WO2015199567A1

WO2015199567A1 - Method and apparatus for deploying a parachute from falling helicopters, aircraft and land vehicles and for aerial braking

Info

Publication number: WO2015199567A1
Application number: PCT/RO2015/000015
Authority: WO
Inventors: Tiberiu Emil Ilie RÎNEA
Original assignee: Rînea Tiberiu Emil Ilie
Priority date: 2014-06-27
Filing date: 2015-06-15
Publication date: 2015-12-30
Also published as: RO129929A0

Abstract

Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking The invention comprises a group of principles and methods associated so that it forms a new, innovative principle, which, together bails, from falling caused by damage, helicopters, planes, objects, regardless of the external weather conditions. Uses a microcomputer (1) which actively drives the parachute deployment through logical and anticipatively commands, correlated with the status measurements from the damaged aircraft together with spatial measurements for the landing spot. The launching of the parachute is done ballisticaly with a mini-cannon (10) and then with a carrier rocket (12) for the synchronized passing between the helicopter rotor's blades. The launching is reversed, upwards, on a short half-circle route, arriving forcefully open besides the aircraft. Both planes and helicopters can be bailed. A simple non-destructive test stand can be built for invention homologation and unitary series production.

Description

METHOD AND APPARATUS FOR DEPLOYING A PARACHUTE FROM FALLING HELICOPTERS, AIRCRAFT AND LAND VEHICLES AND FOR AERIAL BRAKING

Bibliography

The documentation requested and obtained from OSIM Romania (Inventions and Trademarks State Office) and many other technical informations related to flight :

- Teoria SONICITATII [Sonicity Theory] - Gogu Constantinesc, Vol.1

- Stabilitatea structurilor aeronautice [The stability of aeronautical structures] - dr. ing. G. V., dr. ing.Vasiliev, V. Giurgiutiu - Editura TEHNICA Bucuresti 1990 ISBN 974-31-0126-5

- The study of movement in fluid - water, fluid close to the air, and from this my sporting results - Senior Champion of Romania, National Record man at breaststroke. But also diving, ice skating, amateur motorbike drifting,

- Twentyfive years of Imaginative Work Practice in Industrial Electromechanics Metallurgy design, controlling projects for technical assistance, on project yards, at openings and gathering feedback from the recipients using the equipment

- Practicing technical hobbies in two personal workshops, one at home.

- Air shows, crashes and aeronautical accidents covered in press.

- Detailed analysis of the studies of aircraft crashes on the Internet. Field of the Invention

The invention is referring to a METHOD AND APPARATUS for logical ballistic parachuting for short, special, complex falls in helicopters, aircraft and land vehicles, air braking, designed for:

Bails aircraft through soft landing, with minimal shock for helicopters, aircraft of any type and size, bails through aerial braking in impossible landings, on short landing strips, inadequate to the mass of the aircraft, on slippery landing strips, and bails forced landings outside landing strips.

Bails and protects multiple human and object protection for working personnel facing risk of fall from medium heights of approximately 45 m.

Bails vehicles and cars, racing vehicles, record breaking vehicles, through aerial, supplementary braking,

Brakes quickly the movement of objects through supplementary air braking.

Life safety for persons using these safety devices. Collective human life bailing and for means of transportation.

All these are done by the breakthrough of a ballistic parachute which can work anticipatively, can be independently launched at damage and even have logical, adapted, commands through measuring each situation, determining the moment and favorable place of landing or stopping, avoiding nearby objects and in the case of the delta plane-shaped parachute an intelligent upwards traction can be made for the falling aircraft, like a sky grabbing.

The breakthrough of the reverse quick and short launch of the parachute enables the ballistic parachute, always favorable and by itself and its components, especially for short falls of approximately 45 meters.

A new system is born, which extends several-fold qualities of the existing systems and equipments, in severe conditions, the extension is derived by simply asociating with the new method and apparatus. Safety is born in research with minimal risk, in dangerous zones.

A standard construction appears in a unitary series with different size, for all use cases of the Method and Apparatus in applying its purposes.

Bailing of great valubles, of several hundreds of thousands of dollars of each aircraft, the invention defined by the economic effects, besides the novelty. Without economic qualities the idea remains a simple discovery. Background of the invention

Currently in order to protect the humans and the damaged aircraft several different bailing devices are known such as ejection seats, parachutes, wing gliders, all of these for singular persons such as aerial assault or sportsmen, ejection capsules, having a parachute separated from the aircraft or suspended object, and the flying devices will be destroyed. Also there are known parachuting devices for special, heavy objects such as space ships and tanks.

Usually it's almost impossible to use an individual parachute even in a helicopter or other collective aircrafts while falling damaged or suspended installations or objects while damaged.

Known solutions have the disadvantage that currently there are a few special singular options such as ejection devices for special aircraft which do not apply for the general cases in the use cases or for the technical problem solved by the invention, and mostly there are no STANDARD, mainstream, many-sizes solution which would fulfill the claims in the bailing domain or the technical problems that this invention solves.

From the OSDvl documentation, containing dozens of existing patents, ranging from 1918 through the World Wars, 1954, up to 2013, 1 have analyzed idealistic patents, but all are proven to be unused, proved by the sad accidents on the landing strips and outside them which rarely leave any survivor which practically show viable bailing devices.

I consider that even though interesting ideals have been imagined, apparently impossible, they have never been realized, completed and corrected practically through successful tests.

I have met in the patent list some old, complicated patents of parachutes for helicopters, mounted on top of the main rotor or in other way. The solutions are obviously non-technical anti-aerodynamic and in reality there never where such parachutes that would have tried to bail a single aircraft.

Technical problems solved by the invention

METHOD AND APPARATUS for bailing with active, logic, ballistic parachute for special, short and complex falls in helicopters, aircraft and land vehicles and aerial braking:

Bails through soft landing with minimal shock, helicopters, aircraft of any kind and size, through ballistic method with launching or auto-launching reversed to the bailing direction, like a boomerang and the parachute reversed launch is quick and short, with or without the means of forced opening by pressured tubes mounted on the fabric of the parachute or blowing below the fabric, the short launch being favorable especially for short falls,

Logically guides the landing, counters the unfavorable evolutions using anticipative, logic command programs, correlated with exterior distance measurements, choosing the special method best for each real case, avoids the nearby objects, poles and aerial cables logically applying the specific delaying timings necessary for each special case and bailing place, can do an intelligent upwards traction with a wing-glider-like wing, like sky hook, with a curved, half-circle launching downwards besides the aircraft, similar to a boomerang, and by this the free-fall associated with a long manual command is eliminated,

An independent parachute apparatus appears as a feature of the aircraft, autonomous because once enabled by the pilot it will deploy by itself detecting the damage through unusual movements and accelerations, and mostly it guides itself for a convenient landing in a free zone or somehow better, having routine programming for different situations, but which chooses and applies, through local measurements a zone and situation-specific method.

Bails through aerial braking impossible landings on short landing strips, inadequate to the weight, on slippery landing strips, forced landings outside landing strips.

Bails through supplementary aerial braking through multiple fallen objects protection, fallen from small heights, vehicles and cars, in transit, in competitions, record-breaking, also fast braking of moving objects.

Does a collective life savings for humans in the transportation means.

The method and apparatus can save planes by reorienting them, through adjustments of the landing angle of approximately 3 degrees, through braking for acces on short landing strips or inadequate for the aircraft and even allows emergency landings outside of landing strips. And at any time or after reorienting the aircraft the parachute can be willfully be elliminated along with its anchor.

Extends manyfold the qualities of the aircraft or existing installation by simply equipping them with the new method and apparatus.

Bails great values, of several hundreds of thousands of dollars at each aircraft, different from saving some small valued objects.

A STANDARD construction parachute appears, in unit series of different size, standard series equipments can be homologated, in all use cases of the Method and Apparatus, which realizes the ends through composing equipments and summing up the qualities of all composing equipments. All can be tested completely on a TEST Stand and nondestructively improved before reall application for use.

In order to minimize the landing shock the method can be provided with a mini- capstan at the anchoring cable in aircrafts, and with a well-known retropropulsion equipment in some other aircrafts.

Knowing the shooting of the machine gun through the blades of the propeller of the plane, for certain it is possible to launch the parachutes bag along with the cable through the moving blades of the helicopter rotor, synchronized with the much slower rotation of approximately 172 rpm, of the rotor's blades, but it is also possible to launch the bag on the outside of the circle drawn by the blades and in this case, controlling the synchronization of the passing of the cable kept tight between the blades and the cable will unreel from the bag, controlling the precise slowing of the unreeling just enough to be tensioned tightly and above the moving blades.

The parachute, as in the invention, contains two parachute bags and each bag is mounted on a launch mini-cannon which is used for the fast and precise detachment off the aircraft, of the mass of the bag, synchronized with the movement of the blades, and each bag is equipped with a carrier rocket, with continuous trajectory correction.

The guided carrier rocket, controls its direction and the opening spot of the parachute, with a curved, half-circle route, besides the aircraft, similar to a boomerang.

Disclosure of the invention

Method and apparatus for parachuting, with active logic ballistic unit for short, complex and special falls of helicopters, aircraft and land vehicles,

an autonomous equipment which by microcomputer assisted commands through anticipatory command programs, logic and with the measurement of external distances, executes the launching avoiding nearby objects such as poles and aerial cables, and bails impossible landings, on short landing strips, inadequate to its weight, by swift landing with minimal shock, can also bail forced landings outside landing strips, bails and protects objects fallen from small heights, saves vehicles, cars and simply any moving object from impact by supplementary aerial braking,

or it is intended for quick and short opening of the parachute for low height falls, with forced opening. As in the invention, the parachute can be deployed or it can automatically deploy itself by a program, sensing the damage through accelerations and/or abnormal movements reducing the free fall associated with the manual command, to approximately 45 meters,

A special method fit for each situation will be chosen, with the landing guided through the moment favorable to the deployment, even in the damage crisis, including the short delays caused by the neighboring objects or position.

This way it controls the direction and the location of the opening of the parachute, through a curved, boomerang-like, launching, and in the case of a hang-glider wing parachute type, it can do an intelligent traction with upholding the falling aircraft, like a sky hook,

It is a ballistic parachute with programmed guiding and logically assisted on a half- circle route with reversed launching with respect to the bailing direction, apparently opened the other way around, and in the end vertically turned around by the traction of the falling object,

so the fully open parachute, loaded with air, comes back right beside the bailed aircraft, but the parachute can be launched in a classic manner waiting for the opening.

The route followed by the rocket (12) which stretches the anchoring cable (3) above the blades of the main rotor will have the radius constrained by the length of an anchoring cable (3), tightly stretched, and the length of the chord of the circle that closes the half-circle.

The equipment is comprised of parachute bags (2), mounted in stand-by on the aircraft, each with two force stage parachutes, first stage for braking and turning around and the second stage for main braking

and for launching the parachute bag (2) with passing over the rotor and reaching the most favorable spot, each bag (2) is mounted on a launching mini-cannon (10), adjustable to the situation, with executes the detaching from the aircraft and the quick and precise launch of the body of the bag, synchronized with the blades rotation,

each bag (2) is paired to a guided, carrier rocket (12), for transport, with ongoing trajectory correction and limited propulsion towards the end of the travel and commanded stop,

Knowing that firing a machine gun through the blades of a plane's propeller is possible, the synchronized launching of the bag through the moving rotor's blades is also possible

and during the launching moment the parachute will switch its anchor using its waiting ring from the cabin, pulling the ring below the rotor's blades,

the parachute cable unreeling from the bag, but it must be controlled with the precise slowing of the unreeling so it will be continuously stretched above the moving blades, but launching the bag through the exterior of the circle described by the rotor is also possible and then controlling the synchronization of the passing of the tightened cable through the moving blades or not,

and the unreeling done either from the bag, either from a reel placed on the aircraft having always the end of the cable anchored to the ring (7) which will rise below the rotor (8) and the end of the cable jumping from the end of the reel to the stand-by ring on the aircraft.

A quick turn-around can be done for planes using the standard method and apparatus, allowing to adjust the landing angle at around 3 degrees and brakes for normal access on short, slippery, inadequate landing strips and even allows landing outside landing strips,

And after turning the aircraft around, the parachute with its anchoring can be detached, willingly, at command, including the ring (7) under the rotor, and flight can be resumed.

The invention includes the Non-distructive Testing Stand for each part and gradually the whole method, with the homologation of the Standard Equipment in unitary series of sizes.

The equipment improves most of the features of existing aircrafts. Brief description of drawings

A few practical application examples of the invention related to Fig.l up to Fig.6 which represent :

Fig.l Bailing a Helicopter by launching the parachute between the blades and the new principle of computer assisted QUICK Reverse Launch.

Fig.2 Bailing a Helicopter by launching the parachute outside of the blades and the new principle of computer assisted QUICK Reverse Launch.

Fig.3 TEST Stand for simulating the method, apparatus and equipment homologation

Fig.4 Bailing a Plane - use cases for the method and apparatus.

Fig.5 Bailing a fall from a tower using the method and apparatus.

Fig.6 Overview of USES with small figures of all presented applications.

We will see an example of practical application of the invention, related to Figure 1 and 2, Figure 1 representing - Bailing a Helicopter by launching the parachute between the blades and the new principle of computer assisted QUICK Reverse Launch, and also related to Figure 2 which represents - Bailing a Helicopter by launching the parachute outside of the blades and the new principle of computer assisted QUICK Reverse Launch.

The functioning description is also related to the points a, b, c, d, e, f, g, h, i, j, k, 1 which are "Stage highlights of the route points" described by the bag and parachute, with the equipment of this invention.

Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking, characterized by forming an active, logic, unitary aggregate by assisted commands received from a fast complex and special command microcomputer (l)(Stage-a), which makes a ballistic, preferential parachuting with launching against the direction of the bailing and like a boomerang, which initially opens the parachute apparently against the direction of the bailing, but then, automatically corrects itself by turning around vertically by the natural traction of the falling object, and so the parachute arrives already open by the side of the aircraft or object to be saved, in a correct position and fully open and the reverse-launching system (20) of the parachute forces the opening even in the rapid air flow generated by its pulling with the carrier rocket, fast and short, limited by the anchoring cable (Figure Stage f-j), with a unitary, typical standard construction for all parachuting needs and accomplishes all its purposes by the synergy of all its constitutive equipment, which bails through short, fast aerial braking, through gentle landing with minimal shock for damaged aircraft and also helicopters but also any kind and size of aircraft, unit which bails through air braking impossible landings, on short runways, inadequate for weight or slippery, which can bail crash landings outside of runways, bails and protects fallen objects from small heights, bails from impact vehicles and auto vehicles or simply moving objects, through supplementary air braking, using parachutes with auxiliary devices and with associated objects as elements of this invention and this way succeeds in counteracting unfavorable evolutions, using pre-emptive and logic command programs, correlated with measurements of exterior distances, logically applying average and specific delay times and necessary to each special case and place of bailing, and realizes them if during the failure and during all the time all specified equipment used specific to the place and application are placed and in stand-by, with status signaling capable of functioning at microcomputer, being also under the control or command of the pilot of the aircraft.

And in the application example, method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking in accordance with claim 1, characterized by the fact that the parachute can deploy itself with a program, detecting the damage by accelerations and/or abnormal movements (and others) if the pilot willingly set the unit status from Stand-by to Auto or Deploy, and by this the free fall will be reduced at a minimum of approximatively 45 meters, the favorable moment will be chosen, even during the damage crisis, the landing is logically guided, can perform an intelligent traction with upper holding of the falling aircraft in case a hang- gliding-like parachute is being used, like hanging from the sky, the landing is logically guided, controls the direction and place of parachute deployment, with a curve, boomeranglike deployment trajectory, a logical, active deployment is made avoiding nearby objects (poles, aerial cables), a fast turn-around of planes can be made, using the method and standard equipments, being able to adjust the landing able by 3 degrees, brakes for access to short or slippery landing strips, inadequate for the aircraft or weight and/or allows landing outside of the arranged landing strips, and/or even after the aircraft turnaround an intended command can be issued to even detach the parachute and its anchor, and this way the aerial evolution before deployment can be resumed.

The method and apparatus provides two parachute Bags (2) installed in stand-by on the aircraft or object each with two parachutes with two deployment stages, first stage for braking and turning around, the second stage for supplementary braking in conjunction with the first one, and for deploying the parachute bag and passing by the rotor, and in the target spot chosen as most favorable, each bag is installed on a mini-canon (10) (Figure Stage-a) for deploying used for launching off the aircraft and for fast and precise launching of the bag synchronized with the rotation of the blades, the mini-cannon having a certain angle of orientation (11), (Figure Stage-a) adjustable for the needs of the current state, and each bag is also equipped with a guided carrier rocket (2), (Figure Stage-f), for transport, with moving correction of initial launching direction and with limited propulsion at the end of the intended trajectory and with commanded stopping, (Figure Stage-j), with programmed and logically assisted deployment on a prolonged half-circle route, if needed, route with radius limited by the momentary length of the anchor cable (3) strongly stretched and the route is generated by the rocket (12) which stretches the anchoring cable (3) above the blades of the main rotor, and guided and the force resulting from the centrifugal force of the rocket on the half-circle with the centripetal reaction force of the anchoring cable (3) stretched, and the parachuting method and apparatus provides that the parachute bag (2) contains usually the anchoring cable (3) too, folded or reeled for unreeling from the bag, but sometimes the cable can unfold from a reel mounted on the aircraft but with the end from the aircraft made as a springer in order to be anchored on the same radial-axial bearing, bearing that is prepared to lift and fasten under the rotor's blades at the moment of the cable's stretching, launched with the carrier rocket, and in any case the cable of each parachute is anchored to a axial-radial bearing (7) mounted on a main rotor's shaft (8) in helicopters, and only in tandem rotor helicopters working in opposite directions a crisis solution will be adapted, through anchoring the parachute cable from the side of the aircraft, as an intended measure in order to tilt the aircraft and protect the parachute cable from touching the cable (3) by the two rotors, and accepting to save the rolled-over aircraft somehow, but succeeding in saving the buckled persons and partially the aircraft, and with the special fire protection handled with the special evacuation measures of the saved personnel, and at tandem rotor helicopters, the parachuted fall to the ground and on an extremity of the aircraft with a roll-over or on the rotors, can save lives in a crisis situation as an effect of minimizing of the energy of the shock, specifically of the weight of the aircraft multiplied by the speed of the impact, by subtracting from the impulse the crunching of the rotor or any other compression, and the other protected objects, the bag (2) is anchored with two cables (3) balanced on the aircraft and the cable has enough length for the needed placement even with a short surplus and it has unreel control by light braking, just enough to keep it in a favorable position above the main rotor and not being clipped by the blades and therefore succeeding its launching, and the cable prolonging is only for positioning the open parachute, or not if the case, in an final, optimal position (Figure Stage-j), usually besides the saved object where it arrives in a fully open state and loaded with air, only if the launching, activation and command of each component is made in a logical way from the microcomputer 1 or from the pilot.

And the deployment of the bag is made specifically using a type and ballistic method with reversed launching, on a route like a whip in a half-circle, (Figure Stage e to j) route reversed in comparison to the bailing, and having the parachute open apparently against the bailing direction, but then automatically turns around vertically correctly using natural traction of the falling object and when the parachute arrives already open besides the aircraft or the saved object in a correct position and fully open, loaded with air and the reverse launching system (20) of the parachute, forces the opening even against the fast air flow generated by its fast, short and limited pulling with the carrier rocket, by that anchoring cable (Figure Stage f-j), and this solution is favored by delayed remote controlling of the parachute, relatively at the end of this half-circle route, in all cases the positioning of the parachute bag is logically chosen on the carrier rocket (12), either with the direction of the opening of the parachuted reversed to the direction of the carrier rocket, either the other way, but launching in the usual way of the evolution of a parachute is also possible if the height and time allows, by the microcomputer or the pilot, and if required by the environment conditions and forced opening of the parachute will be according to claim 5, so that the total length of the anchoring cable of the parachute of several parachute heights, and furthermore the total length of the anchoring cable of the damaged aircraft, considered from the saving command received from the microcomputer 1, up to the upholding of the damaged aircraft with both fully open parachutes and loaded with air, will probably be longer with the length of an open parachute, and if t³*⁴™ is not greatly exagerated, the damage fall is several tens of meters shorter,

[LENGTH OF FALL in meters] = [9.81 x (r³¹*™ + t^{reversed la}∞<=^h)2] / 2, finally this method is more favorable by placing the parachute in calmer air, without whirlwinds, besides the turbulanced air flow the rotor was pulling from when the aircraft was running, trying to achieve the positioning besides the optimal position by prolonging the rotor's axle to a zenith point, all these if the procedures of each installation component is made logically from the microcomputer (1) or the pilot.

And the reversed launching of the parachute can be augmented by the forced opening of the parachute (Figure Stage i or j), with a system of hardening tubes (2a) under pressure, tubes placed on several diameters of the parachute's circular fabric and on a radius towards the anchoring point to the cable (3), and, if appropriate, also with a blowing equipment (2b) under the fabric of the parachute, and simultaneously with the deployment of the parachute, the microcomputer (1) logically commands also some maneuvers of the aircraft, preventing the parachutes from being drawn to the rotor, in the blades or in the engine, using a blade timing tuning command system (14) and, if appropriate, by slowing down the rotor or stopping the power delivered to it, or in aircraft reversing the engines.

For helicopters the method and apparatus provides the deployment of the parachute bag (2) installed in stand-by on the helicopter, to be made in two ways, -deployment through the blades of the main rotor while spinning, and then the bag must be placed besides or above the cabin, with the route upwards above the rotor (Figure Stage-a), and aside of the rotor's axis and the deployment is synchronized with the blades rotation, -and the second way, the deployment is made through the side and on the outside of the circle drawn by the blades, but with the route still upwards of the aircraft but on a detour route, following the passing of the cable synchronized between the blades and then the bag must be placed besides or below the aircraft, and in any way the procedures described in claims 2, 3, 4, and if appropriate, 5, using the launching mini cannon (5), adjustable with an variable angle (6), variable after the synchronization requirements, but also after the needs of the real life close objects, such as power lines, and using for each bag (2) the equipment of a small guided carrier rocket (12) for the route to the target, curved route, as in earlier claims, in any way taking special care that the anchoring cable (3) is braked in its unreeling just enough to be tensioned tightly and sustained above the blades, by the continuous traction of the guided mini carrier rocket (12), considering that the blades can still be rotating, and also considering that in any way the rocket should have, in general, limited propulsion for the optimal parachute opening point and have its stopping command there.

And it is provided that the synchronization of passing through the rotor's blades of the parachute bag (2) or only of the cable (3) at the deployment besides the blades, is done by the triggering of the deployment by a cam (9) real or virtual, magnetic or inductive, placed on an axle (8) at the main rotor (Figure Stage-c), with a timing angle and the passing-by is helped also by the angle (11) between the launching cannon (10), with a tilt from the normal to the rotation plane of the blades, (Figure Stage-a), and in the direction of the tangent to the passing point in the plane, tilt that will alleviate an unwanted shock blade-bag or blade-cable in the case of de-synchronization caused by aggressive external factors and for this in case of simultaneous damage with great chaotic influences, the passing through the blades will be solved also through adaptation and change of the initial angle of the launching mini-cannon (10).

The method and apparatus uses equipment auxiliary to the anchoring cable, (Figure Stage-c, j) of the parachute, the auxiliary equipment which is novelty, but especially as a group, but which allows the success of installing and bailing by themselves, such as : an equipment (4) (Figure Stage-c), which prevents the twisting of the anchoring cable (3) by radial slip, an equipment (5) for detaching the parachute, of rotary lock type, lock with slip flap or another kind, for detachment of the anchoring cable (3) and decoupling and removal of the parachute that did not perform well and, if appropriate, the removal of the axial-radial bearing (7) that anchors the cable (3) on the main rotor's axle (8) at helicopters, the decoupling being made motivated by the pilot for launching more timely of the backup parachute, an equipment (6) for an elastic extension of the cable (3) and reducing the shock of parachuting, elasticity obtained somehow and even by the simple reeling, weaving, of the rope's strands, preferably made of carbon fiber or some other way.

And the method and apparatus provides that the reverse parachute launch system (20) can be applied in all cases, regardless of the conditions of the damage of the aircraft or the rolled over position or external reactions, such as strong wind, or if requested quickly after clarification time for the pilot after successive hits such as lightning strike, hits from an enemy cannon or missiles and the parachute stages are logically used, the initial one for turning around vertically and braking, followed by the force stage for a maximum time till the touch down, or if appropriate both stages quickly, and for persons or fallen objects from a high platform a simpler equipment is used as in claim number 3.

And the method and apparatus can be provided that the parachute reverse launching system (20) for falling, damaged aircraft with combined movement and other parasite movements, with tail spin or chaotic deviation, to request that the microcomputer (1) should delay the launching of the parachute, waiting for the favorable position in which the launching can be made upwards or sideways, or any other direction, appropriately chosen by the microcomputer (1), similar to the claims above, with the auxiliary rocket (12) with curved route, then downwards and finally, with the parachute fully open and besides the damaged objects, and so to have the falling traction of the damaged object to make the quick rolling of the parachute in a normal vertical position, but we show that the parachute can be launched from the beginning and normally, with its opening direction downwards, if it is appropriate so, considering at a moment that the time and space is sufficient for such a strategy, consideration being made either automatically from the microcomputer (1) which analyses all possible strategies, corroborated with all condition factors, either from the pilot that commands the aircraft, and who owns the authorization decision of the automatic command or manual command, and also to appreciate if the launched parachute failed and its evolution failed and then, if necessary, to release this and launch a backup parachute.

Through the method and apparatus the qualities of the existing systems are extended, of the aircraft and existing vehicles, for more severe conditions of use than those that were designed for (such as landing on short strips), and the extension being done by simply equipping it with a method and apparatus of ballistic parachute for securing, which besides offering peace of mind, really allows the use of existing aircraft in more severe conditions than those that the aircraft was designed for which allows for more courage and better chances for flying in remote, dry areas.

Always all comprising elements of the method and apparatus are similar to all cases and sometimes identical, forming a standard equipment (14), a serial number, between them being just physical size differences specific to the application, such as at the parachute bag, the launching cannon and the carrier rocket, and the rest of the components being almost identical and, at some of the applications, even existing, if appropriate, simplifications through removal of some elements.

Always the method and apparatus can be equipped, if appropriate to the size and weight of the bailed object and judging the possible anchoring points, with a well known for retro-propulsion for a short duration and a force corresponding to the bailed weight (16), at the imminent time of touch down, time detected with a proximity radar, but also with a contact weight or in another way, at some objects or equipment protected as shown above, and can be equipped with a mini-capstan (17) at the anchoring cable, mechanical capstan or a tube with pyrotechnical counter-piston or another kind, for brief pulling from the parachute right before touchdown and mitigates the shock of the fall and the touchdown shock, similar to the technique used by professional skydivers, proximity detected with a radar, but also with a soil-contact weight or another way.

The method and apparatus can be tested and improved on the Test STAND (figure 3) which is the certainty of success and safe functioning. The similarity is a technique of reproducing proportional and step-by-step the examples of use of the invention in figure 1 and 2, specifically, the bailing of a helicopter by deploying the parachute between the blades of the main rotor while it is rotating or the deployment outside of the circle described by the blades of the main rotor while rotating and so for all of the five examples of use of the invention. In the end, the tests are complete in order to reach the ideal bailing method.

It is desired a standard equipment as a unitary solution 14 but in a number of different dimensions, applying the principle 20 of reverse parachute launch, assisted by the

microcomputer 1, for bailing of a helicopter through reverse launch of the parachute through the blades or through the exterior of the circle of the main rotor's blades, in order to bail an aircraft or bail from the fall of an object off a tower.

The stand allows photographing and normal or slow-motion playback for critical observations and status measurements and then new theories complementary to each experiment and thus improvements. And then the observations and innovations can be repeated.

Obtaining a good, safe and repeatable working operation requires an adequate concept and design, with practical experiments in all working conditions and in all possible situations. This begins with each technical and physical component and then with the ensemble of the method and apparatus. In this area of the technique of flight, we must re-iterate a well-known warning: a badly executed or incomplete experiment can reject a concept no matter how correct it may be.

The following example, of practical application of the invention, related to Figure 3, represents a TEST Stand for simulating the method, apparatus and equipment homologation

The functioning description is also related to the points a, b, c, d, e, f, g, h, i, j, k, 1 which are "Stage highlights of the route points" described by the bag and parachute, with the equipment of this invention. The following example, of practical application of the invention, related to Figure 4, represents Bailing a Plane - use cases of the method and apparatus.

The functioning description is also related to the points a, b, c, d, e, f, g, h, i, j, k, 1 which are "Stage highlights of the route points" described by the bag and parachute, with the equipment of this invention. Damaged airplanes can be recovered and bailed by combined and consecutive braking, which should allow the landing on a short and inadequate landing strip by reorienting the landing angle at about 3 degrees but also air braking and also safe landing outside a landing strip on arid soil such as forest or hill side by always equipping with parachutes as in the invention having sufficient size for the weight of the aircraft and with new pilot maneuvering techniques, that is, deployments of parachute units at the desired spot and intentional disconnection of them and disposing of the first parachutes, and then a new air brake and so a new support On air' appears in place of the wings and a hanging up is realized,

The recovery of the landing angle can be done with two parachute deployed slightly delayed one from the other, one for lifting the nose through a reverse launch and upwards, anchored to the front part of the chassis, and quickly another parachute used for air braking.

A sledge can be used for the rear of the aircraft, at beckie, and land in two stages, on the beckie and then on the landing gear.

Landing in stages, first on the beckie and then, with a roll, towards horizontal, will soften the shock of the fall.

The following example, of practical application of the invention, related to Figure 5, represents Bailing Tower fall using the method and apparatus.

Next, an example of high fall of a tower follows, related to Figure 5. In the case of working on tall constructions, such as marine oil platform or similar, working on assembly or repair, there is a natural danger of falling for valuable installations. The danger exists for both falling objects and for the existing objects at the base.

People working on these are also endangered and usually are tied with ropes.

Concluding, when working at tall construction sites where there is the natural danger of falling for people, equipment but also the danger of destruction of the ones down at the base and when those in danger cannot be secured with ropes or cannot be manipulated conveniently while tied to the tower, an extreme solution is securing with a parachuting equipment as in the invention

The object or person is anchored to a standard parachuting equipment and if the microcomputer detects the damage through movements that are too fast or abnormal accelerations will sound the alarm and in case the alarm is not canceled by the worker or external special observer, the parachute will be deployed. The parachute bag will be launched with its accessories, using a mini-cannon for detaching off the support and the bag is launched ahead with a carrier rocket towards a direction that the microcomputer detects as object-free, free for landing without disturbing others and convenient for the landing.

The bag will follow a half-circle route, first upwards and then descending to a target point chosen in a free area and the anchoring cable unreels from the bag, from an object or person, and the required length is short, really the cord that closes the half-circle arch of the route. The opening of the parachute is done in the forced advancing in the descend on the half-circle and the parachute will arrive relatively besides the falling object and during its forced pulling by the fall of the object it will quickly roll in vertical bailing position and already open.

The reverse launching method has the advantage that by proximity sensor and the chosen anticipatory strategy, the microcomputer (1), decides the target point favorable for the situation and the half-circle route, so the fallen object will be placed right beside the tower from which it slipped off so in the fall it will not hit the tower wall.

Highlights of the advantages obtained from applying the invention

By applying the Method and Apparatus the following problems are being solved, always simpler, and therefore safer and cheaper than other solutions, and only where these truly exist.

Fast and short parachute opening system through reverse deployment, favorable for medium falls or anywhere.

Bailing through gentle landing with minimal shock in helicopters, aircraft of any type and size, bailing through aerial braking at impossible landings on short landing strips, inadequate for the weight, on slippery landing strips, bailing for forced landings outside landing strips designed for wheel-based landing gear.

Bailing forced landings outside fields designed for landings.

Bailing and multiple protection for objects fallen from low heights.

Bailing vehicles and autovehicles, in tranzit, in competition, record breaking, through suplementary aerial breaking.

Life safety for those working with or using these devices or installations, bailing themselves.

Collective life saving, of those in the means of transportation.

Safety in research and minimal risk, boldness, in dangerous or unsafe zones, with risk of fall or where transportation with land vehicles or aircraft is unsafe.

Unitary series of Standard Construction, in all use cases of the Method and Apparatus for active, logic, ballistic parachute of fast, complex command, and similar equipment which achieve the proposed purposes merging the qualities of the constitutive equipment.

Multiple extension of the nominal qualities, of existing devices and equipment, for much harsher environments, by simply equipping with the new invention.

Claims

1. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking, characterized by forming an active, logic, unitary aggregate by assisted commands received from a fast complex and special command microcomputer (l)(Stage-a), which makes a ballistic, preferential parachuting with launching against the direction of the bailing and like a boomerang, which initially opens the parachute apparently against the direction of the bailing, but then, automatically corrects itself by turning around vertically by the natural traction of the falling object, and so the parachute arrives already open by the side of the aircraft or object to be saved, in a correct position and fully open and the reverse-launching system (20) of the parachute forces the opening even in the rapid air flow generated by its pulling with the carrier rocket, fast and short, limited by the anchoring cable (Figure Stage f-j), with a unitary, typical standard construction for all parachuting needs and accomplishes all its purposes by the synergy of all its constitutive equipment, which bails through short, fast aerial braking, through gentle landing with minimal shock for damaged aircraft and also helicopters but also any kind and size of aircraft, unit which bails through air braking impossible landings, on short runways, inadequate for weight or slippery, which can bail crash landings outside of runways, bails and protects fallen objects from small heights, bails from impact vehicles and auto vehicles or simply moving objects, through supplementary air braking, using parachutes with auxiliary devices and with associated objects as elements of this invention and this way succeeds in counteracting unfavorable evolutions, using pre-emptive and logic command programs, correlated with measurements of exterior distances, logically applying average and specific delay times and necessary to each special case and place of bailing, and realizes them if during the failure and during all the time all specified equipment used specific to the place and application are placed and in stand-by, with status signaling capable of functioning at microcomputer, being also under the control or command of the pilot of the aircraft.

2. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking in accordance with claim 1, characterized by the fact that

the parachute can deploy itself with a program, detecting the damage by accelerations and/or abnormal movements (and others) if the pilot willingly set the unit status from Standby to Auto or Deploy, and by this the free fall will be reduced at a minimum of

approximatively 45 meters, the favorable moment will be chosen, even during the damage crisis, the landing is logically guided, can perform ah intelligent traction with upper holding of the falling aircraft in case a hang-gliding-like parachute is being used, like hanging from the sky, the landing is logically guided, controls the direction and place of parachute deployment, with a curve, boomerang-like deployment trajectory, a logical, active deployment is made avoiding nearby objects (poles, aerial cables), a fast turn-around of planes can be made, using the method and standard equipments, being able to adjust the landing able by 3 degrees, brakes for access to short or slippery landing strips, inadequate for the aircraft or weight and/or allows landing outside of the arranged landing strips, and/or even after the aircraft turnaround an intended command can be issued to even detach the parachute and its anchor, and this way the aerial evolution before deployment can be resumed.

3. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1 and 2, characterized by the fact that provides two parachute Bags (2) installed in stand-by on the aircraft or object each with two parachutes with two deployment stages, first stage for braking and turning around, the second stage for supplementary braking in conjunction with the first one, and for deploying the parachute bag and passing by the rotor, and in the target spot chosen as most favorable, each bag is installed on a mini-canon (10) (Figure Stage-a) for deploying used for launching off the aircraft and for fast and precise launching of the bag synchronized with the rotation of the blades, the mini-cannon having a certain angle of orientation (11), (Figure Stage-a) adjustable for the needs of the current state, and each bag is also equipped with a guided carrier rocket (2), (Figure Stage-f), for transport, with moving correction of initial launching direction and with limited propulsion at the end of the intended trajectory and with commanded stopping, (Figure Stage-j), with programmed and logically assisted deployment on a prolonged half-circle route, if needed, route with radius limited by the momentary length of the anchor cable (3) strongly stretched and the route is generated by the rocket (12) which stretches the anchoring cable (3) above the blades of the main rotor, and guided and the force resulting from the centrifugal force of the rocket on the half-circle with the centripetal reaction force of the anchoring cable (3) stretched, and the parachuting method and apparatus provides that the parachute bag (2) contains usually the anchoring cable (3) too, folded or reeled for unreeling from the bag, but sometimes the cable can unfold from a reel mounted on the aircraft but with the end from the aircraft made as a springer in order to be anchored on the same radial-axial bearing, bearing that is prepared to lift and fasten under the rotor's blades at the moment of the cable's stretching, launched with the carrier rocket, and in any case the cable of each parachute is anchored to a axial-radial bearing (7) mounted on a main rotor's shaft (8) in helicopters, and only in tandem rotor helicopters working in opposite directions a crisis solution will be adapted, through anchoring the parachute cable from the side of the aircraft, as an intended measure in order to tilt the aircraft and protect the parachute cable from touching the cable (3) by the two rotors, and accepting to save the rolled-over aircraft somehow, but succeeding in saving the buckled persons and partially the aircraft, and with the special fire protection handled with the special evacuation measures of the saved personnel, and at tandem rotor helicopters, the parachuted fall to the ground and on an extremity of the aircraft with a roll-over or on the rotors, can save lives in a crisis situation as an effect of minimizing of the energy of the shock, specifically of the weight of the aircraft multiplied by the speed of the impact, by subtracting from the impulse the crunching of the rotor or any other compression, and the other protected objects, the bag (2) is anchored with two cables (3) balanced on the aircraft and the cable has enough length for the needed placement even with a short surplus and it has unreel control by light braking, just enough to keep it in a favorable position above the main rotor and not being clipped by the blades and therefore succeeding its launching, and the cable prolonging is only for positioning the open parachute, or not if the case, in an final, optimal position (Figure Stage-j), usually besides the saved object where it arrives in a fully open state and loaded with air, only if the launching, activation and command of each component is made in a logical way from the microcomputer 1 or from the pilot,

4. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2 and 3, characterized by the fact that the deployment of the bag is made specifically using a type and ballistic method with reversed launching, on a route like a whip in a half-circle, (Figure Stage e to j) route reversed in comparison to the bailing, and having the parachute open apparently against the bailing direction, but then automatically turns around vertically correctly using natural traction of the falling object and when the parachute arrives already open besides the aircraft or the saved object in a correct position and fully open, loaded with air and the reverse launching system (20) of the parachute, forces the opening even against the fast air flow generated by its fast, short and limited pulling with the carrier rocket, by that anchoring cable (Figure Stage f-j), and this solution is favored by delayed remote controlling of the parachute, relatively at the end of this half-circle route, in all cases the positioning of the parachute bag is logically chosen on the carrier rocket (12), either with the direction of the opening of the parachuted reversed to the direction of the carrier rocket, either the other way, but launching in the usual way of the evolution of a parachute is also possible if the height and time allows, by the microcomputer or the pilot, and if required by the environment conditions and forced opening of the parachute will be according to claim 5, so that the total length of the anchoring cable of the parachute of several parachute heights, and furthermore the total length of the anchoring cable of the damaged aircraft, considered from the saving command received from the microcomputer 1, up to the upholding of the damaged aircraft with both fully open parachutes and loaded with air, will probably be longer with the length of an open parachute, and if r³*⁸"" is not greatly exagerated, the damage fall is several tens of meters shorter, [LENGTH OF FALL in meters] = [9.81 x (t^alann + t^reVCTSed ««™*)2] / 2, finally this method is more favorable by placing the parachute in calmer air, without whirlwinds, besides the turbulanced air flow the rotor was pulling from when the aircraft was running, trying to achieve the positioning besides the optimal position by prolonging the rotor's axle to a zenith point, all these if the procedures of each installation component is made logically from the microcomputer (1) or the pilot.

5. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3 and 4, characterized by the fact that the reversed launching of the parachute can be augmented by the forced opening of the parachute (Figure Stage i or j), with a system of hardening tubes (2a) under pressure, tubes placed on several diameters of the parachute's circular fabric and on a radius towards the anchoring point to the cable (3), and, if appropriate, also with a blowing equipment (2b) under the fabric of the parachute, and simultaneously with the deployment of the parachute, the microcomputer (1) logically commands also some maneuvers of the aircraft, preventing the parachutes from being drawn to the rotor, in the blades or in the engine, using a blade timing tuning command system (14) and, if appropriate, by slowing down the rotor or stopping the power delivered to it, or in aircraft reversing the engines.

6. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4 and 5, characterized by the fact that provides the deployment of the parachute bag (2) installed in stand-by on the helicopter, to be made in two ways, -deployment through the blades of the main rotor while spinning, and then the bag must be placed besides or above the cabin, with the route upwards above the rotor (Figure Stage-a), and aside of the rotor's axis and the deployment is synchronized with the blades rotation, -and the second way, the deployment is made through the side and on the outside of the circle drawn by the blades, but with the route still upwards of the aircraft but on a detour route, following the passing of the cable synchronized between the blades and then the bag must be placed besides or below the aircraft, and in any way the procedures described in claims 2, 3, 4, and if appropriate, 5, using the launching mini cannon (5), adjustable with an variable angle (6), variable after the synchronization requirements, but also after the needs of the real life close objects, such as power lines, and using for each bag (2) the equipment of a small guided carrier rocket (12) for the route to the target, curved route, as in earlier claims, in any way taking special care that the anchoring cable (3) is slowed in its unreeling just enough to be tensioned tightly and sustained above the blades, by the continuous traction of the guided mini carrier rocket (12), considering that the blades can still be rotating, and also considering mat in any way the rocket should have, in general, limited propulsion for the optimal parachute opening point and have its stopping command there.

7. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5 and 6, characterized by the fact that it provides that the synchronization of passing through the rotor's blades of the parachute bag (2) or only of the cable (3) at the deployment besides the blades, is done by the triggering of the deployment by a cam (9) real or virtual, magnetic or inductive, placed on an axle (8) at the main rotor (Figure Stage-c), with a timing angle and the passing-by is helped also by the angle (11) between the launching cannon (10), with a tilt from the normal to the rotation plane of the blades, (Figure Stage-a), and in the direction of the tangent to the passing point in the plane, tilt that will alleviate an unwanted shock blade-bag or blade-cable in the case of de-synchronization caused by aggressive external factors and for this in case of simultaneous damage with great chaotic influences, the passing through the blades will be solved also through adaptation and change of the initial angle of the launching mini-cannon (10).

8. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6 and 7, characterized by the fact that uses equipment auxiliary to the anchoring cable, (Figure Stage-c, j) of the parachute, the auxiliary equipment which is novelty, but especially as a group, but which allows the success of installing and bailing by themselves, such as : an equipment (4) (Figure Stage-c), which prevents the twisting of the anchoring cable (3) by radial slip, an equipment (5) for detaching the parachute, of rotary lock type, lock with slip flap or another kind, for detachment of the anchoring cable (3) and decoupling and removal of the parachute that did not perform well and, if appropriate, the removal of the axial-radial bearing (7) that anchors the cable (3) on the main rotor's axle (8) at helicopters, the decoupling being made motivated by the pilot for launching more timely of the backup parachute, an equipment (6) for an elastic extension of the cable (3) and reducing the shock of parachuting, elasticity obtained somehow and even by the simple reeling, weaving, of the rope's strands, preferably made of carbon fiber or some other way.

9. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7 and 8, characterized by the fact that it provides that the reverse parachute launch system (20) can be applied in all cases, regardless of the conditions of the damage of the aircraft or the rolled over position or external reactions, such as strong wind, or if requested quickly after clarification time for the pilot after successive hits such as lightning strike, hits from an enemy cannon or missiles and the parachute stages are logically used, the initial one for turning around vertically and braking, followed by the force stage for a maximum time till the touch down, or if appropriate both stages quickly, and for persons or fallen objects from a high platform a simpler equipment is used as in claim number 3.

10. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7, 8 and 9, characterized by the fact that it can be provided that the parachute reverse launching system (20) for falling, damaged aircraft with combined movement and other parasite movements, with tail spin or chaotic deviation, to request that the microcomputer (1) should delay the launching of the parachute, waiting for the favorable position in which the launching can be made upwards or sideways, or any other direction, appropriately chosen by the microcomputer (1), similar to the claims above, with the auxiliary rocket (12) with curved route, then downwards and finally, with the parachute fully open and besides the damaged objects, and so to have the falling traction of the damaged object to make the quick rolling of the parachute in a normal vertical position, but we show that the parachute can be launched from the beginning and normally, with its opening direction downwards, if it is appropriate so, considering at a moment that the time and space is sufficient for such a strategy, consideration being made either automatically from the microcomputer (1) which analyses all possible strategies, corroborated with all condition factors, either from the pilot that commands the aircraft, and who owns the authorization decision of the automatic command or manual command, and also to appreciate if the launched parachute failed and its evolution failed and then, if necessary, to release this and launch a backup parachute.

11. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7, 8, 9 and 10, characterized by the fact that the qualities of the existing systems are extended, of the aircraft and existing vehicles, for more severe conditions of use than those that were designed for (such as landing on short strips), and the extension being done by simply equipping it with a method and apparatus of ballistic parachute for securing, which besides offering peace of mind, really allows the use of existing aircraft in more severe conditions than those that the aircraft was designed for which allows for more courage and better chances for flying in remote, dry areas.

12. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7, 8, 9,10 and 11, characterized by the fact that all comprising elements of the system are similar to all cases and sometimes identical, forming a standard equipment (14), a serial number, between them being just physical size differences specific to the application, such as at the parachute bag, the launching cannon and the carrier rocket, and the rest of the components being almost identical and, at some of the applications, even existing, if appropriate, simplifications through removal of some elements.

13. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12 and 13, characterized by the fact that it can be equipped, if appropriate to the size and weight of the bailed object and judging the possible anchoring points, with a well known equipment for retro propulsion for a short duration and a force corresponding to the bailed weight (16), at the imminent time of touch down, time detected with a proximity radar, but also with a contact weight or in another way, at some objects or equipment protected as shown above, and can be equipped with a mini-capstan (17) at the anchoring cable, mechanical capstan or a tube with pyrotechnical counter-piston or another kind, for brief pulling from the parachute right before touchdown and mitigates the shock of the fall and the touchdown shock, similar to the technique used by professional skydivers, proximity detected with a radar, but also with a soil-contact weight or another way.

14. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claims 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12 and 13 characterized by the fact that falls from a tower or from tall construction sites where there is the natural danger of falling for people, equipment but also the danger of destruction of the ones down at the base and when those in danger cannot be secured with ropes or cannot be manipulated conveniently while tied to the tower, an extreme solution is securing with a parachuting equipment as in the invention. The object or person is anchored to a standard parachuting equipment and if the microcomputer detects the damage through movements that are too fast or abnormal accelerations will sound the alarm and in case the alarm is not canceled by the worker or external special observer, the parachute will be deployed. The parachute bag will be launched with its accessories, using a mini-cannon for detaching off the support and the bag is launched ahead with a carrier rocket towards a direction that the microcomputer detects as object-free, free for landing without disturbing others and convenient for the landing.

The bag will follow a half-circle route, first upwards and then descending to a target point chosen in a free area and the anchoring cable unreels from the bag, from an object or person, and the required length is short, really the cord that closes the half-circle arch of the route. The opening of the parachute is done in the forced advancing in the descend on the half-circle and the parachute will arrive relatively besides the falling object and during its forced pulling by the fall of the object it will quickly roll in vertical bailing position and already open. The reverse launching method has the advantage that by proximity sensor and the chosen anticipatory strategy, the microcomputer (1), decides the target point favorable for the situation and the half-circle route, so the fallen object will be placed right beside the tower from which it slipped off so in the fall it will not hit the tower wall.

15. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claims 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13 and 14 characterized by the fact that damaged airplanes can be recovered and bailed by combined and consecutive braking, which should allow the landing on a short and inadequate landing strip by reorienting the landing angle at about 3 degrees but also air braking and also safe landing outside a landing strip on arid soil such as forest or hill side by always equipping with parachutes as in the invention having sufficient size for the weight of the aircraft and with new pilot maneuvering techniques, that is, deployments of parachute units at the desired spot and intentional disconnection of them and disposing of the first parachutes, and then a new air brake and so a new support On air' appears in place of the wings and a hanging up is realized, from the sky.

A sledge can be used for the rear of the aircraft, at beckie, and land in two stages, on the beckie and then on the landing gear. Landing in stages, first on the beckie and then, with a roll, towards horizontal, will soften the shock of the fall

16. Method and apparatus for bailing with logic ballistic parachute for special, short, complex falls in helicopters, aircrafts and land vehicles and aerial braking as in claim 1, 2, 3, 4, 5, 6, 7, 8, 9,10, 11, 12, 13, 14 and 15, characterized by the fact that the Test STAND (figure 3) is the certainty of success and safe functioning. The similarity is a technique of reproducing proportional and step-by-step the examples of use of the invention in figure 1 and 2, specifically, the bailing of a helicopter by deploying the parachute between the blades of the main rotor while it is rotating or the deployment outside of the circle described by the blades of the main rotor while rotating and so for all of the five examples of use of the invention. In the end, the tests are complete in order to reach the ideal bailing method.

Knowing a World War I invention of the Romanian inventor Gogu Constantinescu who achieved machine gun shooting through the blades of the propeller while rotating at 6000 rpm, the propeller having 3 or 4 blades, I am sure that it is possible to launch a bulky bag through the narrow blades of the main rotor of a helicopter, blades that rotate much slower and constant at approximately 172 rpm.

The invention of Gogu Constantinescu was so simple that even the enemies of England couldn't replicate it from the captured airplanes, not being sure that a cam placed on the axle of the propeller of the plane can send a sure pulse to the trigger of the machine gun by sending the pulse through a water pipe having push pistons at each end. The Sonicity Theory was not known at the time.

Here are the stages for creating and testing of all 20 components of the method and apparatus as in the invention :

Stage a) A test stand (5) will be built as in figure (3), a platform that can rock up and down with a mechanical spring, on which a tall rotor axle (8) will be installed, equipped with blades similar to those of a helicopter, which rotates with a typical speed attained in helicopters.

In order to simulate the reverse launching of the parachute on a half-circle route, boomerang-like, having the parachute arrived beside the damaged aircraft and there, by gravitational falling, to pull and roll in normal, vertical bailing position, at the top part of the axle (XX) a reeling roll (19) is mounted on which the cable (3) is pulled with a capstan (XX)

Stage b) Devising a profile for the parachute bag (2) with volume and weight identical to the one projected in the invention.

A fake bag is used at first for economical reasons.

The bag, in the end, will have two targets : weight and volume, and aerodynamic profile, so that the volume is large enough for two parachutes, a carrier rocket (12) with automatic guidance, a light, carbon fibre cable, as long as 4 heights of the parachute and a small cable for elastic prolonging, for a perfectly constant braking and reduced friction in cable unreeling, and for the opening and forced inflating of the parachute equipment, either through tubes that harden under pressure, either through forced opening by blowing under the parachute fabric.

Stage c) Launching of the bag (2) from the oscillating platform (15) which would simulate a damaged helicopter, will be done with the mini-cannon (10) in order to detach quickly the mechanical mass of the bag from the damaged aircraft, with the adjustable direction angle (11) and then will continue with the guided directioning rocket (12) or with a tail rocket for half-circle route.

In order to simulate the bailing of a helicopter it is favorable to launch the bag, not through the rotor's blades, but through a plane rotating board with a small hole that should allow the bag to pass through, on which the launching imprecision errors will be marked.

Stage d) In order to test the launching of the bag (2) by simulating the launching off a helicoter with the main rotor moving, the launching must be synchronize the mini-cannon (10) with the blades of the main rotor. The timing timing angle (98) of the command cam on the rotor axle will be determined, the size of the angle (11) of the mini-cannon (10) and other form and load improvements of the bag (2).

The experiments are done progressively, for the form and size of the bag (2), of the mini-cannon, size of the carrier rocket, adding, one by one all the elements such as : the axial- radial bearing for anchoring the cable (3) on the main rotor axle (8) of the helicopter, the magnetic or inductive cam, the real or virtual cam on the axle (9), the adjustable timing angle, then the radial slip anchor for cable twisting, equipment (5) for cable detachment (3) from the anchor, an equipment (6) of elastic extension and preferably carbon fiber or other.

Stage e) Finishing touches for the short, quick, reverse launch system (20), launching the parachute bag (2) through the main rotor's blades, then the overtaking of the bag (2) by the guided rocket (12) on a descending route, half-circled shaped, and with forced opening of the parachute at the far end of the half-circle right beside the platform (15) (in real use right beside the aircraft) the parachute being ready-open but the other way around, then pulling the parachute and rolling it in the normal, braking position, to the cable (3) by pulling the cable (3) with the capstan (19) and placement on the roll (18).

Stage f) Final testings on aircraft can be done gradually, initially with unmanned aerial vehicles, on drones, on planes that allow the pilot to eject and after finalization of the standard equipment (14) and after sufficient training of the piloting staff, even on planes.

First a turn-around parachute will be deployed and after temporary use, the first parachute will be detached, then experimenting with remote command even for forced, distructive landing by using a beckie for touch-down, with obsolete airplanes after completing their lifetime, landings on a hilltop bailing only dummy staff.

Recording and high framerate slow-motion playback will allow for improving all of the components of the invention.

As a logical consequence, all the derived ideas, naturally resulted from the

experiments and detailed as in claims 1 to 15 belong to the present invention.