RU2661375C1 - Adapter for the space crafts installation - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to aerospace engineering. Space crafts installation adapter consists of a number of structurally identical platforms, connected in series to each other by means of load-bearing booms. Lower platform is fixed to the carrier rocket (CR) by means of attachment points. Platforms are equipped with fitment holes with the possibility of the space crafts (SC) separation systems attaching therein. On the platforms on the SC installation side forming the square configuration cells channels are made. In each cell by the four fitment holes are arranged equidistant from the these cells covering channels. Channels contain pyrotechnic devices covering the fitment holes used for the SC separation systems securing. Pyrotechnic devices are enclosed with protective covers installed in grooves made on platforms on both sides along the channels. Bearing booms are equipped with separation units, ensuring mutual separation of the adjacent platforms.EFFECT: technical result of the invention is provision of the possibility of mounting various types of SC to the adapter and increase in the SC from the CR separation reliability.3 cl, 8 dwg

Description

The invention relates to the field of rocket and space technology, and more particularly to adapters for the installation and separation of spacecraft during their launches on launch vehicles.

Adapters are usually developed for specific spacecraft, and their design allows you to install spacecraft of a certain mass and size on them through separation systems, also developed for specific spacecraft.

A known adapter for installing a spacecraft containing a platform made in the form of a conical adapter, with attachment points to the launch vehicle. The platform is equipped with landing holes for installing and fixing the spacecraft separation system in them (see, for example: P. Paveltsev “Jianbin-8”: urgent amplification, “Cosmonautics News” magazine, No. 2, February 2015 (p. 24 -25), as well as I. Lisov “Ziyuan-3” and the Argentinean debut, “Cosmonautics News” magazine, No. 7, July 2016 (p. 22-25).

The disadvantages of this adapter are:

- unambiguous binding of landing holes for installation and fastening of the separation system of a particular spacecraft;

- the ability to install only one spacecraft on the adapter (excluding the possibility of placing associated payloads on the adapter);

- loss of the spacecraft in case of failure of its separation system.

An adapter is also known for the installation of spacecraft belonging to the classes of nanosatellites (mass up to 10 kg) and picosatellites (mass up to 1 kg), in which spacecraft of the indicated mass category are placed in cells of the "chest" type, and when separated, are pushed out by spring mechanisms from the corresponding cells of their “chests of drawers” (see, for example: Yu. Zhuravin “The Norwegian student nanosatellite will fly to the Dnieper,” Cosmonautics News, No. 7, July 2004 (p. 39).

The disadvantages of the adapter with the placement of spacecraft in the cells of the "chest" type are:

- difficult (limited) access to places of service (electrical connectors, pneumatic pads, fuel nozzles, etc.) of spacecraft placed in cells of the "chest of drawer" type;

- restrictions on the mass range of spacecraft installed in the cells of the "dresser" type (the use of the "dresser" circuit for spacecraft weighing more than 10 kg leads to undue overload and significantly complicates the design of the adapter and, as a result, to its economic inefficiency);

- Unambiguous binding of cells of the "chest of drawers" type to the overall dimensions of the spacecraft placed in them;

- loss of spacecraft when their separation systems fail.

An adapter for installing spacecraft is also known, comprising a platform with attachment points to the launch vehicle. The platform is equipped with landing holes for installing and fixing the separation systems of the main (full-sized) and associated (small) spacecraft in them. Mechanical devices (spring mechanisms or pneumatic pushers) are used as the separation system for the main spacecraft. A pyrotechnic device is used as a separation system for the associated spacecraft (see, for example: V.N. Blinov, V.A. Grinevich, N.N. Ivanov, Yu.N. Sechenov, V.V. Shalai "Adaptation of spacecraft with launch vehicles and ground equipment during the implementation of single, cluster (group) and associated launches ”, study guide, book 1.“ Adaptation of spacecraft with launch vehicles ”, Omsk, Omsk State Technical University, 2012, pp. 21-23) as well as I. Marinin, A. Vladimirov, I. Lisov “The Kapustin Yar Cosmodrome is reborn”, magazine l “Cosmonautics News”, No. 6, June 1999 (p. 1-11).

The disadvantages of this adapter are:

- unambiguous binding of landing holes for installation and fastening of the separation system of specific spacecraft;

- the ability to install on the adapter a limited number of specific spacecraft;

- inefficient (in terms of occupied volume) use of the run-off space of the launch vehicle to accommodate the payload (spacecraft);

- loss of spacecraft when their separation systems fail.

Currently, small spacecraft of the Cubsat type, belonging to the class of nanosatellites and picosatellites and based on a single Kubsat cell or a set of Kubsat cells (dimensions of a single Kubsat cell are 10 cm × 10 cm × 10 cm), are widely used. In this case, small spacecraft such as cubsat can consist of both series and parallel connected cubsat cells.

At launches, the cubsats play the role of associated payloads and in each particular case it is necessary to solve the problem of not only placing the cubsats in the free zone of the free space (not occupied by the main payload), but also their attachment to the adapter. This leads to an increase in the duration and cost of adapting the cubesat to a launch vehicle (launch vehicle). The problem increases many times with the increase in the number of cubsats launched in one launch.

An example of the relevance and complexity of this problem was the launch on February 15, 2017 of the Indian PSLV LV of 104 spacecraft, of which 96 spacecraft belonged to the class of nanosatellites (see N. Yachmennikova “With one sweep - 104 devices at once”, “Rossiyskaya Gazeta” from 16 February 2017 (p. 6).

The objective (goal) of the present invention is to expand the functionality (installation of spacecraft of various sizes and masses on the adapter, the most efficient use of space-free space to accommodate spacecraft in it) and increase operational characteristics (increase the reliability of separation of spacecraft from the launch vehicle) of the adapter for spacecraft.

To achieve the goal (task) in the adapter for mounting spacecraft, containing a platform equipped with attachment points to the launch vehicle and landing holes for installing and fixing spacecraft separation systems in them, channels are formed on the platform from the side of the spacecraft installation to form a platform of square-shaped cells (channels on the platform are implemented as a system (“grid”) of intersecting channels). In each cell of the platform are four landing holes for attaching spacecraft separation systems. The landing holes of each cell are equidistant (located at the same distance) from the platform channels covering these cells. Landing holes for attaching spacecraft separation systems are located in each cell, and pyrotechnic devices are placed in the channels of the platform with the formation of closed loops, covering the landing holes in plan, in which the spacecraft separation systems are fixed. Pyrotechnic devices are closed with elastic protective covers installed in the grooves of the platform, located on both sides along the channels of the platform. Protective covers are elastic (quick-detachable, deformable laterally from the hand).

Modern spacecraft have small sizes and masses (for example, nanosatellites and picosatellites). Therefore, placing a group of this type of spacecraft in one tier on the same adapter platform does not allow for efficient use of the volume of space and energy characteristics (due to the small total mass and overall dimensions of the payload being removed) for most modern launch vehicles designed to launch multi-ton and large-sized payloads.

For a more efficient (rational) use of the energy capabilities of launch vehicles and the volume of the payload zone in the run-off space of launch vehicles, it is proposed that the adapter be made up of a series of identical (structurally similar) platforms, connected in series by means of support rods fixed through the landing holes of the platform cells located in their centers. Bearing rods are equipped with separation units, which ensure separation of the upstream platforms after all spacecraft installed on them are separated. Bearing rods are installed so that their longitudinal axes coincide with the longitudinal axis of symmetry of the platforms, and the height of the bearing rods is made to exceed the highest height of the spacecraft in conjunction with the separation system installed on the lower platforms.

Mounting the platforms in several tiers by means of load-bearing rods installed in the center of the platforms (when the longitudinal axes of the load-bearing rods coincide with the longitudinal axis of symmetry of the platforms), maximizes the use of the platform area (not occupied by load-bearing rods) to place spacecraft on it. The supporting rods are equipped with separation units, which ensure separation of the upstream platforms from the downstream platforms after separation of all spacecraft installed on them from the upstream platforms. It should be noted that the separation of spacecraft from upstream platforms is carried out both by triggering standard separation systems and by triggering the corresponding pyrotechnic devices with the destruction of part of the upstream platform (within (in a closed loop) platform cells with landing holes for attaching separation systems of the respective spacecraft )

The coincidence of the longitudinal axes of the supporting rods with the longitudinal axes of symmetry of the platforms is necessary in order to eliminate the undesirable inclination of the supporting rods during assembly (formation) of the adapter.

Each platform is equipped with a reflective screen fixed along the outer contour of the platform from the side opposite the installation side to the platform of the spacecraft. A bushing (ring) is made in the center of the reflective screen, covering the support bar below its separation unit. The reflective screen is designed to protect spacecraft installed on downstream platforms from the possible expansion of fragments (particles) in the event of separation of some spacecraft from the upstream platforms due to the operation of pyrotechnic devices, as well as from the possible expansion of fragments (particles) when separating the upstream platforms from operation separation units located on supporting rods. The reflective screen mounted on the lowest platform is designed to protect the upper compartments (booster blocks) of the launch vehicles on which this platform of the proposed adapter is installed.

The universality of the adapter design is ensured by the presence of a number of structurally identical platforms, sequentially installed along the height of the payload placement zone in the lateral space of the launch vehicle, execution of standard (identical) square configuration cells on the platform surface, and a system of landing holes in the cells, which allows installation on the adapter a different number of spacecraft of different sizes with separation systems.

When forming the head unit - the adapter with payloads (spacecraft) - the seats for installing their separation systems are placed either in one cell formed by intersecting channels, or in several cells (depending on the size of the spacecraft). The installation (installation) of pyrotechnic devices (for example, flexible low-pulse detonating cords) into the channels is carried out (carried out) depending on the location of the seats for mounting the separation systems of specific spacecraft. For example, if the spacecraft has small overall dimensions and landing holes for its separation system are located in one cell, then the pyrotechnic devices fit into the channels along the contour of this cell. If the spacecraft has sufficiently large dimensions and the seats for its separation system are located in several cells, then the pyrotechnic devices fit into the channels along the contour of all the cells inside which the seats are located. The requirements are laid down for laying pyrotechnic devices in intersecting channels on the platform: the first is the formation of a closed loop, and the second is the formation of a closed loop in plan that should cover all the seats intended for fixing the separation system of the corresponding spacecraft. Thus, pyrotechnic devices are not placed in all channels on the platform, but only around the landing holes (places) on which the separation systems for spacecraft mounted on the adapter are mounted.

A system of cells of a square configuration with four landing holes in each cell, equidistant from the channels covering these cells, allows you to attach various separation systems with spacecraft of different sizes and masses to the adapter. Landing holes made in the platform cells allow you to vary the number of spacecraft installed on the adapter.

The minimum number of spacecraft installed on the adapter is one large spacecraft, the separation system of which can be fixed to the landing holes of the lower platform (in this case, the upper platforms with supporting rods are not installed) located (in plan) in several cells.

It is possible to install large-sized spacecraft and a number of small spacecraft on the platform of one tier with the provision of gaps between them. The overall dimensions of spacecraft such as nanosatellites and picosatellites allow you to place up to several dozen pieces of such spacecraft on the same platform.

For quick installation (and if necessary dismantling), the protective covers are elastic, with the possibility of interaction with the longitudinal grooves of the platform, made along the channels on both sides. Quick installation of protective covers on the platform and removal from the platform is done by pressing (manually) their side surfaces and fixing (unlocking) in the grooves (from the grooves) of the platform. The grooves have a wedge-shaped cross-section to ensure the free exit of the protective covers from the grooves when the platform is separated after the pyrotechnic device is triggered.

Until the pyrotechnic device is activated, the platform structure remains solid and the spacecraft is attached to it through an appropriate separation system. When an initiating current pulse is supplied, a pyrotechnic device is ignited (for example, a low-pulse detonating cord), which destroys the design of the adapter platform in a closed circuit of its laying in channels. In this case, the adapter platform is divided into two parts: a part of the platform with seats for mounting the separation system with the spacecraft and a part of the platform remaining fixed on the launch vehicle. Part of the platform with seats for mounting the separation system with the spacecraft is not connected with the rest of the platform and is separated from it.

It should be noted that the activation (initiation) of pyrotechnic devices is carried out if the spacecraft for some reason does not separate from the adapter platform (and hence from the launch vehicle) after the standard separation system is activated. If the spacecraft is separated from the launch vehicle normally, then there is no need to use pyrotechnic devices installed (placed) on the adapter platform.

The design of the proposed adapter for installing a group of spacecraft is illustrated in figures 1-8.

The figure 1 shows the adapter with installed spacecraft with separation systems.

Figure 2 shows a view A according to figure 1.

The figure 3 presents a section bB according to figure 1.

The figure 4 shows the remote element B according to figure 1.

The figure 5 shows a diagram of the separation of the spacecraft from the adapter platform when triggered by the separation system (standard).

The figure 6 presents a diagram of the separation of the spacecraft from the adapter platform by activating a pyrotechnic device.

The figure 7 shows a diagram of the separation of the upstream platform from the downstream platform of the adapter.

Figure 8 shows an adapter with spacecraft installed on it with isometric separation systems.

The proposed adapter contains a platform 1 (Fig. 1, 8) with attachment points (for example, brackets with bolted connections) 2 (Fig. 1) to the launch vehicle 3. The platform 1 is equipped with landing holes 4 (Fig. 2, 3) with the possibility fastening in them systems of separation 5 (Fig. 1) of spacecraft 6.

On the platform 1 from the installation side of the spacecraft 6 there are intersecting channels 7 (Fig. 2, 3), which form cells 8 of a square configuration. In each cell 8 there are four landing holes 4, equidistant from the channels 7, covering these cells 8.

Such a system of landing holes 4 provides the installation of separation systems 5 with spacecraft 6 of various sizes. For unification, the landing holes 4 in the cells 8 for fixing the systems of the compartment 5 are made of the same diameter (Fig. 2, 3). The number of landing holes 4 used for mounting a specific spacecraft 6 depends on the size and configuration of its separation system 5.

Pyrotechnic devices 9 (Fig. 4) are laid in the channels 7, which cover the landing holes 4 for fastening the closed-circuit space separation systems 5 of the spacecraft 6. Pyrotechnic devices 9 are made, for example, in the form of low-pulse detonating cords. Pyrotechnic devices 9, laid in channels 7 in a closed circuit, are closed with protective covers 10 (Fig. 2, 3, 4). The protective covers 10 are made elastic (quick-detachable) and installed in the grooves 11 (Fig. 4), made on the platform 1 on both sides along the channels 7. To ensure the free exit of the protective covers 10 from the grooves 11 (when pyrotechnic devices 9 are activated), the grooves 11 have wedge-shaped section (Fig. 4).

In addition, the protective covers 10 due to their elastic properties are in contact with the pyrotechnic devices 9, fixing (pressing) them in the channels 7 of the platform 1 from possible movement under the action of dynamic loads on the adapter (Fig. 4).

The configuration (in plan) of the closed loop for laying the pyrotechnic device 9 depends on the location of the landing holes 4 used for fastening the separation systems 5 of the spacecraft 6.

If the landing holes 4 used for fastening the spacecraft 6 are located in one cell 8 of the platform 1, then the pyrotechnic device 9 is laid in channels 7 along a closed circuit closest to the used landing holes 4, with the coverage of one cell 8 (Fig. 2) .

In some cases, to ensure the safety of a particular spacecraft 6, a closed loop laying pyrotechnic device 9 can cover (in plan) not only the landing holes 4 used to attach the separation system 5 of the spacecraft 6, but also the contour (in plan) of the spacecraft 6 , which, as a rule, exceeds (covers) the placement contour of the landing holes 4 for installing the separation system 5 of this spacecraft 6.

For spacecraft 6 having a separation system 5 with large dimensions and complex shape in plan, the used landing holes 4 are located in several cells 8, and the pyrotechnic device 9 is laid in channels 7 along the nearest external closed loop (ensuring coverage of all landing holes 4 used for fastening the separation system 5) with the coverage of several cells 8 (Fig. 3). Moreover, in the channels 7 located inside the closed loop, the pyrotechnic device (low-pulse detonating cord) 9 is not installed (does not fit).

The proposed adapter consists of a number of structurally identical platforms 1, sequentially mounted on the (lower) platform 1, mounted on the carrier rocket 3 by means of attachment points 2. Installation of the upstream platforms 1 on the downstream platforms 1 is carried out by means of support rods 12. Support rods 12 (Fig. 1, 8) are, for example, tubular section rods with upper and lower flanges 13 and 14 (Fig. 1, 7), respectively, through which the supporting rods 12 are attached to the platforms 1. The supporting rods 12 are provided with nodes once division 15 (Fig. 1). The separation nodes 15 are installed on the supporting rods 12 in the span between their fastening to adjacent platforms 1. The separation nodes 15 are, for example, pusher locks, which serve as both fastening means and separation means. When they are activated, the support rods 12 (Fig. 7) are divided into two parts: the upper part 16 (Fig. 7) of the support rod 12 is separated together with the upstream platform 1, the lower part 17 (Fig. 7) of the support rod 12 remains fixed on the downstream platform 1. Bearing rods 12 are installed in the center of the platforms 1 and attached (Fig. Fasteners are not shown conventionally) to the mounting holes 4 of the cells 8 located in the centers of the platforms 1 (Fig. 2, 3). The longitudinal axis of the supporting rods 12 coincide with the longitudinal axis of symmetry of the platforms 1.

On each platform 1, a reflective screen 18 is installed (Fig. 1, 7), fixed (Fig. 1, fasteners are not shown conventionally) along the outer contour of the platform 1. In the center of the reflective screen 18, a bushing 19 is installed (Fig. 1, 7), covering the supporting rod 12 below the node of its separation 15.

At the same time, the hole 20 (Fig. 7) in the bushing 19 on the reflective screen 18 (lower) of the platform 1, which is attached directly to the launch vehicle 3 by means of attachment points 2, is closed by a plug (not shown conventionally in Fig.).

The adapter is assembled in parallel with the installation and fastening of the spacecraft 6 to the adapter in the following sequence:

- the lower platform 1 with a reflective screen 18 pre-mounted on it is mounted on a technological stand (not shown conventionally in Fig.).

- the support rod 12 is installed, equipped with a separation unit 15, and its fastening to the lower platform 1 through the landing holes 4, made in the Central cell 8 of the lower platform 1;

- spacecraft 6 with separation systems 5 are attached through landing holes 4 to the lower platform 1 (forming the lower tier of spacecraft 6), pre-installed on the technological stand (not shown conventionally in Fig.);

- in the installation area of each spacecraft 6 in the channels 7 of the lower platform 1 (with coverage in terms of landing holes 4 for fastening its separation system 5), a pyrotechnic device 9 is placed and closed with protective covers 10 installed in the longitudinal grooves 11 of the lower platform 1 along its channels 7;

- an upstream platform 1 (with a reflective screen 18 pre-mounted thereon) is mounted on the support rod 12, structurally identical to the lower platform 1 (in this case, the bushing 19 of the reflection screen 18 covers the support bar 12 mounted on the lower platform 1);

- spacecraft 6 with separation systems 5 are installed on the upstream platform 1, forming another tier, similar to the installation of spacecraft 6 on the lower platform 1;

- in the installation area of each spacecraft 6 in the channels 7 of the upstream platform 1 (with coverage in terms of landing holes 4 for fastening its separation system 5), a pyrotechnic device 9 is placed and closed with protective covers 10 installed in the longitudinal grooves 11 of the upstream platform 1 along its channels 7.

If the adapter contains several upstream platforms 1 in the same sequence (similarly), the spacecraft 6 are installed, the pyrotechnic devices 9 are placed on the upstream platforms 1 and the adjacent platforms 1 are interconnected by means of support rods 12.

The adapter in horizontal or vertical position with installed spacecraft 6 is docked (attached) to the launch vehicle 3 by means of attachment points (for example, brackets with bolted joints) 2 located on the lower platform 1.

On the launch site of the launch vehicle 3, the spacecraft 6, in the docked position with the corresponding separation systems 5, are mounted on the platforms 1. The separation systems 5 of the spacecraft 6 are fixed to the platforms 1 through the landing holes 4 made on the platforms 1.

After putting into orbit, when a command is sent to the compartment, the spacecraft 6 are separated in a certain (predetermined) sequence from the launch vehicle 3 due to the operation of mechanisms, such as mechanical locks and pushers (not shown conditionally in FIG.), Separation systems 5 (FIG. 5 )

First, the spacecraft 6 mounted on the upper platform 1 is separated. In case of a failure in the supply or passage of an electric command to separate any spacecraft 6 or when its separation system 5 fails, for example, when mechanical locks are jammed (not shown conventionally in Fig. ) separation system 5, which led to the non-separation of the spacecraft 6 from the launch vehicle 3 (spacecraft 6 remains connected to the platform 1), a pyrotechnic device 9 is placed in the channels 7 of the boards Form 1 with coverage of the landing holes 4 of the separation system 5 of the non-detached spacecraft 6.

When the pyrotechnic device 9 is triggered (according to the sequence diagram for working with the non-separated spacecraft 6), the platform 1 is destroyed along the closed stacking path (along the packing perimeter) of the pyrotechnic device 9 in the channels 7 of platform 1. As a result of the pyrotechnic device 9 being activated and the platform 1 is destroyed, the spacecraft 6 the separation system 5 and part of the platform 1 is not connected with the non-destructible part of the platform 1 and is separated from it (Fig.6). The separated part of the platform 1 has a plan shape corresponding to the closed laying loop of the pyrotechnic device 9. The protective covers 10 covering the pyrotechnic device 9, when it fires, exit the grooves 11 of the platform 1, which is destroyed (shared) along the laying contour of the pyrotechnic device 9, and do not interfere separation of the spacecraft 6. After separation of all spacecraft 6 from the upper platform 1, the upper platform 1 is separated.

The separation of the upstream platform 1 from the downstream platform 1 (or lower platform 1) is carried out by triggering the separation unit 15 (made, for example, in the form of a pusher lock) located on the support rod 12 (the support rod 12 is divided into the upper part 16 and the lower part 17) installed between adjacent platforms 1 (Fig. 7). After the separation of the upstream platform 1, the separation of the spacecraft 6 is carried out, installed on the downstream platform 1 (or lower platform 1).

Thus, the proposed adapter device allows for the separation of spacecraft 6 from the launch vehicle 3 even if some spacecraft 6 does not separate from the launch vehicle 3 as a result of abnormal operation of their separation systems 5.

The presence of a reflecting screen 18 under (each) platform 1 protects the spacecraft 6 installed on the lower platforms 1, and the launch vehicle 3 when separating the spacecraft 6 using pyrotechnic devices 9, as well as when the separation units 15 are triggered when separating the upstream platforms 1 .

After separation of the spacecraft 6 from the actuation of the pyrotechnic device 9, its configuration will differ from the configuration after the standard separation (from the actuation of the separation system 5) due to the fact that its separation system 5 and the separated fragment of the platform 1 will be connected to the spacecraft 6, which will lead to a change in the mass centering and mass inertia characteristics of the spacecraft 6 as a whole. However, a change in the mass inertia characteristics compared to the mass inertia characteristics of the spacecraft 6 in the standard configuration will be insignificant and will not lead to a limitation of the operability of its systems or to a significant deterioration of the stabilization and controllability parameters of the spacecraft 6. Moreover, the separation of the spacecraft 6 together with the separation system 5 and part platform 1 by activating the pyrotechnic device 9 allows you to save the basic functionality of the spacecraft 6 and exclude to kill him with complete loss.

In the proposed adapter, the separation of spacecraft can be carried out in two ways with different levels of impact on the detachable spacecraft 6 and spacecraft 6, remaining fixed on the adapter. Therefore, in order to reduce the loads (impacts), the separation of spacecraft 6 installed on one platform 1 is advisable to carry out in the following sequence: first of all, from the operation of standard systems of separation 5 (with minimal impact on spacecraft 6), in the next turn (if unsuccessful an attempt to separate from operation the standard systems of separation 5) - with the use of pyrotechnic devices 9 (with possible dynamic loads on spacecraft 6).

The proposed adapter device for the installation of spacecraft allows you to:

- make a second attempt to separate the spacecraft from the launch vehicle to perform the target task (in the case of a failed first attempt to separate it through the standard system) by installing a backup pyrotechnic device;

- install and separate from the launch vehicle groups of identical spacecraft and spacecraft of different masses, dimensions, configurations, by performing on a structurally identical platform a universal "grid" of landing holes (places) for fastening spacecraft;

- it is more efficient to use (in height) the run-off space of the launch vehicle due to the tiered placement of spacecraft.

It should be noted that the most effective and popular is the use of the proposed device for group launch of small spacecraft.

Thus, the proposed adapter device for the installation of spacecraft has significant differences from previously known devices and allows you to expand the functionality and improve the operational characteristics of the adapter for the installation of spacecraft.

Claims (3)

1. An adapter for installing spacecraft containing a platform equipped with attachment points to the launch vehicle and landing holes with the possibility of installing spacecraft separation systems in them, characterized in that channels are formed on the platform from the spacecraft installation side to form cells on the platform surface square configuration, while in each cell of the platform there are four landing holes equidistant from the channels covering these cells, and in the channels of the platform enes pyrotechnic device to form their loops covering in terms of fitting holes into which installed spacecraft separation system, wherein the pyrotechnic device closed elastic protective covers mounted in grooves platforms disposed on both sides along the platform channels. 2. The adapter for installing spacecraft according to claim 1, characterized in that it is made up of a series of identical platforms connected in series by means of support rods fixed through the landing holes of the cells located in the centers of the platforms, while the support rods are equipped with separation units and their longitudinal axes coincide with the longitudinal axes of symmetry of the platforms, while the height of the supporting rods is made to exceed the highest height of the spacecraft in conjunction with the separation system mounted on geolocation platforms. 3. The adapter for the installation of spacecraft according to claim 2, characterized in that each platform is equipped with a reflective screen fixed along the outer contour of the platform from the side opposite to the installation on the platform of the spacecraft, while a bushing covering the carrier is made in the center of the reflective screen the bar below the node of its separation.

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