condition and an expanded condition. A plurality of suspension lines have first ends connected to the periphery of the canopy and second ends connected to an elastic member. First and second risers are connected by their first ends to the upper surface of the aircraft between the front end and center of gravity on either side of the longitudinal axis and by their second ends to the elastic member. A restraint system releasably restrains the parachute in the stored condition on the top surface of the aircraft; and a release system coupled to the restraint system releases the parachute upon command such that aerodynamic forces will cause the parachute to open.

Abstract: A miniature, unmanned aircraft having a parachute which deploys automatically under certain conditions. The aircraft has a flight control system based on remotely generated signals, potentially achieves relatively high altitude flight for a remotely controlled aircraft, and can thus operate well beyond line-of-sight control. For safety, an automatically deployed parachute system is provided. The parachute deployment system includes a folded parachute and a propulsion system for expelling the parachute from the aircraft. Preferably, a microprocessor for flight management sends intermittent inhibitory signals to prevent unintended deployment. A deployment signal is generated, illustratively, when the microprocessor fails, when engine RPM fall below a predetermined threshold, and when the aircraft strays from predetermined altitude and course.

Abstract: An airbag system for elevating the fuselage of an aircraft off a landing surface a sufficient degree to allow for emergency egress of passengers and crew through ventral emergency exit doors. An airbag assembly made up of a plurality of independent airbags is disposed within the aircraft. When activated, the airbag system deploys the airbags external of the aircraft that elevate the fuselage of the aircraft a sufficient degree to allow for utilizing the ventral emergency exit doors on the fuselage to enable evacuating the passengers and crew. An activation mechanism is connected to the inflation.devices associated with each of the airbags. The activation mechanism generates an electrical signal which activates the inflation devices, which in turn fill the airbags with a compressed fluid, thus expanding the airbags and lifting the fuselage. A crew member initiates the activation of the airbag system through one or more switches.

Abstract: A flying drone includes a flight control computer, a parachute system with a parachute, a power supply system, a propulsion system, and an actuating drive system, without any of these systems being redundantly duplicated. To prevent uncontrolled crashing of the drone due to a critical error of any subsystem, signals or data are supplied from the power supply system, the propulsion system, and the actuating drive system, to an error detection or recognition device, which detects defined errors or error combinations in the provided signals or data and then supplies a deployment signal to the parachute system, which responsively generates a control signal that triggers an ejection mechanism to eject the parachute.

Abstract: A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload. Servo system adjust the length of each of the plurality of control lines attached to the parachute to provide a means for controlling the parachute so as to control the speed, direction and lift of the parachute recovery system.

Abstract: A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload. Servo system adjust the length of each of the plurality of control lines attached to the parachute to provide a means for controlling the parachute so as to control the speed, direction and lift of the parachute recovery system.

Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.

Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.

Abstract: Inflation of impact absorbing bags is effected in time delayed relation to selective jettisoning of damaged landing gear on a helicopter prior to landing for replacement of the landing gear by the bags, without puncture thereof by the landing gear being jettisoned.

Abstract: A parachute recovery system which provides for the recovery of a payload such as a target drone without damage by allowing for a safe, non-destructive landing of the payload at a desired landing location. The parachute recovery system comprises a payload, a parachute or parasail and a guidance control electronics and servo system. The parachute, which is rectangular in shape, is connected by a plurality of control lines to the guidance control electronics and servo system, which is attached to the payload. The payload may be an air launch component such as a spacecraft, a target drone, unmanned air vehicle, camera film, or similar apparatus. The guidance control electronics and servo system is used to control glide path trajectory and provide for a safe non-destructive landing of the payload.

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract: A relatively simple system for avoiding light aircraft crashes, using rate-of-turn sensors, high pressure air containers and solenoid-operated air valves. The rate-of-turn sensors, when magnitude of turns exceed the predetermined values, close one or more relays, which then cause solenoids to operate to open air valves, allowing high pressure air to blast out to prevent misbehavior of the aircraft, such as excessive roll or pitch axis turning, while also providing buoyancy to the aircraft so that the aircraft does not lose altitude rapidly. This aircraft crash avoidance system operates automatically, without any need for pilot input. However, the pilot has the ability and option to disengage any or all portions of the crash avoidance system.

Abstract: A retractable airfoil assembly (20) augments the wing surface area (28) of an aircraft (22) enabling it to fly without stalling at reduced speeds during takeoff and landing. The airfoil assembly includes flexible sails (42, 44) and a furling mast (24) for extending and retracting the sails. The furling mast includes a furling drum mounted for clockwise and counterclockwise rotation on a static tube (50). The flexible sail assembly also includes guide tracks (80) located along a leading edge (101) or tailing edge (40) of the wings. The tracks guide the flexible sails during extension and retraction. A drive cable (26) extends and retracts the sails (42, 44) along the guide tracks and maintains tension in the sails while they are extended.

Abstract: A parachute device for a helicopter includes a canopy confining case having a stationary casing part, and a removable casing part mounted removably on the stationary casing part. The stationary and removable casing parts cooperatively form a compartment to receive a parachute canopy that has a release cord connected to the removable casing part, and a suspension line unit. An anchoring line has one end that extends into the canopy confining case and that is coupled to the suspension line unit of the parachute canopy. A rocket member includes a launch tube mounted on the stationary casing part externally of the compartment, and a rocket disposed in the launch tube and connected to the removable casing part. The rocket is capable of propelling from the launch tube when ignited. An ignition control line has a first end connected to the rocket member, and a second end provided with an ignition unit that is operable so as to ignite the rocket.

Abstract: A helium actuated airplane parachute including an airplane having a rectangular compartment formed therein with an associated top opening. A flexible inelastic parachute is included having a closed hemispherical configuration with an open bottom having a peripheral edge. A plurality of strings each have a first end spacedly coupled to the peripheral edge and a second end mounted to a bottom face of the compartment. A helium gas tank is situated adjacent the compartment. The gas tank is connected to an actuator valve mounted on the bottom face of the compartment below the parachute when in a folded undeployed orientation. The actuator valve is adapted to release gas within the compartment thereby deploying the parachute.

Abstract: An aircraft landing assist system comprised of a preformed and prepacked parawing-bag and fuselage housing and deployment is described. In case of emergency the system can be deployed automatically, manually, or by means of explosive charge. After deployment the open doors and the self inflated parawing-bag catch the on rushing air forcing the nose of the aircraft up. This helps increase the glide ratio and decrease the velocity of the aircraft. Control of the aircraft remains through the use of the upper wing surfaces and tail assembly. Upon landing the system helps extend the time of, and surface area of impact. Drains are provided in the aft section of the parawing-bag(s) to release rain or snow.

Abstract: A water-impact release mechanism has a hub with a first sleeve coupled thto. The first sleeve has a plurality of circumferentially distributed holes therein. A spring assembly, coupled to the hub, extends into the first sleeve. In a relaxed state, the spring assembly obstructs the holes while, in a compressed state, the spring assembly does not obstruct the holes. A second sleeve, concentric with the first sleeve, is elastically coupled to the hub and biased away therefrom. The second sleeve has an inwardly-facing annular groove. A ball resides in each of the holes and is large enough to extend beyond the confines of its hole. When the bias of the second sleeve is overcome, the annular groove aligns with the holes in the first sleeve thereby allowing the radial outward movement of the balls. A plate, coupled to the second sleeve, extends radially outward therefrom to define a water-impact surface.

Abstract: An airbag protection system for helicopters. Airbags are inflated either automatically or manually, or a combination of both, prior to the helicopter striking the ground, thus avoiding or ameliorating a crash. Proximity sensors detect a fast descent to trigger inflation of the airbags located beneath the helicopter fuselage so that they can cushion the impact with the ground. Venting of the gas from the airbags is also provided to release the gas from the airbags so as to prevent rebound of the helicopter from the ground.

Abstract: The assistant landing device of a troubled airplane of the present invention comprises a storing chamber under the front end of the airplane, which has a freely opened door, and a strengthen network the front end of which is connected with the airplane body. When the network is expanded from the storing chamber, it will not affect the descent of the front and back landing gears. A plurality of canopy packets arranged as an array are installed on the front and back sides of the network and may be opened by controlling so that a group of canopy packets are formed on the right and left sides of the body of the airplane so that the airplane may be descended slowly. Each of the canopy packets has a large and a small canopy packets and a gas container for being quickly charged with air so that the small canopy packet may be opened.

Abstract: An aircraft rescue system is provided including a plurality of parachutes coupled to a tail of the aircraft, a midsection of the aircraft, and a nose of the aircraft. The parachutes are adapted to deploy upon the actuation thereof. A control mechanism is included for allowing a pilot to manually actuate the parachutes.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section and a lower section. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded closed, extracted from an aircraft, deployed in the air and landed with the aid of parachutes.

Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: An emergency soft-landing system (10) for use on a rotor-type aircraft such as a helicopter (70). The system (10) includes at least one parachute-containing structure (12) that houses at least one parachute (50). The structure (12) is designed to be selectivelly attached to various locations on the helicopter's lower surface (76), the sides (82), and to the landing gear struts (85). The parachute (50) is deployed from the structure (12) when an out-of-control landing is unavoidable or an extreme emergency exists. The system (10) can be designed so that the parachute-containing structure (12) operates in combination with an airbag (60). An airbag can be attached to the helicopter's lower surface (76) near the rear end (78), and front end (80), and to the center of the helicopter between the landing gear (84). The parachute(s) (50) and airbag(s) (60) are designed to be manually deployed by a helicopter crew member or automatically by a dynamic responsive switch (34).

Abstract: An air-chute safety system (10) for an aircraft (12) having a fuselage (14) with a cockpit (16) and a tail end (18), and a pair of wings (20) with engines (22). The system (10) comprises a plurality of drag parachutes (24) stored in and deployed from the tail end (18) of the fuselage (14), in conjunction with an aerodynamic braking apparatus in the aircraft (12), which will shut down the engines (22) during an emergency when in flight, so that the aircraft (12) will slow down. A plurality of top parachutes (26) are provided. A structure (28) is for storing each of the top parachutes (26) in vertical spaced apart relationships below a top surface (30) of the fuselage (14) between the cockpit (16) and tail end (18) thereof.

Abstract: The present invention relates to an emergency landing auxiliary apparatus of an aircraft using a parachute, whereby a rapid accident crash of an aircraft can be avoided through releasing the chute set inside an apparatus accepting room 11 and the landing distance of the aircraft can be reduced in case of an emergency landing. Therefore, the present invention is effective in decreasing a possible loss of lives and the damage of the aircraft itself.