CIRCULATION CONTROL SLOTS IN HELICOPTER YAW CONTROL SYSTEM

Abstract: To achieve the required optional controllability and navigability of the hovering motion of the hovering body in a free liquid environment, the hovering body is equipped with a suitably created mechanism for optional control of direction and/or the position of the hovering motion in the form of the basic jacket (1) suitably equipped with at least one slot jet (14) where the basic jacket (1) is suitably connected to the elongated jacket (2) mechanism for the optional stabilisation of the direction and/or the position of the hovering motion suitably equipped with at least one uplift component (24).

Description: CIRCULATION CONTROL SLOTS IN HELICOPTER YAW CONTROL SYSTEM Technical Field The patent refers to a hovering body, especially a helicopter, equipped with an autonomous drive for setting the body in motion especially in a free liquid environment and it is equipped with at least one mechanism for optional control of direction and/or position of its hovering motion implemented in the form of an elongated basic jacket which has a covering profile constructed as a close joint curve, smooth in parts. Moreover, the basic jacket is equipped along its longitudinal axis with at least one slot jet for controlled ejection of liquid from the internal environment of the basic jacket into a free liquid environment. State of the Art So far known solutions of hovering bodies equipped with an autonomous drive for setting a body in motion in a free liquid environment are perforce equipped with a suitable, feasible mechanism for optional control of direction and/or position of the hovering motion to ensure adjustable parameters of its direction and/or position at any given moment, which is usually manifested in any hovering bodies which move in a hovering way in liquid, e.g. ships or submarines, or move in air which e.g. aeroplanes or helicopters usually in the form of an elongated basic jacket where covering profile is constructed as a close joint curve, smooth in parts. Such a basic jacket is then equipped with at least one outlet jet for controlled ejection of liquid from its internal environment into a free liquid environment to fulfil the basic functions of setting and changing direction and/or position of the hovering body. Comparable known solutions of mechanisms for optional control of direction and/or position of hovering motion are mostly applied in such hovering bodies, largely in helicopters, where a quick change of position or motion seems to be most desirable due to their utilisation functions, the solution described in the French patent file No. 1332300, which stems from the technical utilisation of Coand's effect, represents in the case of their utilisation in hovering bodies constructed as helicopters a significant step forward in known comparable implementation of mechanisms at this time for optional changing of direction and/or position of hovering motion. Concurrently, the said patent is followed by another solution which could be considered even more progressive and which is described in US patent file No. 4200252 where the solution, in contrast with the previous one, tries to solve the problem of system of operation for a helicopter where the previously proposed system of anti-momentum compensation is not efficient or adequate. Another significant comparable solution is the European patent file No. 0524044 which is extremely demanding from the technical as well as technological point of view in that it combines the classical rotary compensatory system with the circulatory system. Such a solution is operationally very complicated and no practical application has, as yet, been found for it. The only more efficacious solutions to the problem of optional control of direction and/or position of the motion of a hovering body in a free liquid environment are those demonstrated in the case of helicopters by U.S. company McDonnel Douglas, based on the above mentioned US patent file 4200252. The said solution is fully functional in all the systems of operation concerning the hovering motion of a helicopter, nevertheless its mechanism for optional control of direction and/or position of hovering motion of the helicopter is, due to its relatively low efficiency caused by a low ceiling on the coefficient of compensatory momentum unfortunately leads to its extraordinarily great external phasing out dimensions and thus also to a higher weight. The weight is significantly increased even further by the necessity of using low-pressure slot jets, as these significantly and unfavourably lower torque and flexion durability of the entire mechanism for optional control of direction and/or position in such machines. Such a reduction of stress in this solution is dependent on the inherent disruption of circumambient flow of the jacket surface tension mechanism for optional control of direction and/or position of hovering motion of a helicopter in those places where the low-pressure slot jets are located. Disclosure of Invention We are trying to solve the above mentioned problem as well as eliminating deficiencies in existing solutions by a hovering body equipped with an autonomous drive for setting it in hovering motion in free liquid environment, where such a body is equipped with at least one mechanism for optional control of direction and/or position in its hovering motion implemented in the form of an elongated basic jacket where its covering profile is constructed as a closed joint curve, smooth in parts. Also where the basic jacket is in the direction corresponding with the direction of its longitudinal axis equipped with at least one slot jet for controlled ejection of liquid from the internal environment of the basic jacket into a free liquid environment. According to this patent the key to implementation lies in the fact that the slot jet is formed by at least one or more vents led through the ring of the basic jacket and by at least one cover led in the direction, which corresponds with the direction of the longitudinal axis of the basic jacket and the cover is in the position of the longitudinal axis of the basic jacket lying within the main horizontal plane of symmetry of the basic jacket arranged by its boarder attack adjacent to the upper top circumferential spot of the external surface of the basic jacket in contact with the external surface of the basic jacket and its outlet edge averted from the upper top circumferential spot of the external surface of he basic jacket. It is arranged at a distance from the external surface of the basic jacket and the vents are arranged between the boarder attack of the cover and outlet edge of the cover and the summary surface of cross-sections of the vents is larger than the surface of the outlet cross-section in the area of spacing where the outlet edge of the cover is separated from the external surface of the basic jacket. Furthermore, use of the patent achieves a suitable solution for a hovering body due to for the significant reduction of its weight and phasing out dimensions of the mechanism for optional control of direction and/or position of the hovering body by the fact that the basic jacket is connected via its internal surface to the source of controlled liquid flow with the compression coefficient being at least 1 1 Even greater enhancement of the efficiency of the mechanism for optional control of direction and/or position of hovering motion of the hovering body, according to the invention taking into account the contemplated characteristics of its system of operation, was achieved by the fact that the basic jacket is equipped with two slot jets arranged in tangential direction of the external surface of the basic jacket in the angular spacing in the range of 20° to 80° Another significant improvement of the complex operational possibilities of the hovering body according to the invention was achieved specifically by the fact that one forward side of the basic jacket is connected to a mechanism for optional stabilisation of direction and/or position of the hovering motion carried out in the shape of an elongated jacket closed into a covering profile where its longitudinal axis is in alignment with the longitudinal axis of the basic jacket, and where its mam horizontal plane of symmetry is in alignment with the main horizontal plane of symmetry of the basic jacket, where the elongated jacket is equipped with at least one uplift component led in the direction, which corresponds with the direction of the longitudinal axis of the elongated jacket and where the uplift component is in the position of the longitudinal axis of the elongated jacket lying under the main horizontal plane of symmetry of the basic jacket, said component arranged by its boarder attack in contact with the external surface of the elongated jacket which lies on the joint curve of the inflection points of contact with the external surface of the elongated jacket where the convex and/or concave surface of the uplift component, defined by its longitudinal dimension at the level of the boarder attack and at the level of the outlet edge, is in its shape expanding into the main horizontal plane of symmetry of the basic jacket by at least in multiple ratio of the longitudinal dimension at the level of the boarder attack according to the longitudinal dimension at the level of the outlet edge Where the mean curve of the transverse profiles projected onto the normal plane according to the main hoπzontal plane of symmetry of the basic jacket, it forms an arc where the angle of its bowstring at the level of the boarder attack differs from the angle of the bowstnng at the level of the outlet edge of the uplift component Furthermore, the invention offers a suitable solution for a hovering body for a significant reduction of its weight as well as phasing out dimension of the mechanism for optional control of direction and/or position by the fact that the basic jacket together with the longitudinal jacket forms an integral unit Thus, the solution according to this invention achieves even better results of the aforesaid hovering body, according to the invention, by the fact that the end place of the uplift component is arranged at a distance from the external surface of the longitudinal jacket Moreover, the invention achieves a possible suitable solution for a hoveπng body due to the demonstrable improvement of parameters of its operational properties, as well as functional reliability, by the fact that the end place of the uplift component is arranged in contact with the external surface of the longitudinal jacket, which is at a distance from the point of contact between the boarder attack of the uplift component and the external surface of the longitudinal jacket. The invention provides even further improvement of the application of the solution for a hovering body, including the aspects of acquisition cost, economy, operational reliability, and functional service life by the fact that at least one of the uplift components is equipped with a multi-directional reactive jet for controlled ejection of liquid from the internal environment of the basic jacket into a free liquid environment. The advantages of constructing the hovering body according to the invention can be seen especially in the fact that, as well as maintaining the properties of current known comparable solutions, its concept for creating the mechanism for optional control of direction and/or position of hovering motion of the proposed hovering body is simple as it is set in motion by its autonomous drive, which is in the form of a carrying rotor. The mechanism for optional control of direction and/or position of the hovering motion of the hovering body according to the invention represents a very efficient construction framework, which by its technically simple and economically undemanding technical means provides for achieving all the required operational properties of a hovering body, especially a helicopter, in the operational regime for a stable position, e.g. in the operational regime when a helicopter hovers in place, as well as in all the operational regimes of dynamic motion. Due to a higher fall in the pressure gradient in comparison with current known low-pressure systems we can achieve, at the level of the outlet edge of the cover of slot jet, a significantly higher relative average speed in an arbitrary point of Coand's flow, as it is more turbulent than the equivalent level of turbulence of existing Coand's flow systems, which can be considered a significant advantage of the solution of a hovering body according to the invention. The value of the absolute speed of Coand's flow remains clearly subsonic. Higher energy potential of Coand's flow allows for achieving a markedly higher real bending polarisation of the flow of liquid in the surroundings of the basic jacket of the mechanism for optional control of direction and/or position of the hovering motion of the hovering body according to the invention as well as reaching a higher coefficient of equivalent buoyancy, which enables creation of such a mechanism for optional control of direction and/or position of the hovering body according to this invention with significantly lower phasing out dimensions and, therefore, also significantly lower weight. Hence, the hovering body according to the invention, with regard to the concrete proposed conditions of its optimal operation in service, can advantageously use a whole range of possibilities of variation of quantity, its own creation and disposition arrangement of the said slot jets and their correspondent vents or covers moulded in the basic jacket of the mechanism for optional control of direction and/or position of the hovering body, where yet more possible ways of creating of a hovering body according to the invention with regard to its concrete proposed conditions of operation and due awareness of the given physical properties of the surrounding liquid environment, there are still a whole range of variations of solutions for a mechanism for optional stabilisation of direction and/or position of the hovering motion, especially with regard to the number, shape and mutual dispositional arrangement of uplift components, concretely manifested, where all the variations of creating a hovering body according to the invention can be appropriately and advantageously constructed, even with regard to the optimisation of its operational properties as far as the lowest level of acquisition costs as well as the extreme technological standards of its real production and achievement of the highest possible operational reliability and functional service life, while fulfilling guaranteed and fault- free requisite functions of the hovering body in any system of operation of hovering which is undoubtedly assisted by such a formation of its elongated jacket, where at least one of the uplift components is equipped with a multi-directional jet for controlled ejection of liquid from the internal environment of the basic jacket, which is integrally connected to the elongated jacket, into a free liquid environment. Brief Description of the Drawings The invention will be described in more detail via the attached drawings where Fig. 1 illustrates a solution for the hovering body according to the invention presented by a helicopter in a schematic longitudinal view. Fig. 2 illustrates a solution for the basic jacket of the mechanism for optional control of direction and/or position of the hovering motion according to Fig. 1 in a schematic longitudinal view. Fig. 3 illustrates a solution for the basic jacket according to Fig. 1 and Fig. 2 in cross section. Fig. 4 illustrates a solution for the basic jacket according to Figs. 1 to 3 in cross section where the direction of the flow of the liquid circumfluent around the hovering body is schematically marked. Fig. 5 illustrates a solution for the elongated jacket of the mechanism for optional stabilisation of direction and/or position of the hovering motion according to Fig. 1 in a schematic longitudinal view. Fig. 6 illustrates a solution for the elongated jacket according to Fig. 5 in cross section. Fig. 7 illustrates a solution according to Figs. 5 and Fig. 6 where the liquid circumfluent around its uplift components in the forward motion of the hovering body is schematically marked. Fig. 8 illustrates the resolution of forces in circumfluent liquid according to Fig. 7. Fig. 9 illustrates a solution according to Figs. 5 and 6 where the vertical upper liquid circumfluence around its uplift components is schematically marked. Fig. 10 illustrates the resolution of forces in vertical upper liquid circumfluence as marked in Fig. 9. Fig. 11 illustrates a solution according to Figs. 5 and Fig. 6 where vertical lower liquid circumfluence around its uplift components is schematically marked while Fig. 12 illustrates the resolution of forces in vertical upper liquid circumfluence as marked in Fig. 11. Best Mode for Carrying Out the Invention A hovering body according to the invention carried out, for example, in the form of a ship, submarine, aeroplane, or helicopter as illustrated in Fig. 1 , which means such a overing body, which hovers under control in a specific way in a free liquid environment due to its autonomous drive, is usually equipped with at least one mechanism for optional control of direction and/or position of the hovering motion carried out in the form of the elongated basic jacket i of mainly cigar shape where the covering profile is carried out as a closed joint curve smooth in parts. To ensure optional control of direction and/or position of the hovering motion of the hovering body said basic jacket 1 is equipped with at lest one slot jet 14 arranged on the basic jacket 1 in the direction of its longitudinal axis ϋ serving for controlled ejection of liquid from the internal environment of the basic jacket 1 into a free liquid environment. According to Fig. 2 and Fig. 3 it is clearly visible that the correspondent slot jet 14 constructed on the basic jacket 1 is implemented as one and/or more vents 15 which are led through the rings 10 of the basic jacket 1 and also as at least one cover 16 adapted on the basic jacket 1 in the direction corespondent with the direction of its longitudinal axis 11 Fig. 2 illustrates that the cover 16 is in the position of the longitudinal axis ϋ of the basic jacket 1 where it lies within the main horizontal plane 19 of symmetry of the basic jacket 1 arranged by its boarder attack 17 adjacent, in the stipulated position of the cover 16 to the main horizontal plane 19 of symmetry of the basic jacket 1, to the upper top circumferential point of the external surface 12 of the basic jacket 1 in contact with the external surface 12 of the basic jacket 1. When contemplating the same position of the cover 16 to the main horizontal plane 19 of symmetry of the basic jacket 1 , the cover 16 is arranged with its outlet edge 18 averted from the upper top point of the external surface 12 of the basic jacket 1 at a distance from the external surface 12 of the basic jacket 1. From the above mentioned Fig. 2 and Fig. 3 it is clear that each of the created vents 15 always arranged between the boarder attack 17 of the cover 16 and the outlet edge 18 of the cover 16 is on the basic jacket 1, where the creation of the body as well as the spatial arrangement of the vents 15_and their corresponding covers 16 is, advantageously, such that the total surface area of sections of the vents 15 are always larger than the surface of outlet section in the place there is a gap between of the outlet edge 18 of the cover 16 and the external surface 12 of the basic jacket 1 To guarantee the required advantageous functions of the hovering body according to the invention, presented especially in the case of a helicopter, it is crucial that the basic jacket 1 is attached to its pertaining source of controlled liquid flow by its internal environment, with the coefficient of compression being at least 1.1. To achieve practical controllability and navigability in each proposed operational regime of the hovering body according to the invention, especially in the case of a helicopter, the basic jacket 1 is equipped with two slot jets 14 arranged in a tangential direction from the external surface 12 of the basic jacket 1 at an angle of 20° to 80°, as illustrated in Fig. 3. Further significant improvement of the required controllability and navigability is provided by such an implementation according to the invention, where a mechanism for optional control of direction and/position of the hovering motion is connected to at least one forward side 13 of the basic jacket 1 as it is schematically illustrated in Fig. 1 and further in Fig. 5 and Fig. 6. Such a mechanism for optional stabilisation of direction and/or position of the hovering motion is carried out in the form of an elongated jacket 2 of a closed covering profile where its longitudinal axis 21 is covered by the longitudinal axis H of the basic jacket 1 while the main horizontal plane 23 of symmetry of the elongated jacket 2 is covered by the main horizontal plane 19 of symmetry of the basic jacket 1. The said elongated jacket 2 is equipped with one and/or more uplift components 24 each of which is on the external surface 22 of the elongated jacket 2 arranged in the direction corresponding with the direction of the longitudinal axis Λ of the elongated jacket 2. The relevant uplift component 24 is in the position of the longitudinal axis 21 of the elongated jacket 2 lying within the main horizontal plane 19 of symmetry of the basic jacket 1 arranged by its boarder attack 25 in contact with the external surface 22 of the elongated jacket 2, where the boarder attack 25 lies on the joint curve of inflection points of contact with the external surface 22 of the elongated jacket 2. The convex and/or concave surface of such an advantageously implemented uplift component 24 is defined by the longitudinal dimension of the uplift component 24 at the level of the boarder attack 25 of the uplift component 24 and at the level of the end place 26 of the uplift component 24. The said surface is develops in its unrolled shape into the main horizontal plane 19 of symmetry of the basic jacket 1 and is equal to at least a multiple of the ratio of the longitudinal dimension at the level of the boarder attack 25 to the longitudinal dimension at the level of the end place 26, where the mean curve of cross profiles of the uplift component 24 projected onto the normal plane to the main horizontal plane 19 of symmetry of the basic jacket 1 forms an arc, where the angle of its bowstring at the level of the boarder attack 25 of the uplift component 24 differs from the angle of its bowstring at the level of the end place 26 of the uplift component 24. It seems quite natural that among the best modes for carrying out the invention will be such a solution for a hovering body according to the invention where the basic jacket 1 together with the elongated jacket 2 forms an integral unit as is illustrated in Fig. 1 , in the case of the best mode for carrying out the hovering body according to the invention in the form of a helicopter hovering in the air medium. To ensure the requisite level of controllability and navigability of the hovering body according to the invention in the proposed operational systems we can assume such a solution to be advantageous, where the uplift component 24 is arranged by its end place 26 at a distance from the external surface 22 of the elongated jacket 2 as illustrated in Figs. 5 to 7 where for other specific operational regimes of the hovering body we can assume such a constructed uplift component 24 that it is advantageous and it is arranged by its end place 26 in contact with the external surface 22 of the elongated jacket 2 and it is at the same time arranged at a distance from the point of contact of the boarder attack 25 of the uplift component 24 with the external surface 22 of the elongated jacket 2. As schematically illustrated in Figs. 1 , 5, and 6 to ensure secure orientational stability of the hovering body according to the invention even in spatial dynamic controllable changes of its direction and/or position, it is equipped with at least one from the, as already mentioned, arranged uplift components 24, multi-directional reactive jet 27 for controlled ejection of liquid from the internal environment of the basic jacket 1 into a free liquid environment. The principle of the function of the hovering body, according to the invention carried out in the best mode in the form of a helicopter, is as follows. Introducing the best mode for carrying out a helicopter, shown in principle in Figs. 1 to 12 by means of its autonomous drive, i.e. a carrying rotor, set in the hovering motion in the air where the air flows through the carrying rotor and is accelerated in the direction down to the tail end of the helicopter and thus also to circumfluence of the basic jacket 1 with its appropriately created slot jets 14 and also of the elongated jacket 2 and individual uplift components 24. The vector of velocity of the descending flow of the air is further combined with the vector of velocity of the forward and/or other spatial motion. The flow of air of the given resultant vector circumfluent around the basic jacket 1 is divided into two parts, where part of the air flow circumfluent around a part of the external surface 12 of the basic jacket 1 on which the slot jets 14 are arranged is accelerated by Coand's flow generated through the slot jet 14, where the air slows from the necessarily utilised source of controlled pressure of air with a compression coefficient of at least 1.1, as shown in the attached drawings. Extreme increases in the level of turbulence and thus also of the Coand's flow are reached particularly by double gradual expansion of pressure air at the level of the outlet from the vents 15 under the cover 16 and on the ejection from the outlet edge 18 of the cover 16. Coand's flow, generated by the slot jet 14 according to the invention, is extraordinarily highly turbulent having high relative average velocity at each point of such a flow, where the average pressure at any equivalent point of the said Coand's flow is lower than in any point of free flow by which, according to known patterns of circumfluence around curved surfaces of bodies, the flow of the circumfluent air, marked in Fig. 4 as 01, presenting generally the direction of the circumfluent liquid bends significantly. Such a significant real bending of the circumfluent air is further, in an advantageous solution for the hovering body according to the invention, achieved by a suitable creation of spatial configuration utilising two slot jets 14 on the external surface 12 of the basic jacket 1 in such a way that the second slot jet 14 is arranged at such a tangential distance from the first slot jet 14 to create better conditions for adherence of the Coand's flow emerging already from the first slot jet 14, as here both Coand's flows generated by the slot jets 14 combine. Hence, as it is known the resultant uplift force V comes about, as shown in Fig. 4, as a vector perpendicular to the direction PT of the velocity of the entering air and the resultant uplift force V is in the case of carrying out the body according to the invention in this illustrated best mode for carrying out, in the form of a helicopter, utilised to compensate the torque momentum emerging as a consequence of the function of the carrying rotor which ensures the autonomy of motion of the helicopter. We can deduce easily from Fig. 4 that the magnitude of the said resultant uplift force V can be positively influenced by means of regulating functional parameters of the necessarily utilised source of controlled air pressure, thus we can also efficiently influence the direction and/or position of the helicopter in the air. For achieving the optional stabilisation of the motion of the helicopter in its movement through the air, a mechanism for optional stabilisation of the direction and/or position of the hovering motion of the helicopter in connected to one forward side 13 of the basic jacket I of the said helicopter, which is carried out in the form of the elongated jacket 2 that forms in the best mode of the solution shown in Fig. 1 , an integral unit together with the basic jacket 1. On the elongated jacket 2, in the best mode for carrying out the hovering body according to the invention in the form of a helicopter as shown in Figs. 5, 6, 7, 9, and 11, there are arranged three uplift components and each of these uplift components 24 is distinguished by different geometric parameters. The three basic examples of possible functionality of the said mechanism for optional stabilisation of the direction and/or position of the hovering motion are clearly shown in Figs. 7, 9, and 11 where their correspondent resultant vectors are shown in Figs. 8, 10, and 12. Fig. 7 shows the best mode for carrying out the elongated jacket 2 with three uplift components which show their principal function in the forward motion of the helicopter. This function is shown in Fig. 7 by the vector sum of individual resultant forces of the aerodynamic left-hand forces marked as FU , FL2, FL3 which come into being on the uplift components, while from Fig. 8 it is clear that the position of the resultant uplift force FV in its horizontal projection, which means in its arrangement in the main horizontal plane of 19 symmetry of the basic jacket 1 shown in Fig. 8 as the resultant left-hand compensatory force KFL by which it operates anti-momentum against the torque momentum of the carrying rotor, and in the consequence of this it takes a significant part in the basic directional stabilisation of the forward motion of the helicopter. Fig. 9 shows the elongated jacket 2 with three uplift components 24 according to Figs. 5 and 6 where the function of these uplift components 24 is shown in the upward direction PT of the entering air which corresponds, for example, with the operational regime of elevation of a helicopter. Such a function is shown in Fig. 10 presented by the sum of individual aerodynamic forces, which come into being on the uplift components 24, which lead to the resultant left-hand force FL and the resultant right-hand force FP and Fig. 8 shows that from the position of the resultant uplift force FV it is clearly visible that the resultant uplift force FV in the same horizontal projection, which means in its arrangement in the main horizontal plane 23 of symmetry of the elongated jacket 2 as well as in the main horizontal plane 19 of symmetry of the basic jacket 1 , marked as the resultant left-hand compensatory force KFL converges to the left by which it operates anti-momentum against the torque momentum of the carrying rotor and in the consequence of that it takes a significant part in the basic directional stabilisation of the upward motion of the helicopter. Figs. 9 and 10 clearly show that the higher the resultant left-hand compensatory force KFL the greater the value of the rising velocity of the helicopter and thus also the circumfluence of air will be more intensive if the value of the rising velocity of the helicopter is higher and also if the circumfluence of the air around the basic jacket 1 and/or elongated jacket 2 is more intensive in the direction PT of the air which is functionally very advantageous as it will be able, without any intervention on the part of the pilot, or of another mechanical or electrical mechanism, more efficiently to compensate with anti-momentum the value of the torque momentum from the carrying rotor of the helicopter Fig 11 shows that best mode for carrying out the elongated jacket 2 with three uplift components 24 in a cross-section according to Figs 5 and 6 where the principal function of the said uplift components 24 is marked in their circumfluence in the downward direction PT of the entering air, which corresponds with, for example, the operation of descent of the helicopter This function is shown in Fig 12 as the sum of the individual aerodynamic and dynamic forces coming into being on the uplift components 24 and these are the resultant left-hand force FL and the resultant right-hand force FP and from the position of the resultant uplift force FV shown in Fig 11 it is clear that the resultant uplift force FV in the same horizontal projection, that means in its arrangement in the main horizontal plane 23 of symmetry of the elongated jacket 2 as well as in the main horizontal plane 19 of symmetry of the basic jacket I, marked as the resultant right-hand compensatory force KFP which is oriented to the right by which, in the operational regime of descent of the helicopter, i e in the system that corresponds with a significant reduction of the torque momentum of the carrying rotor according to the total reduced energy input needed for the descent of a helicopter, takes part in the balance of the forces and stability of the motion of the helicopter This function, shown in Fig 12, is extraordinarily important also and mainly in the operational regime of the autorotation of the helicopter, when it is necessary to compensate with anti- momentum the force contrary to the autonomous motor flight of a helicopter It is clear that other variants of different operational regimes of the hovering motion of the helicopter carried out according to the invention will always be a combination of different acting resultant forces, e g as shown above on the three basic mentioned examples of the function of the hovenng body according to the invention carried out in the form of a helicopter, but also of other different resultant forces, where the optional objective was predominantly suitably selected when solving the mutual position and shape of individual uplift components 24 being such that their spatially arranged geometric design in which optional stability of direction and/or position of the hovenng body, undisturbed in the course of the hovenng motion by any external force, is achieved most advantageously according to the invention in a free liquid environment Autonomous used uplift components 24 of the elongated jacket 2 are, nevertheless, earned out mainly depending on the utilised values of Reynold's number in such a way that their individual parts and groupings of profiles show the highest and/or lowest efficiency of their function depending on concrete conditions of the hovenng motion of the helicopter which as a result leads to even greater and more significant increase of functionality of these uplift components 24 Utilising parameters which define the value of Reynold's number in constant kinematic viscosity of a liquid environment (that means the characteristic dimension and, concretely, in the proposed example the values of the depth of the individual profiles of the uplift components 24) multiplied by instantaneous hovenng forward velocity of the hovering body according to the invention, such stabilisation ratios of the mechanism for optional stabilisation of direction and/or position of the hovering motion have already been reached at the point of the proposed concrete construction of the body of the mechanism together with the required optional directionality of the resultant vector of the stabilisation force of the whole of the said mechanism which both lead to a significant decrease in the extreme requirements of the supplementary stabilisation of direction and/or position of the hovering body according to the invention in the whole range of the operational velocities and systems of the hovering motion of the hovering body according to the invention. The industrial applicability The solution for the hovering body according to the invention is multilaterally utilisable in any hovering bodies e.g. ships or submarines, which move in a hovering fashion in liquid, or e.g. aeroplanes or helicopters, which move in a hovering fashion in air.

Claims: CLAIMS 1. A hovering body, especially a helicopter, comprising an autonomous drive to set it in hovering motion in a free liquid environment equipped with at least one mechanism for optional control of direction and/or position of its hovering motion, carried out in the form of an elongated basic jacket, which has a covering profile carried out as a joint curve, smooth in parts, where that basic jacket is, in the direction corresponding to the direction of its longitudinal axis, equipped with at least one slot jet for controlled ejection of liquid from the internal environment of the basic jacket into the free liquid environment, c h a ra cte rized i n , that the slot jet (14) is formed by one or more vents (15) conducted through the ring (10) of the basic jacket (1) and at least one cover (16) conducted in the direction corresponding to the direction of the longitudinal axis (11) of the basic jacket (1) where the cover (16) is in the position of the longitudinal axis (11) of the basic jacket (1) coming under the main horizontal plane (19) of symmetry of the basic jacket (1) arranged by its boarder attack (17) adjoining to the top circular location of the external surface (12) of the basic jacket (1 ) in contact with the external surface (12) of he asic jacket (1) and its outlet edge (18) averted from the upper top circular location of the external surface (12) of he basic jacket (1) is from the external surface (12) of the basic jacket (1) arranged at a distance where the vents (15) are arranged between the boarder attack (17) of the cover (16) and the outlet edge (18) of the cover (16) and the total surface area of cross section of the vents (15) is larger that the surface area of the outlet cross section in the location of the spacing of the outlet edge (18) of the cover (16) from the external surface (12) of the basic jacket (1 ). 2. The hovering body, according to claim 1, ch a racte rized i n , that the basic jacket (1) is in its internal space linked to the drive of the controlled flux of liquid with the coefficient of compression being at least 1.1. The hovering body, according to claim 1, c h a racte rized i n , that the basic jacket (1) is equipped with the slot jets (14) arranged in tangential direction to the external surface (12) of the basic jacket (1) at an angular distance between 20° to 80°. 4. The hovering body, according to claim 1, ch a racte ri zed i n , that one forward side (13) of the basic jacket (1) is connected to a mechanism for optional stabilisation of the direction and/or the position of the hovering motion carried out in the form of the elongated jacket (2) of the closed cover profile where the longitudinal axis (21) is in alignment with the longitudinal axis (11) of the basic jacket (1) and where the main horizontal plane (23) of symmetry is in alignment with the main horizontal plane (19) of symmetry of the basic jacket (1), where the elongated jacket (2) is equipped with at least one uplift component (24) conducted in the direction corresponding with the direction of the longitudinal axis (21) of the elongated jacket (2) where the uplift component (24) is in the position of the longitudinal axis (21) of the elongated jacket (2) coming under the main horizontal plane(19) of symmetry of the basic jacket (1) arranged by its boarder attack (25) in contact with the external surface (22 of the elongated jacket (2), which lies on the continuous curve of the inflection points of the contact with the external surface (22) of the elongated jacket (2) where the convex and/or concave surface of the uplift component (24) is defined by its longitudinal dimension at the level of the boarder attack (25) and at the level of the end place (26) is in its developed form into the main horizontal plane (19) of symmetry of the basic jacket (1) at least in multiple ratio of the longitudinal dimension at the level of the boarder attack (25) towards the longitudinal dimension at the level of the end place (26) where the mean curve of the transverse profiles projected onto the normal plane according to the main horizontal plane (19) of the symmetry of the basic jacket (1) forms an arc where the angle of its bowstring at the level of the boarder attack (25) differs from the angle of bowstring at the level of the end place (26) of the uplift component (24). 5. The hovering body, according to claim 1 and4, c h a racte rized i n , that the basic jacket (1) together with the elongated jacket (2) form an integral unit. 6. The hovering body, according to claim 1 and 4, c h a racte ri zed i n , that the uplift component (24) is by its end place (26) arranged in a distance from the external surface (22) of the elongated jacket (2). 7. The hovering body according to claim 1 and 4, c h a racte ri zed i n , that the uplift component (24) is by its end place (26) arranged in contact with the external surface (22) of the elongated jacket (2) which is at a distance from the position of contact of the boarder attack (26) of the uplift component (24) with the external surface (22) of the elongated jacket (2). 8. The hovering body, according to claim 1 and 5, c h a racte ri zed i n , that at least one of the uplift components (24) is equipped with a multi-directional jet (27) for controlled ejection of liquid from the internal environment of the basic jacket (1) into a free liquid environment.

Inventors: NAMISNAK JAN, NAMIS&NCARON
Applicants: NAMISNAK JAN, NAMIS&NCARON
Application year: 2000
Main classification: B64C27
IPC codes: B64C27