RU2643307C2 - Method of space installation of initially disclosed heat-resistant solid cordless parachute for multiton cargoes descent from the planet orbit - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: parachute with a canopy (3) is assembled from individual thermal plates and it has an end flat circular wall (6), a side wall (5) in the form of a truncated cone, a side cylindrical wall (4) and hoses (7) above the canopy, communicated with the holes in the end wall (6). The canopy (3) is provided with stiffening ribs (12). A descent payload (1) with a thermal shield (9) is connected to the canopy by a central pipe (8) fitted with a charge (10) to break the pipe (when landing) at the screw connections (11) of its parts. For preliminary slowdown of the parachute to acceptable speeds of atmosphere entry, descent modules (2) with jet engines installed on the end-edge of the cylindrical wall (4) are provided. Rigging of the parachute is carried out in orbit in an airtight space between the space film balls covering the space station and the assembly equipment (cabins with manipulators). Before landing, the film is cut, releasing the parachute.

EFFECT: improved processability and safety of the rigging process of the parachute and expanding the fleet of means of payload delivery from orbit to Earth.

3 cl, 11 dwg

Description

The invention relates to parachutes and provides for the installation of a vaulted structure consisting of self-supporting plates capable of absorbing an increased load.

(1) A rapidly opening parachute with a diameter of 30.5 m with an inflatable screen of six or eight meter diameter is known and tested (I. Afanasyev The second test of an air brake for Mars./f. Cosmonautics News, 2015, issue 8, p. 50- 51). For launching manned spacecraft with a mass of 15-20 tons to Mars, for the development of parachutes in this direction, a system is needed that can introduce a parachute with a diameter of 70-80 m in a few seconds into a supersonic stream and deploy parachutes for this purpose, but they are torn, so how they experience a huge jerk, falling into a supersonic stream of air. Therefore, the final braking when using the deploying parachutes is carried out near the surface of the planet using jet engines.

Therefore, the disadvantage of the said parachute is that the parachute from a large area fabric breaks when it is quickly opened in a supersonic air stream, no matter how strong materials are made.

(2) There is a known method of removing space debris from orbit and burning it in the upper atmosphere of the Earth, as well as an alternative way to use molecular replicators to collect new spacecraft from debris directly in space (A. Ilyin New ideas for our industry. MSU round table -Roskosmos / f. Cosmonautics News, 2014, issue 8, p. 44).

The disadvantage of this idea of molecular replicators is the long stage of its implementation. At the same time, for example, the life of the international space station is coming to an end, and a solution is needed that allows you to gently land the used space station on Earth, where it can be easily disposed of or used as a museum.

 (3) A combined aircraft is known to be lighter than air (according to the patent for the invention of the Russian Federation No. 2318697 according to the application No. 2006104265/11 of February 13, 2006, B64B 1/22, B25J 3/00), which is a semi-rigid airship containing a gondola and copy-type manipulators controlled from the driver’s nacelle. The device is equipped with electronic maneuvering equipment in a vertical plane. The device can be equipped with devices and tools for performing work in various fields of economic activity.

A known apparatus is given as an example of a device of a copy-type manipulator controlled from the driver's cab.

(4) A device is known for protecting an object in outer space (according to the patent for the invention of the USSR No. 1709899 according to the application No. 4613067/23 of 03.16.1987, B64G 1/52), containing a multilayer inflatable shell surrounding the object, characterized in that in order to improve the operating conditions of an object in outer space by approximating these conditions to the earth, the spaces between the layers of the shell are filled with gas with a decrease in pressure as the transition from the gas surrounding the object to the gas bounded by the outer shell layer, with each shell layer and connected to an adjacent sheath layer by at least four connecting elements. In addition, each layer of the shell can be made of a material that does not impede the transmission of electromagnetic waves. In addition, one of the layers of the shell can be made of a material that prevents the transmission of electromagnetic waves. In addition, each layer of the shell can be made in the form of outer films and carrier tissue located between them. In addition, the spaces between the object and the inner layer of the shell and between the layers of the shell can be filled with an inert gas.

The known device is given as an example of the organization of space around a space station.

(5) Known for a truck-mounted crane mounted on a dump truck type (according to the patent for the invention of the Russian Federation No. 2225804 according to the application No. 2003106146/11 dated 03.03.2003, B60P 1/54, B60P 1/16, B66C 23/42), which contains a truck tractor, a metal-loading platform with a body tipping back using an autonomous elevator and a hydraulic manipulator with a multi-link swinging boom equipped with a gripping body of a clamshell type.

A well-known crane-manipulator is given as an example of a multi-link pivoting boom, which can be used to move a cabin with a manipulator in space.

(6) A sample of the hull of the spacecraft’s return vehicle under development is known (MAKS 2015. Manned systems. / F. Cosmonautics News, 2015, issue 10, p. 3), the inner and outer casing of which is made of carbon fiber sheet filled with aluminum honeycombs and frames made of monolithic carbon fiber, 80% of the spacecraft will consist of carbon fiber, which reduces the total weight of the ship by 1 t.

The disadvantage of the proposed technical solution is the narrow scope, it is possible to expand the arsenal of landing gear made from the described carbon fiber.

(7) A parachute is known (according to the patent for the invention of the Russian Federation No. 2126764 according to the application No. 96123356/28 dated 12/10/1996, B64D 17/02), containing slings and a dome made with a system of symmetrically located sleeves descending from the openings to the edges of the dome, equipped with at the ends, elastic elastic nozzles pivotally connected to the dome, the surface of which above the holes is solid, characterized in that the sleeves, the surface of which is solid, have a semicircular cross section and the ends of the sleeves provided with nozzles are located above the Ania dome, the openings are arranged in pairs symmetrically with respect to the dome pole. In addition, the distances between the holes of different pairs may be different. In addition, pairs of holes can be located at the same level.

The disadvantages of the described parachute are the following:

1) it is not applicable at high descent speeds for spacecraft in the upper atmosphere, since it will burn, including slings;

2) it is not applicable for launching multi-ton cargo from the orbit of the planet, since it must have a large area that does not allow it to quickly turn around; when deployed, it will experience a big jerk that will tear it;

3) in the manufacture of dense solid material at different distances between the holes of various pairs, the sleeves located at different distances will have their centers of gravity, between which swinging is possible, which can lead to trembling of the parachute, and with it the passengers of the descent vehicle.

(8) A parachute is known (according to the patent for the invention of the Russian Federation No. 2336202 according to the application No. 2007123825/11 dated 06.25.2007, B64D 17/18), the hemispherical dome of which is made with a pole hole, over which a reflective screen is fixed. The screen is made with sleeves, the free ends of which are located in the aerodynamic dimming zone. Additional pole slings are passed through the holes in the pole part of the dome and mounted on the screen. The total cross-sectional area of the sleeves is chosen equal to the cross-sectional area of the pole hole.

The disadvantages of the described parachute are the following:

1) it is not applicable at high descent speeds for spacecraft in the upper atmosphere, since it will burn, including slings;

2) it is not applicable for launching multi-ton cargo from the orbit of the planet, since it must have a large area that does not allow it to quickly turn around; when deployed, it will experience a big jerk that will tear it;

3) the standard hemispherical shape of the parachute does not allow for additional braking due to the shape.

(9) A parachute is known and is proposed as a prototype (according to the patent for the invention of the Russian Federation No. 2038268 according to the application No. 4952039/23 of 06.28.1991, B64D 17/02), containing a dome, the base of which is made with a flat end and cylindrical parts, and slings attached to the cylindrical part, characterized in that in order to increase the drag coefficient of the parachute, between the flat end and cylindrical parts of the base of the dome is installed an additional part in the form of a truncated cone, with a large base facing the cylindrical part.

The disadvantages of the described parachute are the following:

1) it is not applicable at high descent speeds for spacecraft in the upper atmosphere, since it will burn, including slings;

2) it is not applicable for launching multi-ton cargo from the orbit of the planet, since it must have a large area that does not allow it to quickly turn around; when deployed, it will experience a big jerk that will tear it;

3) the outlet at the top of the end of the parachute directs the flow of air or other atmospheric gas perpendicular to the direction of descent, so atmospheric gas moving above the parachute is not used for additional braking.

The aim of the invention is the creation of a parachute for descent from the orbit of the planet onto its surface of multi-ton cargo.

The technical results of the invention are as follows:

- a parachute is made, braking in which is carried out both due to its conical-cylindrical shape, and due to the sleeves,

- an initially opened parachute is made, which cannot be torn when opened,

- a heat-resistant stringless parachute is made, which does not burn during landing,

- a heavy, durable parachute is made of solid reinforced materials, the large mass of which is compensated by the increased diameter,

- a parachute is made that has a central tube similar to the handle of an umbrella that holds the central load and has loads in the form of landers with jet engines suspended from the edge of the dome, which eliminates the use of slings,

- the assembly of the parachute is carried out from individual plates delivered to the orbit of the Earth or another planet by rockets or in the space elevator cabin, in the assembly space enclosed by oilcloths,

- assembly is carried out by two cabins with copy type manipulators,

- during assembly, the joints between the plates are covered with heat-insulating projections of the plates, which excludes the direct penetration of heated gas during landing between the plates,

- the fastening of the side surfaces of the plates is simple due to the spirals inserted into each other at the ends of the plates,

- the fastening of the front-back and upper-lower surfaces of the plates is double: simple by inserting the narrowing of the reinforcing pipes into the reinforcing pipes of the neighboring plates and difficult, strong by screwing the maces into the thickenings inside the reinforcing pipes of the neighboring plates,

- the invention increases the arsenal of means in which the thermal protection of the Soyuz spacecraft and modern landing craft modification descent vehicles can be applied,

- the parachute can be disassembled, for example, after a test assembly.

This technical result is achieved by the fact that the method of mounting in space the initially discovered solid heat-resistant stringless parachute for multi-ton cargo launched from the planet’s orbit, including mounting a parachute, the dome of which consists of a flat round end wall, a truncated cone-shaped wall and a cylindrical side wall, containing openings around the center of the end wall, over which there are sleeves that open nozzles on the wall in the form of a truncated cone above the lower edge of the last wall, characterized the fact that

carry out the installation of a parachute of the specified form with the location of the oval inlet openings of the arms around the circumference near the upper pole of the canopy of the parachute from individual plates having thermal insulation in the lower part and behind it having pipes and reinforcement rods perpendicular to each other,

they begin installation by docking to the end compartment of a space station located in the orbit of the planet under the protection of its magnetic field, stacks of descent vehicles with jet engines,

Next, the space station is surrounded by balls of oilcloth, between the balls, connecting them together, the cables are pulled, the spaces between the balls are filled with gas with increasing pressure from the periphery to the center, there may be liquid inside the central ball, as a result one end of the station opens out of the balls, the second end the station opens into the assembly space between the second and third outside balls, the largest part of the station is located in the central ball, the hatches of the station open into each inter-ball space,

further drivers from the station board enter the cabs with the hands of manipulators, close the cab and station hatches,

then undock from the end compartment of the cabin with the hands of the manipulators and spread them to the required distance with arrows,

then they feed from the open hatch of the terminal compartment of the station the plates of the canopy of the parachute, take them with the hands of the manipulators of the cabs and stick them by connecting the textile fastener to the inner surface of the second outside ball, enclosing the assembly space from the outside,

they supply from the same hatch of the station pliers or screwdrivers enlarged by the size of the manipulators and fix them in tool boxes attached to the cabins with manipulators,

feed from the same station hatch sections of the central tube of the canopy of the parachute, fold them together and with the station casing using a sleeve connection,

they feed the apex tube from the same hatch of the station, the hands of the manipulators of the first cabin hold it and the plates attached to it in place, the hands of the manipulators of the second cabin tear off the plates of the first annular row from the inner surface of the outer ball enclosing the assembly space, and the ends of the reinforcement pipes are inserted into the holes of the vertex tube plates of the first annular row, poking the side spirals of adjacent plates into each other, then the arms of the manipulators of the second cabin attach to the first row a second ring-shaped row of plates, with uniting their lateral edges by pushing the side spirals into each other and connecting their anteroposterior edges by inserting the narrowing of the second row of reinforcement pipes into the first row of reinforcing pipes, as well as screwing the maces inside the reinforcing pipes into the thickening of the walls of the joined reinforcing pipes,

then the cabin with the hands of the manipulators winds the top pipe with two annular rows of plates connected to it onto the axial tube of the central tube,

then they attach like the connection of the second ring-shaped row to the first the remaining ring-shaped rows up to the plates on the lower edge of the cylindrical side wall of the dome, tearing the plates from the inner surface of the outer ball enclosing the assembly space,

in the valves opening on the edge of the lower edge of the pipe, screw plugs and ears for fastening light side loads,

detached in turn the descent vehicles with jet engines from the end compartment, then the arms of the manipulators of the first cabin hold the descent apparatus with jet engines under the lower edge of the parachute, and the arms of the manipulators of the second cabin screw on it a cylindrical base with ears, for which they are attached to the ears with bolts and nuts on the edge of the lower edge of the canopy,

Before landing, the cab manipulators cut the oilcloths of two outer balls around the perimeter of the parachute with enlarged knives or enlarged scissors.

In addition, the method of mounting in space the initially discovered solid heat-resistant string-free parachute for multi-ton cargo launched from the planet’s orbit can differ in that, by attaching the plates fed from the hatch of the end compartment of the plate to the inner surface of the outer ball enclosing the assembly space, a little further than the parachute, they build heat shield, which is similar in design and method of assembling the canopy to the parachute, but smaller than it, and has no holes and sleeves, its central tube is short, and it is directed towards the plan when landing in the convex part, undock the planted part of the station from the rest of the station inside the assembly space, and at the end opposite the end of the undocked part of the station from the end with the canopy of the station, fasten the short central tube of the heat-shielding screen with a sleeve connection, turn on the side engines after cutting the outer balls, and the undocked part of the station moves away from the station towards the planet for landing so that the exhausts of the side engines do not fall into the parachute and heat shield.

In addition, the method of mounting in space the initially discovered solid heat-resistant stringless parachute for multi-ton cargo launched from the planet’s orbit may differ in that for landing the entire station around a separate pair of spacecraft docked to each other, having its own booths with manipulator arms and moving boom booms , build a shelter from a small number of balls, while one end of a pair of ships protrudes from the shelter and joins the same free end of the above space station , then a heat shield is constructed, which is similar to the device and method of assembling the parachute dome, but smaller than it, and has no holes and sleeves, its central tube is short, and it is directed towards the planet when landing with the convex part, after cutting the balls around the parachute dome , heat shield and side engines of the station, include the side engines of the station so that their emissions do not fall into the parachute and heat shield, and the station goes towards the planet for landing.

Description of drawings

The drawings show the following images.

In FIG. 1 is a general view of the assembled parachute in a vertical central cut, in FIG. 2 - stiffener at the side of the lateral connection of the plates in cross section, in FIG. 3 - installation of two plates with a common stiffening rib, side view, in FIG. 4 - joints of plates of three adjacent rows in a side section upside down, in FIG. 5 - mace inside the reinforcement pipe before installation, in FIG. 6 - mount the top of the parachute, in FIG. 7 - the location of the assembly space, the assembly means inside it and the portion of the assembled parachute, in FIG. 8 - fixing the central tube 8 to the spacecraft, which acts as a heavy central load, in FIG. 9 - fastening the ears with holes for the bolts to the descent apparatus, in FIG. 10 is an enlarged free lower thin end of the club handle in a vertical section, in FIG. 11 is a layout of nozzles of a rocket engine and fuel tanks inside a descent vehicle in a vertical cut.

The numbers in the drawings indicate:

In FIG. 1: 1 - descent heavy central load, 2 - descent vehicles with jet engines, 3 - parachute canopy, 4 - cylindrical side wall of the dome, 5 - dome wall in the shape of a truncated cone, 6 - flat round upper end wall of the dome, 7 - sleeves above the dome, 8 - the central tube, 9 - heat shield of the central load, 10 - TNT charge for breaking the tube 8, 11 - screw connection of the tube parts, 12 - stiffeners.

In FIG. 2: 13 - a spiral of the edges of the right plate, 14 - a spiral of the edges of the left plate, 15 - reinforcement pipes, 16 - side with a heat-protective coating.

In FIG. 3: 17 - abutting plates, 18 - directions of the retraction of the spirals of the edges of the plates into each other, 19 - the protrusion of the spiral, which does not enter the spiral of the mounted row, but enters the spiral of the next row.

In FIG. 4, 5: 20 - the gap between the adjacent plates of adjacent rows, 21 - the wall of the reinforcement pipe 15, 22 - the narrowing of the wall 21 of the reinforcement pipe 15 for insertion into the next pipe, 23 - the thickening of the wall 21 with a cylindrical hole having a thread in the center, 24 - a mace handle with a thread at the end corresponding to the thread of the hole in the wall 23, 25 - a thickening of the wall 21 with a cylindrical hole having a thread in the center, 26 - a thickening of the mace with a thread corresponding to the thread of the hole in the thickening 25 of the wall 21, 27 - protrusion of thermal protection blocking slit 20 in the place of joining of reinforcement pipes, 28 - a protrusion at the end of the handle 24 for gripping with enlarged pliers during installation.

In FIG. 6: 29 - axial tube as part of the central tube 8, 30 - thermal insulation of the axial tube 29, 31 - connection of the thread on the axial tube and the threads on the ends of the plates of the upper row, 32 - top pipe made of reinforcing pipe material with internal thread, 33 - radial holes in the pipe 32 for installing the pipe fittings, 34 - the ends of the pipe fittings protruding from the plates corresponding to the holes 33 in the pipe 32.

In FIG. 7:35 - space station, 36 - balls of different diameters from oilcloth, 37 - outer ball of oilcloth, 38 - radial cables connecting the balls, 39 - arrow with adjustable position, 40 - manipulator driver’s cab, 41 - manipulator’s hands, 42 - the terminal compartment of the station, located in the assembly space, which in some cases can serve as a descent load, 43 — oilcloth of the penultimate ball with a fleecy inner surface for connecting the textile fastener, 44 — assembly space, including the space between the third and second balls from the outside, where there is a parachute assembly, 45 - hatches for access to the inter-ball spaces, 46 - an external box on the cabin 40 for the tool.

In FIG. 8, 9: 47 - the hull of the spacecraft used as the central cargo 1, which is the terminal compartment of the station 42, 48 - the hatch, 49 - the sliding ring of the docking device, 50 - a cylindrical hole with internal thread in the hull, 51 - cylindrical extension of the axial tube 29 with an external thread corresponding to the thread of the hole 50, 52 — the lander body used as light weight 2, 53 — cylindrical base with an external thread corresponding to the thread of the hole 50, ears for attachment to the edge of the parachute, 54 — ears with holes tures for attachment bolts and nuts to the lugs on the bottom edge of the parachute.

In FIG. 10:55 - the level to which the thread reaches, corresponding to the thread of the hole 23.

In FIG. 11: 56 - the inclined nozzle of the jet engine, 57 - the axis of the central direction of the thrust of the nozzle 56, 58 - the central direction of the thrust acting on the exhaust gases, nozzles 56, 59 - the vertical component of the force 58, 60 - the horizontal component of the force 58, 61 - reactive engines, 62 — a vertical jet engine nozzle, 63 — the axis of the central direction of the nozzle traction 62, 64 — the central direction of the traction force acting on the exhaust gases, nozzles 62, 65 — the thermal insulation layer that will evaporate in the upper atmosphere, 66 — the central fuel tanks otse and 67 - the fuel tanks of the side compartments.

Before proceeding with the description of the assembly order of the parachute, it is necessary to describe the place where this assembly takes place. Interplanetary stations must have increased radiation protection, since the Earth's magnetic field does not protect them from particle fluxes from the Sun. You can protect people inside the interplanetary station by increasing the thickness of the walls of the spacecraft ships. But this will lead to a heavier ship station, as a result, they will be able to take on board less payload, as well as to reduce the living volume inside the station. It is advisable as radiation protection to use inserted from each other balls made of oilcloth with air or other gases absorbing solar radiation (such as hydrogen and helium) between oilcloths with increasing pressure from the center to the periphery. By oilcloth is meant two layers of a film with a supporting fabric between them. I am not inventing anything new compared to the application mentioned in the prior art in paragraph 4, with the only difference being that an interplanetary space station is placed inside the balls (Fig. 7). The premises of the station inside the central ball are most protected from radiation, the premises of the station that lead to the outer balls of the station are less protected from radiation, and the cosmonauts will be in them for a limited time. In FIG. 7 is not shown, but there should be a compartment on the other end of the station, opposite end 42, that leads to the outside of ball 37 so that spacecraft can dock to the station from the outside. Solar batteries are located on the outer ball of oilcloth 37 (not shown in Fig. 7), which also have the form of a multilayer oilcloth and are attached to it even on Earth. During installation, balls made of oilcloths are sewn from individual canvases deployed from rolls by astronauts in spacesuits. In this case, the lateral edges of adjacent canvases are bent towards each other and are either glued and stapled with a stapler, or are soldered to each other with heated tongs. The bends of the front and rear edges of the rolls are also glued or soldered to the station body. When all the coils from both ends are attached to the station, their glued or soldered bends are covered with a cable around the station body, the ends of the cable are screwed with a sleeve connection to each other. The cable presses the bends of the canvases to the station building. So that the rolls do not unfold when the side edges of the sheets are fastened, U-shaped clamps are inserted into them, which press the outer layer of the oilcloth to the innermost in the central hole of the roll. On the station’s ships, there are gas ducts leading outside the ships, to which gas cylinders are connected from the inside, which is discharged out between the balls until a pressure is reached, which is measured by pressure gauges located opposite the windows outside the station in inter-ball rooms. To fill the room outside the station inside the central ball, you can use water or other liquid, which is pumped out of the cylinders inside the station by pumps. Cables are pulled between the balls: on the ball, which is closer to the center, the bends of the cloths are pierced by the middle of the cable, and the two ends of the cable, containing rings similar to key rings, are attached to the bends of the canvases of the neighboring ball, which is further from the center. The holes in the bends of the canvases around the places where the cable and rings are pierced contain a metal edging, which is still made on the Earth and is located on the curved edges of all the canvases at equal distances. In places where the bends of the canvases are located on opposite sides of the balls, there are bookmarks with metal edging for fastening the cables, which are a continuation of the bent edges of the canvases and are laid between the bent side edges of the canvases, protruding from the other side of the bend. For the astronauts to move inside the balls and outside along the paths along the unfolded rolls, rows of parallel streaks are sewn to the oilcloth on Earth even along the Earth, forming paths along which, as through ladders, fingering the astronaut will be able to move. Stripes mean strips of fabric sewn from two ends to an oilcloth, with places of penetration of threads sealed with glue.

The parachute is assembled on the inner surface of the second outside ball 43 (Fig. 7), which in the general case should not be located too deep inside the remaining balls so that it and just one more external ball can be easily cut and the parachute with the landing gear pulled out. To extract the parachute with the load, it is enough to cut the oilcloths of the ball 43 and ball 37 around the canopy of the parachute with the enlarged knife or scissors with the manipulators and push them apart from the parachute. Cabins with manipulator arms are equipped with searchlights illuminating the place of work (not shown in Fig. 7).

The inner surface of the ball 43 is lined with a cloth with villi to connect the textile fastener with areas on the upper surface of the parachute plates covered with the same cloth with villi. The fibers of the fabric on the parachute plates and on the ball 43 penetrate each other while pressing the portion of the plate to the ball 43, as a result the plate ceases to soar in weightlessness and is fixed on the inner surface of the ball 43. It is advisable to cover the entire surface of the parachute plates with a cloth with fibers, but only protruding ones up areas, for example, on top of the sleeves 7 (Fig. 1).

The assembled parachute itself is almost not distinguished by the originality of the form and is a combination of the forms of the parachute described in paragraphs. 7-9. But unlike these applications, the proposed parachute is not disclosed, it is initially disclosed and made of a solid substance, and not of soft fabric. The surface of the parachute is a truncated cone (Fig. 1), directed wide part down, having a vertical cylindrical side wall 4 at the bottom, forming the edge of the parachute, a horizontal flat round upper end wall 6 and connecting their wall 5 in the form of a truncated cone. Sleeves 7 protrude above the upper surface of walls 5 and 6 to discharge air or other atmospheric gas from the lower surface of the end wall 6 to the edges of the upper surface of the conical side wall 5. The inlet openings of the sleeves 7 have an elongated oval shape and are located at the same distance near the top of the dome. Sleeves 7 in a transverse section have a semicircular shape. When landing atmospheric gas, breaking out of the sleeves 7, flows along the wall 5 and beyond beyond in the same direction of its inclination and creates a countercurrent to the movement of the atmosphere from the bottom up and additional braking force.

It is impossible to use slings in such a parachute, they will burn at high landing speeds in the upper atmosphere. To mount the descent central load 1 to the parachute, a central tube 8 coated with thermal insulation similar to the handle of an umbrella is used. In order to prevent the parachute from turning upside down during landing, additional loads in the form of landers with jet engines 2 are suspended at equal distances in pairs in the form of landers with jet engines 2. They can be used as landers 2 with analogues of the first stages of missiles with two types of engines and nozzles, outside they are covered with a heat-shielding layer similar to that of the Soyuz spacecraft descent vehicles. If a space station or other large object is used as the central cargo, the tube 8 of the parachute dome is attached to its upper compartment, and the tube 8 of the heat shield 9 to its lower compartment. Inside the tube 8, connected to the canopy of the parachute, in one of the places of screwing its sections into each other there is a TNT charge 10, which is detonated at the end of the descent. So that the parachute does not fall on the load and does not damage it, at the end of the landing, jet engines located inside the descent vehicles 2 are turned on, which, after landing and after the TNT explosion, carry the parachute without cargo to the side of the landing site.

The canopy of the parachute 3, as well as the heat shield of the central load, consist of plates fastened together (Fig. 2-6) and are assembled in a similar way. Side 16 of each plate, facing down during the descent, is covered with a heat-protective coating. It is advisable to use a heat-protective coating that has already been tested, the same as on the descent vehicles of modern spacecraft. For example, it’s the same as on modern modifications of the Soyuz spacecraft or made of carbon fiber sheet, the same as on the landing craft currently being developed. Behind the heat shield, the temperature is quite comfortable, so closer to the upper side of the parachute are the reinforcement tubes 15 and reinforcement rods (not shown) perpendicular to them, which give the parachute sufficient strength. The reinforcing pipes 15 and reinforcing bars perpendicular to them are made either of metal, or to facilitate the construction of hard carbon fiber, the same as in the ship’s frames in the prior art of item 6. The plates on the walls 4 have a simple flat shape, the plates on the walls 5 and 6 contain on top of the sleeve 7 - protrusion in the form of curved pipes divided in half, the lateral ends of which are attached to the flat part of the plates of the walls 5 and 6. That is, the sleeve 7 on a transverse section have a semicircular section. The wall plates 6 contain openings for the entry of atmospheric gas into the hoses. Sleeves 7 do not have fittings inside themselves and are made of heat-shielding material. The sections of the wall plates 5 and 6 under the sleeves and the sections of the plates 5 opposite the outlet openings of the sleeves 7 are covered with heat-shielding material, although they are on top of the plates, so that the channel inside the sleeve 7 and the upper section of the plates opposite the outlet openings of the sleeves 7 are completely covered with heat protection, since air or other atmospheric gas heated by friction will flow through them.

The lateral, upper and lower end surfaces of the plates are bonded between adjacent plates in different ways.

The lateral surfaces (Fig. 2) are helically twisted planes in the form of spirals 13 and 14 corresponding to each other at adjacent plates so that the spiral 13 is inserted into the spiral 14 from front to back or back to front (Fig. 3). The spirals 13 and 14 have walls fitted to each other, between which there are minimal gaps of the order of a millimeter, so the connection is strong. In order to obtain a stronger connection not only between the spirals of one ring-shaped row, but also between the spirals of adjacent rows, the spirals 13 or spirals 14 continue inside the protrusion 19, respectively, in the next row to the same distance, the corresponding spirals 13 or 14 are as much shorter in the front - backward so that the protrusion can enter the spiral of the next row. The spirals of the uppermost annular row in the wall 6 do not have a protrusion 19, since the fastening of the first row of plates is different. The spirals of the lowest annular row in the composition of the wall 4 are not short from below, the lower edges of the spirals 13 and 14 reach the lower edge of the parachute dome.

Unlike lateral surfaces, the front and rear surfaces are flat. In the place of their docking there are slots 20 (Fig. 4). Slit 20 and the place of joining of pipes 15 of adjacent plates covers the protrusion of thermal insulation 27. Pipe fittings 15 of neighboring plates have double detachable fastening - simple and complex. A simple fastening is the narrowing of the wall 21 to the wall of the pipe of smaller diameter 22, which corresponds to the diameter of the wall 21 and is tightly inserted into it. But a simple connection of the pipes 15 of adjacent plates is not enough, because if there is only one, the parachute will fly into separate plates during landing loads, the pipes 15 will be pulled out of each other. Complex mounting is also required. In FIG. 5 shows a complex mount on a separate plate outside the wall; FIG. 4 - simple and complex fastening between the plates of three adjacent rows in the dome 3 of the parachute. In FIG. 5 shows 1) the movable part of the complex fastening in the form of a mace, containing a handle 24 with a thread on the lower end and a cylindrical thickening 26 with an external thread (the image is turned upside down), 2) a fixed annular thickening 25 of the wall 21 of the pipe 15 with an internal thread with a diameter, corresponding to the thread of the bulge 26 of the club, 3) a fixed annular bulge 23 of the wall 21 of the pipe 15 with a thread and a diameter corresponding to the thread at the lower end of the handle 24. At the lower end of the handle 24 there is a flat protrusion 28 for easy grip, enlarged flat lips in the hands of the manipulator (in Fig. 10 it is shown close-up) or an incision for installing an enlarged screwdriver in the hands of the manipulator. The middle part of the mace on the handle 24 is threadless and can freely slide through the hole in the bulge 23 until the hole 23 abuts the thread on the end of the handle 24, then during assembly the handle 24 starts to be screwed into the hole in the bulge 23, and at the same time this thickening 26 clubs is screwed into the thickening 25 of the wall of the overlying pipe 15 of the adjacent plate. Thus, in a complex fastening, the mace connects the thickening 23 of the underlying pipe 15 with the thickening 25 of the overlying pipe 15, so that under loads that do not cause rotation of the mace, which are observed during planting, a solid one-piece connection of pipes 15 of adjacent annular rows of plates is obtained.

The reinforcement pipes 15 of one plate are interconnected by perpendicular reinforcement rods to which they are soldered or welded, and with which they form the frame of each plate.

In places where the plates form a single plane, the holes in the thickenings of the walls 25 are made in the middle of the thickenings 25, and the walls of the holes in the thickenings 25 are parallel to the walls 21. In places where the plates form two planes inclined relative to each other, that is, at the joints of the walls 4 and 5, 5 and 6, the holes in the thickenings of the walls 25 are made at an angle with an inclination corresponding to the axis of the overlying pipe 15, then the walls of the holes in the thickenings 25 are located at an angle to the wall 21 of the reinforcing pipe 15 containing them. At the contact points of the plates, the wall 21 is at an angle Pipes reinforcement 15 bends at the ends for mounting therein the narrowing 22 of the underlying row and underlying plates themselves at their upper ends are bent, curved projections 27 and their facing inside dome surface which corresponds to the plane of the overlying plate. The connection of the plates at an angle is shown in FIG. 4, this is the topmost connection of the figure (recall that it is turned upside down).

The diameter of the parachute canopy can reach 100 m, which is necessary for landing large heavy loads.

A separate consideration requires mounting the central tube 8 to the top of the canopy of the parachute (Fig. 6). The central tube 8 consists of an axial pipe 29 made of metal or carbon fiber coated with a heat insulation 30, the same as the heat insulation 16 on the dome 3. The pipe 29 protrudes from the heat insulation 30 on top, and a thread corresponding to the internal thread on the pipe 32 at the top of the dome is cut parachute (Fig. 6).

Together, these two threads form a connection 31. The plates of the upper first ring-shaped row in the wall 6 form, when docked at the top of the parachute, a hole into which the pipe 32 is inserted. In the pipe 32 in its upper part there are radial holes 33 into which the protruding from the plates are inserted onto the wall thickness of the pipe 32 ends 34 of the pipe reinforcement of the first annular row. The diameters of the walls 21 of the ends 34 correspond to the diameters of the openings 33. The complex fastenings of the pipes 15 to the pipe 32 are not applied due to the lack of space for them, since the diameter of the hole between the upper ends of the upper first row of plates into which the pipe 32 is inserted is constantly maintained in a natural way. It cannot expand, since the upper plates and the underlying plates are motionlessly interconnected by complex joints.

The parachute canopy can be dismantled, if necessary, in the reverse order of actions on individual plates. For example, a control assembly can be made on Earth to check the collection of a parachute, then after it the parachute is disassembled back and the plates are loaded into spaceships in rockets or in a space elevator cabin.

To fasten the descent vehicles 2 to the canopy of the parachute, the reinforcement pipes 15 of the lower plates of the lateral cylindrical wall 4 are opened with internal openings outward towards the edge of the parachute. To remove excess holes, plugs are screwed into them; for this, the inner surface of the walls near the outer holes must have a thread corresponding to the thread on the legs of the plugs. Plugs have heat-insulating hats. In those holes in which there are no plugs, ears with screw holes are screwed. These ears have legs with threads corresponding to the threads in the open ends of the tubes 15. At the upper end of the descent apparatus 2, a cylindrical base 53 is installed, which contains ears with holes for bolts 54 (Fig. 9). This cylindrical base 53 is screwed into a cylindrical hole with a thread 50 in the housing 52 in front of the hatch 48 to enter the descent vehicle 2. The ears 54 correspond to the aforementioned ears on the lower edge of the parachute canopy screwed into the open ends of the tubes 15.

Two cabins with manipulators suspend the apparatus 2 under the edge of the parachute, while one cab covers the apparatus 2 with the manipulators and supports it in place, and the second cab bolts the lander 2 by the ears 54 to the ears of the lower edge of the parachute with bolts and nuts. The ears on the lower edge of the parachute and on the upper end of the devices 2, the bolts and fastening nuts have a heat-protective layer on the outside, because when landing, although the device 2 blocks the ears from the air or other atmospheric gas coming in from below, the latter can flow around the device 2 and reach the ears, warming up them. The ears 54 must be at least three so that the load does not swing during landing.

The parachute assembly begins even before the station is surrounded by balloons from oilcloths. First, the stacks of descent vehicles 2 are docked to the end compartment of station 42, which will be located in assembly space 44. Then the station is surrounded by balls of oilcloths as described above, gas is placed in the spaces between the balls with decreasing pressure from the inner to the outer sphere. The ball 43 (Fig. 7), enclosing the assembly space 44 from the outside, is covered with villi from the inside to connect the textile fastener. From the hatch 45 on the end compartment 42, parachute canopy plates are fed from the side of the station, they are captured by the hands of the manipulators 41 of the cabs 40 and transferred to the mentioned villous surface of the ball 43, stick to it so as not to fly into the assembly space 44. After that, sections are fed from the hatch 45 the central tube 8 connected to the canopy of the parachute. They are rolled up with a sleeve connection to each other and to the station building. To connect with the station body, more precisely, with the body 47 of the end compartment 42, a cylindrical extension 51 of the pipe 29 of the central tube 8 is screwed by the manipulators 41 into the cylindrical hole 50 (Fig. 8) with an internal thread in the body 47 in front of the hatch 48. The integrity of the retractable ring 49 the docking station is not broken. At the end, a pipe 32 and enlarged pliers are fed from the hatch 45 of the end compartment 42. The manipulator 41 puts the pliers in the tool box 46 and secures them there between several pairs of stumps of mushroom shape with elastic hats. One cabin 40 holds the top pipe 32 and the plates attached to it by the manipulator 41, the second cabin 40 tears in turn the plates of the first annular row of the end wall of the dome 6 from the ball 43, disconnecting the textile fastener and inserts them into the holes 33 of the tube 32, and side spirals 13 and 14 into each other. Then the second annular row is assembled, the narrowing of the tubes 22 of the second row are inserted into the open ends of the pipes 15 of the first row, and the clubs of the pipes 15 of the second row are screwed into the thickenings 25 of the walls 21 of the pipes 15 of the first row. When the first two rows are assembled, the assembly place becomes indestructible, then the tube 32 with two rows of plates is screwed onto the end of the axial tube 29 as part of the central tube 8 of the parachute dome. Then, by inserting the coils 13 and 14 into each other and the simple and complex joints described above, the remaining plates of the canopy of the parachute 3 are joined. When all the walls of the canopy 3 are assembled, plugs and ears are installed in the open holes of the tubes 15 at the edge of the parachute as described above. Then, in turn, the devices 2 are undocked from the end compartment 42, the cylindrical bases 60 with ears 61 are screwed into the manipulators 41 of one cab 40 into each of them, while the second cab 40 holds the apparatus 2 in place, then the apparatus 2 is suspended under the edge of the parachute, the cockpit 40 by the manipulators 41 holds the apparatus 2 under the edge of the parachute, and the second cabin 40 screws the bolts and nuts into the ears on the lower edge of the parachute and on the apparatus 2.

If the descent central load 1 is the station itself, then a separate spacecraft is launched to assemble the heat shield, a ship with booths 40 on arrows 39 is docked to it, this pair of ships is surrounded by a pair of balls 37 and 43 in the above-described way, then the heat shield 9 is assembled similarly to the assembly the canopy of the parachute, only its tube 8 is very short, after which a pair of spaceships dock to the compartment of the space station that opens out from their balls.

If the descent central cargo 1 is a part of the space station, then the descent compartments are located inside the assembly space between the end compartment 42 and the station (the end compartment 42 is also part of the cargo 1). Then the heat shield 9 is assembled similarly to assembling the canopy of the parachute from separate plates on the inner surface of the same ball 43 on which the parachute canopy plates were mounted, away from the canopy 3. Then the laden load 1 is undocked from the station and the heat shield 9 is connected to the tube 8 by a sleeve connection turns to cargo 1 on the back of the parachute. If the descent load is part of a space station, the assembly space 44 is increased several times compared to the option when the entire station lands, so that it becomes possible to move the heat shield and the descent ship.

Before the descent, the arm of the manipulator 41 cuts the oilcloths 43 and 37 along the perimeter of the canopy of the parachute 3 with an enlarged knife or scissors. The same actions are performed with oilcloths around the heat shield if the entire station descends. Thus, the parachute and heat shield are outside the assembly space. When landing part of the station, the descent ship, also known as cargo 1, includes side engines, the exhaust of which does not fall into the canopy of the parachute and the heat shield, and moves towards the Earth or another planet.

When landing the station, cuts are also made opposite the nozzles of the station’s engines, the exhaust gases of which should be directed away from the parachute and heat shield.

When landing, the parachute first decelerates above the dense layers of the atmosphere to a speed of the order of 2788 m / s in order to prevent its burning during landing. In descent vehicles 2, two types of nozzles 56 and 62 are made, on which motors 61 are installed (Fig. 11). Before reaching the dense atmosphere, the nozzle engines 62 are turned on. These nozzles are not inclined with a vertical discharge of combustion products along axis 63 at a speed of 64 so that there is no loss of speed due to the presence of a horizontal component. After the operation of the first engines with nozzles 62, the descent vehicles 2 are not disconnected in order to stretch the canopy of the parachute instead of slings during landing. The lander significantly loses weight after the first engines have finished working, since most of the fuel inside it is consumed. Since the nozzle 62 can melt and escape during landing due to the high temperature during descent, inside the descent apparatus behind the nozzles 62, layers of thermal insulation 65 are installed around them, which preserves the integrity of the descent apparatus and their resistance to heat. When landing, the parachute is braked in the upper atmosphere, the heat-protective layer 16 of the parachute dome evaporates as it descends, but there is a fairly comfortable temperature behind it, so the tubes 15 and reinforcement bars do not melt if they are made of metal. The lower layer of the heat shield 9 also evaporates. The thermal insulation layer 65 of the apparatus 2 evaporates (Fig. 11), inside which the identical switched-off jet engines 56 are located. When the layer 65 evaporates, the walled nozzle 56 is located behind it 2. In the walled nozzle 56, The vaporization layer 65 is low pressure air. After the evaporation of layer 65, the pressure of air or other atmospheric gas, which runs down from the bottom during landing, rises in the nozzle, high pressure sensors that turn on the ignition and fuel supply are activated, the nozzle begins to throw a jet stream in the lower part of the flight. For ignition and fuel supply it is enough to have two electrical circuits. The first circuit contains a power source, a high pressure sensor and an inductor with a magnet inside that closes the key of the second circuit. The second circuit contains a power source, a spark gap and an electric nozzle that injects the first portion of fuel into the nozzle. When the high pressure sensor is triggered in response to the pressure of the air running down from the landing, the key of the first circuit closes and the second circuit lets the first portion of fuel into the nozzle and sets it on fire.

The nozzle 56 is inclined, therefore the jet is directed not vertically downward, but at an angle of 30-50 ° to the vertical axis (see inclination of axis 57). This gives stability to the apparatus during landing, since the horizontal components 60 of the thrust force 58, for nozzles 56 of the apparatus 2 symmetrically arranged in pairs relative to the central vertical axis of the dome, are directed towards each other. On the one hand, less than two fuel is loaded inside two or three devices 2. In order for their mass to be equal to the mass of devices 2, on the other hand, a blank is loaded in these compartments to balance the dome, the payload should not be loaded, since it is difficult to remove it from a dropped parachute with a cylindrical base 53 in each device 2. When the device with a parachute sits on the surface of the planet, its jet engines under the canopy of the parachute continue to work, but their vertical component of the thrust forces 59 is not enough to lift load 1 above the surface of the planet. Then charge 10 explodes, the canopy of the parachute takes off above cargo 1 due to the vertical component of the thrust forces 59, but since less fuel is loaded on one side, the jet engines stop working on this side, the parachute under the action of the horizontal component 60 of the working engines shifts towards the idle engines and tilts on its side, on that side where the engines do not work. Thus, the canopy of the parachute falls to the side of cargo 1, without touching or breaking it.

Since the mass of fuel for braking the parachute with the load before reaching the dense layers of the atmosphere is very large, the descent vehicles are mounted first without fuel so that the arrows 39 can move them. Further, the tanks of the descent vehicles are filled with fuel as spacecraft arriving delivering fuel from the Earth.

Claims (16)

1. A method of mounting in space an initially discovered solid heat-resistant stringless parachute for multi-ton cargo launched from the planet’s orbit, including mounting a parachute whose dome consists of a flat round end wall, a truncated cone-shaped wall and a cylindrical side wall, containing holes around the center of the end wall over which there are sleeves that open nozzles on the wall in the form of a truncated cone above the lower edge of the last wall, characterized in that they carry out the installation of the parachute specified shaped with the location of the oval inlet openings of the arms around the circumference near the upper pole of the canopy of the parachute from individual plates having thermal insulation in the lower part and behind it having pipes and reinforcement rods perpendicular to each other, they begin installation by docking to the end compartment of a space station located in the orbit of the planet under the protection of its magnetic field, stacks of descent vehicles with jet engines, Next, the space station is surrounded by balls of oilcloth, between the balls, connecting them together, the cables are pulled, the spaces between the balls are filled with gas with increasing pressure from the periphery to the center, and there may be liquid inside the central ball, as a result one end of the station opens out of the balls, the second the end of the station opens into the assembly space between the second and third outside balls, and the largest part of the station is located in the central ball, while the hatches of the station open into each inter-ball space, then the drivers from the station board enter the cabs with the arms of the manipulators, close the hatches of the cabs and stations, then undock them from the end compartment of the cab with the arms of the manipulators and move them to the required distance with arrows, then they feed from the open hatch of the terminal compartment of the station the plates of the canopy of the parachute, take them with the help of the manipulators of the cabs and stick them by connecting the textile fasteners to the inner surface of the second outside of the ball enclosing the assembly space from the outside, feed the pliers or screwdrivers enlarged by the size of the manipulators from the same hatch and fix them in tool boxes attached to cabs with manipulators, they feed from the same hatch of the station sections of the central tube of the canopy of the parachute, screw them together and with the station casing with a sleeve connection, feed the apex tube from the same hatch of the station, and the arms of the manipulators of the first cabin hold it and the plates attached to it in place, the arms of the manipulators of the second the cabs tear off the plates of the first annular row from the inner surface of the outer ball enclosing the assembly space, insert the ends of the pipe fittings of the plates of the first annular row into the holes of the vertex tube, millet Wrapping the side spirals of adjacent plates into each other, then the hands of the manipulators of the second cab attach the second ring-shaped row of plates to the first row, connecting their lateral edges by pushing the side spirals into each other and connecting their front and rear edges by inserting the constrictions of the second row of reinforcement pipes into the pipes reinforcement of the first row, as well as screwing maces inside the reinforcement pipes to thicken the walls of the joined reinforcement pipes, then the cabin with the hands of the manipulators screws the vertex pipe with two annular rows of plates connected to it onto the axial tube of the central tube, then they attach like the connection of the second ring-shaped row to the first the remaining ring-shaped rows up to the plates on the lower edge of the cylindrical side wall of the dome, tearing the plates from the inner surface of the outer ball enclosing the assembly space, screw the plugs and ears into the openings at the edge of the lower edge of the pipe reinforcing jet engines undocked in turn the descent vehicles with jet engines from the end compartment, then the arms of the manipulators of the first cabin hold the descent apparatus under the lower edge of the parachute, and the arms of the manipulators of the second cabin attach a cylindrical base with ears to it, behind which they are bolted with nuts to the ears on the edge of the lower the edges of the canopy Before landing, the cab manipulators cut the oilcloths of two outer balls around the perimeter of the parachute with enlarged knives or enlarged scissors. 2. The method of mounting in space of the initially discovered solid heat-resistant stringless parachute for multi-ton cargo launched from the planet’s orbit according to claim 1, characterized in that, attaching the plates fed from the hatch of the end compartment of the plate to the inner surface of the outer ball enclosing the assembly space a little further than the parachute, construct a heat shield, which is similar in structure and method to the canopy of the parachute, but smaller than it and has no holes and sleeves, the central tube of this screen is short, and it is directed to the sides Planet landing convex part forward, undock the planted part of the station from the rest of the station inside the assembly space and at the end opposite the end of the undocked part of the station from the end with the canopy of the station, fasten the short central tube of the heat shield with a sleeve connection, after cutting the outer balls, the side engines are turned on, while the undocked part of the station moves away from the station toward the planet for landing so that the exhausts of the side engines do not fall into the parachute and heat shield. 3. The method of mounting in space the initially discovered solid heat-resistant stringless parachute for multi-ton cargo launched from the planet’s orbit according to claim 1, characterized in that for landing the entire station around a separate pair of spacecraft docked to each other, which has its own cabins with manipulator hands and moving boom booths, construct a shelter from a small number of balls, while one end of a pair of ships protrudes from the shelter and joins the same free end of the above-described space station, then a heat shield is constructed, which is similar in structure and method to the canopy of the parachute, but smaller and has no holes and sleeves, the central tube of this screen is short, and it is directed toward the planet when landing with the convex part forward, after cutting the balls around the canopy of the parachute, heat shield and side engines, the stations turn on the side engines of the station so that their emissions do not fall into the parachute and heat shield, and the station goes toward the planet for landing.

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