RU2114030C1 - High speed flying vehicle - Google Patents

Abstract

FIELD: manufacture of aircraft; designing of high-speed flying vehicles for rescue of passengers and crew in an emergency. SUBSTANCE: high-speed flying vehicle includes separable upper and lower parts of fuselage equipped with wings with longitudinal quick-release joints; engines, energy carriers, tail unit and cargo compartment, passenger compartments and crew cabin located in upper part of fuselage; wings of upper separable part of fuselage are extensible; engines, energy carriers and cargo compartment are located on lower part of fuselage. EFFECT: possibility to change aerodynamic characteristics of flying vehicle to parameters necessary for landing the flying vehicle on unprepared area at power interaction with relief without breakage of vehicle and survival of crew and passengers, provided neither fire nor explosion occurs. 4 dwg

Description

 The invention relates to aircraft manufacturing and for the construction of high-speed aircraft adapted to rescue passengers and crew in emergency situations.

 Known high-speed aircraft, in which the detachable part of the fuselage is equipped with extendable wing consoles [2].

 Also known is a high-speed aircraft containing wing-mounted, shared upper and lower parts of the fuselage with their longitudinal quick-connect, engines, energy, tail, and cargo compartment, while in the upper part of the fuselage are compartments for passengers and crew [1].

 However, the aerodynamic characteristics of such aircraft do not change to parameters that would allow such aircraft to land on terrain unsuitable for force interaction with the terrain without destroying the vehicle and preserving the life of the crew with passengers with the exception of fires and explosions.

 The technical result from the implementation of the invention is to change the aerodynamic parameters of the aircraft to those values that allow you to land the aircraft on an unsuitable landing area for power interaction with the terrain without destroying the device and preserving the life of the crew with passengers with the exception of fires and explosions.

 This technical result is achieved by the fact that in a high-speed aircraft containing wings with separated upper and lower parts of the fuselage with their longitudinal quick-release connection, engines, energy carriers, tail unit and cargo compartment, compartments for passengers and crew are located in the upper part of the fuselage according to the invention, the wings of the upper detachable part of the fuselage are retractable, while the engines, energy and the cargo compartment are located on the lower part of the fuselage.

 In FIG. 1 is a schematic side view of a high-speed aircraft; in FIG. 2 - view of this device from the crew compartment; in FIG. 3 - one of the elements connecting the parts of the fuselage of the aircraft; in FIG. 4 - additional rollers (wheels) of the aircraft with their drive.

 A high-speed aircraft contains a fuselage 1, consisting of the upper 1-1 and lower 1-2 shared parts of the fuselage with their longitudinal quick-connect. The surface 2 of the connection of the parts is located along the apparatus with sections of the same shape. It can be a plane or a trough-like surface with a narrowing from the head to the rear of the fuselage of the apparatus.

 In the upper part 1-1 are the tail 3, compartments 4 passengers and compartments 5 crew. Part 1-1 has retractable wings 6. These wings 6 form a rotary system with an axis 7, the drive of which is located inside part 1-1. A fairing 8 is located in the front part to maintain the aerodynamic properties of the apparatus in a normal state. Parts 1-2 contain a cargo compartment, energy carriers (not shown in the drawing, since their layout may be different), wings 9 with engines 10 and a retractable landing gear 14. The parts 1-1 and 1-2 are connected by an insert 12 with a fastening 13 The connecting elements of parts 1-1 and 1-2 are made with a recess 14, and the insert 12 has an explosive charge in the recess 14. In the upper part 1-1, recesses 17 are provided on its lower surface for accommodating the rotary support wheels 18 with their drive 19 . In the fore and aft parts of the fuselage 1, parachutes 20 and 21 with an exhaust parachute are provided (condition but not shown).

 A high-speed aircraft is operated as follows.

 In an emergency, an alarm signal is supplied via the control electric line 16 to charge 15, the shell of the insert 12 in the recess 14 is destroyed, an explosive wave arises, which rejects parts 1-1 and 1-2 of the fuselage from each other while maintaining the horizontal flight speed of the device.

 The lower part 1-2 will fall uncontrollably, and the lightened upper part 1-1 after turning the wing 6 on axis 7 acquires a steady movement with the ability to control the tail unit 3 of the crew.

 In this case, the aerodynamic characteristics of the device will change dramatically: the mass of the device will decrease by more than 3 times, and air resistance will decrease (not less than 2 times) due to a decrease in its cross-sectional area. This will enable the aircraft to enter planning mode to search for a landing site. In this case, the flight speed will decrease, which quadratically enters the dynamic resistance. With the contact of part 1-1 of the aircraft, its speed can be reduced to the speed of the car (no more than 50-60 km / h). This will allow contact with the landing pad at any of its terrain without destroying the hull, since the speed will initially be reduced due to friction on surface 2. No permanent damage will occur if passengers and crew are fastened.

 It should also be noted that descent can be carried out only with the help of parachutes 20, 21, since the remaining mass of the hull of part 1-1 of the fuselage with 100 passengers, say, equal to not more than 20 tons, will be less than the mass of the landing tank, parachuted. Since the crew will deal with the emergency until the last moment, the aircraft may decrease with a loss of speed until the separation of parts 1-1 and 1-2 among themselves. After their separation to restore the horizontal position of the parts, the parachute 20 will be released with its subsequent separation after the device has taken a horizontal position. For such a flight mode, a parachute of significant carrying capacity is not required. The parachute can also be used to prevent the rotation of part 1-1 after separation, since the center of mass will shift, and the explosion forces may be different at different points of the quick disconnect.

 The drive 19 and the wing drive 6 may be gas or manual from the muscular efforts of the crew. In this regard, the wings 6 are made rotary in the form of a single wing. This will allow manual rotation of the wing 6 to extend it, since the resistance of both protruding parts will be approximately the same. On the wing 6 can be provided flaps with a cable manual drive, although the action of the tail unit 3 may be sufficient to control the flight.

 Landing tactics can be different, and it depends on the nature of the terrain. In all cases, the use of parachutes (especially parachute 21) is desirable for a sharp decrease in speed, if its reduction by planning and using the direction of the wind proved to be ineffective. When landing on a water surface, the aircraft will be afloat until rescuers arrive, since its average mass is less than the mass of the aquatic environment in the same volume, and the hull is sealed (at least in its lower part). When landing on a relatively flat surface, it can be touched either on surface 2, or using retractable swivel wheels 18.

 Depending on the emergency energy source and the general layout of the aircraft (and its general appearance should be approximately the same as without the detachable part of the fuselage), it is desirable to increase the area of the retractable wings 6, but for this, the axis 7 must be transferred to the head part and the drive of each parts of the wing, which will increase the deployment time of the wings, however, such a technical solution is possible.

 A control pulse on the electric control line 16 can also come from a pressure increase sensor at any point in part 1-2 while simultaneously undermining the windows in it to reduce uncontrolled effects on the hull part 1-2 of the fuselage. Such windows should be made of sheet material that withstands pressure at flight altitudes, but collapses when the pressure drop is exceeded, say, 3 times.

 When landing on the slopes of a mountain, a hill, on a forest, the aircraft can occupy a position with a significant deviation from the horizontal, but the blow will still be softened with parachutes 20, 21, and the friction of surface 2 on small protrusions of the terrain.

 Thus, the goal is achieved, namely: saving the crew and passengers in an accident of any type and in virtually any terrain. This will make flights virtually trouble-free in terms of damage to passengers.

Claims (1)

 A high-speed aircraft containing wings with separated upper and lower parts of the fuselage with their longitudinal quick release connection, engines, energy carriers, tail unit and cargo compartment, while in the upper part of the fuselage there are compartments for passengers and crew, characterized in that the wings of the upper detachable part the fuselage is made retractable, while the engines, energy and the cargo compartment are located on the bottom of the fuselage.

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