RU2215673C2 - Aerospace launching complex mars - Google Patents

Abstract

FIELD: space transport systems; ground organization of space transport systems. SUBSTANCE: proposed complex includes closed rail track in form of two lines located one above other in vertical plane. Upper rail line is used as runway and lower line is used as return line. Track is mounted on truss trestle terminating in vertical ring; said rail lines are interconnected on this ring. Mounted on rails are platforms fitted with quick-detachable attachment units and acceleration engines. After acceleration of platform, vehicle is separated from it and lifts off. After completion of revolution over vertical ring, platform returns to launch over lower rail line. Complex is provided with standard rooms, shops and services. EFFECT: enhanced efficiency of injection of space systems of small and medium mass (to 5 t) into orbits at altitudes from 200 to 1000 km at various inclination. 6 cl, 47 dwg, 3 tbl

Description

 The invention relates to space technology, namely to the aerospace complex launch and launch of spacecraft "Mars" in space.

 In connection with the active, ever-increasing use of outer space for practical activities and the increasing pace of launching spacecraft, one of the fundamental problems is the creation of reusable launch systems and more advanced ways to launch them.

 This problem to a large extent relates to the launching of low and medium spacecraft and small-satellite satellites (up to 5 tons), which make up the bulk of the payloads launched into space, which also have a short operational life (on average up to 5 years) and periodically require replacement.

 Currently, a number of organizations in the aerospace industry are proposing various designs of spacecraft launch systems, including airborne launch systems for payloads from heavy passenger aircraft (Tu-160, An-124 (Ruslan), An- 225 ("Mriya"), which somewhat reduce the cost of putting payloads into space, but do not fully realize the reusability of the elements of the launch system.

 This invention relates to the creation of new aerospace launch vehicles and a fundamentally new design of the spacecraft launch system from the Earth and is aimed at solving the following technical problems.

 1. Improving the efficiency of launching spacecraft of small and medium mass (up to 5 tons) into orbits with a height of 200 to 1000 km with different inclination angles.

 2 Ensuring the reusability of the use of spacecraft.

 3. Ensuring the horizontal launch of spacecraft from the Earth and launch at an angle of inclination close to vertical, with a large vertical speed.

 4. Improving the reliability of the launch.

 5. Simplification of launch technology, reduction of time for technical preparation of spacecraft for launch.

 6. High efficiency, lower startup cost.

 7. Greater responsiveness, flexibility and all-weather launch.

 8. Convenient horizontal landing of crews and passengers in spacecraft indoors, ensuring a favorable physiological and environmental situation at the launch complex and at the launch pad.

 The task is achieved by the fact that the launch of spacecraft and their launch into orbits is carried out by the Mars ground-based aerospace launch complex (ASCC), which is a technical base with a developed infrastructure that provides a full cycle of prelaunch preparation of spacecraft (SC), including docking, verification, control of on-board systems, refueling with fuel and liquids, landing of crews and passengers, launch, as well as escort of spacecraft on the flight path.

 The technical feature of the Mars aerospace complex is the horizontal landing of crews and passengers in spacecraft along horizontal ladders in the enclosed space of the ASCC main body and the horizontal launch of the spacecraft from the Earth, followed by take-off at angles close to vertical.

 This is achieved by the fact that the AKC runway is a two-track track mounted on a metal flyover having a shaped structure ending with a vertical circle - a “vertical ring” of large diameter.

 The rail track has a closed loop, consists of two lines located in a vertical plane, one above the other, the top of them serves as a runway. At the upper point of the vertical ring, the runway ends, after which the rail track smoothly, bypassing the vertical ring, passes into the lower return line, which returns to the building of the technical building.

 The take-off runway originates from the launch pad, located at a distance of 200-250 m from the AKSK hull, along the entire length of the runway the runway has a variable geometric contour and consists of sections: take-off, acceleration and take-off.

 At the take-off section, the rail track has a concave contour formed by an arc of the outer circle mating with the circumference of the vertical ring at point C, while the tangent angle drawn from the point C of the circles to the horizontal is the angle of separation of the ACS from the overpass.

 The angle of take-off of the ACS from the flyover is a function of the size of the diameters of the circles of the vertical ring and the outer circle, with an appropriate selection of these circles, the angle of take-off of the ACS can be brought close to vertical.

 The start of the AKS from the overpass is carried out using the onboard engines of the AKS and the booster platform installed on the rail track.

 The booster platform is an autonomous, self-propelled vehicle equipped with wheeled trolleys, electric motors, a braking device and powerful booster engines (for example, liquid propellant rocket engines) that work for a short time only on the take-off section of the rail track.

 The booster platform is equipped with lodgements for laying on it an aerospace system and butt assemblies connecting it to the ACS, which are automatically undocked when the launch platform reaches take-off point C located on the vertical ring.

 After separation of the ACS, the launch platform, due to inertial speed or electric motors, passes the return path, braking of the acceleration platform on the return path is provided by hydraulic brakes.

 Aerospace payload systems are installed on the booster platform with retracted landing gear.

 The aerospace system launched in ASCC is a two-stage system.

 The first step is a reusable, manned space launch vehicle (SPL) equipped with powerful marching liquid propellant liquid propellant rocket engines and two turbojet engines, for example, ramjet engines operating during acceleration of the ACS along the runway and during takeoff, lifting the ACS to a height of 40-45 km, as well as on the site of controlled flight of SPE in the atmosphere after descent, gravitational planning along the glide path and when landing on the airfield.

 The second stage of the ACS can be various spacecraft with a payload of up to 5 tons, equipped with booster blocks, which ensure that the second stages are brought to the reference or other orbit.

 The launch of payloads into different orbits is ensured by the possibility of flying to the launch site of the second stage with parralax at distances up to 1500 km.

 The space carrier aircraft is equipped with bearing aerodynamic surfaces, aerodynamic control elements and retractable landing gears, providing it with an airplane landing on the base or any other aerodrome of the first category.

 The start time of the ACS overpass 25-30 s, the speed of separation of the ACS from the runway during operation of all onboard-mid-flight engines of the ACS and the acceleration platform engines can be, for example, about M = 1.0 m.

 The return time of the booster platform is about 100-120 seconds, after which preparation for the subsequent launch can be conducted.

 The Mars ground-based aviation space launch complex is implementing a project that will make it possible to launch satellites into orbit faster, more efficient and less expensive.

The main advantages of the Mars launch complex, ensuring its high competitiveness, are
- reusability of spacecraft and the exclusion of exclusion zones on Earth;
- horizontal launch of spacecraft from the ground and vertical take-off from the ground at a large initial vertical speed;
- convenient horizontal landing of the crew and passengers in spacecraft in the enclosed spaces of the launch complex;
- greater responsiveness and flexibility, significant savings in startup time;
- reduction in the cost of launch;
- all-weather launch, constant readiness of the runway;
- high reliability and safety;
- high environmental start.

The design of the aerospace launch complex "Mars" is presented in the following figures:
Figure 1 General view of the aerospace launch complex.

 Figure 2 View of the main building AKSK (side view).

 Figure 3 The same (plan view).

 Figure 4 View of the Main building (front view).

 Figure 5 View of the 3rd floor of the Main building (plan view).

 Fig.6 View of the landing ladder during landing of the crew and passengers on the spacecraft.

 FIG. 7 Technology of loading the launch vehicle onto the booster platform (side view).

 Fig. 8 The same (front view).

 FIG. 9 Loading of the orbital stage onto the launch vehicle (side view).

 Figure 10 The same (front view).

 11 Scheme AKSK and launch flyover (side view).

 Fig. 12 The same (plan view).

 Fig. 13 General view of the vertical ring of the flyover and the final take-off path of the spacecraft (side view).

 Fig. 14 The same (plan view).

 Fig. 15 Section A-A of a flyover.

 Fig. 16 Acceleration platform (side view).

 Fig. 17 Same (plan view).

 Fig. 18 Same (view along AA).

 Fig. 19 Same (view in "BB").

 FIG. 20 View of the booster platform on the return rail track 76 (side view).

 Fig. 21 The same (plan view).

 Fig.22 The same (view along aa).

 FIG. 23 Design of the booth for overturning the booster platform, view of the booster platform before the coup on the booth (side view).

 Fig. 24 The same (plan view).

 Fig. 25 View of the booster platform after the coup on the stand (side view).

 Fig.26 The same (plan view).

 Fig.27 Scheme of maneuvering the booster platform at the site of its revolution on the stand in the technical building.

Fig. 28 Rail track on the take-off run:
a) side view
b) front view.

Fig.29 Rail track in areas of acceleration and take-off:
a) side view
b) front view.

Fig.30 Rail track at the transition to the vertical ring:
a) side view
b) front view.

Fig.31 Rail track in the lower section of the vertical ring:
a) side view
b) front view.

FIG. 32 Rail track on the return section of the booster platform to the technical building:
a) side view
b) front view.

 Fig. 33. Enclosed launch vehicle of the 1st reusable stage of the Angara type on the runway (side view).

 Fig. 34 The same (plan view).

 Fig. 35 The same (view along "A").

 Fig. 36 Schematic diagram of a reusable space carrier aircraft with a second stage in the form of a reusable spacecraft (side view).

 Fig. 37 The same (front view).

 Fig. 38 Same (plan view).

 Fig. 39 The same (view aa).

 FIG. 40 Schematic diagram of the technology of launching the spacecraft from the flyover. The position of the ACU on the take-off section of the flyover.

 Fig. The position of the AKC on the flyover before takeoff.

 Fig. 42 The position of the AKC at the time of take-off and separation from the booster platform.

 Fig. 43 Diagram of the movement of the booster platform along the vertical ring of the flyover and return along the return path.

 FIG. 44 Schematic diagram of the launch of spacecraft by the Mars aerospace complex.

 Fig. 45 Acceleration platform, closed fairing (side view).

 Fig.46 The same (plan view).

 Fig. 47. The same (view along section AA).

 The Mars aerospace launch complex consists of a number of buildings, including the Main Building 1, the Technical Building 2, the Prelaunch Building 3, the hangars 4, the auxiliary service buildings 5, the radio communications, flight control and control, and the public premises (FIG. .1).

 Technological prelaunch preparation of aerospace vehicles (ACS), assembly, docking, loading, automated control of on-board systems, fueling and gases are carried out in prelaunch building 3 adjacent to the Main building 1, where ACS after prelaunch movement are moved along rail 7 ( figure 2, 3).

 The main building 1 is a multi-storey building with a wide staircase 8, side exit sliding gates 6, mezzanines 10 and upper floors 11.

 The central part of the Main building 1 is occupied by the main hall 12, for example, 15 m high, up to 40 m wide, equipped with technical mobile platforms and horizontal folding ladders 13, which serve for the maintenance of the ACS and the landing of the crew and passengers in spacecraft (Figs. 4, 5 )

 In the mezzanines 10 there are working, technical and domestic premises 14 for technical personnel and crews, warehouses of inventory, equipment.

 On the second floor there is a restaurant 15, on the third floor - a waiting room for passengers 17 with access to the boarding ramps 13 and cafe 16 (Figs. 4, 5), the hotel is located on the upper floors 18, on the upper platform of the Main Building 1 there is a radio and satellite service radio communications, control and reduction 19, as well as a helicopter station 20 with hangars (figure 1).

 When the aerospace launch complex is a ground landing aerodrome 21 with a conventional coating and a runway, which serves as a double-track 7 installed on the overpass 22 (11, 12).

 Overpass 22 (Fig. 11, 12) is an engineering structure of a shaped structure on which two rail lines located in a vertical plane are rigidly fixed, consisting of three sections: upper lines (7a), lower lines (7b) and circular rail lines ( 7c), linking them together, mounted on a vertical ring 23.

 The upper rail line (7a) is a runway that ends at point C of the separation of the ACS from the overpass (Fig. 13).

The runway has a variable contour and consists of sections: take-off (I), acceleration (p) and take-off (w). In the take-off section (w) (Fig. 11), the rail track has a concave profile in the form of a parabola formed by a part of the arc of the outer circle (D _{inner circle} ) 24 with a radius R (Fig.13), which is mated with a circle (D _count ) vertical ring 23 at point C.

Moreover, the angle (γ ^° ) of the tangent OS drawn from point C (the conjugation of two circles) relative to the horizontal is the angle of the ACS from the flyover.

 The dimensions of the diameters of the vertical ring 23 and the outer circle 24 determine the angle of descent of the ACS from the spacecraft overpass and are selected mathematically based on the take-off mass of the ACS of the available power of the propulsion system and the speed of the ACS when separated from the flyover.

According to preliminary calculations of the project, during take-off of the ACS weighing about 120 tons, the length of the runway can be about 3000 m. And with a diameter of the vertical ring (D _k ) of 70 m and an outer circumference diameter D _int.ocr = 3.0-3.5 D _{to the} angle of tangent OS γ ^° can be 60 ^o .

When installing the AKS on an accelerating platform with an angle corresponding to the take-off of 8-10 ^o , the angle of take-off of the AKS from the overpass can practically be about 70 ^o .

 The start of the ACS from the overpass is carried out with the participation of the accelerating platform 25, equipped with high-power accelerating engines 26, for example, liquid-propellant rocket engines, operating for a short time only at the runway stage (7a) of the overpass 22.

 The accelerating platform 25 (Fig. 16, 17) is an autonomous self-propelled apparatus mounted on a rail equipped with wheeled trolleys 27, 28, electric motors 33 with drive wheels 34, a braking device, tool holders 30 that serve as supports for laying the ACS on the platform with quick-disconnect butt assemblies 31 connecting the ACS to the platform 25, which are automatically undocked when the accelerating platform reaches the point of separation of the ACS from the overpass.

 Inside the accelerating platform 25, electronic automatic control equipment and a hydraulic system are placed, which activates the braking device 29 (Fig. 16, 17), which serves to cancel the inertial speed of the platform after the start of the ACS and movement in the opposite direction along the vertical ring 23 and the return line.

 To reduce aerodynamic drag (Cx), the accelerating platform from the outside is closed by a streamlined metal skin (45) with smooth contours and a smooth surface (Figs. 45, 46).

 The rail track 7 has a closed structure along the return rail line (7b), the platform independently returns to the AKSK building. The acceleration platform is moved inside the buildings using its electric motors 33 along the trolley line.

 The booster platform 25 returns to the technical building along the path (7b) in an inverted position (Fig. 20, 21) and is brought into operation by means of a stand 35 located in the technical building.

 The overturning platform of the booster platform (FIGS. 22, 23, 24, 25) consists of a bed 36, the revolution mechanism 37, equipped with an electric drive 38, and the rear support device 39.

 After the coup, the booster platform maneuvers along the rails laid in the compartment of the technical building 3, and returns again to the take-off rail (7a) in the operating position (Fig. 26).

 The return time of the booster platform 25 to the technical building after the start of the ACS is about 100-120 s.

 The operation of overturning the booster platform 25 at the bench for about 120 s, after which the booster platform 25 is ready for subsequent use (without taking into account, for example, refueling or preparing the liquid propellant rocket engine).

 The rail track of the viaduct is double track, consists of metal rails 7, laid on metal sleepers 40, included in the construction of the viaduct.

 On the take-off run, the rails 7 on each side are fenced with low barriers 41 (Fig. 27), reinforced with brackets 42.

 At the acceleration and take-off section, barriers 43 are installed having a height slightly larger than the diameter of the wheels of the acceleration platform 25.

 On the annular section of the track (7c), starting from the transition point of the take-off section to the vertical ring (from point C), the rails are installed on the upper shelves of the metal beams 44 forming the power part of the vertical ring 23 having a U-shaped profile (Fig. 29, 30 )

 Due to the relatively small mass of the booster platform, freed from the spacecraft and the large peripheral speed of movement along the vertical ring 23, the rails mounted on the vertical ring can have a lightweight structure in the form of wide steel strips.

 On the way back and indoors, the rails can have a similar lightweight design.

LOADS AND OVERLOADS
When launching spacecraft from a flyover, their design is not subject to large overloads due to the fact that they are installed on an accelerating platform and stacked on lodgements or carriages.

 In this case, the lodgements have a movable structure that allows moving them along the accelerating platform, and can be installed at any place where the power frames of the spacecraft structure are located or the loads are concentrated.

 Therefore, on the take-off and acceleration section, the spacecraft design does not actually experience static overloads, with the exception of the action of acceleration forces.

On the take-off section of the flyover, the design of the spacecraft mounted on the acceleration platform is subjected to acceleration and centrifugal forces, which are however not large due to the small curvature of the track, which is part of the arc 24 of the outer circle (D _okr ), which has a large diameter (Fig. thirteen).

After takeoff from the overpass, the action of centrifugal forces on the spacecraft structure is terminated. At this stage, the design of the spacecraft is exposed to aerodynamic loads and small transverse forces, which at takeoff angles of 60 ^o -70 ^o create an overload of the order of 1.25 g, which does not require strengthening the shell structure of the first stage of the launch vehicle.

 The accelerating platform after separation of the space system from it is subjected to inertial and centrifugal forces, which, with the mass of the accelerating platform, about 15 t • s, are quite large, but due to the high peripheral speed (250-300 m • s), its mass does not have a significant radial load on the ring rail track.

 On the run along the annular path, the accelerating platform 25 is braked by an inertial brake system, and on the return path, by the brake hydraulic system.

AVIATION-SPACE SYSTEMS STARTED FROM AKSK "MARS"
The launch of spacecraft with a payload into orbits is performed using the ACS, the first stage of which are reusable carriers, which can be, for example:
1. The Angara launch vehicle with a reusable Baikal-type rocket accelerator (45), developed by the GKNPTs im. Khrunicheva together with OAO NPO Molniya equipped with a rotary wing (46) (Figs. 31, 32).

 2. A reusable space carrier aircraft (47), which is a manned spacecraft equipped with aerodynamic surfaces (48), tail unit (49), landing landing gear (50) (Figs. 34, 36), equipped with main propellant rocket engines (51), a system reactive control and two PTRD - direct-flow type (52).

 The carrier aircraft contains a cabin for two crew members, fuel tanks for liquid-propellant rocket engines with liquid oxygen and kerosene, and fuel tanks for anti-tank engines.

 The second stage can be various spacecraft with a payload equipped with booster blocks or space orbital planes (53).

 The second stage is installed on the carrier aircraft closer to its tail and is connected to it by quick-detachable nodes.

 Other reusable aerospace systems can also be launched from the Mars launch complex.

 According to the preliminary design, the Mars aerospace system may have weight characteristics (see Table A).

 The composition and characteristics of engines installed on KSM, RB and booster platform are presented in table. B.

 The operating procedure of the ACS engines and their power at the stages of take-off, take-off and landing of the carrier aircraft on the runway are presented in Table 1.

TECHNOLOGY OF START AND WITHDRAWAL OF SPACE VEHICLES WITH AKSK "MARS"
The start of the aerospace systems ASCC "MARS" begins with a ground launch pad (55) located outside the complex at a distance that reduces noise and reduces the effect of emissions from turbojet engines on the atmosphere in the buildings of the complex (Fig. 12).

 The launch pad is free of any buildings and masts. The ACS is transported to the launch pad on an accelerating platform moving with its own electric motors (33).

 Take-off and acceleration of the ACS along the overpass is carried out by the LRE boosters (26) installed on the acceleration platform, as well as by two ATGMs mounted on the carrier aircraft. At the take-off site, for example, 2 seconds before the ACS detachment from the overpass, the LRE of the first stage of the reusable missile system (45) (Fig.31.32) or the carrier aircraft (47) (Fig.34, 36) are turned on.

 At that moment, when the rear wheel car (28) of the accelerating platform (25) crosses point C (Fig. 25) on the vertical ring of the flyover (23), and the front wheel car (27) is on the track of the vertical ring (current 8), automatic separation of the ACS from the booster platform is performed (25).

 In this case, the booster platform is at an angle φ relative to the direction of the runway, which ensures a safe and reliable separation of the ACS from the flyover (Fig.25).

In connection with the installation of the booster aircraft on the boarding platform at a positive angle α _{cr of} about 8-10 ^{o, the} actual take-off angle of the ACS from the flyover will be greater than the angle of inclination of the tangent OS (Fig. 25), which in principle allows us to bring the ACS descent angle closer to the vertical.

 When the ACS is raised to a height of 40-45 m, the ramjet engines of the carrier aircraft are turned off and the further flight is ensured by the operation of the main engines of the rocket engine.

 Upon reaching an altitude of, for example, 120-140 km, the second stage (RB) is separated from the carrier aircraft, while the LRE of the carrier aircraft are turned off, and at the second stage, the LRE of the booster block (RB) is turned on and it is brought to a predetermined orbit.

 After the launch of the second stage, the Mars spacecraft performs a ballistic flight with a decrease along a given glide path, entering the upper atmosphere (at an altitude of, for example, 35 km), airborne turbojet engines are activated, on which the aircraft performs a controlled flight in the atmosphere, pre-launch maneuver and landing to the base or to another aerodrome, which may be located at a distance of more than 1,500 km from AKSK.

 The accelerating platform after separation of the ACS by inertia bypasses the rail track on the vertical ring and returns to the premises of the complex.

 On the way back, the accelerating platform is braked by the hydraulic braking system, while running along the vertical ring it is braked by the centrifugal braking system.

According to the preliminary project for launching the ACS with a take-off mass of 120-130 tons, the length of the take-off path of the flyover can be about 3,000 m, with a vertical ring diameter of 70 m, the angle of the ACS exit from the flyover is 60 ^o (without taking into account the installation angle α _cr ).

 The run time of the ACS along the runway is about 25 s, the take-off speed from the overpass can be brought up to 0.8 m or more.

 The return time of the booster platform is about 100-120 s. Thus, the total start time of the ACS can be within 3-4 minutes.

ADVANTAGES OF THE MARS AVIATION AND SPACE COMPLEX
The proposed system for launching spacecraft from the ground and the basic design of a reusable space carrier aircraft are distinguished by the following advantages.

 1. Launch of carrier spacecraft is carried out horizontally from the ground, which facilitates the technical training of the spacecraft and simplifies the landing of crews and passengers in spacecraft.

 2. The take-off of the ACS is carried out from the ground flyover at vertical angles at high separation speeds, which reduces the time of the departure of the ACS beyond the Earth’s atmosphere and reduces the time of putting payloads into orbits.

 3. Pre-launch preparation of the ACS, docking, fueling, gas filling, and a comprehensive check of all systems are carried out by technical personnel in closed, environmentally friendly, comfortable rooms.

 4. The launch system of the Mars complex provides a high degree of reliability and safety.

 5. The cost of training and maintenance is reduced.

 The design of the runway provides constant readiness for launch at any time of the year.

 6. The launch system reduces the cost of removing payloads, ensures a high pace of launches, and opens the way to widespread commercialization.

 7. The design of the Mars carrier aircraft provides multiple use and launch of various types of spacecraft and payloads into orbits with different deflection angles.

 8. The launch system implements a two-stage reusable launch system with the first stage - a space carrier aircraft and is the most economically advantageous.

Claims (6)

 1. Aerospace launch complex "Mars", containing a runway in the form of a rail with a geometric contour of variable curvature, mounted on a ground flyover truss, having a variable height along its length, as well as acceleration platforms equipped with quick disconnect assemblies mounted on a rail fastenings on them of aerospace vehicles and accelerating engines, briefly working only on the runway, characterized in that the overpass ends with a vertical count end, the rail track is made by a double track closed, laid on the overpass and consists of two rail lines connected to each other on the indicated vertical ring of the flyover and located one above the other in the vertical plane, while the upper rail line is the take-off strip, and the lower one is the reverse rail line , the geometric contour includes run, acceleration and take-off sections, and on the take-off section, the rail track has a concave contour formed by an arc of a circle conjugated with a circle of a specified vertical linen ring.  2. The complex according to claim 1, characterized in that the said rail track is laid on metal sleepers, on both sides it is protected by curbs with brackets, on the specified vertical ring and on the return line the rail track is installed on the U-shaped beams that make up the power section of the flyover: on the runway, rail rails are installed with the upper working part, on the indicated vertical ring and the reverse rail line, the rails consist of steel wide strips mounted on the shelves of the U-shaped beams from their inner side, and overpass seemed from the outside left and right panels closed, electrified and equipped with warning lights.  3. The complex according to claim 1, characterized in that the accelerating platform has liquid rocket engines as accelerating engines and is an autonomous self-propelled device consisting of a rigid metal frame equipped with two-wheeled carts, electric generators, an electro-hydraulic braking system operating on the free run areas of the accelerating platforms along the vertical ring and the return rail line, fuel tanks for accelerating engines and mobile lodges are installed on the accelerating platform You are for laying aerospace vehicles with the landing gear retracted onto the platforms, and for attaching these devices to the booster platforms, there are three attachment points, one of which is located in the front of the platform, and the other two in the back of the platform, and these attachment points are located in areas of the front pillar and the main landing gear of the aerospace apparatus, the acceleration platform is closed from the outside by a streamlined metal skin with smooth contours and a smooth surface.  4. The complex according to claim 1, characterized in that the launching platforms are designed to automatically separate aerospace vehicles from them when they descend from the overpass and the platforms transition to a vertical ring.  5. The complex according to claim 1, characterized in that for the return of the accelerating platform to its starting position and movement inside the buildings of the complex, the platform is equipped with electric motors with wheel drives powered by a trolley line mounted on the overpass.  6. The complex according to claim 1, characterized in that it is equipped, after sections of the vertical ring and the reverse rail line of the overpass, by the accelerating platform, with a rotary stand equipped with an electromechanical drive, by means of which the accelerating platform is turned over to its normal position and re-displayed on the runway .

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