RU2688630C2 - Space platform - Google Patents

Abstract

FIELD: machine building.SUBSTANCE: invention relates to machine building, particularly, to space platforms. Space platform (SP) comprises structural frame of housing (SFH) composed of mesh structure made of composite materials, on which instrument compartment is arranged. Note here that SFH ends protrude beyond plane of instrument compartment panels. On ends of SFH there are assembling units with separation system and payload, and inside SFH there are tanks for working body storage for engines of correction, orientation and stabilization systems. Instrument compartment is made of interconnected panels, and some of them are radiator panels. Instruments and equipment of onboard service systems are arranged inside and outside the instrument compartment. Outside on instrument compartment there are: engines of orientation and stabilization system, assemblies with payload, rotary wings of solar battery (SB), folded in start-up state, fixed symmetrically on two opposite sides of instrument compartment by means of rods to devices of rotation of wings of SB, at that wings of SB are made in the form of flat panels attached to each other. Besides, SP comprises engines providing completion of geostationary orbit arranged outside the instrument compartment and capable of changing its position.EFFECT: higher platform power.7 cl, 4 dwg

Description

The invention relates to the rocket and space industry in the manufacture of spacecraft (SC).

The space platform (CP) is a structurally and functionally separate module that combines the service subsystems that ensure the work of the payload. In the process of creating a spacecraft, a gearbox is combined with a payload, which is also a structurally and functionally separate module. The payload combines the airborne repeaters, antennas and all other elements that directly provide the solution to the target task of relaying information of a specific spacecraft in accordance with the necessary requirements. Since each specific spacecraft has its own frequency plan <and service areas, and its own transponder has its own scheme, number of transponders and their energy characteristics, the payload for each spacecraft is unique. The problems solved by the KP are common for a number of similar class spacecraft of the same class, therefore it is a unified element common to the whole series and having standard output characteristics and interfaces. Only basic principles for constructing a payload and interfaces with gearboxes, which are the main condition for the possibility of creating a spacecraft based on one of the unified platforms, should be common to a number of similar types of spacecraft. The modular construction allows, within the framework of the standard KP design, to obtain various modifications that best meet the requirements of specific spacecraft created on the basis of the KP.

The unified structural base of unpressurized platforms is the power structure of the body (SCC) made in the form of a mesh structure made of composite materials, with installed on it:

- pivoting wings of solar batteries (BS);

- separation devices;

- storage tanks of the working fluid;

- instrument compartment, with instrumentation and equipment of service systems, propulsion systems (Space platform [Electronic resource]. - Access mode: https://ru.wikipedia.org/wiki/Kocmicheskaya_platform, free. - Title from the screen).

To provide easy integration with various payload modules (MPN) corresponding to different spacecraft, the control panel has simple and well-defined unified interfaces, including:

- mechanical interface;

- electrical interface;

- thermal interface;

- information interface.

The design and characteristics of the interfaces are universal and provide the possibility of integration with various types of spacecraft MPN, which meet the range of interface requirements of the platform.

All interfaces are located in the docking areas of the platform and payload, and they are easily accessible at all stages of ground operation.

To install the spacecraft on the inference engine, the control panel has a unified interface.

The interface with the launch vehicle is also used for docking with the ground transportation and process equipment during assembly, integration and testing of the platform and the spacecraft in general, as well as transportation and preparation at the launch site.

KP incorporates onboard systems capable of ensuring the functioning of the spacecraft at the site of launching into orbit, drift and installation at a given point of the orbit, and the fulfillment of targets during the service life:

- General management of all subsystems and equipment and interaction with the ground control complex;

- transfer of the platform from the starting configuration to the working one;

- orientation and stabilization of the spacecraft body with the required accuracy;

- retention of the spacecraft at a given point of the orbit with the required precision;

- formation of controlling forces and moments in the process of orientation, stabilization of the spacecraft and control of its movement;

- power supply of all subsystems of the platform and MPN in all modes of operation; -support of temperature regimes of all elements of the KP and MPN within the specified limits;

- maintaining all the elements of the spacecraft in the desired mutual position at all stages of operation and protection from external influences;

- ensuring the conduct of ground testing and testing of the spacecraft and its onboard systems, interaction with ground-based test equipment.

From the prior art known "Multi-purpose service platform for the creation of spacecraft" (patent for invention RU No. 2375267, B64G 1/10, B64G 1/22, published 12/12/2009), the platform contains a module of service equipment in the form of a rectangular parallelepiped board and four side boards. Inside there are two intermediate boards dividing the module into three compartments for service equipment. Antennas and devices of the orientation and stabilization system are mounted on the side plate. On one of the boards are mounted docking units with the separation system. The propulsion system is mounted in the area of the proposed center of mass. BS panels are mounted on brackets protruding beyond the module. The units of the installation MPN are located on the free ends of the side plates of the module and protruding brackets. Moreover, the devices of the target equipment of the payload are located in the space between the BS and the free zone of the module from the side of its open part.

The disadvantages of this technical solution are:

- restriction of the required maximum permissible mass of a spacecraft created on the basis of this KP-analogue;

- the impossibility of removing the spacecraft from the intermediate orbit to the desired one.

As the closest analogue (prototype), the “Space platform” was selected (patent for invention RU№2569658, B64G 1/00, published 11/27/2015), containing a CCM, made in the form of a spatial network structure made of composite materials, on which the instrument compartment is placed, formed from the panels fastened among themselves, and some of them are panels radiators. From the side of the instrument compartment, at the end of the CCM, docking units with the separation system are located, and inside the CCM there are tanks for storing the working fluid for the engines of correction systems (CK), orientation and stabilization (CAS). Inside and outside the instrument compartment there are instruments and equipment of service systems. Outside on the instrument compartment are placed: engines SK, SOS, units of installation of the module of the payload, rotating wings BS, folding in the starting state, fixed symmetrically from two opposite sides of the instrument compartment with rods to the devices turn, and BS wings are made in the form of flat panels, fastened together.

The basic composition of the KP prototype:

- design KP;

- onboard control complex (BKU);

- orientation and stabilization system;

- power supply system;

- correction system;

- thermal control system (CTP);

- navigation and motion control system;

- mechanical devices and design KP;

- onboard cable network.

A number of significant drawbacks characteristic of the prototype, is as follows:

- limiting the required maximum permissible mass of a spacecraft created on the basis of a given prototype KP;

- the impossibility of removing the spacecraft from the intermediate orbit to the desired one.

When creating a spacecraft based on the claimed KP, the main requirements are:

1. Increasing the energy and mass resources provided to the payload due to the introduction of a scheme and means of increasing the output of a spacecraft:

- the total mass of the spacecraft on the basis of this gearbox is up to 5,000 kg;

- payload power consumption - up to 18 kW;

- heat release of the payload - up to 10 kW.

2. The implementation of the stage of additional spacecraft delivery from the intermediate geo-transfer orbit to the operating point of the geostationary orbit (GSO) due to the use of electric propulsion engines.

3. The use of new, more efficient instruments, equipment and technical solutions of onboard systems.

4. Carrying out flight tests of onboard equipment, onboard systems and spacecraft in general throughout the entire active life (CAC) period in order to ensure debugging and prediction of any types of failures, subsequently ensuring the creation of reliable instruments.

5. SED - at least 15 years in the GSO.

6. The accuracy of the orientation of the associated axes of the spacecraft (roll, pitch, yaw - ± 0.07 °).

7. Accuracy of holding in a given orbital position (no more than ± 0.05 ° in longitude and latitude during the entire SAS).

The tasks addressed by the claimed technical solution are: improving the technical and operational characteristics of the gearbox, increasing the maximum mass of the spacecraft created on the basis of this spacecraft, the ability to reach the operational point of the spacecraft, increasing the functionality and power of the target spacecraft equipment.

Tasks are solved due to the fact that the claimed KP contains a CCM, made in the form of a mesh structure made of composite materials, on which the instrument compartment is located, with the ends of the CCM protruding beyond the plane of the instrument compartment panels. At the ends of the CCM there are docking units with a separation system and a payload, and inside the CCM there are tanks for storing the working medium for SC and SOS engines. The instrument compartment is made of panels fastened together, some of which are radiator panels. Instruments and equipment of onboard service systems are placed inside and outside the instrument compartment. Outside on the instrument compartment are placed: SOS engines, docking units with payload, BS turning wings folded in the starting state, fixed symmetrically from two opposite sides of the instrument compartment using rods to BS wing turning devices, with BS wings made in the form of flat panels, fastened together. The gearbox also contains engines providing dovdedevanie KA on GSO, located outside the instrument compartment, capable of changing their position.

Technical results provided by the above set of features are:

- an increase in the maximum permissible mass of a spacecraft on the basis of this KP due to the improvement of the CCM;

- dovvydevanie KA from intermediate orbit to the operating point of the GSO due to the use of engines of electro-jet propulsion;

- increase the functionality and power of the target equipment by increasing the maximum mass of the spacecraft;

- The creation of a universal platform super heavy class;

- reducing the time and cost of work on the adaptation of the spacecraft to the launch vehicles.

The claimed space platform is illustrated by drawings, which depict:

- in fig. 1 - general view (starting state of the gearbox in axonometric projection);

- in fig. 2 - general view (starting state of the gearbox in axonometric projection);

- in fig. 3 - a general view from below (starting state of the gearbox in axonometric projection);

- in fig. 4 - placement of storage tanks for working fluid for propulsion systems.

KP contains CCM 1, made in the form of a mesh structure made of composite materials, which houses the instrument compartment 2, while the ends of the CCM 1 protrude beyond the plane of the panels of the instrument compartment 2. At the ends of the CCM 1 are placed docking nodes 3, 10 with a separation system and a payload , and inside the CCM 1 there are tanks 4, 5 for storing the working fluid for engines 6, 7 SC, SOS. The instrument compartment 2 is made of panels fastened together, some of which are radiator panels 8. Instruments and equipment 9 onboard utility systems are placed inside and outside the instrument compartment 2. Outside on the instrument compartment 2 are placed: engines 7 SOS, docking units 10 with a payload, rotary wings 11 BS, folding in the starting state, fixed symmetrically from two opposite sides of the instrument compartment 2 using rods 12 to the devices 13 turning the wings 11 BS, and The wings of the BS 11 are made in the form of flat panels fastened together. KP also contains engines 14, providing dovdedenie spacecraft on the GSO, located outside the instrument compartment 2, able to change its position.

In order to improve and improve the specific characteristics of the spacecraft as a whole, the composition of the prototype KP was changed by replacing a part of the power supply equipment, the control center, the ICS with newer equipment, from other spacecraft manufactured by JSC “ISS”, and also upgraded the CCM.

Thus, the following composition of KP is determined, which meets the requirements for design:

- design KP;

- onboard control complex;

- power supply system;

- orientation and stabilization system;

- correction system;

- thermal control system;

- onboard cable network;

- BS mechanical devices;

- separation device.

KP design is designed:

- to accommodate and ensure the required interposition of the equipment of service equipment at all stages of ground and flight operations of the spacecraft;

- to ensure the necessary values of the levels of mechanical loading at all stages of manufacturing, ground and flight operation of the spacecraft;

- to accommodate the elements of the CTP, allowing to provide the necessary temperature of the seating surfaces of the equipment KP;

- to provide interfaces with antenna-feeder device;

- to provide interfaces with gearbox with overclocking unit (RB);

- to protect equipment KP from space factors.

KP is a structure consisting of a SCC with an instrument compartment fixed to it, formed of three-layer honeycomb panels interconnected by aluminum brackets. The ends of the CCM are equipped with frames. With the frame, located next to the instrument compartment is docked with the device branch (PP). With another frame is docked with the base panel MPN. Instruments and equipment KP are placed on the inside of the side dash panels, as well as outside on the base panels.

The launch mass of the spacecraft created on the basis of this gearbox is assumed to be 5000 kg. The increase in the mass of the spacecraft is due to the need to increase the capabilities of the payload (increase in the equipment of the payload, the introduction of large antenna systems). To meet the requirements for mechanical loads, a ground-based experimental testing of the SCC was developed and carried out, during which the weaving scheme was changed with enhanced strength and stiffness characteristics, which would also allow implementing the function of launching spacecraft from GPO to GSO.

Onboard control complex. The BKU is designed to control and monitor the spacecraft autonomously and jointly with the ground control complex. The experimental equipment developed for this gearbox includes on-board equipment of the command-measuring system manufactured by JSC “ISS”.

The BKU includes the following equipment:

- on-board digital computing complex (BTsVK);

- control unit BKU;

- block interface BKU;

- onboard equipment for remote signaling;

- programmable network switch;

- onboard instrumentation instrumentation system;

- block network filters;

- software.

The power supply system (BOT) solves the problem of providing power supply to the equipment of the onboard subsystems of the spacecraft with electric power of the required quality and power in accordance with the requirements of the energy budget at all stages of operation.

BOT includes the following equipment:

- solar battery;

- rechargeable battery;

- battery electronics unit;

- energy conversion complex;

- software BOT;

- onboard cable network.

Functionally, the BSE multicolumn current collector devices, structurally located in the BS rotational drives, which are an integral part of the AS, are also part of the EPB. The software implemented by the on-board computer is the main organizing element in solving problems of ensuring the functioning of the battery and performs the function of monitoring the state of the EPS.

The system of orientation and stabilization is created on the basis of the SOS KP prototype.

SOS is designed to solve the following tasks:

- conducting calm and initial orientation of the spacecraft from the moment the SOS is turned on until the transition to the normal triaxial stabilization mode;

- provision of three-axis spacecraft stabilization in the orbital coordinate system in accordance with the requirements for operation during the entire SAS, including during the orbit correction;

- ensuring the orientation of the BS wings to the Sun;

- provision of hardware solar orientation mode (PACO) - spacecraft survivability mode.

The main difference from the base SOS is the introduction of a new task - ensuring the orientation of the spacecraft for the required position of the thrust vectors of the engines at the stage of bringing to the GSO.

As an experimental instrument, it is proposed to use: a two-coordinate small-sized Sun sensor, a small-sized digital device targeting the Sun, an electromagnetic actuator, a solid-state wave unit measuring angular velocities, a new drive for the BS turning device. In addition to using the new equipment, an alternative method of unloading the electromechanical actuator of control flywheels using SC engines installed on turntables and the possibility of rejecting hydrazine engines in favor of a pneumatic system (nozzles on cold gas - xenon) for conducting initial modes and PACO are considered. The expected positive effect from the application of these innovations is the reduction of the mass of the spacecraft.

The SOS software is borrowed from the KP - prototype with changes in the part of working with the instruments and their functioning at the stage of completion of the spacecraft from the SCG to the GSO.

Correction system. The new equipment for the SC is following from the requirement for additional output and final mass of the spacecraft: electric propulsion system with a conversion and control system and the necessary reserve of the working body, ensuring the implementation of the stage of the spacecraft output. Otherwise, the IC uses standard solutions that have been tested on other satellites produced by JSC “ISS”. SC spacecraft should provide the following tasks:

- issue of impulses of impulse for docking of spacecraft from GPO to GSO;

- issuing thrust impulses for eliminating errors in bringing up the spacecraft and bringing the spacecraft into a given orbital position (can be combined with endurance);

- issuing thrust impulses to keep the spacecraft in a given orbital position during the service life with errors not exceeding the given;

- issuing thrust impulses to transfer the spacecraft from one orbital position to another;

- issuance of impulses for transferring the spacecraft into a disposal orbit after the completion of normal operation;

- issuing impulses for creating moments in accordance with the needs of the orientation and stabilization system during the entire period of regular spacecraft operation, including in spacecraft survivability modes.

SC for the tasks of completion and correction of the orbit has the following composition:

- high pressure fuel tank (with xenon) (one for the tasks of finishing and correction);

- xenon supply unit for engines;

- engines;

- conversion and management system;

- xenon supply unit;

- interblock pipelines;

- software.

Thermal management system. At KP, a combined PAGE is used, which includes a redundant combined fluid circuit (LC) in combination with heat pipes and augmented with controlled electric heaters and passive thermal control means. When constructing the CTP, the CP laid down such principles in the thermal control of the spacecraft, which would ensure the maximum heat dissipation capacity of the CTP 13,000 W at the lowest mass cost. On this basis, a combined MFR (hybrid scheme) is proposed, which includes the following principles:

- the use of new elements in the LCD: high-performance electric pump unit and a more technologically advanced and larger volume compensator volume;

- introduction to CTP of openable radiators for removal of excess heat flux;

- transfer of excess heat flux to open radiators should be carried out both with the help of liquid crystal and with the help of loop heat pipes;

- as a thermostatic coating on radiators of the CTP, a lightweight coating of optical solar reflectors should be used.

The use of this MFR allows you to create a spacecraft on its basis with a heat emission of up to 13 kW.

Mechanical systems

Mechanical devices (MU) of BS wings are designed to locate and install photovoltaic cells in the transport position and transfer them to the working position, as well as to bring the spacecraft into a working configuration in orbit.

The gearbox uses two mechanical devices of BS wings symmetrically located on both sides of the instrument compartment. The base case was taken the existing design MU BS KP prototype. For the spacecraft created on the basis of the claimed CP it is necessary to increase the area of the BS frames to 120 m ² .

When designing borrowed the following fundamental decisions:

- temperature interchanges;

- philosophy of checking and unscrapping;

- the order of disclosure;

- The basic construction of the hinge nodes and their zarekovki.

The BS bar is developed on the basis of the solutions implemented in the prototype KP rods. The package of BS panels differs from the package of BS panels of the KP prototype by the number of panels in the package and the size of the frames. The frameworks of the BS panels are made of carbon-fiber pipes, which have been tested according to the BS system qualification program and flight operation.

The prototypes of equipment introduced into the base composition of the KP will be able to obtain flight qualification, which will make it possible to eventually form the composition of a promising super-heavy space platform with reliable instruments, sophisticated technical solutions that have a modern level of development in the global space technology market. KP has the characteristics and resources for the payload, significantly surpassing the existing platform of the heavy class, such as Express 2000. At the same time, the possibility of implementing the stage of launching a spacecraft with a GPO to a GSO by means of an SC spacecraft allows you to create, on the basis of the designed gearbox, a wide range of heavy spacecraft. Thus, a scientific and technical reserve has been created for the formation of a super-heavy platform class.

Claims (7)

1. The space platform containing the power structure of the body (SSC), made in the form of a mesh structure made of composite materials, on which the instrument compartment is located, with the ends of the SSC extending beyond the plane of the instrument panel panels; load, and inside the SCC there are tanks for storing the working fluid for the engines of the correction, orientation and stabilization systems; the instrument compartment is made of panels fastened together, some of which are radiator panels; Instruments and equipment for onboard utility systems are placed inside and outside the instrument compartment; outside on the instrument compartment are placed: engines of orientation and stabilization system, docking units with payload, rotary wings of the solar battery, folded in the starting state, fixed symmetrically from two opposite sides of the instrument compartment using rods to devices of the solar wings turning, and a solar wing made in the form of flat panels bonded to each other, characterized in that the space platform contains engines that ensure the completion of the spacecraft a (s) in a geostationary orbit (DGES - engines driving to a geostationary orbit) located outside the instrument compartment, capable of changing their position. 2. Space platform according to claim 1, characterized in that one or more engines are used as DGSS. 3. The space platform according to claim 1, characterized in that ionic or plasma engines are used as DGSOs. 4. The space platform according to claim 1, characterized in that the vectors of the DGSOs pass through the actual center of mass of the spacecraft. 5. Space platform according to claim 1, characterized in that xenon is used as the working fluid of the DGSO. 6. Space platform under item 1, characterized in that DGSO use a working body intended for engines of the correction system. 7. Space platform according to Claim. 1, characterized in that the DGES are designed to control the angular position of the spacecraft.

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