UA70304C2 - Shell of real weight - Google Patents

Abstract

The invention concerns rocket production, in particular, the construction of a shell of real weight of cargo bay of rocket. A shell for protection of real weight has the shape of surface of a revolution body and is made with possibility of separation with the help of the system of separation lengthwise into the segments. Shell has the nose cone made of two halves, conical part made of two halves and fixed with possibility of disconnection of cylindrical part from the carrier rocket. Separation system has a system of vertical and horizontal separation with possibility of simultaneous separation of shell of real weight into longitudinal segments, separation of shell from carrier rocket and removal of longitudinal segments from the carrier rocket. The pyrotechnic system of separation is made with possibility of the synchronous activation of horizontal and vertical systems of separation. Invention ensures the ejection of shell without damage of remaining part of the carrier rocket and real weight.

Description

Description of the invention

The invention relates to rocket engineering, namely the design of the payload fairing of the cargo compartment 2 of the rocket.

A payload fairing is known for protecting a payload to be transported by a launch vehicle, and the fairing is in the shape of the surface of the body of rotation and is excavated so as to be separable by means of a separation system along at least one plane of separation into at least two longitudinal segments, capable of separating laterally from the remaining part of the launch vehicle, and this skin has 70 a nose fairing made of two halves forming its front part, a conical part made of two halves forming its middle part, and made of of two naves and fixed with the possibility of disconnecting from the remaining launch vehicle, the cylindrical part, while each of the halves of the nose fairing, the conical part and the cylindrical part are made non-detachable, as well as the components of the halves of the longitudinal segments of the nose fairing, the conical part and the cylindrical part , are inseparably connected to each other, and the division system 12 has a vertical division system (d iv US patent Mo5585596).

The payload fairing of this type, which contains the payload to be transported in space, forms the uppermost and the very front part of the launch vehicle. The main function of the payload sheathing is to to protect the payload transported by the rocket from harmful effects, in particular from moisture, rain, sun, salt particles and dirt particles in the air, during the stay of the launch vehicle in the launcher and, in addition, from aerodynamic and thermal loads during rocket take off At the appropriate time, namely when the need to protect the payload disappears, the payload fairing is removed from the remaining part of the rocket.

The disadvantage of the known design is that it is made of segments, and the removal of this skin from the remaining part of the launch vehicle is carried out by dividing it into segments, which are then ejected from the side of the rocket. In this case, problems often arise. For example, the segments do not separate completely from each other (9 from each other, resulting in an inclined position with respect to the longitudinal axis of the rocket, and some or all of the segments remain on the remaining part of the launch vehicle instead of being removed from it; or the segments break up into small component parts that are retained to a certain extent in the remaining part of the launch vehicle. M

The basis of this invention is the task of creating an improved casing of the payload Ha") of the above-mentioned type, which could be discarded without harming the remaining part of the launch vehicle and, above all, without harming the payload. at

The task is solved due to the fact that the payload fairing for the protection of the payload intended for transportation by means of a launch vehicle, and this fairing has the shape of the surface of the body of rotation 32 | separable by means of a separation system along at least one plane of separation into at least two longitudinal segments capable of being separated laterally from the remaining part of the launch vehicle, and this skin has a nose fairing made of two halves , which forms its front part, made of two halves, a conical part, which forms its middle part, and made of two halves and "fixed with the possibility of disconnection from the remaining launch vehicle, a cylindrical part, while each of the halves the nose fairing, the conical part and the cylindrical part are made non-separable, and the components of half of the longitudinal segments of the nose fairing, the conical part and the cylindrical part are inseparably connected to each other, and the mass separation system is a vertical separation system, according to the invention the separation system is made with the possibility of simultaneous separation of the payload casing into longitudinal segments, the separation of the specified casing from the rocket-n the remaining axis and the removal of longitudinal segments from the remaining launch vehicle, the fission system in addition to the vertical fission system contains a horizontal fission system, as well as a pyrotechnic system, while the pyrotechnic system is made with the possibility of synchronous av | activation of the specified horizontal and vertical separation systems, and the vertical separation system is equipped with linear blocks with a detachable stopper located on the border areas of the longitudinal segments of the payload casing, each of which has one linear piston and one linear cylinder, which hold the longitudinal segments together at 20 unweakened stopper, and when the stopper is weakened, the specified longitudinal segments are mutually disconnected and removed from the remaining launch vehicle, and to activate the weakening of the

T" support is provided with a pyrotechnic system, while the horizontal separation system is equipped with a tension belt in the zone of the separation ring.

The nose fairing is formed by a shell and a three-dimensional frame structure made with the possibility of 52 divisions along at least one plane of division, and in each segment of the nose fairing there is a corresponding

GF) part of the shell and the frame structure are rigidly connected to each other.

The conical and cylindrical parts of the payload casing are formed by a multilayer structure with a porous core and a shell applied to the outer surface of the core, and the multilayer structure is made with the possibility of separation along at least one plane of separation, and is rigidly connected to the covering 60 layers.

The separation system is equipped with a redundancy system and includes horizontal and vertical separation systems, as well as a pyrotechnic system, while the horizontal separation system is dug with the possibility of connecting and subsequent separation of the payload fairing from the remaining part of the launch vehicle, the vertical separation system is completed with the possibility of connection and subsequent division of the payload sheathing into longitudinal segments, and the pyrotechnic system is made with the possibility of synchronous activation of the specified horizontal and vertical separation systems, which have approximately the same reaction periods.

The horizontal separation system is equipped in the zone of the separation ring with a tension belt consisting of at least two parts, the ends of which meet at points outside at least one plane of separation, while in

In the zone of each meeting point, there is a tensioning device for tensioning the specified belt, made mainly in the form of a tension bolt, and a dividing device, made mainly in the form of a cutter, for dividing parts of the specified belt, and the dividing device is made with the possibility of activation using a pyrotechnic system.

The vertical separation system is equipped with linear blocks with a removable stopper located on the border areas of the longitudinal segments of the 7/0 payload sheathing, each of which has one linear piston and one linear cylinder that hold the longitudinal segments together when the stopper is not loosened, and when it is loosened, it is mutually disconnect the indicated longitudinal segments and remove from the remaining part of the launcher, and a pyrotechnic system is provided to activate the weakening of the stopper.

The payload fairing is equipped with a pyrotechnic manifold, through which, on a signal from part /5 of the remaining launch vehicle, detonation incendiary devices are ignited, igniting, in turn, if possible, synchronizing the vertical and horizontal separation systems to activate the separation device of the horizontal separation system and loosening of the stopper of the vertical separation system.

The payload casing is provided with electrostatic protection, mainly in the form of an electrically conductive layer of paint on electrically insulated component parts in contact with electrically conductive parts. It is also equipped with thermal protection, which can be combined with electrostatic protection, and/or a ventilation system.

The idea behind the creation of the payload casing according to the invention is that any involuntary division of the payload casing into component parts is impossible. So, for example, frame or load-bearing structures, as well as the cores of multilayer structures do not fall apart into separate parts, the skins put on the load-bearing and frame structures and the film-like covering layers of multilayer structures do not separate; there is also no involuntary division of longitudinal segments into parts. However, if necessary (8), separation of the payload fairing from the remaining part of the launch vehicle is carried out, and full and synchronous separation of the fairing into separate longitudinal segments. Immediately following the aforementioned separation and division, the freed longitudinal segments are removed and thrown aside relative to the remaining part of the launch vehicle without damaging the payload and dynamic characteristics of the remaining launch vehicle.

Other characteristics and advantages of the invention are described below with the help of examples of implementation and with reference to the attached drawings. co

The drawings show:

Fig. 1 Payload casing according to the invention with the maximum volume (proved by 5 Shaded) for the payload, in the longitudinal section of the launch vehicle; Cha

Fig. 2 Payload cladding according to Fig. 1, side view;

Fig. 3 Functional diagram of the separation system;

Fig. A4 Horizontal division system in vertical section;

Fig. 5 System of horizontal division in a horizontal section; "

Fig. 6 System of vertical division before ignition; z c Fig. 7 System of vertical separation after ignition;

Fig. 8 Pyrotechnic system; ;" Fig. 9 Cable distribution (fragment);

Fig. 10 Electrical contact (schematic);

Fig. 11 Electrostatic and thermal protection; -I Fig. 12 Cooling system.

It is worth pointing out that the designations of the type "above", "below", "right", "left" refer to the corresponding location of the described structural elements on the corresponding drawings. The indicated dimensions should be considered as examples.

The casing of the payload 1 (Fig. 1-2) for the protection of the payload transported by means of a launch vehicle consists essentially of two connected longitudinal segments 2, З and contains a spherical segment surface of the nose fairing 4, the conical front part 5 and the cylindrical rear part 6. The nose fairing 4 consists of two halves 7, 8, the conical part 5 - from two surfaces in the form of obtuse semi-cones U, 10 and the cylindrical part b - from two surfaces in the form half cylinders 11, 12.

Nose fairing 4 is made of aluminum alloy. The structures of the conical part 5 and the cylindrical part 6 are a multi-layered structure consisting of covering film 13 made of carbon glass fiber and openwork

F) porous core 14 made of aluminum, on opposite outer surfaces of which covering films are fixed. ka The nose fairing 4 of the payload fairing 1 contains both halves 7, 8 and forms the front part of the payload fairing 1 in the form of a hemisphere. As already mentioned, the nose fairing consists, as a matter of fact, of an aluminum alloy and is formed by a supporting and frame structure and a shell. The shell, which has assumed a hemispherical shape as a result of stretching or stretching, has a thickness of 1 to 2 mm. Each of the two halves 7, 8 is divided into three segments of the nose fairing. Carriers of the channel profile, extending along the quarter-circle line or the line of the hull, are fixed with rivets on the shell at equal distances in relation to each other to ensure the necessary stability and rigidity. Two horizontal frame parts in the shape of a 65 semicircle, which are essentially located in a plane perpendicular to the longitudinal axis of the payload casing, are fixed on the shell and vertical carriers in the shape of a quarter circle, due to which a rigid,

a somewhat closed box structure in which all vertical supports are connected by both frame parts.

A silicone elastomer seal is attached to one of the fairing halves.

The conical part 5 of the casing of the payload 1 consists, as already mentioned, of two halves 9, 10.

Each of the halves 9, 10 of the conical part 5 connects one of the halves of the fairing 7 or 8 with one of the halves 11, 12 of the cylindrical part b of the casing of the payload 1. The conical part 9, 10 is essentially formed by vaults-shells of porous ventilated multilayer construction , the thickness of the walls of which without a thermal protective layer is 25 mm. The ventilated or openwork core of the multilayer structure is made of aluminum and has a porous structure. Covering layer 13 is made of layered with carbon reinforcement 7/0 fiber; and the directions of the fibers are established on the basis of the requirements for strength, stiffness and stability in the axial and tangential directions. Casings-sheaths are made of P segments located at an angle of 90".

Channel profiles made of fiberglass material are attached along the vertical straight edges of each element. Segments are connected by rivets with external or partially connected aluminum parts. /5 stiffeners are attached along the top and bottom edges of the carbon fiber glass of each multilayer element. The front frame 15 of the conical part is riveted to the nose fairing frame, while the connection of the conical and cylindrical parts is carried out by means of rivets through the aluminum intermediate frame 16 and the aluminum outer part 17.

The cylindrical part 6 of the casing of the payload 1, consisting of two halves 11. 12, has essentially the same design as the conical part 5 of the casing of the payload 1.

As already mentioned, the longitudinal segments 2, Z of the casing of the payload 1 are connected to each other by means of a removable fastener. In the same way, the payload fairing can be separated from the remaining part of the launch vehicle with the help of the separating ring 18 located at the rear end of the cylindrical part. | finally, the released longitudinal segments can be ejected laterally from the remaining portion of the launch vehicle. with

Fig. 3 schematically shows the design of the device designated as the separation system 19. The separation system 19 is designed to initially keep the given shape of the cladding i) of the payload 1 for the required time and keep it on the remaining part of the launch vehicle, and then at the right moment to separate it and separate it from the remaining part of the launch vehicle. The separation system 19 contains three subsystems, namely: firstly, the horizontal separation system 20, secondly, the vertical separation system 21, "g

Thirdly, pyrotechnic system 22.

The horizontal separation system 20 is shown in Fig. 3, 4 and 5. As shown in Fig. 3, it includes a pyrotechnic cutter 22, a guillotine device 24, a tie bolt 25, an end connection 26, a tie collar 27, and a harness power lines 28 and connecting clip 29.

The steel clamping collar 27 with a thickness of 3 to 5 mm, which passes along the lower end of the cylindrical part 6 of the casing of the payload 1 around the dividing ring 18 (Fig. 5), is divided into two parts 30, 31, each of which passes at an angle of approx. 180" and is maintained in a tensioned state. For this purpose, two tensioning bolts 25 are provided, located on the symmetrical axes of both longitudinal segments 2, of the sheathing of useful wattage 1. In the zone of each of the tensioning bolts 25, one cutter 23 is located. Each of the cutters 23 is intended in order to cut off its fastening bolt 25 at the right moment, this will cause disconnection in the "horizontal separation system 20 and separation of the payload fairing 1 from the remaining part of the launch vehicle. c Each cutter 23 contains two cutting knives that can be actuated independently of each other, which achieves the necessary reserve for the horizontal division system 20, The system makes it possible to prevent;" the release of combustion products and metal parts, which in turn prevents the possibility of contamination and damage to the remaining part of the launch vehicle. Both halves 30, 31 of the clamping collar 27 during the removal of both halves 2, From the payload fairing 1 are fixed on them. For this serves as a groove in -I the lower part of the separating ring 18 and clamps on the upper part of the separating ring. When both halves 2,

From the casing of the payload 1 fixed on the remaining part of the launch vehicle, a measuring device is used to control the tension in each tension bolt 25 of the horizontal separation system 20. After 2) setting the tension in the tension bolts 25, the cutters 23 are fixed in their position. Both cutters 23 are fixed in the casing of the payload 1 in such a way that all the pyrotechnic equipment related to the cutters 23, as well as the remaining part of the pyrotechnic system 22, are located on one of the two halves 2 of the casing of the payload 1.

The vertical separation system 21 is shown in Fig. 3, b and 7, and Fig. b shows the state of the system before ignition, and Fig. 7 shows the state after ignition. As shown in Fig. 3, the vertical separation system 21 contains a transition tube 32, an upper end seal 33, a lower end seal 34 and linear blocks 35. In turn, each linear block 35 is equipped with a linear explosive device 36, gas discharge

F) attenuators 37, a bellows-type gas cylinder 38, a piston 39, a cylinder 40, a bolt 41 and a rivet 42. ka Linear explosive device 36, designed to supply the energy necessary to separate and remove both halves of the payload casing and contains m' as detonating ignition lines near the ends of pyrotechnic caps.

The vertical separation system 21 serves two purposes; firstly, it holds together both halves of the shell of the payload 1 so that in the launch phase they form a single integral unit, and secondly, it supplies a certain amount of energy to carry out the lateral separation of the shell of the payload 1 into two longitudinal segments 2 , 3. The vertical separation system 21 operates on the principle of a linear energy source to 65 extend the so-called linear piston 39 (Fig.b), connected to one of the longitudinal segments of the shell of the payload 1, from the so-called linear cylinder 40, from connected to another longitudinal segment of this shell.

The linear energy source consists of one single line of weakly detonating explosive substance, and the amount of explosive substance of the line determines all available energy and thus the lateral speed of both longitudinal segments 2, From the casing of the payload 1 when removing them from part of the launch vehicle, which

Remained. As already mentioned, the vertical separation system 21 is also intended to hold together both halves 2 of the payload fairing 1 during launch and until they are separated. The already mentioned linear piston 39 together with the already mentioned linear cylinder 40 form the linear unit 35.

Each of the two linear blocks 35 has a displacement retainer 43 that holds together the linear piston 39 and the linear cylinder 40. These displacement retainers 43 form a Locking Device; they prevent the separation of 70 longitudinal segments 2, from the sheathing of the payload 1 and transfer forces between two longitudinal segments 2, from the sheathing of the payload 1 until their separation; if this locking device is loosened, the two longitudinal segments 2, C are separated from each other. This is the case when the weakly detonating incendiary device 44 is ignited.

The vertical separation system 21 is a closed system of continuous action, which extends from the rear 7/5 separation ring 18 of the cylindrical part 6 forward to the nose clearance of the fairing 4, namely in the separation plane that separates the zone of the nose fairing from the area of the conical part 5, then horizontally across and to the opposite side or to the opposite line of the body and along it back to the separation ring 18. At both lower ends of the vertical separation system 21 there is a detonator block that forms the interface to the ignition device. In this way, the detonation signal will be transmitted from the pyrotechnic system 22 to the weakly detonating incendiary device 44 of the vertical separation system 21. The continuous action explosion line runs from the bottom of one side of the vertical separation system 21 up, across the top and down the opposite side, and each of the two lower ends in its detonator block. The pyrotechnic signal is transmitted simultaneously to both blocks of the vertical separation system 21, which ensures full redundancy of the vertical separation system 21. One sealing element forming part of the detonator block is provided at both ends of the active part of the vertical separation system ch 21. This ensures the tightness of the vertical separation system 21 and the presence of combustion products inside i) the system. It should also be noted that the so-called linear blocks 35 are made of magnesium alloy, that they are subjected to appropriate surface treatment, compacted or sealed in such a way that unprocessed magnesium of any kind cannot harm either the external environment or the payload . Presented in Fig. 3, 8, the pyrotechnic system 22 includes SOE 45, collector 46 and detonators 47. Together with the horizontal 20 and vertical separation systems 21, the pyrotechnic system forms a general separation o system 19, designed in such a way that the horizontal separation system 20 and the vertical separation system 21 s can operate simultaneously. This is achieved due to the use of the central conductive pyrotechnic line for igniting the detonator ignition device, which in turn ignites the horizontal separation system 20 and the vertical separation system 21. Ignition through the central conductive pyrotechnic line is carried out with the help of electrical signals emanating from the rocket and transmitted on two electric cables for two pyrotechnic detonators 47. These detonators ignite pyrotechnic charges placed in the pyrotechnic conductive line. The pyrotechnic charges of the current-conducting pyrotechnic line ignite in turn the pyrotechnic ignition caps on the tips of the pyrotechnic current-conducting line of the above-mentioned detonating "ignition devices." Six detonator ignition devices are ignited simultaneously and, in turn, in s transmit a pyrotechnic signal to each end of the vertical separation system 21 and to four cutters 23 of the horizontal separation system 20. Due to the high speed of propagation - from bOO0Ω/s to 800Ω/s - which has detonator ignition devices of almost the same length, activation of the vertical separation system and the horizontal separation system is carried out within the order of ZOOmks. It is provided that the pyrotechnic bcurrent line can be manually fixed in the "blocking" position or in the "action" position, and the indication of one or another position is carried out by simple means.

The next part of the description concerns the electrical wiring shown in Fig. 9 and the electrostatic protection shown in Fig. 10, 11. The general internal wiring and external 2) wiring for connection to the launch vehicle must be compatible. In this connection, it is necessary to consider the following points: 1) the length and passage of the cables, taking into account the total resistance; 2) type of cables, taking into account current/voltage-capacitance parameters; 3) cable configuration, taking into account the location of contacts, grouping by signal type and redundancy. Cabling essentially includes three zones, namely: 1) cabling of devices; 2) cable separation of the pyrotechnic part; and

C) electrical connection between the payload fairing and the remaining part of the launch vehicle. 5B Cable connection of devices is provided only for the first flight, for example, before putting the payload into operation; it connects the various devices that make up the instrument equipment of the flight with (F, separate power sources and signal devices and supplies energy and signals to the launch vehicle through an interface on each longitudinal segment of the payload fairing 1. To make measurements concerning separation of the payload fairing 71 and the mode during its lateral removal, part of the cable instrument bo equipment assumes the possibility of lengthening, pulling or unwinding. This allows, after a known relative displacement, to break the connection between the payload fairings 1 and the remaining part of the launch vehicle, and namely, by pulling the loop fixed on the payload fairing 1. For the operational part of the flight, which does not involve measurements related to the separation and removal of the payload fairing 1, no extension or unwinding of the cable equipment is required. Fully autonomous cable equipment 65 longitudinal segments 2 It is used for the transmission of electrical signals from the casing of the payload on the pyrotechnic power line. This switching circuit has two identical connections and is completely redundant. Initiating signals are generated in the remaining part of the launch vehicle and transmitted to the payload fairing through the interface connections fixed at the junction of the payload fairing - the rocket. When separating and removing the payload fairing, the connections are interrupted with the help of two loops fixed on the payload fairing.

Devices for electrical contact are presented in Fig. 10 and serve to ensure a reliable electrical connection between metal parts of cable equipment; thereby minimizing unwanted electrostatic effects that could cause mutual interference between individual signals. In particular, connecting clamps 48 are installed at the junction of halves 7, 8 of the nose fairing 4 and surfaces 9, 10 of the conical front part 5 of the payload fairing 1. Similarly, at the junction of surfaces 9, 10 of the conical front part 5 and/or surfaces 11, 12 of the cylindrical rear part 6 of the payload fairing 71 provides contact articulation 49. In addition, electrical contact is provided by a vertical doubler or low impedance link 50, a reference signal board 51 with control of external connections, a deployable connecting cable 52, and additional connection control points 53. The division line is indicated in Fig. 10 by position 54.

The low-impedance link 50 connects all metal parts to the contact point and is provided for the reason 7/5 that the payload fairing structure 1 cannot be used as a conductive return link.

The specified low-impedance link 50 is formed by aluminum composite parts that connect the conical 5 and cylindrical b parts of the payload casing to each other. All other conductive parts of the structure and electrostatic protection are connected to these mating parts made of aluminum.

Electrostatic protection (Fig. 11) includes a metal plate 55 with conductive glue 56, as well as a frame of the joint zone 57 with cork material 58 and an electrically conductive coating 59. Protection is necessary for the following reasons: electrostatic energy that will be generated on non-metallic and, as a result, electrically isolated outer parts of the payload fairing 1. can be transformed due to discharge phenomena into electromagnetic energy, which, in turn, can cause interference in the electrical system. This could happen, for example, on thermal protection formed from cork, which is provided with the sheathing of payload 1; however, this can be prevented by applying an electrically conductive coating 59 in contact with the metal parts of the structure. Besides. this coating can increase thermal protection if it is made of a suitable material, i) for example, an electrostatic paint that reflects solar rays and has a high hemispherical transmission capacity of radiation.

In conclusion, Fig. 12 presents the cooling system. The air from the tower will flow through the wall 60" from the cladding along the composite hose 61 and exit through the ventilation holes or air outlets 62. The path of air passage is shown in the drawing with arrows 63. o

The payload fairing 1 is held and separated from the remaining part of the launch vehicle by means of the separation system 19 in the following manner.

In the closing phase, the vertical separation system 21 holds together both longitudinal segments 2, From the cladding o

From Payload 1 along its vertical limits, and the horizontal separation system 20 provides a strong and mechanical connection with the remaining part of the launch vehicle. At the moment when the casing of the payload 1 should separate from the rest of the launch vehicle, according to the electrical signal received from the launch vehicle, pyrotechnic detonators 47 are ignited, which simultaneously activates the vertical separation system 21 and the horizontal separation system 20. The horizontal separation system 20 separates the casing of the payload 70 from the remaining part of the launch vehicle. The vertical separation system 21 separates the two longitudinal She)s segments 2, from the payload fairing 1 and removes or catapults them away from each other mainly in opposite directions, as a result of which they are also separated from the remaining part of the launch vehicle. ;" Because c pyrotechnic components and because all the elements that ensure the separation of the payload fairing 1, the separation of the payload fairing 1 and its removal from the remaining part of the launch vehicle are critical to the successful performance of the mission of the launch vehicle as a whole and, ultimately account, - And in order to preserve the operability of the payload, maximum attention should be paid to the separation system 19.

The principles by which the payload casing is designed and manufactured are fundamentally independent of its dimensions. Suitable payload covers can have a diameter in the range of 4m and a length of 8 to 12m. 2) The nose fairing can instead of being exactly hemispherical have a different shape, but closed in front and favorable in terms of aerodynamics. The conical part can completely fall off, and then the nose fairing and the cylindrical o part are directly connected to each other. For the above description, an example of the lining of the payload, divided into two longitudinal segments, was chosen; but the sheathing of the payload can be made with the possibility of dividing it into a larger number of segments. In this case, the number of distribution planes naturally increases. In the future, payload casings can be created, divided into two longitudinal segments, in which each longitudinal segment, in turn, consists of several parts inseparably connected to each other; In addition, longitudinal segments can be divided lengthwise and crosswise. name) 60 b5

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Claims (8)

The formula of the invention 1. The casing of the payload intended for transportation by means of a launch vehicle, which has the shape of the surface of the body of rotation and is made with the possibility of separation using a separation system along at least one plane of separation into at least two longitudinal segments that can be separated into lateral sides from the remaining part of the launch vehicle, and the skin has a nose fairing made of two halves, which is --. . --. . and forms its front part, made of two halves, a conical part, which forms its middle part, and a cylindrical part, made of two halves and fixed with the possibility of disconnecting it from the launch vehicle, which 75 remained, while each of the halves of the nose the fairing, the conical part and the cylindrical part are made -I inseparable, and also has the constituent halves of the longitudinal segments of the nose fairing, the conical part and the cylindrical part, connected to each other inseparably, and the division system has a vertical division system, which differs in that , that the separation system is made with the possibility of simultaneously dividing the cladding of the payload into longitudinal segments, separating the specified cladding from the remaining launch vehicle, and removing the longitudinal segments from the remaining launch vehicle, the separation system in addition to the vertical separation system contains a system horizontal division, as well as a pyrotechnic system, while the pyrotechnic system is made by them" with the possibility of synchronous ac tivization of the specified horizontal and vertical separation systems, and the vertical separation system is equipped with linear blocks with a detachable stopper located on the border sections of the longitudinal segments of the payload fairing, each of which has one linear piston and in ONE linear cylinder, which hold the longitudinal segments together when the stopper is not loosened , and when the stopper is weakened - the specified longitudinal segments are mutually disconnected and the remaining (F) is removed from the launch vehicle, and a pyrotechnic system is provided to activate the stopper weakening, while the GI system of horizontal separation is equipped with a tension belt in the zone of the separation ring. 2. Payload cladding according to claim 1, which is characterized by the fact that the nose fairing is formed by a shell and a three-dimensional frame structure, made with the possibility of separation along at least one plane of separation, and in each segment of the nose fairing, the corresponding part of the shell and frame structure is rigidly connected with each other C. Payload casing according to claims 1-2, which is characterized by the fact that its conical and cylindrical parts are formed by a multilayer structure with a porous core and a shell applied to the outer surface of the core 65, and the multilayer structure is excavated with the possibility of separation along at least one plane of separation, and rigidly connected to the covering layers. 4. Payload cladding according to claims 1-3, which differs in that the separation system is equipped with a redundancy system. 5. Covering for the protection of payload according to claim 4, which is characterized by the fact that the separation ring consists of at least two parts, the ends of which meet at points outside at least one plane of separation, while in the area of each meeting point there is a tensioning device for tensioning the specified belt, made mainly in the form of a tension bolt, and a separating device, made mainly in the form of a cutter, for separating parts of the specified belt, and the separating device is made with the possibility of activation using a pyrotechnic system. 70 b. The payload fairing according to claim 5, which is distinguished by the fact that it is equipped with a pyrotechnic collector, through which, on a signal from the remaining part of the launch vehicle, detonation ignition devices are ignited, which in turn ignite, if possible, the vertical and horizontal separation systems synchronously to activate the separation device of the horizontal separation system and loosen the stopper of the vertical separation system. 7. Payload cladding according to claims 1-6, which is characterized by the fact that it is provided with electrostatic protection, preferably in the form of an electrically conductive layer of paint on electrically insulated component parts in contact with electrically conductive parts. 8. Payload cladding according to claims 1-7, which is characterized by the fact that it is provided with thermal protection, which can be combined with electrostatic protection, and/or a ventilation system. 0. и и и 0. Official Bulletin "Industrial Property". Book 1 "Inventions, useful models, topographies of integrated microcircuits", 2004, M 10, 15.10.2004. State Department of Intellectual Property of the Ministry of Education and Science of Ukraine. c 6) « «c) (ze) «c) and - - and? -i («c) (95) («c) c» name) 60 b5