RU2085448C1 - Method of delivery of cargoes to space and system for realization of this method - Google Patents

Abstract

FIELD: rocketry and space engineering; space systems for delivery of payload to far-out space and to earth orbit. SUBSTANCE: start of space vertical takeoff vehicle provided with liquid-propellant rocket engine and servicing plane and their joint flight are performed simultaneously; servicing plane and vertical takeoff space vehicle are connected by means of flexible propellant-transfer device before takeoff and in course of joint and parallel flight, propellant is transferred from servicing plane to space vehicle before takeoff. Transfer of propellant to engine plant of space vehicle is started immediately after takeoff. EFFECT: enhanced reliability. 13 cl, 16 dwg

Description

 The invention relates to rocket science and astronautics, and more specifically to methods and space transport systems for delivering goods to Earth orbit and deep space, especially heavy loads.

 Known methods for delivering cargo into space include the use of single-stage rockets, multi-stage rockets with a sequential arrangement of stages, multi-stage rockets with a parallel arrangement of stages, rigidly interconnected in one way or another.

 In some cases, it is envisaged that some or all of the steps will be returned to Earth with parachute landing or landing on air or cosmodromes. Landing can be carried out horizontally using bearing planes or vertically using rocket engines.

 Aerospace systems are also known, providing for the vertical launch of aerospace vehicles.

 Reusable aerospace vehicles (MVKA) such as the Space Shuttle and Energy-Buran are known that contain a launch vehicle (LV) and an aerospace aircraft (VKS).

Reusable vertical launch vehicles have the following disadvantages:
the failure to return some parts of the MVKA to the Earth, which prevents their reuse and increases the cost of operating reusable systems;
the need to alienate large areas of the earth's surface to ensure the safe fall of non-returnable parts of the MVKA (for example, the first steps), which is especially important for Russia, where launches take place in the continental part of the country, and not from a promontory protruding into the ocean;
the large size and weight of MVKA at the start, which leads to the creation of the whole infrastructure of the spaceport and special enterprises located near the spaceport for the assembly of MVKA and their transportation to the launch pad;
Significant economic and temporary risk associated with the possible destruction of costly and difficult to recover launch sites in the event of an accident.

 During the development of astronautics, alternative proposals were made that outline the ways for the further development of methods and systems for the delivery of goods into space.

 K. E. Tsiolkovsky came to the conclusion that, using only the idea of composite (multi-stage) rockets, it is impossible to ensure the fulfillment of the tasks of launching rocket devices into deep space. He showed that for this it is necessary to change the approach to creating rocket systems, namely to launch from the earth's surface a group of missiles that, after using each missile half of the initial fuel supply, must somehow pairwise connect with each other, and one rocket from each pair must quickly transfer your remaining fuel to the neighboring one, replenishing its fuel supply to the initial amount, and then disconnect from it. Further, only half of the initial number of rockets continues to move into space, but these rockets are completely filled with fuel. After a while, the cycle will repeat. At the end of this process, one completely rocket-filled rocket remains. The disadvantage of this idea is the need to pump a large amount of fuel in a very short time, which requires the installation of powerful and heavy means of pumping fuel.

K.E. Tsiolkovsky formulates his idea this way: “But we will now point out other methods of obtaining much higher rocket speeds. They consist in hitting several identical and modest (in speed) rockets. They, in addition to the latter, consume only half of the explosive stock taken substances, and they supply each other with the other half. Only the last missile acquires the highest speed. The remaining shells, which have been freed up from the reserve, descend to Earth "(KE Tsiolkovsky. Fundamentals of the construction of gas machines, Ch. X Naibo lower rocket speed, in the book: KE Tsiolkovsky, Proceedings in Cosmonautics, Investigation of World Space by Jet Devices Edited by MK Tikhonravov, M. Mechanical Engineering, 1967, p. 363.)
ME AND. Perelman supplemented the idea of K.E. Tsiolkovsky, proposing 512 rockets to constructively connect into one unit and transfer fuel from one rocket to another after spending half of it (Perelman Y.I. K. E. Tsiolkovsky. M. ONTI. Main editorship of popular and youth literature, 1937, pp. . 148-1530.

 M.K. Tikhonravov in a report of the Academy of Artillery Sciences in 1948 I. Yatsunsky On the activities of M.K. Tikhonravova from 1947 to 1953 to justify the possibility of creating composite missiles. On Sat From the history of aviation and astronautics, Akamedia of Sciences of the USSR. Soviet national association of historians of science and technology. Vol. 42, M. 1980, p. 31-38. Belyakov A. Who conceived the first artificial Earth satellite. Journal of Inventor and Rationalizer, M. 1990, N 11, p. 32-39) proposed an improved version of combining missiles "missile package" with the simultaneous operation of engines of all stages, starting from the start. The engines of all missiles pump fuel out of a single rocket and only after it is empty, they discard it and start pumping fuel out of the next rocket and so on to one rocket. Different transport systems can be assembled using the same type of missiles, recruited in the right amount in a package. At M.K. Tikhonravova is talking about rigidly interconnected missiles and the question of the constructive forms of combining missiles has not been worked out.

 However, the "package of missiles" M.K. Tikhonravova has several disadvantages. Such a package can be very cumbersome on the launch pad, which places high demands on launch facilities.

Similar ideas about combining several missiles into a package have been developed in a number of patents:
US patent N 3369771, NKI 244-162, from 02.20.1968, GD Walley, "Spacecraft";
US patent N 4834324, MKI B 64 G 1/14, NKI 244-160, dated 30.0.1989, DR Criswell "Space transport system, forming many configurations, suitable for reuse";
US patent N 5141181, MKI B 64 G 1/40, NKI 244-172, from 08.25.1991, BP Leonard "A spacecraft with pipelines for the transfer of fuel between stages".

 All of these patents describe rocket associations in which fuel is transferred from one rocket to another, with the rockets being rigidly interconnected before launch.

 In the report "Refueling in space and the problem of multistage" at the Fourth Astronautical Congress in Zurich in 1953, G.A. Crocco proposed his own ways of delivering cargo into space (G. A. Crocco. Levitallement dans et le Probleme des polistades. The Fourth Astronautical Congress "Space-Flight Problems" Published by the Swiss Astronautical and Aeronautical Federation, pp. 152-160). One of the proposed G.A. Crocco’s methods include launching separate, non-interconnected, rigid rockets of two types of missiles (according to the terminology adopted in this application of a vertical take-off spacecraft, CAVV) with a payload and one or more missiles carrying fuel tanks (in terminology, accepted in this application refueling with a vertical take-off, ZVV). At a given altitude, the CAVV with the payload for some time flies in parallel next to the air supply tank carrying the fuel supply, and the fuel is emitted free of charge (in a directed stream) from the air storage tanks into the hole in the air storage device and, thus, the existing fuel consumption in the CAVV is replenished (KAVV and ZVV engines are switched off during fuel transfer). Like Tsiolkovsky, Krocco's individual rockets during the launch are not rigidly combined into a single structure, they fly freely, separately from each other. This allows you to significantly simplify all devices on the launch pad, reduces the total weight of the missiles (compared to a rigidly coupled design of several missiles), as it avoids problems with the strength of connecting individual missiles into a single aircraft.

 But the drawback of the system proposed by Crocco is the need to perform search, approximation, and alignment of the CAVE and ZVV in the active part of the trajectory, which will require considerable time.

 Another disadvantage of such a system is the shutdown of the engines during pumping, which is associated with the loss of part of the already gained speed under the action of the Earth's gravity. When pumping fuel with a free directed jet, turning off the engines during the pumping time is fundamentally necessary to avoid an explosion.

 The combined effect of these factors significantly reduces the time allocated to pumping fuel. The need to reduce this time makes it necessary to pump fuel with a large volume of pumped fuel per unit time. This requires the use of powerful and heavy pumps for pumping fuel.

 In addition, the proposal to transfer fuel from one rocket to another without special pipelines seems unrealizable in practice. It will lead to the loss of a significant part of the fuel, which is unacceptable from both an economic and environmental point of view. For example, when using liquid hydrogen and oxygen, they will evaporate over the entire length of the jet.

 Apparently, it is impossible to implement simultaneous refueling with two fuel components in the system under consideration, because it leads to the inevitable contact of the two fuel components, which creates an atmosphere fraught with explosion.

 The method of delivery of goods into space and the system for its implementation, proposed by Crocco, are the closest analogue (prototype) of the invention.

In the invention, the following technical tasks are set and solved:
ensuring the start of fuel pumping almost immediately after the separation of CAVV from the Earth due to the docking of tanks CAVV and ZVV on Earth and the exclusion of preparatory operations for pumping during the flight,
the exclusion of the stages of search and rapprochement of KAVV and ZVV, leading to a decrease in the time allocated to pumping fuel.

reducing the power and weight of the device for pumping fuel due to the longer time allocated to pumping, and accordingly, increasing the weight of the cargo displayed in space,
reduction of fuel consumption in the system due to the exclusion of an idle flight of air-polluted air prior to its connection with the air-to-air storage unit for pumping fuel and, consequently, a decrease in the height of the air-blasting device,
ensuring greater safety during pumping, especially of two-component fuel, and compliance with stricter tolerances for environmental pollution during pumping. The proposed invention virtually eliminates the loss of part of the fuel and its release into the surrounding space during pumping.

 The main idea of the invention is to create a method and system for the delivery of goods into space, using a group of co-flying rockets that are exchanged in flight, which are flexibly associated with take-off.

The essential features of the method of delivering cargo into space are that
place the fuel necessary for delivering the cargo into space in the tanks of the vertical take-off spacecraft and at least one vertical take-off tanker,
provide for a part of the trajectory of the vertical take-off spacecraft a simultaneous parallel parallel flight of the vertical take-off spacecraft and at least one tanker with vertical take-off,
during the joint flight of the vertical take-off spacecraft and at least one tanker with vertical take-off, transmit fuel from at least one tanker with vertical take-off to the vertical take-off spacecraft (distinguishing features follow),
before take-off of a vertical take-off spacecraft and at least one tanker with vertical take-off, connect a vertical take-off spacecraft and at least one tanker with vertical take-off using at least one flexible means of fuel transfer,
carry out joint take-off of a vertical take-off spacecraft and at least one refueling tank with vertical take-off with at least one flexible means for transferring fuel connected between them,
carry out the specified simultaneous synchronous parallel flight of the vertical take-off spacecraft and at least one vertical take-off tanker with at least one flexible fuel transfer means connected between them.

 This option involves the use of one KAVV and one ZVV and allows you to solve all of the listed technical problems.

 In another embodiment of the method of delivering goods into space, the amount of fuel consumed in flight in the vertical take-off spacecraft per unit time is continuously measured, the data of these measurements are transferred from the vertical take-off spacecraft to the control system of the vertical take-off tanker and fed continuously from the vertical take-off tanker to vertical take-off spacecraft the amount of fuel per unit time equal to the amount of fuel spent per unit time in the spacecraft ver ikalnogo takeoff during the flight.

 This option provides for variable-thrust operation of the KAVV mid-flight engine, if the need arises.

In another embodiment of the method for delivering goods into space, the necessary fuel is delivered for delivery of cargo into space in the tanks of the vertical take-off spacecraft and two, first and second, vertical take-off tankers,
provide, on a part of the trajectory of the vertical take-off spacecraft, a joint synchronous parallel flight of the vertical take-off spacecraft and two vertical take-off tankers,
during the joint flight of the vertical take-off spacecraft and two tankers with vertical take-off, the fuel is transferred from the first tanker with vertical take-off to the spacecraft of vertical take-off, and from the second tanker with vertical take-off to the first tanker with vertical take-off, (distinguishing features follow),
Before takeoff, the vertical take-off spacecraft and two vertical take-off tankers connect the vertical take-off spacecraft and to the first vertical take-off tanker using the first flexible means of fuel transfer, and the first vertical take-off tanker with the second vertical take-off tanker using the second flexible transmission means fuel
carry out a joint take-off of a vertical take-off spacecraft and two vertical take-off tankers with two flexible means of fuel transfer connected between them, and then carry out the specified parallel group parallel flight of a vertical take-off space vehicle and two vertical take-off tankers with two flexible means of fuel transfer connected between them .

This option provides for the use of two tankers, which allows:
with the same refueling tank sizes as in the case of a single tanker, increase the lift height and speed of the KAWV, which has full fuel tanks for further flight; or
reduce the size of the tanker compared to the method with one tanker while ensuring the same lifting height KAVV with full tanks, as in the compared method.

In another embodiment of the method of delivery of goods into space
place the fuel necessary for delivering the cargo into space in the tanks of the vertical take-off spacecraft and the vertical take-off tanker,
provide, on a part of the trajectory of the vertical take-off spacecraft, a joint synchronous parallel flight of the vertical take-off spacecraft and the vertical take-off tanker,
during the joint flight of the vertical take-off spacecraft and the vertical take-off tanker, transmit fuel from the vertical take-off tanker to the vertical take-off spacecraft (distinguishing features follow),
before take-off of a vertical take-off spacecraft and a vertical take-off tanker, a vertical take-off spacecraft and a vertical take-off tanker are connected using a connecting cable,
before take-off, place a flexible means of fuel transfer in a tanker with vertical take-off,
carry out joint take-off of a vertical take-off spacecraft and a vertical take-off tanker with a connecting cable connected between them,
pulling into the vertical take-off spacecraft a connecting cable with a flexible fuel transfer means connected thereto so that one end of the flexible fuel transfer means remains connected to the vertical take-off refueling device, and the other end of the flexible fuel transfer means is connected to the vertical take-off spacecraft,
carry out the specified joint synchronous parallel flight of the vertical take-off spacecraft and the vertical take-off refueling device, the fuel transfer being carried out through a flexible means of fuel transfer during the flight.

 In this embodiment, it is intended to be used for a connecting cable for connecting the CABB and the ZVV before take-off. A GSPT is attached to the connecting cable, which allows take-off with a GSPT sheltered in the air-to-air gun housing, and then quickly connect the CAVV and the air gun using the GSPT.

In another embodiment of the method of delivery of goods into space
place the fuel necessary for delivering the cargo into space in the tanks of the vertical take-off spacecraft and the vertical take-off tanker,
provide for the part of the trajectory of the vertical take-off spacecraft a joint flight of the vertical take-off spacecraft and the tanker with vertical take-off,
transmit during the joint flight of the vertical take-off spacecraft and the vertical take-off tanker fuel from the vertical take-off tanker to the vertical take-off spacecraft, (the distinguishing features follow),
before take-off of a vertical take-off spacecraft and a vertical take-off tanker, a vertical take-off spacecraft and a vertical take-off tanker are connected using a connecting cable,
place GSPT in KAVV,
carry out parallel simultaneous take-off of a vertical take-off spacecraft and a vertical take-off tanker with a connecting cable connected between them,
draw a connecting cable with a flexible fuel transfer means connected thereto so that one end of the GSPT remains connected to the CABB and the other end of the GSPT is connected to the ZVV,
carry out the specified joint flight of a vertical take-off spacecraft and a vertical take-off refueling vehicle, the fuel being transferred via the GSPT during the flight.

 This option provides for the use of a connecting cable to which a GSPT is attached, which allows take-off from a GSPT sheltered in the KAVV housing, and then quickly connect the KAVV and the SVV using the GSPT.

 The following describes the essential features of the system for implementing the method of delivery of goods into space.

In the first embodiment, the system for delivering goods into space contains:
a vertical take-off spacecraft with a propulsion jet engine, fuel tanks and cargo, and
a vertical take-off tanker with a marching engine, at least one fuel tank for vertical take-off space vehicle fuel and a fuel transfer device (UPT) between a vertical take-off tanker and a vertical take-off space vehicle (distinguishing features follow),
at least one flexible fuel transfer means that is included between the fuel tanks of the vertical take-off spacecraft and the vertical take-off tanker, said means being connected before take-off, during take-off and during a simultaneous simultaneous parallel flight with the possibility of disconnection in flight.

 This option involves the use of one KAVV and one ZVV and allows you to solve all of the listed technical problems.

In another embodiment, the system for the delivery of goods into space contains:
a vertical take-off spacecraft with a propulsion jet engine, fuel tanks and cargo, and
at least two vertical take-off tankers with marching engines, fuel tanks for the vertical take-off spacecraft fuel and fuel transfer devices between the vertical take-off tanker and the vertical take-off space vehicle (distinguishing features follow),
at least two flexible means of transferring fuel that are included between the fuel tanks of the vertical take-off spacecraft and at least two refueling tanks with vertical take-off, said means being connected before take-off, during take-off and during a joint synchronous parallel flight with the possibility of disconnection in flight .

This version of the system provides for the use of two tankers, which allows:
with the same refueling tank sizes as in the case of a single tanker, increase the lift height and speed of the KAWV, which has full fuel tanks for further flight; or
reduce the size of the tanker compared to the method with one tanker while ensuring the same lifting height KAVV with full tanks, as in the compared method;
increase the fuel transfer rate through the use of two UPT and two GSPT.

In another embodiment, the system for the delivery of goods into space contains:
vertical take-off spacecraft with marching jet engine, fuel tanks and cargo,
a first vertical take-off tanker with a marching engine, at least one fuel tank for vertical take-off space vehicle fuel and a fuel transfer device between a first vertical take-off tanker and a vertical take-off space vehicle,
a second vertical take-off tanker with a marching engine, at least one fuel tank for vertical take-off spacecraft fuel and a first vertical take-off tanker and a fuel transfer device between the second and first vertical take-off tankers (distinguishing features follow)
first and second flexible means of fuel transfer,
wherein the first flexible fuel transfer means is included between the fuel tanks of the vertical take-off spacecraft and the first vertical take-off tanker,
a second flexible fuel transfer means is included between the fuel tanks of the first and second vertical take-off tankers,
and said flexible means for transferring fuel are connected prior to take-off, during take-off and during a joint synchronous parallel flight with the possibility of disconnection in flight.

This version of the system provides for the use of two tankers, which allows:
with the same refueling tank sizes as in the case of a single tanker, increase the lift height and speed of the KAWV, which has full fuel tanks for further flight; or
reduce the size of the tanker compared to the method with one tanker while ensuring the same lifting height KAVV with full tanks, as in the compared method;
to gain a gain in the flight energy by switching off the second tanker at a lower altitude.

In another embodiment, the system for the delivery of goods into space contains:
vertical take-off spacecraft with cargo,
launch complex with launch pad for the vertical take-off spacecraft,
vertical take-off tanker with fuel tank for vertical take-off spacecraft fuel,
a launch complex with a launch pad for a vertical take-off tanker (distinguishing features follow),
at least one flexible fuel transfer means and
means for separating launch complexes to ensure safety in case of accidents,
moreover, the vertical take-off tanker and the vertical take-off spacecraft are interconnected before the take-off, during and during the joint synchronous parallel flight, using the flexible fuel transfer means,
means for separating launch complexes is located between the launch pad of the vertical take-off spacecraft and the launch pad of the vertical take-off tanker,
moreover, in said separation means there is a groove extending from the upper base of the separation means towards the Earth to the level of passage of said flexible means and having a width not less than the maximum transverse dimension of said flexible fuel transfer means, which is located in said groove before take-off and during take-off.

 This version of the system provides for the preservation of parts of the system in an emergency.

In another embodiment, the system for the delivery of goods into space contains:
means for fixing said groove before takeoff and opening it immediately before takeoff.

 This version of the system provides for the improvement of the previous version by increasing the degree of isolation of the complexes before take-off.

In another embodiment, the system for the delivery of goods into space contains:
a vertical take-off spacecraft with a propulsion jet engine, fuel tanks and cargo, and
a vertical take-off tanker with a marching engine, at least one fuel tank for the vertical take-off spacecraft fuel and a fuel transfer device between a vertical take-off tanker and a vertical take-off space vehicle (distinguishing features follow),
a flexible means for transmitting fuel, a connecting cable, a device for receiving a connecting cable, a storage device for a flexible means for transmitting fuel and a connecting cable,
the connecting cable is connected between the vertical take-off spacecraft and the tanker with vertical take-off before take-off, during take-off and flight, and connected to the receiving cable receiving device and to the storage device of the flexible fuel transmission means and connecting cable, and the flexible fuel transmission means is connected to the connecting cable with the ability to move a flexible means of transferring fuel between the spacecraft of vertical take-off and the tanker with vertical take-off along with a connecting pipe Som.

 In this version of the system, a quick connection between CAVV and ZVV with the help of GSPT is provided immediately after take-off.

 In another embodiment of the space delivery system, a storage device for a flexible means for transmitting fuel and a connecting cable is located in a vertical take-off tanker, and a connecting cable receiving device is located in a vertical take-off spacecraft.

 In this version of the system, a quick connection between KAVV and ZVV with the help of the GSPT immediately after take-off is also provided, moreover, a flexible means of transferring fuel and a connecting cable are stored before the flight in the ZVV.

 In another embodiment of the system for delivering goods into space, a storage device for a flexible means for transmitting fuel and a connecting cable is located in the spacecraft of vertical take-off, and the device for receiving the connecting cable is located in the tanker with vertical take-off.

 In this version of the system, a quick connection between KAVV and ZVV using GSPT immediately after take-off is also provided, moreover, a flexible means for transferring fuel and a connecting cable are stored before the flight to KAVV.

In FIG. 1 and 2 invented a system for the delivery of goods into space (on two sheets); in FIG. 3 system for the delivery of goods into space at launch, in flight and after disconnecting the GSPT; in FIG. 4 section of the nozzles of the mid-flight engine of the air-blast engine perpendicular to its longitudinal axis; in FIG. 5 cyclogram of the operation of the mid-flight engine of the air-blast engine consisting of several component engines in FIG. 6-8
a system for the delivery of goods into space, consisting of KAVV and two ZVV connected to KAVV (on three sheets); in FIG. 9-11 a system for the delivery of goods into space, consisting of KAVV and two ZVV connected in series (on three sheets); in FIG. 12 system for the delivery of goods into space with launch complexes KAVV and ZVV (a means of separating launch complexes is shown in section); in FIG. 13 system for the delivery of goods into space (a top view of the KAVV and ZVV, located at the start); in FIG. 14 means for separating launch complexes (side view, cross section of the GSPT); in FIG. 15 means for separating launch complexes with means for closing the groove in the separation means for launch complexes (side view, cross section of the GSPT); in FIG. 10 fragment of a system for delivering goods into space using a connecting cable.

 The following notation is used in the figures: 1 CABB; 2 marching rocket engine KAVV; 3 tanks KAVV for the first component of fuel; 4 KAVV tank for the second fuel component; 5 cargo; 6 fuel-pumping unit KAVV; 7 - pipelines for supplying fuel to the main engine KAVV; 8 ZVV; 9 - mid-flight engine (MD) ZVV; 10 tank ZVV for the first component of the fuel; 11 - tank ZVV for the second component of the fuel; 12 fuel and pumping unit MD ZVV; 13 pipelines for supplying fuel to MD ZVV; 14 UPT; 15 pipelines for supplying fuel from the fuel tanks of the ZVV to the fuel tanks of the KAVV; 16 GSPT; 17 - steering engines; 18 fuel connectors; 19 fuel valves; 20 is a cross section of nozzles MD ZVV perpendicular to its longitudinal axis 21 longitudinal axis MD ZVV; 22 the first pair of component engines MD ZVV; 23 second pair of constituent engines MD ZVV; 24 third pair of component engines MD ZVV; 25 fourth pair of component engines MD ZVV; 26 thrust of a pair of constituent engines 22; 27 thrust of a pair of component engines 23; 28 - thrust of a pair of constituent engines 24; 29 thrust of a pair of component engines 25; 30 first ZVV; 31 second ZVV; 32 first GSPT; 33 second GSPT; 34 - launch complex KAVV; 35 starting table KAVV; 36 communication line KAVV; 37 - start-up complex ZVV; 38 start-up table of air-explosives; 39 central control center (CPU); 40 line of communication ZVV; 41 separation means for security; 42 groove in the separation means; 43 means for closing the groove; 44 connecting cable; 45 connection cable receiving device; 46 storage device GSPT and connecting cable; 47 locking device GSPT; 48 receiving device GSPT.

 The method according to this invention is as follows. In FIG. 1 shows a system for the delivery of goods into space containing CAVV 1.

 By CAVV in the application is meant an aircraft having a marching liquid-propellant engine 2, providing lift, allowing the CAVV to carry out vertical take-off, climb and speed in flight. KAVV also has a tank 3 for the first fuel component and a tank 4 for the second fuel component. KAVV carries cargo 5 into space. KAVV has a fuel-pumping unit 6 and pipelines 7 for supplying fuel to the main engine 2.

 KAVV 1 carries cargo 5 into space, and the lower the cost per unit weight of the cargo and the more the cargo itself, the more effective, in the general case, is the method and system for delivering cargo into space. A cargo means not only cargo delivered from Earth to space, but also a device for capturing and placing cargo removed from orbit on the CAVV.

 CAVV may have wings for the possibility of flight in the atmosphere, for example, at the stage of return to Earth. CAVV after take-off gradually switches to flight along a trajectory located at a given angle to the Earth’s surface, goes beyond the atmosphere into outer space, fulfills its purpose, for example, the removal of a cargo (communication satellite, etc.) or some other operations in space . Then, the landing and horizontal landing of the KAVV on the Earth are carried out using the aerodynamic properties of the wings of the KAVV. Vertical descent can also be used.

 By ZVV 8, the application refers to an aircraft carrying fuel for refueling KAVV 1, which has a marching jet engine 9 that provides lift, allowing the ZVV 8 to take off, gain altitude and speed in flight. ZVV has a tank 10 for the first fuel component and a tank 11 for the second fuel component. ZVV has a fuel-nasal assembly 12 and pipelines 13 for supplying fuel to the main engine 9. ZVV 8, like KAVV 1, may have wings for flight in the atmosphere. ZVV 8 takes off and flight simultaneously and parallel with KAVV 1 along the trajectory, starting from the launch complex to a certain height, and then the descent and horizontal (or vertical) landing of ZVV 8 to the Earth are carried out.

 In preferred embodiments of the proposed method and system for the delivery of goods into space, the simultaneous joint take-off of CAVV 1. KAAV 1 and ZVV 8 with fully filled tanks is used. Immediately after the take-off of the KAWV 1, fuel from the STZV 8, which takes off together with the KAVV 1 and connected to it by a flexible means of transferring fuel 16, begins to flow into it using the fuel transfer device 14 through pipelines 15. For maneuvering in flight, the KAVV 1 and the STZV 8 have steering engines 17. GSPT 16 is connected to the pipelines KAVV 1 and ZVV 8 using the fuel connectors 18. In the pipelines are installed fuel valves 19 to ensure the overlap of the pipelines.

The proposed method for the delivery of goods into space involves the following operations:
1. Place cargo 5 on KAVV 1.

 2. Place the fuel necessary for the delivery of cargo 5 into space in tanks 3 and 4 of the CAVV 1 and 10 and 11 of the airborne explosives 8. In this case, it is possible to use not one but several air-pollutants. The fuel for engines 2 and 9 KAVV 1 and ZVV 8 may be the same, but may be different. In the latter case, ZVV 8 has a separate tank (or tanks) for fuel KAVV 1.

 3. Before takeoff, the KAVV 1 and the ZVV 8 are connected using a flexible means of transferring fuel 16, for example, a fuel hose (Fig. 3). It is possible to use not one, but several GSPT, or GSPT with several separate channels for fuel. The length of the hose can be, for example, 15-20 m. Since the connection of the GSPT 16 is carried out on Earth, and the time spent on this connection is not strictly limited, the required quality of the connection is ensured (from the point of view of fuel conservation and environmental requirements).

 4. Carry out simultaneous take-off of KAVV 1 and ZVV 8 with a flexible means for transferring fuel connected between them 16. The simultaneous and synchronous take-off of KAVV 1 and ZVV 8 ensures the integrity of the GSPT 16 connected between them, the length of which must be not less than the distance between the places of connecting the GSPT to KAVV 1 and ZVV 8.

 5. Provide on the part of the trajectory KAVV 1 joint synchronous parallel flight KAVV 1 and ZVV 8.

 6. During the joint flight of KAVV 1 and ZVV 8, fuel is transferred from the ZVV 8 to the KVV 1. The fuel from the ZVV 8 enters the tanks 3 and 4 of the KVV 1. At the same time, the amount of fuel burned in the engine 2 of the KVV 1 is equal to that transferred from the ZVV 8, and tank 3 and 4 KAVV 1 remain full until the end of the joint flight.

 7. Disconnect the flexible means of transferring fuel 16 after the end of the transfer from STZ 8 to KAVV 1. Disconnecting the GSPT 16 contains a number of operations necessary to prevent part of the pumped fuel from entering the space. Such operations include, for example, purging GSPT 16, if the fuel is toxic, with inert gases, shutting off valves providing sealing of GSPT 16, and pipelines KAVV 1 and ZVV 8. Disconnect GSPT 16, in most cases, from KAVV 1, after which GSPT 16 climbs in STZ 8 and returns to Earth with the latter. But options are possible, for example, disconnecting the GSPT 16 from both KAVV 1 and ZVV 8.

 8. The joint flight of KAVV 1 and ZVV 8, in which the transfer of fuel has ended, is terminated. After this, the SVV 8 returns to Earth, and the KAVV 1 continues the flight, starting to spend fuel on its own tanks full by the time the joint flight with the SVV 8 is completed.

In a preferred embodiment of the method for delivering cargo into space, KAVV 1 performs a flight with constant acceleration, since the mass of KAVV 1 does not change during joint flight, and it is desirable to maintain maximum thrust of the main engine 2. ZVV 8 should fly at the same speed and with the same acceleration as KAVV 1. But the mass of ZVV 8 is rapidly reduced due to combustion of fuel in KAVV 1 and ZVV 8. Therefore, the thrust of the mid-flight engine 9 of ZVV 8 should be constantly reduced. It is clear that the main engine 9 ZVV 8 should allow for deep thrust adjustment. To do this, MD 9 ZVV 8 may, for example, contain several component engines. In FIG. 4 shows a cross section of nozzles 20 MD 9 ZVV 8, perpendicular to the longitudinal axis 21 of MD 9 ZVV 8. Component motors (22, 23, 24 and 25) are preferably pairs symmetrical about the longitudinal axis 21 of MD 9 ZVV, having different thrusts P ₁ , P ₂ , P ₃ , P ₄ , (26, 27, 28, 29, Fig. 5). In FIG. _Figure 5 shows the sequence _{diagram of} the thrusts of the component engines, and P _1max , P _2max , P _3max and P _4max indicate the maximum thrusts of the first, second, etc. pairs of component motors, and through P _1min , P _2min , P _3min and P _4min the minimum thrusts of component pairs of engines are indicated. When taking off, turn on all the component engines for maximum thrust. Then, the thrust of P ₄ is reduced to P _{4min in} proportion to the decrease in the mass of ZVV 8. Then, the thrust of P _{3 is} reduced in the same way to P _3k = P _3max -P _4min . After that, the third pair thrust is simultaneously switched off abruptly to P _3max . This process is repeated until only the first pair of component engines remains switched on, and its thrust is reduced to P _1min . Thus, the thrust adjustment limits of MD 9 are from P _1max + P _2max + P _3max + P _4max to P _1min .

 Other algorithms for the operation of MD 9 with component engines are also possible. For example, during take-off in a mid-flight engine, 9 air-blast engines 8 include N component engines (SD) so that the traction force of at least one of the SDs is greater than its minimum traction force, while in flight they gradually reduce the traction force of at least one SD, while the total decrease in the magnitude of the traction effort of the LED does not become equal to the magnitude of the traction force of any one or more of the included LEDs, which or which instantly turn off, and simultaneously with the shutdown of the indicated one or more LEDs, the total value of the traction the strength of the remaining unconnected LEDs is increased to a value equal to the total traction force of the marching engine at the time before the indicated one or more LEDs are turned off, the indicated sequence of operations is repeated M times until the sum of the ranges of smooth changes in the traction forces of the disconnected (N + 1-M ) SD will not become less than the magnitude of the pulling force of any one of the SDs.

 In this variant of the method, alternating smooth and stepwise adjustment of the traction of the LEDs forming the mid-flight engine 9 of the HVS 8 is provided. At the moment of disconnecting one of the LEDs, the thrust of the other LEDs is regulated so that the total thrust of the sustainer engine remains unchanged.

 In some cases, the method of delivering goods into space also provides for the use of a larger number of refueling agents, for example, two, and, accordingly, a larger number of UPT 14 and GSPT 16. At the same time, each of the ZVV 8 is connected to KAVV 1 using the corresponding one or more GSPT 16. ZVV 8 can be the same and carry the same amount of fuel.

 However, it is possible to use different types of air pollutants (Fig. 6-8). For example, the first ZVV 30 may carry one fuel component, and the second ZVV 31 another. The first ZVV 30 is connected to KAVV 1 using the first GSPT 32, and the second ZVV 31 is connected to KAVV 1 using the second GSPT 33. Moreover, the sizes of the ZVV 30 and 31 can be different. Such an option is also possible when one of the air pollutants carries two fuel components, and the second one. In this case, the size of the air pollutants can be the same, and the GSPT 32 and 33 are of different types. Detachment of the ZVV 30 and 31 from the KAVV 1 can be carried out both simultaneously and in turn. Otherwise, this method does not differ from the above option.

 The transfer of fuel from the ZVV to KAVV can be carried out from the moment of take-off. This reduces energy costs for the "idle" rise in the air pollutants. Indeed, the earlier the refueling of the CAVB from the GWS begins, the lower the height of the GWS will rise along the path parallel to the CAVW until the end of the refueling (for a given capacity of the transfer system). On the other hand, the start of pumping at the time of take-off allows, due to a certain increase in the time of refueling KAVV, to reduce the capacity of the pumping system (and, therefore, its weight) and to reduce the cross-section of the GSPT.

 Fuel can be transferred from the air-to-air storage unit to the air-to-air storage unit during the entire joint parallel flight of the air-to-air storage device to the air-to-air storage unit from the moment of take-off to the transfer of the entire specified amount of fuel, and then disconnect the GSPT. Continuity of fuel supply also reduces energy costs for the "idle" rise of air pollutants.

 It is possible to maintain a constant thrust of the main engine KAVV and to continuously transfer fuel from the STZ to KAVV, the amount of which per unit time is equal to the amount of fuel consumed in the KAVV per unit time.

 A variant of the method of delivery of goods into space (Fig. 1 and 2), in which the thrust of the main engine KAVV 1 is not constant. Then the amount of fuel consumed in flight in KAVV 1 per unit of time is continuously measured, the data of these measurements are transferred from KAVV 1 to the control system of ZVV 8 and continuously supplied from ZVV 8 to KAVV 1 is the amount of fuel per unit time equal to the amount of fuel consumed per unit time in KAVV 1 during the flight. Fuel tanks 3 and 4 KAVV 1 remain full until the end of the transfer of fuel.

You can set the thrust P _star marching engine 9 ZVV 8 in accordance with the ratio
P _sv m ₂ • P _cav / m ₁ ,
Where
P _kavv thrust of the marching engine 2 KAVV 16
m ₁ mass KAVV 1 with full tanks 3 and 4,
m ₂ mass of ZVV 8 before fuel transfer.

Then, after the start of the fuel transfer, it is possible to continuously decrease the thrust P of the _mid-flight engine 9 of the air-tight air blower 8 in direct proportion to the decrease in the mass of fuel in the tanks 10 and 11 of the air-blower 8.

 In another embodiment of the method for delivering goods into space (Fig. 9-11), KAW 1 and two, the first and second, HEL 30 and 31, connected in series, that is, the first HMS 30 are connected to the HAC 1, and the second HAM 31 to the first ZVV 30. It is preferable that the first ZVV 30 transferred fuel to KAVV 1 from the moment of take-off. At the same time, the second ZVV 31 transfers the fuel to the first ZVV 30. The amount of fuel transferred to KAVV 1 should compensate for the fuel consumption in it. The amount of fuel transferred to the first ZVV 30 should compensate for the fuel consumption in it, and the fuel consumption in the first ZVV 30 is the sum of the fuel consumption in KAVV 1 and directly in the very first ZVV 30. Thus, in the considered mode, the amount transferred from the second ZVV 31 more fuel than the first. When the second ZVV 31 finishes the transfer of fuel and shuts off, KAVV 1 and the first ZVV 30 have full tanks and continue flying, as is the case with one ZVV 8. The number of “connected” ZVV can be more than two.

 In another mode, the amount of fuel transferred along the air-pollutant chain is constant and equal to the amount of fuel consumed in the air-blast tank 1. For simplicity, we assume that all air-pollutants are the same. At the same time, the last ZVV (the farthest from KAVV 1) spends fuel on its engine and on transmission to the GSPT, and any of the other ZVV spends fuel only on its engine. When you disconnect the farthest ZVV all the other ZVV have an equal amount of fuel remaining in the tanks. From this moment, the “penultimate” ZVV becomes “the farthest” and the process is repeated until all the ZVV are disconnected in sequence. At the moment when KAVV 1 is left alone, it has completely filled tanks.

 A mixed combination of “serial” and “parallel” connection of the air-pollutant to KAVV 1 is possible. For example, to KAVV 1 two or more sequential chains of SVB can be connected symmetrically. Such a connection will provide a symmetrical mutually balancing effect of fuel flows on KAVV 1.

 In another embodiment of the method for delivering goods into space (Fig. 16) before take-off, KAVV 1 and ZVV 8 are connected using a connecting cable 44 (ST), and not using GSPT 16, which is located in KAVV 1, connected to the fuel tank in KAVV 1 and attached to CT 44. Take-off of KAVV 1 and ZVV 8 is carried out with CT 44 connected between them. After take-off, they draw CT 44 into ZVV 8, while GSPT 16 attached to ST 44 is connected to the tank pipeline in ZVV 8. After the transfer is completed fuel from ZVV 8 in KAVV 1 disconnect GSPT 16 from ZVV 8 and using CT 44 is pulled into KAVV 1.

 In another embodiment of the method for delivering goods into space, in contrast to the previous version, GSPT 16 is located in the ZVV 8 before take-off and after take-off using CT 44 is connected to the fuel tank in the KAVV 1.

 Unlike the options described above, all fuel can be used, it is necessary to deliver the cargo into space, place it in one or more air-pollutants, and practically do not load fuel in the air-gas storage tanks. In this case, the joint flight of the air-to-air explosives and the air-to-air missiles is carried out right up to the launch of the air-to-air missiles and to a predetermined orbit.

 The system for delivering goods to space, used to implement all the options (except the last one described) of the proposed method, contains KAVV 1 with marching liquid-propellant engine 2, fuel tanks 3 and 4 and cargo 5, as well as ZVV 8 with marching engine 9, fuel tanks 10 and 11 for the fuel of the vertical take-off spacecraft and the fuel transfer device 14 between the ZVV 8 and the KAVV 1 (Figs. 1 and 2).

 It also has a GSPT 16, which is connected using the fuel connectors 18 between the fuel tanks 3 and 4 KAVV 1 and tanks 10 and 11 ZVV 8 on the launch pad before takeoff. GSPT 16 remains connected during take-off and during further joint synchronous parallel flight and has the ability to disconnect in flight, for example, after the end of the fuel transfer. The system can simultaneously use several GSPT connecting KAVV 1 and ZVV 8. One GSPT 16 may have several pipelines, for example, to transfer several fuel components. KAVV 1 and ZVV 8 can have several tanks with fuel each. KAVV 1 may have, for example, the number of tanks equal to the number of fuel components. In ZVV 8, there may be separate tanks for engines of ZVV 8 and tanks with fuel KAVV 1 and ZVV 8 have commonly used control systems that provide them with flight along predetermined trajectories. ZVV 8 may contain known devices for retracting and storing GSPT 16 after its use.

 In the system for delivering cargo into space, the ZVV 8 mid-flight engine must have a fairly deep thrust control. Therefore, it can contain several pairs of component engines, consisting of the same in pair and located symmetrically relative to the longitudinal axis of the mid-flight engine 9 of the air-breathing device 8 and together and equally adjustable in thrust of the component engines. This symmetry makes it possible to keep the direction of the velocity and acceleration of air-blasting agent 8 unchanged at the same time disconnecting the engines of one pair. At the same time, the thrust of the main engine of the air-blasting device 8 is provided for significant limits, which is necessary in conditions of a significant reduction in the mass of air-blasting devices 8 and constant mass of the air-blast gun 1 during their joint flight. Of course, other engine variants with a sufficient thrust control range can also be used in ZVV 8.

 In another embodiment, the system for the delivery of goods into space contains KAVV 1 and two ZVV 30 and 31 (Fig. 6-8). KAVV 1 has a marching liquid-propellant engine 2, fuel tanks 3 and 4 and carries a load of 5. Two ZVV 30 and 31 contain mid-flight engines 9, fuel tanks 10 and 11 for fuel KAVV 1 and a fuel transfer device 14 between ZVV 30 and 31 and KAVV 1. The system has two GSPT 32 and 33, which are connected between the fuel tanks 3 and 4 KAVV 1 and the fuel tanks 10 and 11 of the ZVV 30 and 31. The fuel tank of one ZVV may contain the first fuel component for KAVV 1, and the fuel tank of another ZVV may contain the second fuel component for KAVV 1 (while KAVV 1 contains at least two aka).

 In another embodiment (Fig. 9-11), the system comprises, in addition to KAVV 1, the first ZVV 30 with a fuel transfer device between the first ZVV 30 and KAVV 1 and the second ZVV 31 with a fuel transfer device between the second ZVV 31 and the first ZVV 30. The system also contains the first and the second GSPT 32 and 33. The first GSPT 32 is connected between the fuel tanks of the KAVV 1 and the first ZVV 30, and the second GSPT 33 is connected between the fuel tanks of the first ZVV 30 and the second ZVV 31. The indicated GSPT 32 and 33 are connected before take-off, during take-off and during joint synchronous parallel flight with the possibility of disconnection tions in flight.

 It should be noted that in the system a larger number of air pollutants can also be used, there can be as many as can be placed around KAVV 1 on the launch pad and in flight, taking into account the length of the GSPT. To these ZVV, placed around KAVV 1, in turn, other ZVV can be connected. In this case, various system configurations may be formed. For example, you can turn on three GSPTs, with two ZVV connected to each other and each of them with KAVV 1 (this creates a "triangular" configuration of the system). Various configurations provide the system with additional features, for example, higher reliability.

 In another embodiment, the system for delivering goods to space (Fig. 12) contains KAVV 1, the KAVV launch complex 34 with the launch pad 35 for the KAVV 1, ZVV 8 with the fuel tank 10 for the KAVV 1 fuel, the 37 ZVV launch complex with the launch table 38 for the ZVV 8, at least one GSPT 16 and a central control center 39 connected by communication lines 36 and 40 with launch complexes 34 and 37.

 ZVV 8 and KAVV 1 with the help of GSPT 16 are interconnected before take-off, during take-off and during a joint synchronous parallel flight until the end of the fuel transfer.

 The launch pad 34 KAVV 1 is located from the launch pad 38 of the ZVV 8 at a distance shorter than the length of the GSPT 16. The system for delivering goods into space also includes a means 41 for separating launch complexes for accident safety, which is located between the launch pad 35 of the KAVV 1 and launch pad 38 ZVV 8. Dimensions and strength of the means 41 separation of launch complexes are calculated according to the specified allowable excess pressure. In the separation means 41 there is a groove 42 (FIGS. 12-14) extending from the upper base of the separation means 41 towards the Earth to the level of passage of the flexible fuel transfer means 16 and having a width not less than the maximum transverse dimension of the flexible fuel transfer means 16, which is in front of take-off and during take-off is located in groove 42.

 In another embodiment (Fig. 15) there is a means 43 for closing the groove 42 before takeoff and opening it immediately before takeoff. This can be, for example, a moving (or discarded) shield.

 In this embodiment of the system, the separation means 41 (for example, a wall) protects one of the parts of the system in the event of an emergency in another part, for example, from explosion or ignition.

 In the following two embodiments, the system for delivering goods into space (Fig. 16) contains CABB 1, HEC 8, GSPT 16, connecting cable (ST) 44, receiving device 45 ST, storage device 46 GSPT and ST. Connecting cable 44 is connected between KAVV 1 and ZVV 8 before takeoff, during takeoff and flight, and connected to a receiving device 45 ST and to a storage device 46 GSPT and ST. GSPT 16 is connected to CT 44 with the possibility of moving GSPT 16 between KAVV 1 and ZVV 8 together with ST 44. Thus, GSPT 16 does not connect KAVV 1 and ZVV 8 before takeoff, but is, for example, in KAVV 1. Before takeoff between KAVV 1 and ZVV 8, only connecting cable 44 is included. In KAVV 1 there is a storage device 46 GSPT and ST. In this device, GSPT 16 and a part of CT 44 are stored until take-off in collapsed state. GSPT 16 is connected in KAVV 1 to the KAVV fuel tank (not shown in Fig. 16). In ZVV 8 there is a receiving device 45 ST. ZVV 8 also contains a receiver 48 GSPT 16, which is connected via a pipeline to the fuel tank of ZVV 8 (the pipeline and the tank are not shown in FIG. 11). The end of the GSPT 16 connected to the connecting cable 44 has a locking device 47 designed to connect the GSPT 16 (after take-off) with the GSPT receiving device 48 located in the STZV 8. After take-off, the GSPT 16 connects the STZV 8 and KAVV 1 tanks, and part of the connecting the cable 44 is stored in the receiving device 45 of the connecting cable. The receiving device 45 of the connecting cable and the storage device 46 GSPT and connecting cable can be made in the form of drums with the necessary drives. The locking device 47 GSPT and the receiving device 48 GSPT can be made as well as known devices (catchers) used to joint hoses when refueling aircraft in flight.

 In another embodiment, the GSPT 16 is located prior to take-off in the GSPT and connecting cable storage device 46 located in the STB 8, and the receiving cable receiving device 45 and the GSPT receiving device 48 are located in the CAVV 1.

 A fuel tank may be absent in the space cargo delivery system in KAVV 1, while the entire flight of KAVV 1 is due to the fuel supplied from STZ 8. In this case, the STZ accompanies the KAVV until a speed is reached to reach a specified orbit.

 For the implementation of the method of delivery of goods into space and the creation of the proposed system, a number of devices are important, including fuel transfer systems, engines, control systems, launch complexes.

 In theoretical terms, the problem of pumping fuel from one spacecraft to another based on the ideas of K.E. Tsiolkovsky and M.K. Tikhonravova was considered in several works, in particular, in the article by L. I. Slabkov “Optimization of the parameters of an aircraft such as the Tsiolkovsky rocket squadron with proportional fuel overflow” (Proceedings of the 13th readings by K.E. Tsiolkovsky, Kaluga, 1978 Section "Problems of rocket and space technology. In the collection of ideas of KE Tsiolkovsky and problems of the effectiveness of space rocket systems. M. 1989. S. 97-103). Earlier this problem was considered in the report of Crocco G.A. Space refueling and the multi-stage problem (Crocco GA "Levitaillement dans l'espace et le signalme polistades" // The Fourth Astronautical Congrees "Space-Flight Problems", Zurich, 1953. Published by the Swiss Astronautical Society by order of the Internautical Aeronautical Federation. P. 152-160, 221-224).

 For practical implementation in the present invention can be used various fuel transfer systems, which are described in patents and other scientific and technical literature (US patents NN 5.129.602 and 5.141.181, author B. Leonard; international application number WO 86/05158, date publication 12.09.86; become Chandler FO "Expendable resupply fluid system design issues" // AIAA papers. 1986. N 1758. P. 1-8; article by Eberhardt RN et al "Orbital spacecraft resupply technology" // AIAA papers. 1986. N 1604. P. 1-15; article Rudland R. et al "Liquid hidrogen pressurization, venting and ressupply in Iow-G" // AIAA papers. 1986. N 1251. P. 1-7; article Kirkland Z. et al "On-orbit propellant resupply demomstration.//AIAA papers. 1984. - N 1342. P. 1-5).

 Fuel transfer systems can be implemented as described in Sutton D. Rocket Engines. M. Publishing House of Foreign Literature, 1952, p. 200-243, translation of the book Sutton G. Rocket propulsion elements, New York - London, 1949 and in the book of Aleshkov M.N. and Zhukova I.I. The physical basis of rocket weapons. M. Military Publishing House of the Ministry of Defense of the USSR, 1965, p. 135-163. As a fuel transfer device, known turbo pump units can be used (see the mentioned book Sutton D. p. 207-233).

 As flexible means of transferring fuel, known hoses can be used for refueling aircraft in the air. Such hoses may include wire reinforcement and / or metal rings to increase strength. GSPT can also be made in the form of articulated connecting segments of inflexible pipelines, and the flexibility of the GSPT is ensured by several degrees of freedom of movement of the articulated joints.

 The device for connecting hoses to tank pipelines can be simplified in comparison with devices used for connecting hoses in flight, since the operation of connecting the GSPT in the proposed invention is carried out manually on Earth. GSPT can have remotely controlled valves (valves) that shut off the pipeline after the end of the fuel transfer in order to prevent fuel spillage after disconnecting the hose. GSPT should also have such devices for attaching hoses to the pipelines of the tanks (fuel connectors), which ensure their automatic disconnection. It can be, for example, pyrotechnic locks or mechanical locks with solenoid or other control.

 The KAVV engine is arranged and operates in the usual way, as in other space rocket vehicles. Such engines are described, for example, in Sutton D. Rocket Engines. M. Publishing House of Foreign Literature, 1952, p. 141-185. LRE are also described in the book Aleshkov M.N. and Zhukov I.I. The physical basis of rocket weapons. M. Military Publishing House of the Ministry of Defense of the USSR, 1965, p. 75-112. Aircraft with LRE are also described in the book Design of Guided Ballistic Missiles, edited by A.M. Sinyukova and N.I. Morozova, M. Military Publishing House of the Ministry of Defense of the USSR, 1969, p. 24-40.

 In addition to the marching engines, KAVV and ZVV can have steering engines for maneuvering and stabilizing the position. Such engines are described, for example, in US patent N 4635885, CL. B 64 G 1/26. Managing the maneuvering and stabilization engines can be carried out, for example, by the method described in US patent N 5130931, CL. B 64 G 1/26.

 KAVV and ZVV have conventional control systems that allow spacecraft to move along a given trajectory with given fairly tight tolerances for deviations from it. This makes it possible to carry out the flight of CAVV and ZVV along parallel trajectories at the required distance from each other, which ensures safe stable movement of a group of spacecraft.

 However, due to the fact that the problem of the free movement of objects connected by flexible communications moving with great acceleration is being solved, additional control tools, including means for determining the relative position of the CAVV and the SVV, can be used to reliably ensure the relative preset location of the CAVV and the air-blast. For example, systems such as aircraft radio altimeters can be used to measure the distance between CAVV and ZVV. To determine the relative position of the CABB and the HEL, for example, you can use the system described in US patent N 5109345, CL. B 64 G 1/64, which allows you to obtain information about the relative position of spacecraft in several coordinates. In flight KAVV and ZVV can be used position and speed control systems described in US patent N 5130931 and N 5140525, CL. B 64 G 1/26, as well as in the above-mentioned book of M.N. Aleshkova and I.I. Zhukov, from 240-322.

 Like well-known launch complexes, launch complexes KAVV and ZVV may contain the following types of equipment: transport, lifting and loading, refueling, electric power, testing, communication and control equipment. In addition, launch complexes may contain shelters and storage facilities and similar engineering structures (see the book of MN Aleshkov and II Zhukov mentioned above, pp. 385-406).

 Due to the fact that instead of launching the rigid multi-ton structure of a multi-stage rocket, several relatively small missiles are launched simultaneously, the launch complex is simplified.

 Launching sites for launching the CAVV and the CWS can be autonomous, located at a relatively small distance from each other (this distance does not exceed the length of the flexible means for transferring fuel from the CWS to the CWS) and are combined by the Central Control Center system.

 Due to the simplification of the launch complex, the cost of creating and operating the launch complex according to the invention should be less than the same costs at existing spaceports.

 Another advantage of the launch complex according to the invention, due to the fact that the launch pads are autonomous and small, is the possibility of its quick and relatively inexpensive recovery from accidents.

 The launch complex for the proposed system also differs from the existing ones in that it may not carry out the operations of manufacturing and assembling non-transportable modules of rockets currently used at space launching sites for launching heavy transport rockets, since the CAVV and SVV should be smaller in size and relatively easy can be transported by ordinary vehicles.

The operation of the system of delivery of goods into space was partially described in the description of various options for the method of delivery of goods into space. Simultaneous take-off and parallel and synchronous flight of KAVV and ZVV can be provided by the choice of the corresponding take-off and flight modes that specify the operation of the engines. Takeoff and flight control can be provided in unmanned mode using well-known control systems. To known control systems can be added control systems for the relative position of aircraft, used, for example, when docking spacecraft. These are various radar, laser and other systems, sometimes using reflective targets and the like.
Consider the flight of KAVV 1 together with one ZVV 8.

 This invention in a preferred embodiment implements a flight plan, which can be divided into three different stages.

The first is the stage of preparation for take-off. At this stage:
transportation of CAVV 1 and ZVV 8 to the starting position (Fig. 7),
placement of space-borne cargo 5 in KAVV 1,
refueling of tanks 3 and 4 of KAVV 1 and tanks 10 and 11 of ZVV 8 with fuel,
connection KAVV 1 and ZVV 8 flexible means of fuel transfer 16.

The second stage is the take-off of KAVV 1 and ZVV 8. At this stage:
starting engine 2 KAVV 1 and engine 9 ZVV 8,
the simultaneous take-off of KAVV 1 and ZVV 8 from launch tables 35 and 38,
joint flight of KAVV 1 and ZVV 8 along parallel trajectories, moreover, constant thrust of the main engine 2 KAVV 1 is supported,
pumping fuel from ZVV 8 to KAVV 1 from the moment of take-off (in this case, the fuel coming from ZVV 8 is used to operate the KAVV 1 main engine 2, and fuel from tanks 3 and 4 of KAVV 1 is not used),
KAVV 1 and ZVV 8 move in parallel until the end of pumping a specified amount of fuel. For example, the remaining fuel in tanks 10 and 11 of ZVV 8 should be enough to return to Earth, both tanks 3 and 4 of KAVV 1 at this moment are filled with fuel.

The third stage is the end of the joint flight of KAVV 1 and ZVV 8, in which:
the cessation of fuel transfer from ZVV 8 to KAVV 1,
disconnection of GSPT 16 from KAVV 1 and fixing it to the ZVV 8,
the return of ZVV 8 to the take-off place or to another place with horizontal or vertical landing.

 Flight CAVV 1 continues until it enters Earth orbit or deep space.

 The return of CAVV 1 to Earth is carried out in the usual way, i.e. braking is first performed, and then aerodynamic flight in the atmosphere and horizontal or vertical landing at the take-off place or in another place.

 A possible variant of the system when the thrust of the main engine 2 KAVV 1 is unstable, for example, when you need to change the flight path. In this case, the amount of fuel consumed in flight in KAVV 1 per unit of time is continuously measured, the data of these measurements are transferred from KAVV 1 to the control system of ZVV 8 and continuously supplied from ZVV 8 to KAVV 1 is the amount of fuel per unit time equal to the amount of fuel consumed per unit time in KAVV 1 during the flight. More fully engine operation described above.

 Of course, it is understood that KAVV 1 and ZVV 8 have the means to ensure a decrease in speed in the atmosphere and the necessary means of thermal protection. In addition, they may have parachute means for braking during landing. Their descent can be carried out by the type of descent VKS "Buran" or "Space Shuttle".

 It should be noted that the cessation of fuel transfer from ZVV 8 to KAVV 1, disconnection of GSPT 16 from KAVV 1, the return of ZVV 8 and KAVV 1 to the take-off place or to another place with horizontal or vertical landing are operations that, in some cases, use of the method and system not required. So a case is possible when both KAVV 1 and ZVV 8 in a "bunch" will go to deep space, and the transfer of fuel through GSPT 16 will be periodically resumed.

 In another embodiment, the system for delivering goods into space contains CAVV 1 and two CTA 30 and 31, both CIA can be connected to CAVV 1. In this embodiment, all the above stages of the system are repeated with some changes. Fuel pumping can be carried out simultaneously from two air-blast cleaners 30 and 31 to the air-cleaners 1, while the required diameter of the GSPT 16 is reduced (compared with the version with one air-tight storage unit 8). Fuel transfer can be carried out "sequentially", i.e. first, the first air-conditioning device 30 is pumped into KAVV 1 fuel, and after its disconnection the second air-conditioning device 31. At the same time, the diameter of the GSPT 16 does not decrease (compared to the variant with one air-cooling device 8), but fuel is saved (compared to the variant with two air-cooling device 8, operating at the same time, and compared with the option with one ZVV 8) due to faster disconnection of the first ZVV 30 and, accordingly, raising it to a lower height.

 In another embodiment, the system for delivering cargo into space also contains KAVV 1 and two ZVV, but the first ZVV 30 is connected to KAVV 1, and the second ZVV 31 is connected to the first ZVV 30. Fuel is also pumped in series, i.e. the second ZVV 31 first transfers fuel to the first ZVV 30, which spends this fuel to operate its engine and to transfer fuel to KAVV 1. After the end of the transfer of fuel from the second ZVV 31, it switches off and the first ZVV 30, which has kept its tanks full by this moment , begins to transfer 1 fuel to KAVV. Obviously, in this embodiment, the diameter of the GSPT 16 connecting the second ZVV 31 with the first ZVV 30 should be increased. But at the same time, the total fuel consumption for lifting the cargo may decrease.

 In an embodiment of the system, when two or more ZVV are used, the weight and dimensions of the SVV can be reduced. If you use the same size of air pollutants, the fuel supply of the system can be increased, which will provide a large final speed.

 When the system operates in the above-described variants, the fuel can be pumped not only from the moment of take-off, but also after some rather short time.

 A fuel tank may be absent in the CAVV, while the fuel from the HVS is supplied directly to the CAVV engine, starting from the moment of take-off and until a speed sufficient to bring the CAVV to a given orbit or to the trajectory of its flight into deep space. ZVV can work as follows: to accompany KAVV in the further flight, to remain in the changed orbit, to fly along the changed trajectory or to return to the Earth. Since there is no fuel in the KAVV, a cargo of large dimensions and heavy weight can be placed in it.

 In another embodiment of the system, when KAVV 1 and ZVV 8 are connected prior to takeoff by connecting cable 44 (Fig. 16), the operation of the system is described quite fully in the previous sections. Since the length of the part of the cable 44 located between KAVV 1 and ZVV 8 can be increased by unwinding a relatively thin cable from the receiving device 45 of the connecting cable, when taking off KAVV 1 and ZVV 8 have the ability to be located relative to each other with greater tolerances than in the case of connecting KAVV 1 and ZVV 8 before take-off with the help of GSPT 16. Then, after establishing a stationary mode of joint flight, the distance between KAVV 1 and ZVV 8 is stabilized and they are connected using GSPT 16. This option also provides Olsha safety GSPT 16 during takeoff.

 The system for delivering goods into space can have one launch complex with two launch tables and a common CPU.

 In another embodiment of the system, when it includes launch complexes 34 and 37 separate for KAVV 1 and ZVV 8 with launch tables 35 and 38, the CPU 39, using communication lines 36 and 40 for transmitting control and measurement signals, ensures that the KAVV 1 and ZVV 8 (simultaneous take-off).

 In another embodiment of the system, between the launch complex 34 KAVV 1 and the launch complex 37 ZVV 8 establish a means of separation to ensure safety 41, for example, a wall of the necessary strength, which increases the safety of KAVV 1 and SVV 8 and launch complexes in case of possible accidents. The dimensions and strength of the wall 41 are selected so that during an explosion on the launch pad, for example, ZVV 8, the launch pad KAVV 1 and KAVV 1 itself are not destroyed. Before takeoff, the GSPT 16 is connected to the CAVV 1, pulled through a vertical groove in the wall 41, and then connected to the SVV 8.

 In another embodiment, the systems close the groove in the wall 41 with a special means for closing the groove 43, for example, with a movable shield. Immediately prior to takeoff, shield 43 is pushed back (or discarded) to open the upper part of the groove 42, along which GSPT 16 will rise along with CAVV 1 and ZVV 8 during take-off.

 To implement the method of delivering goods into space, known and available in aviation and astronautics elements can be used, including well-known rocket engines, UPT, GSPT, etc.

 For example, in US patent N 3100614, NKI 2440135, 1963 describes a flight refueling system. A device for refueling an aircraft in flight is also described in US patent N 3008674, NKI 244-135, 1961. A device for automatically docking and undocking hydraulic systems is described in USSR author's certificate N 185241, class. B 64 D 39/06, 1966. In US patent N 5141178, NKI 244-135A, 1992 "Air refueling system" describes a drum for winding and unwinding a hose for transferring fuel when connecting and undocking the tanker aircraft. The disconnection of the cable with the help of a pneumatic cylinder is described in the USSR author's certificate N 453339, cl. B 64 D 3/00.

 Of course, known devices must be adapted to perform the functions of a particular system, but it is obvious that the achieved level in aviation and astronautics already allows us to implement the proposed method and system, and the presence of known and applicable components allows us to implement the method and system quite quickly and with low costs compared with other proposed methods and systems.

Thus, in the proposed invention solved the above technical problems. In addition, in the proposed invention, as in the prototype, the cost of transporting goods into space is reduced:
by reducing the cost of creating the infrastructure necessary for the manufacture, transportation to the launch pad and launch of aircraft;
by reducing the size of structures located on the launch pad, and reducing losses from their destruction in the event of an accident.

 Various changes and additions may be made to the specific embodiments described above that are obvious to those skilled in the art. The invention is not limited to the described examples, other variants of the present invention may be proposed without going beyond its scope defined by the claims.

Claims (13)

 1. A method for delivering goods to space, in which the fuel necessary for delivering cargo into space is placed in the tanks of the vertical take-off spacecraft and at least one refueling tank with vertical take-off, provide for a joint synchronous parallel flight of the vertical take-off spacecraft on the path of the vertical take-off spacecraft and at least one tanker with vertical take-off, is transferred during the joint flight of the spacecraft of vertical take-off and at least one tanker with vertical take-off fuel from at least one tanker with vertical take-off to the space apparatus of vertical take-off, characterized in that before taking off the spacecraft of vertical take-off and at least one tanker with vertical take-off connect the spacecraft of vertical take-off and at least one vertical take-off tanker using at least one flexible fuel transfer means, take-off a vertical take-off spacecraft together and at least one tanker with vertical take-off with at least one flexible means for transferring fuel connected between them, carry out the specified simultaneous simultaneous parallel flight of the spacecraft of vertical take-off and at least one tanker with vertical take-off with at least one connected between them flexible means of fuel transfer.  2. The method according to claim 1, characterized in that the amount of fuel consumed in flight in the vertical take-off spacecraft per unit of time is continuously measured, the data of said measurements are transferred from the vertical take-off spacecraft to the vertical refueling control system and fed continuously from the refueling tank with vertical take-off into the spacecraft of vertical take-off, the amount of fuel per unit time is equal to the amount of fuel consumed per unit time in the spacecraft of vertical take-off and during the flight.  3. A method of delivering cargo into space, in which the fuel necessary for delivering cargo to space is placed in the tanks of the vertical take-off spacecraft and two, first and second, vertical take-off tankers, provide for joint synchronous parallel flight of the spacecraft on the path of the vertical take-off spacecraft vertical take-off and two tankers with vertical take-off, transmit during the joint flight of the spacecraft vertical take-off and two tankers with vertical fuel take-off from the first tanker with vertical take-off to the spacecraft of vertical take-off, and from the second tanker with vertical take-off to the first tanker with vertical take-off, characterized in that before take-off of the spacecraft of vertical take-off and two tankers with vertical take-off connect the spacecraft of vertical take-off with the first tanker with vertical take-off using the first flexible means of transferring fuel, and the first tanker with vertical take-off is connected to the second tanker m with vertical take-off using a second flexible means of fuel transfer, carry out a joint take-off of a vertical take-off spacecraft and two refueling tanks with vertical take-off with two flexible means of fuel transfer connected between them, and then carry out the specified joint flight of a vertical take-off spacecraft and two refueling tanks take-off with two flexible means of fuel transfer connected between them.  4. A method for delivering cargo to space, in which the fuel necessary for delivering cargo into space is placed in the tanks of a vertical take-off spacecraft and a vertical take-off tanker, provide a simultaneous parallel flight of a vertical take-off spacecraft and a vertical refueling spacecraft on a part of the vertical take-off spacecraft trajectory during take-off, during the joint flight of the vertical take-off spacecraft and the tanker with vertical take-off, the fuel from the tanker with vertical take-off spacecraft take-off, characterized in that before take-off spacecraft vertical take-off spacecraft and a vertical take-off tanker, a vertical take-off spacecraft and a vertical take-off tanker are connected using a connecting cable, before take-off, a flexible fuel transfer means is placed in a vertical take-off tanker carry out a joint take-off of a vertical take-off spacecraft and a vertical take-off tanker with a connection connected between them with a cable, pull the connecting cable into the vertical take-off spacecraft with a flexible fuel transfer means connected to it so that one end of the flexible fuel transfer means remains connected to the vertical take-off refueling device, and the other end of the flexible fuel transfer means is connected to the vertical take-off space vehicle , carry out the specified joint synchronous parallel flight of the vertical take-off spacecraft and the vertical take-off tanker, and before Fuel is supplied through a flexible means of transferring fuel during the flight.  5. A method for delivering cargo to space, in which the fuel necessary for delivering cargo into space is placed in the tanks of a vertical take-off spacecraft and a vertical take-off tanker, provide a joint synchronous parallel flight of a vertical take-off spacecraft and a vertical tanker on a part of the vertical take-off space path during take-off, during the joint flight of the vertical take-off spacecraft and the tanker with vertical take-off, the fuel from the tanker with vertical take-off spacecraft take-off, characterized in that before take-off spacecraft take-off spacecraft and a vertical take-off tanker, a vertical take-off spacecraft and a vertical take-off tanker are connected using a connecting cable, a flexible fuel transfer means is placed in the vertical take-off spacecraft before take-off carry out a joint take-off of a vertical take-off spacecraft and a vertical take-off tanker with and connecting cable, pull the connecting cable into the tank with a vertical take-off with a flexible fuel transfer means connected to it so that one end of the flexible fuel transfer means remains connected to the vertical take-off spacecraft, and the other end of the flexible fuel transfer means is connected to the vertical refueling device take-off, carry out the specified joint synchronous parallel flight of the vertical take-off spacecraft and the tanker with vertical take-off, and before Fuel is supplied through a flexible means of transferring fuel during the flight.  6. A space delivery system comprising a vertical take-off spacecraft with a marching liquid-propellant engine, a fuel tank and cargo, and a vertical take-off tanker with a marching engine, at least one fuel tank for the vertical take-off spacecraft fuel and a fuel transfer device between vertical take-off tanker and vertical take-off spacecraft, characterized in that the system comprises at least one flexible fuel transfer means, which is included ezhdu fuel tanks spacecraft VTOL and VTOL tanker, said means being connected to take-off during takeoff and during flight joint synchronous parallel detachably in flight.  7. A space delivery system comprising a vertical take-off spacecraft with a marching liquid-propellant engine, fuel tanks and cargo, and at least two vertical take-off tankers with marching engines, vertical take-off space vehicle fuel tanks and fuel transfer devices between vertical take-off tanker and vertical take-off spacecraft, characterized in that the system contains at least two flexible means of fuel transfer, which include between the fuel tanks of the vertical take-off spacecraft and at least two tankers with vertical take-off, and these means are connected before take-off, during take-off and during a joint synchronous parallel flight with the possibility of disconnection in flight.  8. A space delivery system comprising a vertical take-off spacecraft with a marching liquid-propellant engine, fuel tanks and cargo, a first vertical take-off tanker with a marching engine, at least one fuel tank for a vertical take-off spacecraft fuel and a fuel transfer device between the first vertical take-off tanker and the vertical take-off spacecraft, the second vertical take-off tanker with a marching engine, at least one fuel tank For fuel, a vertical take-off spacecraft and a first vertical take-off tanker and a fuel transfer device between the second and first vertical take-off tankers, characterized in that the system comprises first and second flexible fuel transfer means, the first flexible fuel transfer means being included between the fuel tanks a vertical take-off spacecraft and a first vertical take-off tanker, a second flexible fuel transfer means is included between the fuel tanks of the first and W Other vertical take-off tankers and the indicated flexible means of fuel transfer are connected before take-off, during take-off and during a joint synchronous parallel flight with the possibility of disconnection in flight.  9. A system for delivering goods into space containing a vertical take-off spacecraft with cargo, a launch complex with a launch pad for a vertical take-off spacecraft, a vertical take-off tank with a fuel tank for fuel of a vertical take-off spacecraft, a launch complex with a launch table for a vertical tanker take-off, characterized in that the system comprises at least one flexible means for transmitting fuel and a means for separating launch complexes to ensure safety and accidents, with the vertical take-off tanker and the vertical take-off spacecraft using the above flexible fuel transfer means are connected to each other before take-off, during a simultaneous simultaneous parallel flight, the launch complexes separation means is located between the launch table of the vertical take-off spacecraft and the refueling launch table with vertical take-off, and in the specified means of separation there is a groove extending from the upper base of the separation means towards the Earth e to a level of said flexible transmission means and having a width not smaller than the maximum transverse dimension of said flexible fuel transfer means which prior to takeoff and during takeoff while disposed in said groove.  10. The system according to claim 9, characterized in that it contains means for closing the specified groove before take-off and opening it immediately before take-off.  11. A space delivery system comprising a vertical take-off spacecraft with a marching liquid-propellant engine, a crowd tank and cargo, and a vertical take-off tanker with a marching engine, at least one fuel tank for the vertical take-off spacecraft fuel and a fuel transfer device between a vertical take-off tanker and a vertical take-off spacecraft, characterized in that it comprises a flexible fuel transfer means, a connecting cable, a connection receiving device a cable, a storage device for a flexible means of transferring fuel and a connecting cable, the connecting cable being connected between the spacecraft of vertical take-off and the tanker with vertical take-off before take-off, during take-off and flight, and connected to a device for receiving a connecting cable and to a device for storing a flexible means of transferring fuel and a connecting cable, and a flexible means of transferring fuel is connected to a connecting cable with the possibility of moving a flexible means of transferring fuel between space cal device VTOL and VTOL tanker together with the connecting cable.  12. The system according to claim 11, characterized in that the storage device of the flexible means for transmitting fuel and connecting cable is located in the tanker with vertical take-off, and the device for receiving the connecting cable is located in the spacecraft of vertical take-off.  13. The system according to claim 11, characterized in that the storage device of the flexible means for transmitting fuel and connecting cable is located in the spacecraft of vertical take-off, and the device for receiving the connecting cable is located in the tanker with vertical take-off.

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