RU2152335C1 - Emergency rescue system for rescue of passengers, crew and cargoes in case of in-flight accident - Google Patents

Abstract

FIELD: rescue equipment. SUBSTANCE: rescue system includes fuselage base with engine nacelles and nose undercarriage leg on which glider is secured by means of separation devices. Port and starboard main undercarriage legs are secured respectively under glider wing. Fuselage base has fuselage undercarriage leg. Outer wing panels of glider are provided with fairings which are used as floats and two cantilever supporting struts retracted in these fairings. Separation devices are made in form of four holders with locks provided with pyrotechnical drive or double-acting drive (pyrotechnical and pneumatic). Separation devices have two pyro separation engines mounted in tail section of glider. It is held from longitudinal shift by means of front and rear stops of holders. EFFECT: enhanced reliability. 5 cl, 3 dwg

Description

 The invention relates to the field of aircraft construction, emergency equipment and aircraft protection equipment.

 The inventive system is a structure connecting the aircraft with a glider and designed to save passengers and crew in case of an airplane accident in the air, as well as to deliver various cargoes to the planned delivery location.

 The system can be used mainly to create passenger aircraft of the middle and executive class, as well as for transport and special purpose aircraft of unconventional design.

 An analogue of one of the two component parts (manned part) of the claimed aircraft structure is a design such as a landing glider towed by a towing aircraft.

 In 1936 - 37 years. in our country, the Ts-25 heavy landing assault glider and the Ts-25M landing monoplane designed by P. Tsybin were built with two 165 hp engines (Presented in Fig. P. 83 in the book by G.S. Vetrov "S.P. Korolev in Aviation." - M .: "Science", 1988).

 In 1942, the aircraft designer O.K. Antonov designed and built a CT gliderlet (Tank Wings) to transport a light tank. The glider IL-32, Yak-14, were also created (UDC 629.734 book of V. M. Zamyatin "Gliders and gliding". - M.: Mechanical Engineering, 1974, p. 22, Fig. 1.22; p. 219, Fig. 6 , 5; p. 221 - 222).

 During the Great Patriotic War, gliders were used for the needs of the army and partisans. Gliders were used in other countries.

 The main features of the glider were: high aerodynamic quality, low landing speed and limited wing load. These advantages are provided by the installation on the glider of a relatively low-power engine, which allows independent take-off of the machine without load. The loaded glider, after separation from the towing aircraft, can continue to fly on its own. Characteristic of the glider is the fact that this aircraft opens up broad prospects for its use in modern aviation technology, as well as for the development of gliding and training of flight personnel.

 Like an airplane, a glider has a fuselage combining the cockpit and the passenger (cargo) cabin, has a wing and tail unit with rudders, a power plant, landing gear and auxiliary equipment.

 The shortcomings of the glider were: the need for towing it to a given flight altitude by a towing aircraft and its low carrying capacity. Because of these shortcomings, glider planes were not widely used, and with the advent of heavy transport aircraft they lost their role.

 Closest to the claimed invention is the "Emergency rescue system of the aircraft" (US Patent N 4651952, MKI B 64 D 25/08; NKI CL 244-2) - prototype.

 The aircraft contains a fuselage with a cabin, a passenger cabin and a storage of compressed fluid. Wing consoles with control elements and a fuselage nacelle are attached to the fuselage. Under the wing are attached the main landing gear. The nose landing gear and engines are attached to the fuselage gondola.

 The fuselage nacelle is equipped with a lower cushion, which works in conjunction with the fuselage and gives the fuselage a streamlined shape during normal flight. In the fuselage nacelle there are several separate fuel tanks equipped with shut-off valves controlled from the cockpit. Between the bottom of the fuselage of the glider and the fuselage nacelle in the recess is placed an inflatable chamber. One of the engines has a device for pumping fluid from storage into the chamber.

 When fluid is injected into the chamber, the chamber acts as a means of separating the fuselage nacelle from the airframe.

 Between the bottom of the fuselage of the airframe and the fuselage nacelle there are couplings for attaching the fuselage nacelle to the airframe, as well as devices that connect and disconnect the main pipelines, and between the wing planes and nacelles there are pipelines through which fuel is supplied to the engines.

 There is an option to completely stop the supply of fuel to the engines. There is a fire system.

 In an emergency, the crew has the ability to separate (dump) the fuselage nacelle with engines and fuel tanks from the airframe using separation means to continue in emergency mode.

 In an autonomous (emergency) landing of the airframe, the wing main struts and the tail support available from the airframe are used. After landing, the tail of the glider fuselage and, accordingly, the rear door are closer to the ground than during normal landing, which simplifies the evacuation of passengers.

This emergency aircraft rescue system has a number of shortcomings that seem significant:
1. If in an emergency the fuselage nacelle (the base of the fuselage of the aircraft), together with the engines attached to it, is accidentally reset, then this glider becomes only a glider. But can a glider, without any engines at all, with a crew, a significant number of passengers or cargo make a safe emergency landing?
2. If the engines are stopped by shutting off the fuel lines, the transfer pumps will not work, as they are driven (as indicated in the description) by the engine (s) of the aircraft. Then the emergency will only get worse.

 3. The engine stops, the onset of unexpected silence, in addition, psychologically affects passengers.

 This invention proposes a two-module design of a self-rescuing "glider plane" as an emergency rescue system.

 The inventive aviation system is a structure that contains two main parts: 1 - the base of the fuselage - the lower longitudinal compartment of the fuselage, which houses all the equipment of the aircraft, which could pose any danger to passengers and crew, explosive and fire hazard equipment, main fuel tanks ; engine nacelles, landing gear (nose strut and fuselage with a wheeled cart) and the 2nd part are detached in case of an accident in the air, the upper part of the fuselage, which combines the crew cabin and the passenger compartment, which is a glider that contains a middle or upper wing with flaps and roll rudders and tail with rudders of height and direction. Two small engine nacelles are attached to the keel base, in which two auxiliary jet engines of the required power are placed, to ensure autonomous flight and for emergency landing of the glider in a convenient place on the ground.

 The glider in the nose of its fuselage has a two-wheeled nose landing gear, which is used (produced) only when the glider is autonomous landing, and its wing, common with the “airplane”, is equipped with the main landing gear.

 The glider is attached to the base of the fuselage using, for example, four beam holders (two front and two rear), the locks of which have a pyrotechnic drive or a double-acting drive - pyrotechnic and pneumatic (for increased reliability of separation of the glider from the base of the fuselage).

 Moreover, the beam holders and glider mount locks are installed on the power elements of the fuselage base structure, and the suspension yokes are an accessory of the glider. A glider has amphibious properties (in the event of an emergency landing on water), and it can also be given the properties of an ekranoplan.

 The wing of the glider plane near the center wing has an almost circular shape in plan that provides more stable flight, and at an extremely low altitude - the creation of a screen (air cushion). Such a wing, at a certain ground speed, creates significant lift, providing a safe descent and landing of a glider with crew and passengers.

 The claimed invention is aimed at solving a technical problem, which consists in creating a glider aircraft, the design of which is an emergency rescue system that provides the rescue of passengers (cargo) and crew in case of an airplane accident in the air or in case of failure of aircraft systems, on which flight safety depends, with the help of a glider, which is an aircraft that is detached from the base of the fuselage of the aircraft, and contains a comfortable crew cabin and a passenger compartment that meet modern m requirements upper- or sredneraspolozhennoe wing, tail, an auxiliary reactive propulsion system and the chassis, consisting of its own bow and the main wing struts, according to the claimed invention.

The solution to the technical problem is achieved:
1. The creation of a two-module aircraft structure consisting of two main parts (the base of the fuselage and the one mounted on it with beam holders and locks with a pyrotechnic glider drive).

 2. The creation of a glider with a comfortable cockpit and passenger compartment, made of fireproof and composite materials with buoyancy properties.

 3. Equipping a glider with its own two-wheeled nose (for reliability) rack-mountable chassis.

 4. The creation of reliable and easily detachable nodes for fixing the glider to the base of the fuselage and docking nodes of electric and pneumatic connectors.

 5. Equipping the glider with a brake parachute and gas jet brake engines to effectively reduce ground speed (if necessary), placed along the sides in the bow of the glider.

 6. Equipping the glider with the necessary life support systems, communications, alarms and towing devices (for towing both by land and by water).

 7. The separation of the glider from the base of the fuselage of the aircraft and piloting of the glider until the emergency landing at a selected or indicated terrestrial services area, or at an alternate aerodrome.

 Comparative analysis with the prototype shows that the claimed rescue system is a two-module unconventional aircraft design, has several advantages, is more reliable, safe for both passengers and crew.

 This emergency rescue system differs from the prototype both in principle and constructively. This aircraft rescue system provides for the use of modern means and technology at a modern level.

 A glider plane contains two modules: passenger module N 1 and fuselage - module N 2. Moreover, module N 1 is manned, and module N 2 is “resettable,” that is, destroyed in the event of an accident related to its equipment (main engines, fire or the destruction of the landing gear).

But there may be provided an embodiment of the fuselage module N 2 in the form of an autonomous aircraft equipped with a retractable folding wing, the main propulsion system, its own tail unit, the keel of which with the rudder is installed under the tail of the fuselage base and folds at an angle of 90 ^o C, and the chassis, which consists of a bow and two fuselage racks.

 With auxiliary engines running, a glider, in the event of an emergency landing on water, can sail on the water or taxi to the shore (wharf).

 Auxiliary engines, with their total thrust equal to the thrust of one main engine, can be used as a third engine in the event of failure of one of the main engines of a glider plane, as well as to provide accelerated take-off and, if necessary.

 Such an aviation system can be used not only in civil aviation, but also for the urgent delivery of necessary goods to disaster areas on the instructions of the Ministry of Emergencies or, for example, for the delivery of troops and other tasks.

 The proposed rescue system is presented in figures 1 to 3.

In FIG. 1 shows a General view of a glider plane (SP) (in normal flight), which contains:
1 - the base of the fuselage of the aircraft;
2 - glider uniting the cockpit, passenger compartment;
3 - wing of a glider plane;
4 - the left main engine of the aircraft;
5 - keel;
6 - left auxiliary engine (glider flight emergency landing engine);
7 - tail unit;
8 - container brake parachute;
9 - tail unit for an aircraft N 2 with a folding rudder (installed on the aircraft of option 2);
10 - floats (for landing a gliderlet on water), into the body of which the cantilever supporting struts of the aircraft landing gear are removed;
11 - retractable folding wing (installed on the aircraft of option 2);
12 - wing brake flaps;
13 - nozzle of a jet gas brake engine;
14 - alarm lights (lanterns);
15 - landing lights.

 Notes: The autopilot is located at the base of the fuselage (for the aircraft of option 2), and the control panel for the emergency rescue system is located in the cockpit.

 The on-board storage device - “BNI” (black box) and the on-board DC battery are installed on a glider.

 An additional fuel tank for auxiliary engines is located at the base and bottom of the keel.

In FIG. 2 shows the upper overlap of the base of the fuselage with beam holders and pyro locks of the glider to the base of the fuselage of the aircraft (in plan):
1 - the base of the fuselage;
16 - transverse beams of fastening block holders;
17 - beam mounts for fixing the glider to the base of the fuselage;
18 - pyrozamok beam holders;
19 - piston pushers pirozamok.

 The peculiarity of fastening the locks of beam holders is that they should be at equal distances from the center of gravity of the base of the fuselage and from each other in pairs, so that there is no skew during dumping.

 In FIG. 3 shows a glider plane with landing gear extended (front view).

 For landing, the aircraft uses: two-wheeled nose strut 20, two-, four-wheeled main fuselage strut (not shown in Fig.) And supporting landing gear 21 of the landing gear.

 For the autonomous landing of the gliderlet, the following are used: own nose rack 22 of the gliderlet with two smaller diameter wheels than the wheels of the nose rack of the base, and two main wing pillars of the 23 chassis (each rack has two wheels).

 Note. In aviation systems, duplication of critical systems is accepted.

 For greater reliability of the entire rescue system, it is proposed to use two-wheeled landing gear, as upon destruction of a single wheel of any rack, the aircraft may be thrown out of the runway or overturned.

 The emergency rescue system works as follows: the crew commander in an emergency in flight, having decided on an emergency landing, turns on auxiliary engines (glider engines), warning the crew about the need for an emergency landing, puts the main engines into idle or reverse mode and presses the " Airplane compartment "located on the control panel of the emergency rescue system in the cockpit (at the top of the dashboard).

 At the command “Airplane Department”, the pyro locks of the beam holders are triggered: the bearing levers of the locks are released, deployed on their axes and locked in the open position.

 At the moment of release of the yokes from the suspension arms in the locks of the beam holders, the glider yokes under the action of compressed (with the suspension) return springs are recessed into the nests of the bottom of the airframe housing "flush", in order to prevent them from catching on the parts of the lock and the beam holder when reset. The magnitude of the spring force is designed only to overcome the weight of the yoke and the friction force when moving along the guides of the socket.

 When the pyro locks 18 are activated, the pistons and pushers of the locks under the pressure of the gases push the glider 2 out of the seats and fixation units (front and rear stops) of the base of the fuselage 1. At the same time, the electrical and pneumatic connectors are disconnected, and the glider 2 is separated from the base of the fuselage 1. The base of the fuselage 1, under the influence of its weight, inertia and oncoming air flow, begins to fall to the ground in a parabola (the same way as when bombing). At the same time, the pilot operating the glider plane monitors the warning lights and, when the green panel lights up, the “compartment” increases the thrust of two auxiliary engines 6 to the maximum value, and also, increasing the angle of attack by elevators, retracts glider 2 with climb.

 When taking the helm on himself, the pilot presses the button (on the helm) to turn on two pyrodrive of the compartment (not shown in Fig.), Which serve to increase the reliability of the separation of the glider and are installed in the attachment points on the bottom of the tail of the glider, the jet stream of which repels the base of the fuselage 1 aircraft from glider 2, excluding collision with the tail of the base at the final moment of separation.

 Next, the crew commander, choosing a place on the ground for landing or acting on the instructions of the ground-based flight control services, in accordance with the situation on the ground and weather conditions, performs a landing approach using the aerobatic capabilities of the glider, performs a reduction for landing at the alternate aerodrome, agricultural airfield, the selected site (area), on a direct section of the road or on the water surface.

 At the same time, radio communication is made with ground-based flight control services, with local control duty services, and river and sea navigation services. The air defense duty services of the country (district) can inform the local authorities of the coordinates of the place of emergency landing of the glider. The DC generator and accumulator available on the gliderlet provide electrical circuits and consumers with electricity.

 The implementation of the inventive device complex of the aircraft emergency rescue system rescues the crew, passengers or cargo in case of an airplane accident in the air.

 The possibility of creating and using the emergency rescue system of the proposed design is confirmed by the existing and used analogues for transporting airborne assault and military equipment - the T-60 tank, existing and used known technical means, available power plants used in accordance with the claimed invention.

Claims (5)

 1. Aircraft emergency and rescue system, comprising a fuselage base with engine nacelles and a nose landing gear and mounted and secured to it by means of separation glider, under the wing of which the left and right main landing gear are respectively mounted, characterized in that the fuselage base is equipped with a fuselage strut the landing gear, and the glider wing consoles are equipped with fairings, used as floats, and two console supporting posts that can be retracted into them, while the separation means are made in the form etyreh beam holders with fastening locks having a pyrotechnic actuator or a double-acting (pyrotechnic and pneumatic), and planerlet limited against displacement in the longitudinal direction of the front and rear abutments beam holders.  2. The system according to claim 1, characterized in that the means of separation contain two pyroengine separation, installed in the mounting nodes of the bottom of the tail of the glider.  3. The system according to claim 1, characterized in that the auxiliary jet engines of the gliderlet are located in nacelles attached to the base of the keel.  4. The system according to claim 1, characterized in that the glider is equipped with a retractable bow two-wheeled landing gear.  5. The system according to claim 1, characterized in that the glider is equipped with jet brake engines located in the nose of the fuselage along the longitudinal axis passing through the center of mass of the glider body, providing braking of the glider during landing, as well as a brake parachute located in the rear compartment of the glider .

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