Abstract: A propeller-driven rocket has a body that is divided into multiple pieces. During the launch and climb, the body reaction to the torque of the propeller keeps the body panels pressed into their initial orientation. At the apex of flight, or a predetermined time from launch, the propeller reverses direction for short period of time. This reverses the forces on the body panels, causing them to release outward. The body panels are hinged such that they may form a rotor for an auto-rotating, controlled descent.

Abstract: A modular flying car includes a ground vehicle and a flight vehicle. The ground vehicle includes a chassis, a first cabin and a landing platform for landing the flight vehicle. The flight vehicle includes a second cabin and a flight driving device. The flight vehicle is capable of landing and taking off vertically on the landing platform and connected with the ground vehicle by interlocking. Users can choose to travel by the ground vehicle or the flight vehicle, and can transfer between the ground vehicle and the flight vehicle, to solve the traffic jam problem and make the realization of the flying car more feasible. A flying car system and a flying car sharing method are also disclosed.

Abstract: A hybrid airship (drone, UAV) capable of significantly extended flight times can use one of two technologies, or both together. The first technology uses a combination of a lifting gas (such as hydrogen or helium) in a central volume or balloon and multirotor technology for lift and maneuvering. The second technology equips the airship with an on board generator to charge the batteries during flight for extended flight operations, with an internal combustion engine (such as a high power to weight ratio gas turbine engine) driving the generator. A quadcopter or other multicopter configuration is desirable.

Abstract: A geostationary platform is held afloat by a superpressure balloon. A suitable altitude is 25 km. The craft carries electrohydrodynamic thrusters, to overcome winds, held within a scaffold. Sensors determine position, velocity, acceleration and vector. A CPU performs instructions for station-keeping or navigation. A communication system is included to, inter alia, receive instructions from the ground. The craft carries a payload for observation and transmission, cradled in a temperature-controlled chamber. Power to the platform is transmitted in the form of electromagnetic waves (with suitable frequencies including microwaves of 2.45 GHz or 5.8 GHz) from a ground-based transmitter to a receiving antenna on, or affixed to, the balloon which converts the electromagnetic energy to direct current. A step-up voltage converter increases the voltage as required. A ground station monitors craft position and operational efficiency by radar to help ensure safe takeoff, operation, and landing of the craft.

Abstract: A geostationary platform is held afloat by a superpressure balloon. A suitable altitude is 25 km. The craft carries electrohydrodynamic thrusters, to overcome winds, held within a scaffold. Sensors determine position, velocity, acceleration and vector. A CPU performs instructions for station-keeping or navigation. A communication system is included to, inter alia, receive instructions from the ground. The craft carries a payload for observation and transmission, cradled in a temperature-controlled chamber. Power to the platform is transmitted in the form of electromagnetic waves (with suitable frequencies including microwaves of 2.45 GHz or 5.8 GHz) from a ground-based transmitter to a receiving antenna on, or affixed to, the balloon which converts the electromagnetic energy to direct current. A step-up voltage converter increases the voltage as required. A ground station monitors craft position and operational efficiency by radar to help ensure safe takeoff, operation, and landing of the craft.

Abstract: A safety system for an aerial vehicle, preferably including: a ballistic subsystem, preferably including one or more rockets operable to adjust motion of the aerial vehicle and a mounting unit that couples the ballistic subsystem to the aerial vehicle; and/or a deployable parachute subsystem. An aerial vehicle, preferably including a safety system. A method for aerial vehicle operation, preferably including activating a safety system.

Abstract: A multi-modal vehicle (“MMV”) 20a-20d. The MMV 20a-20d includes a fuselage 22 and a chassis 26 supporting at least three wheels 44 having deployed and stowed states. Extending away from the fuselage 22 is a canard wing system 28 and a main wing system 30. The main wing system 30 includes an inboard portion 134 and an outboard portion 132. The inboard portion 134 is pivotally connected to the fuselage 22; the outboard portion 132 is pivotally connected to the inboard portion 134. The MMV 20a-20d further includes a vertical thrust system 32 comprising a pair of ducted fans 100 that are incorporated into the fuselage 22, and a dual-use thrust system 34 that is configured to transition between a first position for supplying vertical thrust and a second position for supplying a horizontal thrust. A controller 42 is configured to control the MMV operations, reconfigurations, or transitions.

Abstract: An intermediate support structure for the cockpit of an aircraft is provided. The intermediate support structure includes a raised floor and at least one structural element extending as an arch above the raised floor, the arched structure being adapted to hold in position at least one item of equipment in the upper part of the cockpit. The intermediate support structure also includes a fastener for mounting the intermediate support structure onto a fuselage primary structure, where the fuselage primary structure defines a portion of the cockpit of the aircraft.

Abstract: A hingeless door system for a pressure vessel; especially, aeronautic and astronautic crafts. The door system has the following major components: a contour in a pressure vessel wall, a doorway opening, a seal, an upper track, a lower track and a door. The door translocates laterally along the tracks from an open position to a closed position and moves radially along the tracks to a sealed position against the contour which closes the door opening. The problem solved by the invention is to reduce weight, operational volume and complexity and increase durability of a door system for a pressure vessel.

Abstract: A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Abstract: An amphibious protection apparatus including wall members, an occupancy space, and an access region is provided. Each of the wall members is foldably and detachably connected to the other wall members. Each of the wall members has an enclosed space that is inflatable by a fluid injected into the enclosed space. The inflation of each of the detachably connected wall members forms a buoyant enclosure of a predefined configuration, which bounces on land and floats on water. The occupancy space is defined by the detachably connected wall members and accommodates the users. The access region defined by opening one of the detachably connected wall members provides access to the occupancy space. The amphibious protection apparatus inflated to form the buoyant enclosure protects the users accommodated within the occupancy space from impacts from different directions on land and water and provides safety to the accommodated users on land and water.

Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

Abstract: A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Abstract: A cockpit and an aircraft including such cockpit. The cockpit includes a front section of an aircraft. Such cockpit includes a pressure bulkhead sealing the section and a pressurization system for pressurizing such section.

Abstract: A parachute support system for supporting a helicopter emergency parachute is provided, comprising a parachute support shaft located within a main rotor shaft, said parachute support shaft being rotationally separated from the rest of the helicopter through the use of bearing supports or enclosures. As the parachute support shaft is connected to the main rotor shaft at multiple distinct and distant points, the system described also provides a preferable load path transfer route, such that parachute system malfunction is minimized.

Abstract: An emergency escape sequence for a commercial aircraft is shown. Individual pods that are separable from the aircraft are ejected individually, following the separation and ejection of the upper cabin from the fuselage. Parachutes are deployed to assist in the safe descent of the pods. Airbags are also deployed to soften the landing and provide flotation in case of a water landing.

Abstract: A method and apparatus for a composite helicopter comprising a rotary wing parent vehicle with various modular cabins detachable therefrom to facilitate various configuration aircraft platforms, dual operation and modular economy.

Abstract: A vertical take-off vehicle includes two thermoreactors/turbine engines having a rectangular air inlet opening into a positive-displacement rotary compressor supplying compressed air to a tank connected to (i) a combustion chamber whose exhaust gases actuate a compressor-driving turbine and discharge onto the fixed rear wing upper surface, and (ii) the combustion chamber of the main engine whose exhaust gases discharge directly onto the wing upper surface, the variable incidence of which, in take-off mode, generates a lift force adding to the forces that develop on the front wings. In take-off mode, the variable-geometry upper surfaces of the front wings have a maximum camber onto which the exhaust gases produced in an internal combustion chamber flow at great speed. In cruise mode, the combustion chamber is off and the upper surface returns to a reduced camber position as the rear wing returns to an incidence optimizing total drag and lift forces.

Abstract: Aircraft 5 with a detachable passenger escape cabin 1 comprising detachable piloting systems, namely the center pedestal 3b, the control stick 1k, the pedals 1r as well as the upright sliding bars 1v, 1v?, and 1t, 1t? between cabin 1 and opening 3 of aircraft 5 for an easy and rapid disengagement of cabin 1 from fuselage 4.

Abstract: An autonomous passenger module is releasably carried on a super-sonic aircraft, such as a military fighter jet, for carrying plural passengers on supersonic and near space flights. The passenger module is equipped with passenger service and life support systems to provide oxygen and the like, a parachute system, and a landing airbag or flotation aid system. The module remains mounted on the aircraft throughout a normal flight. In an emergency situation, the module separates from the aircraft by means of releasable connector elements and descends using parachutes. The module provides high passenger capacity at a low cost in a simple manner for commercial supersonic flights using an existing supersonic aircraft as a carrier platform.

Abstract: An Aircraft Escape (AEC) is designed for manned atmospheric or space vehicles having a fly away capability at any time during the flight of the parent aircraft. The AEC houses the crew, passengers, life support systems, aircraft flight controls, propulsion, navigation instruments, communications equipment, and deceleration devices to permit safe landing of the escape cabin on land or water. A rocket or mechanical device provides the means to actively separate the escape cabin from the parent aircraft during an emergency.

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 ejection escape system for passenger airplane that there is a locking mechanism at the connection of the left top cabin cover, the right top cabin cover with the airplane body, there is also a locking mechanism at the connection of the left top cabin cover and the right top cabin cover, the passenger seat is an ejection escape seat, the switches for the locking mechanism and the ejection escape seat are installed in the cockpit, where the pilot can turn on the locking mechanism switch to open the left and right top cabin covers and turn on the ejection escape switch to eject the seat out of the airplane through the opening of the left and right top cabin covers.

Abstract: An aircraft with a detachable cabin (1) that serves to rescue its passengers as a result of the aircraft's sudden fall either due to its malfunction or fire. The cabin escapes either smoothly or by means of fast ejection and descends slowly to the Earth with the aid of a parachute (13, 14); during a crash on the ground or in the sea external airbags (38a-38f) with which it is equipped and which are located in its lower part are inflated thus absorbing the loads that are developed during the crash. In addition a conventional aircraft (70) of the type being already in use is also described and in which the parachute equipment (71) has already been applied; however, the proposed equipment of the airbag boxes (72a-72c) is adapted to it for the absorption of the energy produced due to its crash on Earth in case of its sudden fall.

Abstract: An evacuation system and method for an airplane. The evacuation system and method consists of an evacuation cabin that is positioned within an airplane, and that is deployed through a trap door in the bottom of the airplane. The evacuation cabin is positioned on guide rails that control up and down movement. One or more parachutes located at an upper portion of the evacuation cabin control its velocity when deployed. A flotation device positioned at the bottom of the evacuation cabin may be used in the event of a water landing, or an as impact attenuator.

Abstract: A apparatus with releasably fastened transport units for carrying a useful load, such as persons or freight.

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: An airplane has an outer shell with a plurality of individual passenger cabins slidably located with it in a tandem manner. The outer shell is severable at a predetermined breakable location by various methods. The outer shell is severable with control explosion devices mounted in a front mounting ring and rear mounting located at the breakable location. It may be severable with a high speed cutting mechanism or a laser cutting knife. The passenger cabins are provided with independent oxygen supply, heating, a heat protective shield, deployable parachutes, descending speed control propulsion jets for landing them safely onto the ground after they have separated from the main body in an air accident. Inflatable rafts are provided on each passenger cabin to support the cabins if it lands on water. The passenger cabins have sealing doors which automatically shut the individual passenger cabin when it separates from the main body.

Abstract: A occupant protection system for protecting an occupant of a motor vehicle, boat, or airplane during a crash. The occupant protection system includes a chair positioned inside a vehicle such as an airplane, automobile, truck, or a boat. The chair has a seat portion and a backrest portion. The seat portion has a pair of leg clamp panels pivotally coupled to it to lock a pair of legs to the seat portion in anticipation of a crash. The backrest portion has a pair of arm clamp panels pivotally coupled to it to press the arms and torso of a user towards the backrest and hold them tightly therebetween. Also disclosed is a capsule in which the chair is disposed. The capsule has several protective layers. An emergency raft forms part of the backrest of the chair when not in use, and is removable for use in case of an accident on or above water.

Abstract: A life preserver for aircraft includes a fire-protective, anti-knock, inflatable bag defining an inflatable chamber and a life chamber within the inflatable chamber and having an exit, a bumper frame structure supported inside the life chamber for protecting the user in the life chamber, a safety helmet with a mouthpiece connected to an oxygen cylinder mounted in the bumper frame structure for providing oxygen to the user, and a parachute carried on the inflatable bag on the outside and controlled by a rip cord suspended inside the life chamber.

Abstract: A method of transporting large numbers of passengers by air from a departure airfield to a destination airfield. The method comprises providing a large flying wing airframe, providing a plurality of passenger pods adapted to be loaded with passengers at a traditional airport gate facility, loading the pods with passengers, transporting the loaded pods to the airframe parked on the tarmac, attaching the loaded pods to the underside of the airframe, and flying the airframe to the destination airfield. The method further comprises detaching the pods from the airframe in the event of an in-flight emergency and deploying parachutes from the detached pods to lower them safely to the ground. A high density air transport system that embodies the method of the invention is also provided.

Abstract: An aircraft passenger extraction system having a fuselage and a tail section removably attached to the fuselage. A plurality of interconnected passenger modules are removably disposed within the fuselage. Four I-beam rails are longitudinally mounted about the inside circumference of the fuselage, and the passenger modules have four sets of wheels that slide on the rails. The tail section has four pairs of separation flaps and four extraction flaps to assist in the separation of the tail section in the event of an airborne emergency. Upon separation of the tail section of the fuselage, the interconnected passenger modules are slidingly withdrawn from the fuselage. Once the passenger modules clear the fuselage, the interconnections of each passenger module are severed in sequence, and a series of parachutes are deployed to safely float each passenger compartment to earth.

Abstract: A safety airplane comprising a carrier portion and a saddle portion. An assembly is for retaining the saddle portion on the carrier portion. A structure is for releasing the saddle portion from the carrier portion, when there is a problem during flight. Paraphernalia is for gently lowering the saddle portion to the ground.

Abstract: The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes.

Abstract: An improved cockpit area for manned atmospheric or space vehicles includes a generally spherical, multi-axis G-compensating cockpit capsule which houses the crewmen, together with the appropriate operational and navigational instruments and the mechanisms necessary for controlling the vehicle and which is rotatably mounted in the vehicle and is controllable by the crewman to permit the crewman direct visual observation throughout virtually a full circle about the vehicle, without altering the course of the vehicle, together with a device for automatically rotating the capsule to minimize the effect of high G-forces on the crewmen, and an emergency mechanism for ejecting the capsule, with the crewmen therein, and for protecting the crewmen during and after descent and landing of the capsule.

Abstract: A personnel capsule extraction apparatus having a personnel capsule mounted on extraction platform which is ejected from a low flying aircraft at an altitude between five and ten feet above the ground. A drougue parachute is utilized to deploy a large extraction parachute which pulls the personnel capsule out of the aircraft.

Abstract: A crew capsule 2 is connected to the body 3 of a spacecraft by a releasable coupling comprising a housing 6 secured to the capsule, a sleeve 9 secured to the body 3, and clamps 11-15 engaging interrupted thread 10 on sleeve 9 and having hooked ends engaging a flange 7 on housing 6. In an emergency during launch, an hydraulic ram 21 energized by a pump 24 is actuated to rotate the clamps 11-15, which are circumferentially interconnected, relative to the sleeve 9 to disengage the clamp threads from the sleeve thread sections 10; then explosive charges 25 are fired to separate the capsule 2 from the body 3, the capsule subsequently descending by parachute.A similar releasable connection may be used between segments of a Solid Rocket Booster, or between the passenger cabin and other parts of a passenger-carrying aeroplane.

Abstract: A crew protection system designed to isolate an aircraft crew and provide a means for safely evacuating an aircraft, particularly hypersonic vehicles, in emergency situations. The crew compartment is designed within the forebody of the main vehicle. The forebody is designed so as to separate cleanly from the main vehicle as by generation of a circumferential structural break, in the event of a catastrophic failure or explosion of the main vehicle fuel tank. In the event of such an uncommanded failure of the main tank and propellant combustion, resulting in the above noted structural failure, the resultant pressure impulse thrusts the forebody containing the crew compartment clear from the remainder of the vehicle. The provision of a system of baffles in the forebody between the crew compartment and the fuel tank, and the shape of the forebody and the materials used in its construction mitigate the effects of the blast pressure impulse on the crew.

Abstract: An integrated capsulized cabin for a passenger aircraft is provided and consists of an independent frame structure with a pair of bulkheads on each end in which sliding bulkhead doors will close by air pressure during air pressure loss to seal the cabin. A very strong elastic wire mesh material is disposed about the frame structure within the fuselage of the aircraft to reinforce the frame structure during expansion and contraction conditions.

Abstract: A multi stage high-altitude data acquisition system comprising a first stage manned lighter-than-air, engine propelled aircraft and a second stage air-buoyant vehicle of stratospheric altitude attaining capability statically sustainable aloft by a sufficient quantity of lighter-than-air gas contained within an expandable envelope balloon to carry the vehicle to a stratospheric float altitude and transportable from ground level to a tropospheric launching altitude by the first stage aircraft from which the air buoyant vehicle and its partially expanded gas containing envelope is releasable at the launching level while the first stage aircraft is established in a flight condition of substantially zero airspeed.

Abstract: A flying emergency ejection seat for endangered airman to escape from distressed aircraft and to fly cross country in the seat to sanctuary of a more favorable environment for recovery having the following existing state-of-the-art non-flying seat survival features of an airman's ejection seat including: a parachute, a rocket/catapult propelled escape seat for ejection, a survival kit for air, land, and water survival equipment, guidance controls on the escape seat and mating guides in the aircraft to direct the path of the seat ejection from the aircraft, seat/man separation device, and added on design features of this invention to make it a flying seat:shall include add-on folding wings for extension in flight to sustain the seat in flight, add-on extendable empennage for extension during ejection to stabilize and guide the direction of flight of the seat in a prone attitude, add-on actuators on the seat bucket to stretch out the airman into a physical prone head down, face forward configuration for minimum

Abstract: An airplane safely body passenger compartment is provided which contains a mechanism for ejecting the passenger compartment from an elongated receptacle in the fuselage when an airplane is in danger of crashing so that parachutes will gently float the passenger compartment to the earth.

Abstract: A turbojet aircraft has a fuselage pod in which all fuel is stored for engines also linked to the pod. The pod and engines can be jettisoned in flight to improve aircraft performance in the event of a forced landing.

Abstract: A capsule and rocket extraction system for providing an inflight escape system for the pilot of a damaged aircraft. The system comprises a capsule that is separable from the main fuselage of the aircraft and a rocket for extracting the pilot from the capsule. A control system is carried by the capsule for sensing the capsule's speed, altitude and attitude, and for actuating only the rocket to extract the pilot directly from the capsule when the speed, altitude and attitude are at predetermined conditions, and for sequentially actuating a capsule separation device to separate the capsule from the main fuselage and then actuating the rocket to extract the pilot from the separated capsule when the speed, altitude and attitude are at different predetermined conditions.

Abstract: A dropable main fuel tank that comprises a portion of an aircrafts lower fuselage or part of the wing structure contains all nonessential fuel for takeoff or landing. Airfoils, parachute, or rocket motor built into the main fuel tank will separate the main fuel tank from the aircraft quickly when dropped or released in a possible crash situation, thus preventing the aircraft from being consumed by its own nonessential fuel in a crash.A nondroppable auxiliary fuel tank on the aircraft will sustain the aircraft after the main fuel tank has been dropped. The auxiliary fuel tank contains only enough fuel for takeoff and landing. Shackels and parallel tracks hold the droppable main fuel tank in place on the aircraft until the main fuel tank is released for subsequent ejection rearward. In refueling the aircraft an external control panel on the aircraft will release the main fuel tank onto a refueling vehicle for refueling at a nearby fuel dump.

Abstract: An airplane features one basic airframe capable of carrying passengers or cargo such as intermodal containers or vehicles. It consists of a basic structure containing the cockpit, wings, engines and empennage. The cockpit and empennage portions are connected by an open, flat section (similar to a flatbed truck) on which the payload is placed. The payload thus forms and constitutes the fuselage shape and may be comprised of a passenger pod, cargo containers or outsized and vehicular equipment. Loading and unloading of such payloads is facilitated by a removable forward section to permit front end access and by laterally disposed vertical tails for aft end access.

Abstract: A powered aircraft has a jettisonable fuel tank releasably secured in the bottom of its fuselage. A valve is arranged to shut off fuel flow from the tank upon releasing of the tank from the fuselage, whereupon a parachute connected to the tank is released to slow the descent of the tank. Additionally, a reserve fuel tank in the fuselage is normally connected to the jettisonable fuel tank, and the valve is so arranged that fuel flow communication is normally maintained between the jettisonable fuel tank and the aircraft engine while fuel is prevented from flowing from the reserve tank to the engine. However, when the jettisonable fuel tank is released from the fuselage, the valve shuts off the flow of fuel from the jettisonable fuel tank and establishes open communication between the reserve tank and the engine to permit continued operation of the aircraft under power of the engine.

Abstract: An aircraft which includes a lower main support structure to which there is attached wings, empennage, and a cabin section. The cabin section is positioned forwardly of the empennage and is supported in overlying relationship respective to the lower main support structure and to the wings attached thereto. The cabin section has a deck attached to an upper platform of the main support structure in such a manner that the cabin section can be moved horizontally and forwardly respective to the platform. A plurality of fasteners are arranged to affix the cabin section to the main support structure. Some of the fasteners are in the form of releasable bolts and other of the fasteners are in the form of shear bolts which attach the platform and deck together. Accordingly, should the aircraft impact against an object with sufficient force, some of the fasteners are released to enable the cabin section to separate from the remainder of the aircraft and to continue to travel away therefrom.

Abstract: An escape capsule integrally designed within a parent aircraft and having a fly-away capability throughout the entire speed range of the parent aircraft. The capsule utilizes segments of the leading edges of the aircraft wings to provide flight capability and stabilization to the capsule, an elevon system controlling the capsule about both its lateral and longitudinal axes, and rudder and vertical stabilizing elements for controlling the capsule about its vertical axis. A rocket is provided to supply the thrust necessary to accomplish positive separation of the capsule from the parent aircraft along a required trajectory. A thrust system, such as a turbojet or fan jet engine, is provided for sustaining the capsule in flight.