RU2428358C1 - Space head for group launch of satellites - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention relates to rocketry. Space head for group launch of satellites comprises adapter module for docking to rocket last stage, satellite attachment module and nose cone. Individual launch units are added made up of platform, instrument module and engine, to be docked to each satellite by means of pyro bolts. ^ EFFECT: possibility to launch both low- and high-orbit satellites by one rocket. ^ 2 dwg

Description

The proposed space warhead (KGCH) relates to the field of rocket and space technology and can be used in the construction of the corresponding launch vehicles.

Known KGCH containing the upper stage, the head aerodynamic fairing, the adapter for group launch of satellites and satellites located on the adapter. The upper stage (RB) is designed to bring the spacecraft into the target (working) orbit with the fulfillment of the requirements for orientation and accuracy of launch and is used when the energy characteristics of the launch vehicle do not allow the spacecraft to be delivered directly to the working (target) orbit. RB consists of a compartment of a propulsion system, an instrument compartment and a transition system. The instrument compartment is located above the propulsion compartment. To fix the satellites on the upper power frame of the instrument compartment, a transition system consisting of an adapter and a separation system is attached. RB is made according to the suspension scheme and suspended inside the transition compartment. The head aerodynamic fairing is attached to the instrument compartment [1]. This design of the KGCH with the upper stage leads to a decrease in the area of the payload, and also does not provide the simultaneous launch of high-orbit and low-orbit spacecraft in their orbits.

Also known KGCH containing a frame on which two spacecraft are sequentially installed with the installation of the upper spacecraft on the lower [2]. The disadvantages of this type of KGCH are the small area for placing the spacecraft under the head fairing and the need for compatibility of spacecraft by mechanical and electrical interfaces (in this case, the lower spacecraft should be further developed or developed taking into account the installation of the upper spacecraft on it).

The closest in technical essence to the proposed OGF is the OGC for single and group launches of satellites, containing a head aerodynamic fairing, an acceleration unit located under it, consisting of a propulsion unit compartment, a fuel compartment and an instrument compartment fixed above it, an adapter for installing satellites around the acceleration unit , adapter for installing a single satellite located above the upper stage, transition compartment for docking with the last stage of the upper stage launch vehicle Utniki [3]. In this case, the adapter for installing satellites is made in the form of an annular platform and is located in the upper part of the upper stage around its instrument compartment. On the annular part of the adapter, mounting holes are made for installing satellites around the booster block, and in the area of the instrument compartment of the booster block, mounting holes are made on this adapter for installing a single satellite adapter located above the booster block. The ring adapter contains a docking frame, with which it is mounted on the upper docking frame of the adapter compartment, and the booster block is suspended inside the adapter compartment using nodes mounted on the instrument compartment of the accelerator module and on the adapter compartment. At the joints of the frames of the transition compartment and the ring adapter and the transition compartment and the booster unit, damping elements are installed. This KCH was taken as a prototype.

The disadvantages of this technical solution are:

1. A large mass of the booster block (especially with an increase in the number of spacecraft launched by one launch vehicle) and, as a result, an increase in the structural mass of the fastening elements and the transition compartment.

2. A small area for spacecraft placement due to the large overall dimensions of the fuel tanks of the main engine of the booster block, which leads to a reduction in the number of satellites during group launch.

3. The lack of the ability to simultaneously launch multiple spacecraft on different remoteness of the working orbit.

For these reasons, the use of this Oscillator is ineffective for group launch of satellites of different purpose, weight and dimensions of one LV.

The aim of the present invention is to provide a design of the OGG capable of launching several spacecraft (both low-orbit and high-orbit) into various orbits and at different points in space to construct a constellation of satellites included in a multi-purpose space system.

To achieve the goal set in the present invention, it is proposed to use individual launch units (BIV), which are docked to each spacecraft, instead of the booster block. BIV consists of a platform unified for mounting spacecraft of various design, instrument compartment and propulsion system (DU) with a marching engine (MD), which creates the main part of the axial thrust impulse, and an orientation and stabilization engine (DOS), creating control forces across all channels control and corrective impulse of axial thrust.

Thus, the composition of the proposed KGCH with BIV includes a transition compartment for fastening the KGCH assembly to the last stage of the launch vehicle, an adapter mounted on the transition compartment and designed for electrical and mechanical docking of the payload (SC with BIV) with the LV, the head fairing and space devices with docked blocks of individual output.

Withdrawal of spacecraft from BIV to near-Earth orbits is possible using two schemes:

1. According to a continuous scheme (launch to low orbits): the remote control is turned on immediately after separation.

2. According to the scheme with a delay (launch to high orbits): after separation from the adapter, spacecraft with BIV are in a stabilized passive flight. Stabilization is carried out due to the engine orientation and stabilization. Upon reaching the apogee of the transitional orbit, the MD is turned on and the vehicle is extended to the required circular orbital speed. Upon reaching the required circular speed, the spacecraft is separated, and the BIV is removed from orbit using a propulsion system.

A comparative analysis with the prototype showed that the present invention is distinguished by the presence of individual launch units docked to various spacecraft, consisting of a platform unified for fastening spacecraft of various design, instrument compartment and propulsion system with a marching engine and an orientation and stabilization engine.

The presence of this distinguishing feature determines the conformity of the proposed technical solution to the criterion of "novelty."

As a result of the patent search, prior to the filing date of the application, no technical solutions have been identified that have characteristics that are identical to the whole set of essential features contained in the proposed application, which indicates the inventive step of the proposed technical solution.

Figure 1 presents a diagram of the KGCH with BIV. The proposed KCH contains a transition compartment (2), designed to ensure the docking of the KCH assembled with the last stage of the launch vehicle (1). An adapter (3) is installed on the platform of the transition compartment, which provides fastening in the KGCH of various spacecraft configurations (5) in one or several tiers. Electrical and mechanical docking to the adapter is carried out using pyrodevices designed for quick and simultaneous separation of the spacecraft from the BIV on the launch trajectory. The head fairing (6) is attached to the transition compartment. Structurally, the head fairing consists of two flaps made of a metal sheet with transverse and longitudinal power sets, which are opened and dumped by means of pushers and pyro locks outside the dense layers of the atmosphere. The individual excretion unit (4) is docked to the spacecraft using explosive pyro-bolts.

Figure 2 shows the SC and BIV in the undocked state. BIV consists of a platform (7), which is a metal structure consisting of a cylindrical shell, closed by end frames. On the side surface of the platform there is a mount to the KGCH adapter. The BIV platform is universal, which is ensured by the presence of various attachment points on its end surface. Using explosive pyro-bolts, a spacecraft is attached to these nodes (5). A connector is mounted on the platform frame, which provides communication between the BIV control system and the spacecraft control system and which is disconnected by the pyrodevice on command from the BIV control system. Inside the platform there are cable networks of pyrodevices, transitional connectors and communications of the spacecraft control system. The other side of the platform is docked with the housing of the instrument compartment (8). The body of the instrument compartment (ON) of the BIV is made of aluminum alloy in the form of a wafer-type shell closed by end frames. Spherical bottoms are welded to both frames from the ends of the software. In the sealed internal volume of the software are located: control system equipment, power sources and electrical connectors of the BIV control system with the onboard missile control system. The instrument compartment is connected to the propulsion system compartment (9), which includes a mid-flight engine (11) with a fixed nozzle that provides a “pushing” driving pattern, and an orientation and stabilization engine (DOS) with four rotary nozzle blocks of transverse thrust (10) . The distribution of thrust between the nozzles is carried out by controlled electromagnetic valves by commands from the BIV control system.

KGH operates as follows. At the end of the operation of the mid-flight engine of the last stage of the launch vehicle, a command is simultaneously issued to trigger the pyro locks of the attachment to the adapter of all SCs with BIV and they are separated to a safe distance, after which each SC with BIV begins an autonomous flight. A few seconds after separation from the adapter, the DOS is turned on and the spacecraft is rotated from the BIV in a given direction. After the turn, the cruise engine is turned on, which works with multiple switching on according to a given program to launch the spacecraft into orbit. During the entire duration of the operation of the marching engine, a DOS also operates, which controls the spacecraft with BIV along the pitch, yaw and roll channels, compensating for the accumulated deviations of the kinematic parameters at the time the last stage of the launch vehicle is completed, and also ensuring the execution of the flight program. In the working orbit, at a given point of launch, the spacecraft is oriented in the necessary direction, it is dashed to the required circular orbital speed, and upon the command to use explosive pyrozones, the BIV is undocked from the spacecraft and removed from the spacecraft’s orbit using a propulsion system.

Literature

1. “Cosmonautics News”, Volume 10, No. 7 (210), 2000, p. 43.

2. “On the prospects for the commercial use of the Titan 34D rocket” ”“ Missile and space technology ”, TsNTI, No. 42 (1251) 1983, p. 11.

3. RF patent No. 2293689 "Space warhead for single and group satellite launches."

Claims (1)

A space head for a group launch of satellites, comprising a transition compartment for docking with the last stage of the rocket, an adapter for attaching satellites and a head fairing, characterized in that individual launch blocks are inserted that are connected to each satellite using explosive pyrotechnic bolts, consisting of a platform, an instrument compartment and propulsion system.

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