RU2336203C2 - Rescue system of airplane (versions) - Google Patents

Abstract

FIELD: transportation.

SUBSTANCE: rescue system of airplane contains operated at flight wing panel connectors, fins, rudders and motor balloon car. In wing fuel tanks and in motor there are pyrocartridges responses simultaneously with connectors, or time-lagged, or blocked.

EFFECT: invention allows improving of efficiency and safety of flights.

3 dwg

Description

The invention relates to the construction of aircraft, both civilian and military. The invention is particularly well suited for integrated layout aircraft / when the fuselage has a wing-shaped profile and a relatively large width, that is, in the aerodynamic sense it is part of the wing - Mig-29, Su-27, Su-31 / and having a “scissors” elevator as a control function and controlled thrust vectors of two engines.

Known aircraft having a detachable in an emergency cabin with wings, engine and controls / cm. U.S. Patent B 419173, MKI V64D 25/12 /. The disadvantage of the prototype is that only the crew is saved and, at best, there is no cockpit / landing gear in the cockpit. The plane itself dies or, at least, cannot continue the flight.

The purpose of the invention is a partial restoration of the aircraft’s operability in case of some damage to the wing consoles, keel and rudders or in case of a fire installed in the engine nacelles. As well as an increase in flight speed in extreme situations and the creation of radar and thermal false targets.

To do this, each wing console has one or more connectors in the longitudinal vertical plane, and the consoles, keels, rudders and engine nacelles themselves are attached to the fuselage with detachable mounts that can be controlled open in flight.

Such fasteners can be, for example, pyro-bolts (hollow bolts having a microproduct of explosive).

Or, the indicated structural elements of the aircraft can be equipped with tape cumulative pyro-charges, "cutting off" it at the command of the pilot or automatically.

A relatively large area of the wings and rudders of modern aircraft, especially supersonic ones, is necessary only for take-off and landing, as well as good maneuverability at low speeds. When flying at speeds close to maximum, the area of the wing and rudders can be reduced by 50-100 times, that is, the lifting force of only the fuselage, which is set at an angle to the incoming flow, may be sufficient. For example, takeoff and landing speed and maximum speed of Mig-29 and Su-27 aircraft differ by about 10 times. The lifting force of the wing is approximately proportional to the second degree of speed. That is, these aircraft can fly at ground level with a wing 100 times smaller in area than the existing one. The wing-shaped area in the fuselage profile is approximately 30% of the total wing area. That is its lifting. force, even taking into account the decrease in the aerodynamic quality of the wing / a at supersonic speeds, it weakly depends on the elongation / it is quite enough to continue the flight and complete the flight mission. If, however, not all the consoles are "shot off", but only part of them, then the plane can even land on a runway of sufficient length.

With a decrease in the wing area, the relative area of the keel and rudders increases, that is, the controllability of the aircraft will not only remain, but also increase.

When shooting one of the keels or rudders, controllability will deteriorate, which can be compensated by an increase in the deviation of the controls. When shooting both keels and / or rudders, handling will deteriorate critically. But aircraft with a controlled thrust vector in two engines can even maintain controllability both in pitch and direction, and in roll / changing the thrust vector of two engines in different directions /, possibly by shooting wings for this console.

When shooting parts of the wing consoles with ailerons, roll control can be maintained even without a controlled thrust vector - due to the mechanism of “scissors” of elevators.

Even having completely shot wing consoles, both keels and both rudders, Mig-29 or S-27 aircraft will be able to continue a controlled flight, and even with even greater speed. That is, to perform a particularly important mission, the pilot can shoot perfectly operational consoles, keels and rudders, complete the task and return to the area convenient for ejection. Moreover, if there is a special device at the aerodrome / for which a separate patent application has been filed / an aircraft with good thrust-weight ratio will be able to make a vertical tail-down landing. If the engine is damaged or malfunctioned in the engine nacelle, it can be shot to reduce weight and aerodynamic drag, and if the aircraft had two or more engines, it will be able to continue the flight and land.

With the real threat of an anti-aircraft missile strike, the pilot can also shoot a perfectly functional engine closest to the rocket in order to save the plane, and then continue the flight and land.

A strain gauge should be introduced into the attachment point of the engine nacelles, blocking the engine disconnection if its thrust exceeds its aerodynamic resistance. And the resultant force acting on the engine nacelle should be directed away from the fuselage. All other connectors are blocked at the minimum allowable disconnect speed.

All kinematic, electrical, and pipe connections at the separation sites are self-disconnecting, for example, using couplings, electrical connectors, slide valves, or ball valves, etc. Or they may have tape cumulative explosive microwaves that "cut off" these compounds upon separation.

The detached parts of the aircraft are false radar trap targets, and the consoles, as a result of the destruction of the wing fuel tanks and the ignition of the fuel residues from the pyro-bolt charges, are also infrared trap targets. For reliable implementation of the latter in the fuel tanks there are pyro-cartridges that fire simultaneously with pyro-bolts or are blocked if the flash causes unmasking. Or triggered with a delay, if their action is a danger to the aircraft. So it is in the engine.

Figure 1 and figure 2 schematically shows an airplane, on which the dotted line shows the possible locations of the rails of the parts of the aircraft. Figure 3 shows a section of the console of the wing of the aircraft in a vertical transverse plane, where 1 and 2 are parts of the wing spar, 3 and 4 are power ribs connected by pyro bolts 5.

The aircraft rescue system works as follows: in case of damage and deformation / for example, as a result of shelling, terrorist attack or falling into the flock of birds / parts of the aircraft, as a result of which further controlled flight becomes impossible, the pilot may cause pyro-bolts 5 to work, and the damaged part will separate from the aircraft . If the wing consoles are damaged, the detachment must be symmetrical.

When detaching consoles, if they are located on the same horizontal with elevators, the pilot should sharply lower the nose of the aircraft before opening. And when disconnecting the engine nacelles, on the contrary, raise it.

In case of fire of one or all engines, the pilot can disconnect one or even all engines and continue the flight, even if planning. which, with a reserve of height, may be enough to complete a mission, a forced landing / if passengers or valuable cargo are on board /, or to leave an area undesirable for ejection.

At the end of the flight, the pilot may be able to land / depends on the type of aircraft and what parts were shot /.

The application of the proposed system will dramatically increase the efficiency and safety of aircraft, especially when used in extreme situations.

Claims (2)

1. Aircraft rescue system comprising in-flight-controlled connectors for wing consoles, keels, rudders and engine nacelles, characterized in that in the wing fuel tanks and engines there are pyro-cartridges operating simultaneously with the connectors, or with a delay, or blocked. 2. Aircraft rescue system containing in-flight-controlled connectors for wing consoles, keels, rudders and engine nacelles, characterized in that the engine nacelle connectors are locked at the maximum permissible thrust, and the rest at the minimum permissible speed, at which a safe disconnection is possible.

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