CZ305548B6 - Life-saving ejection system for multicopters - Google Patents

Abstract

The life-saving ejection system, particularly for multicopters according to the present invention, being arranged inside or outside of the multicopter cockpit (17), comprises a life saving parachute (1) stowed inside a parachute container (2) and connected by means of parachute ropes with the container (2), whereby the system further comprises a gas generator (10). According to the first embodiment of the invention the life saving parachute (1) canopy (3) is connected through the mediation of a strength rope (4) with an ejection weight (5) in the central blind hole (6) of which, there is arranged a pin (7) fixedly anchored by its one end on the multicopter (12) cockpit (17) and provided on its other end with a cavity (8) for arranging therein a gas generator (10) that is connected wirelessly to a switching logic block (11) arranged inside or outside of the multicopter (12) cockpit (17). According to the second embodiment of the invention the life saving parachute (1) canopy (3) is connected through the mediation of the strength rope (4) with an ejection weight (5) in the central blind hole (6) of which, there is inserted a pyro-actuator (15) body, the end of which, overlapping the ejection weight (5) is fixedly coupled with the multicopter (12) cockpit (17). An ejection piston (16) arranged next the other end of the pyro-actuator (15) is accommodated in the pyro-actuator (15) body and below the ejection piston (16), there is arranged the gas generator (10) that is connected wirelessly to the switching logic block (11) arranged inside or outside of the multicopter (12) cockpit (17).

Description

Rescue ejection system, especially for multicopters

Technical field

The invention relates to an ejection rescue system, in particular for multicopters, equipped with at least three propulsion rotors. These multi-engine helicopters allow more precise control of these flying mechanisms. The purpose of the invention is to provide a suitable rescue system intended especially for multicopters.

BACKGROUND OF THE INVENTION

The security device for the vortex is the subject of a utility model DE 20 2012 104 809, Int. Cl. B 64 C 27/02, according to which a fixing ring connected by a steel cable to the parachute casing is placed on the shaft of the rim rotor via a pair of inserted rotating loops. The parachute casing is mounted on a support tube covering the rotor shaft of the rim at points below the rotor blades and under the mounting ring.

The rescue device for helicopters is the subject of the invention GB 2133365, Int. Cl. ³ B64D 17/80. According to this solution, a cylindrical hollow sleeve is terminated in the upper part of the hollow shaft of the helicopter rotor, terminated in its lower part by a base plate, which makes it impossible to leave the hollow shaft of the helicopter rotor when the cylindrical hollow sleeve is fully extended. The cylindrical hollow housing is preferably covered with a removable lid from the top. In the inner space of the cylindrical hollow bushing, a container is mounted on the ball bearings in which two separate chambers are formed. In the first upper chamber there is a folded parachute, in the lower chamber is installed an ejector device for ejection of the stored rescue parachute. The ejector device may be a spring or compressed gas or a pyrotechnic cartridge.

According to utility model CZ 25882, Int. Cl. B 64 D 17/80 is a ballistic rescue system for airplanes with a rotating wing, which are helicopters, gyrocopters or skylights. The essence of the solution is that one or more individual rescue parachutes are attached by means of anchoring rope directly to the rotor of the airplane with the rotating wing under its rotating blades. The anchoring rope is provided between the airplane rotor and the rescue parachute with a rotating hinge to eliminate the rotor speed, thus preventing their transmission to the parachute lines of the rescue parachute. The rescue parachute is folded in a storage container and is equipped with a rocket engine located in the rocket. The rocket engine pulls the rescue parachute from a storage container in the form of a sleeve of at least ten meters.

Another rescue system for radiators or helicopters, located inside or outside the fairing, is the utility model CZ 25106, Int. Cl. B 64 D 17/80, according to which the rescue parachute is stored in a carrier container and packed in a parachute container, which as a whole is pulled by a rocket engine into the free space outside the rescued helicopter or vimax. At a safe distance from the helicopter or vixen by further movement of the rocket engine, the parachute container is removed from the rescue parachute and immediately the rescue parachute is unpacked without the possibility of contact of the rescue parachute with the helicopter or vixen kite. The rescue parachute is connected to the fairing of the helicopter or villum by means of a connecting carabiner and a strength rope, either by means of a sling loop or by means of a sling ring in the space below the helicopter or vortex rotor. The suspension ring or suspension loop encircles the vortex rotor brackets or the helicopter rotor shaft, whereby the strength rope suspension loop is first removably anchored to the helicopter or the helicopter fairing and only comes into contact with the helicopter rotor shaft or helicopter after failure. . with the rotor rotor bracket. A freewheel is interposed between the bonding carabiner of the strength rope and the sling ring or sling to allow the strength rope to rotate about its central axis.

- 1 GB 305548 B6

The subject of the invention is a rescue parachute system for multicopters, which are helicopters with multiple rotors, for example four, six or eight rotors. These flying machines are remotely controlled and controlled by the pilot from the ground. The most common weights of multicopters are up to ten kilograms, but we need to consider increasing their weight up to 50 kg depending on their technical parameters and ability to perform various operations and work.

SUMMARY OF THE INVENTION

The essence of the solution of the rescue parachute system in multicopters is that the canopy of the rescue parachute is connected to the ejection weight by means of a rigid rope. In its impassable central hole there is a mandrel, which is firmly anchored at one end a cavity in which the gas generator is accommodated, wherein activation of the gas generator is effected wirelessly by means of a switching logic block located inside or outside the multicopter fairing. The outer surface of the darkness located in the through hole of the ejection weight is sealed around the gas generator by a plug. Preferably, the gas generator is a pyrotechnic composition.

In an alternative solution, a pyroactuator body is inserted in the through hole of the ejection weight, the end of which protrudes over the ejection weight and is firmly connected to the fairing of the multicopter. In the pyroactuator body there is a firing piston arranged at the other end of the pyroactuator body and on the other hand a gas generator is located under the firing piston in the pyroactuator body. Equally, activation of the gas generator is accomplished wirelessly via a switching logic block located inside or outside the multicopter fairing. Preferably, the gas generator is a pyrotechnic composition.

Clarification of drawings

The invention is illustrated by way of example and schematically in the drawings, in which FIG. 1 shows the rescue action of a defective multicopter on a rescue parachute; FIG. 3 shows the construction of a rescue mechanism with a ejection weight placed in the dark; and 4 an alternative design of the ejection mechanism with a ejection weight in which a pyroactuator with a ejection piston is inserted in the impassable central cavity.

DETAILED DESCRIPTION OF THE INVENTION

In case of any failure or failure. evaluation of the critical flight state of the multicopter 12 is fired by means of a remote control the rescue parachute i stored on the fairing 17 of the multicopter 12 in the parachute container 2. The multicopter 12 is carried on parachute lines 18 of the rescue parachute 1 which was pulled from the parachute container 2 by ejection weight 5 according to fig. The ejection weight 5 remains permanently connected to the canopy 3 of the rescue parachute 1. Depending on the weight of the multicopter 12, the ground plane of the rescue parachute 1 is also selected.

FIG. 2 shows the principle of the ejection mechanism formed by the ejection weight 5, which is pushed through its blind central opening 6 on the dark 7, which is firmly connected to the fairing J / 7 of the multicopter 12. The ejection weight 5 is firmly connected by a rigid rope 4 to the canopy 3 of the rescue parachute I. In the darkness 7, at its upper end in the cavity 8 is a gas generator 10 leading to a blind hole 6 in the ejection weight 5. Preferably the gas generator 10 is pyrotechnic. folds. The outer surface 13 of the darkness 7 is sealed by a gland 14 around the gas generator 10. The rescue parachute 1 is connected by parachute lines 18 to the parachute container 2.

-2GB 305548 B6

Activation of the gas generator 10 is effected wirelessly via the switching logic block 11 located inside or outside the T7 fairing of the multicopter 12. A gas pressure is created in the space between the mandrel 7 and the cavity of the through hole 6 to give the ejection weight 5 an initial velocity and The ejection weight 5 pulls a rescue parachute 1 to a safe distance from the multicopter 12, which is opened by the ambient air flow and is safely dropped to the ground of the multicopter 12 on its parachute lines 18.

1 and 2. According to FIGS. 3 and 4, the lower part of the pyroactuator body 15 is fixedly fixed in the fairing 17 of the multicopter 12. the ejection weight 5 is pushed by its impassable central opening 6, which is fastened to the canopy 3 of the rescue parachute 1 according to FIG. 1 by means of a rope.

In the pyroactuator body 6 in the ejection weight 5. Under the ejection piston 16, in the pyroactuator body 15 there is a gas generator 10 represented by a pyrotechnic composition. After firing the pyrotechnic composition, the firing piston 16 is ejected from the pyroactuator body at high speed, which supplies the firing weight 5 with the necessary energy to pull the rescue parachute out of the parachute container 2. The firing weight 5 moves in the direction of arrow.

The activation of the gas generator 10 is effected wirelessly via the switching logic block 11 located inside or outside the fairing 17 of the multicopter 12.

In the example, specific common values are given for a multicopter rescue system weighing about 7 to 8 kg, which in no way limit the use of the rescue system for smaller or larger flying multi-engine helicopters. For a given weight is used multikoptéry parachute one weighing 307 grams, the number of segments Mas suspension ropes length 2.08 m. This corresponds to about one parachute plan a 3.14 m ^2. In this case, a ejection weight of 50 to 100 grams is used and the pyrotechnic composition used has a weight of 0.5 to 2 grams. At a multicopter weight of about 50 kilograms, a rescue parachute 1 with a surface area of at least 12 m ² would be required.

Claims (17)

PATENT CLAIMS A rescue ejection system, in particular for multicopters, provided inside or outside a multicopter fairing (17) and comprising a rescue parachute (1) located and folded in a parachute container (2) and connected by parachute lines (18) to said container (2), the system further comprises a gas generator (10), characterized in that the canopy (3) of the rescue parachute (1) is connected to the ejection weight (5) by means of a rigid rope (4), (7) fixedly fixed at one end to the fairing (17) of the multicopter (12) and at the other end provided with a cavity (8) in which the gas generator (10) is connected wirelessly to the switching logic block (11); outside the fairing (17) of the multicopter (12). A rescue ejection system, in particular for multicopters, provided inside or outside a multicopter fairing (17) and comprising a rescue parachute (1) placed and folded in a parachute container (2) and connected by parachute lines (18) to the container (2), the system further comprises a gas generator (10), characterized in that the canopy (3) of the rescue parachute (1) is connected to the ejection weight (5) by means of a rigid rope (4), in which the body the end of the pyroactuator (15), the end of which projects beyond the firing weight (5), is rigidly connected to the fairing (17) of the multicopter (12), and a firing piston (16) provided at the other end a pyroactuator (15) and a gas generator (10) connected wirelessly to the switching logic block (11) located inside or outside the firing piston (16) is located below the firing piston (16) multicopters (12). Rescue ejection system, in particular for multicopters, according to claim 1, characterized in that the outer surface (13) of the darkness (7) in the vicinity of the gas generator (10) is sealed by a gland (14). A rescue ejection system, in particular for multicopters, according to claim 1 or 2, characterized in that the gas generator (10) is formed by a pyrotechnic composition. 2 drawings List of reference marks: 1 - rescue parachute 2 - parachute container 25 3 - canopy 4 - strength rope 5 - ejection weights 6 - through hole central 7 -tm 30 8 - cavity 9 - arrow 10 - gas generator 11 - block (switching logic) 12 - multicopter 35 13 - outer surface 14 - seal 15 - pyroactuator 16 - ejection piston 17 - fairing 40 18 - parachute line.