RU213765U1 - Small-scale space platform - Google Patents

Abstract

The utility model relates to the field of space engineering, in particular to space platforms (SP), and can be used to create small spacecraft (SSC) for various purposes for operation in near-Earth orbits. Space platform consists of end plate +X (1), side plate +Y (2), side plate +Z (3), end plate -X (4), side plate -Y (5), side plate -Z (6 ) and frames (7). Housing panels (1-6) are a three-layer structure consisting of two aluminum alloy skins interconnected through a honeycomb in which heat pipes are embedded. The frame (7) is assembled from profiles of an angular (U-shaped) section using a bolted (riveted) connection without the use of welding. The platform additionally includes a central honeycomb panel (22) installed as a load-bearing structure inside the platform. For the target equipment, an area (37) is provided inside the body of the space platform. The technical result achieved by using this solution is to increase the speed of production of the space platform, without losing its reliability and efficiency. 1 w.p. f-ly, 7 ill.

Description

The utility model relates to the field of space engineering, in particular to space platforms (SP), and can be used to create small spacecraft (SSC) for various purposes for operation in near-Earth orbits.

Known universal spacecraft platform (PCA) (patent No. 2624764, IPC B64G 1/22, publ. on it with honeycomb panels for placing on them the equipment of only the service systems module (MSS), which includes the life support systems of the spacecraft, the ends of the SCM protrude beyond the plane of the MSS bases, and the upper end has docking nodes with the SCM of the payload module (MLN), which in Together with the docking nodes of the MSS panels and MLN panels, they ensure the integration of the mechanical interface of the spacecraft in the docking zone of the mechanical interface, in addition, on the outer side of the upper panel of the PKA, there are zones of docking of the electrical and hydraulic interfaces of the MSS with the MLN. At the same time, storage tanks for the working fluid for the propulsion system (PS) of the correction system (SC), storage tanks for the working fluid for the PS SOS, devices of the stabilization and orientation system (SOS), solar battery panels (BS), BS drives and partially PS and SOS are part of the SSC, but can be geographically located in the MLN zone, depending on the layout of the spacecraft and the position of the center of mass of the spacecraft.

The disadvantage of this technical solution is the complexity of the design, which requires significant labor costs for manufacturing, and the use of a cylindrical load-bearing structure leads to inconvenient placement of on-board equipment (BA), the shape of which is more like a parallelepiped.

A unified space platform of a modular construction principle is known (patent No. 2684877, IPC B64G 1/10, B64G 1/22, publ. 04/15/2019), made on the basis of the SCM in the form of racks. Inside the SKK there is a propulsion system with a tank (tanks) of the working fluid and a correction engine. An instrument compartment (OS) is mounted on the SKK, inside of which service systems are installed, and outside - wings of the solar battery. The software consists of basic and modifiable modules. On the basis of the latter, spacecraft for remote sensing of the Earth or communications can be created. All modules are made of honeycomb panels, which together form the body of the software. Each module separately is a service system that has its own set of on-board cable network, mechanical, electrical and other typical elements. The technical result is aimed at improving the reliability, manufacturability and versatility of the spacecraft.

The disadvantage of this technical solution is also the complexity of the design and the multiplicity of interfaces for docking, which is a significant factor affecting the reliability of the system.

Known space platform for small spacecraft (patent No. 132422, IPC B64G 1/10, publ. 09/20/2013), containing a leaky load-bearing body in the form of a parallelepiped of honeycomb panels with devices and instruments of service on-board systems located inside the body, including a chemical battery, and with a propulsion system located outside the body, a payload module fastening element and folding solar panels in the form of wings, consisting of root and end parts, equipped with nodes for turning them into the working position, the body being made of interconnected self-supporting thermally stabilized honeycomb panels with built-in frames and heat pipes, solar battery panels are located on the end parts of the wings and are made three-leaf with the possibility of unfolding the outer wings in a perpendicular direction relative to the direction of unfolding of both parts of the wings, the root parts of which are made in the form of spacers for installation The panels are in working position at a distance from the hull, units and devices of the service on-board systems, resistant to radiation and ultraviolet radiation, are installed on the outer surfaces of the hull, on one of the outer end planes of which the propulsion system and the transition element are rigidly fixed, and on the other the element is fixed attaching the payload module.

The main disadvantage of this technical solution is that the target equipment requires a separate module, which is connected to the block of service systems. This configuration requires a separate study of the module with the target equipment, in particular, a significant study of the thermal management system (COTR). The complex shape of the platform requires additional effort to develop a pattern of screen-vacuum thermal insulation (EVTI), which leads to the appearance of additional joints and seams that violate the thermal balance of the device.

The closest analogue is the space platform, on the basis of which the Earth remote sensing spacecraft was developed (patent No. 198739, IPC B64G 1/22, publ. 24.07.2020). The spacecraft consists of a frame, a side panel +Z, a side panel -Z, a side panel +Y, a side panel -Y, an end panel +X, an end panel -X, an onboard monitoring and control system (OBCS), a traffic control system (SUD ), power supply systems (EPS), SOTR, thermal catalytic control, target equipment in the form of a wide-angle multispectral complex for remote sensing of the Earth, a radar complex and a complex of diffractive optics. At the same time, the case panels are a three-layer structure consisting of two aluminum alloy skins interconnected through a honeycomb filler into which heat pipes are built; part of the surface of the panels, not intended for heat dissipation, is installed by EVTI. The BSCU includes an onboard central controller (OCC), an onboard radio engineering complex (BRK) with two radio transmitting devices and an antenna-feeder device, a telemetric measurement controller, a temperature control controller, a navigation and time controller, a receiving antenna device (AU), transmitting AU , AU navigation equipment. The SUD consists of electromagnets, optical solar sensors, a block for determining the coordinates of stars, flywheel control motors, as well as a complex of actuating and sensitive elements, including a universal multifunctional computer system (UMCS), single-axis angular velocity meters (SIA) and an analog magnetometer (MA). The SEP consists of a photovoltaic battery, a lithium-ion battery and an automatic control, management and regulation unit. SOTR includes film electric heaters, temperature sensors, a controller for measurements and regulation, pipes for thermal panels, thermal contour pipes, and heat pipes for on-board equipment. The design of the frame is a welded structure, consisting of frames and racks made of aluminum-magnesium alloy. Frames consist of beams and fittings welded together. The design of beams and racks is formed by milled channels, connected in pairs by welding. The fittings are also milled. After welding, the structure is subject to annealing and subsequent machining along six planes for the installation of honeycomb panels on them. After machining, the holes are cut for the installation of transitional titanium bushings, which are the places for attaching the honeycomb panels.

The main disadvantage of this technical solution is the laboriousness of manufacturing the supporting frame of the apparatus, in view of the need for milling, as well as the need to manufacture tooling for welding, annealing and subsequent machining.

The task to be solved by the claimed technical solution is to create a simple and efficient design of the space platform with support systems to accelerate the production of small spacecraft based on it.

The technical result achieved by using this solution is to increase the speed of production of the space platform, without losing its reliability and efficiency.

The specified technical result is achieved due to the fact that in a low-mass space platform containing a non-pressurized body, which consists of a frame, four side panels, two end panels, one central panel and brackets, an onboard monitoring and control system (BSCU), a motion control system ( SUD), a power supply system (PSS) and a thermal management system (SOTR), while the body panels are a three-layer structure consisting of two aluminum alloy skins interconnected through a honeycomb core, in which heat pipes are built, on the outer part of the surface panels designed to release heat into outer space, a thermoregulating coating is applied, and on the outer part of the surface of the panels not intended to release heat, screen-vacuum thermal insulation is installed, the platform also contains a thermal catalytic propulsion system (PS) operating on environmentally friendly m monopropellants, at least one engine of which is installed on the outer side of the upper end panel of the spacecraft, and the fuel tanks and fuel supply system are made in the form of a monoblock and installed on the inner edge of the upper end panel, the frame consists of metal profiles fastened together with using a bolted connection, while the automatic control, management and regulation unit (BAKUR) is installed on the lower surface of the central panel.

In addition, the frame profiles are fastened together with a riveted joint.

This design of the frame will improve manufacturability by eliminating the laborious process of milling and welding of components, welding of the frame as a whole, its annealing and subsequent machining, which will reduce the time spent on manufacturing serial small spacecraft based on the space platform.

The technical essence of the proposed technical solution is illustrated by the following drawings:

- in Fig. 1 shows a general view of the platform, a view on the +X, +Y, +Z panels;

- in Fig. 2 shows a general view of the platform, view on the panel -X, -Y, -Z;

- in Fig. 3 shows panel -X with platform frame;

- in Fig. 4 shows the external arrangement of the onboard equipment;

- in Fig. 5 shows panels -Y and -Z with the location of the BA equipment;

- in Fig. 6 shows panels +Y and +Z with the location of the BA;

- in Fig. 7 shows the volume for the target hardware inside the platform. Space platform consists of end plate +X (1), side plate +Y (2), side plate +Z (3), end plate -X (4), side plate -Y (5), side plate -Z (6 ), frame (7), BSCU, SUD, SEP, SOTR and thermocatalytic control. Housing panels (1-6) are a three-layer structure consisting of two aluminum alloy skins connected to each other through a honeycomb in which heat pipes are embedded. On the outer part of the surface of the panels, intended for discharging heat into outer space, a thermoregulating coating is applied, and on the outer part of the surface of the panels, not intended for discharging heat, EVTI is installed. SOTR includes film electric heaters, temperature sensors, pipes for thermal panels, thermal contour pipes. The frame (7) is assembled from profiles of an angular (U-shaped) section using a bolted (riveted) connection without the use of welding. Thermal catalytic control includes a distribution panel (8), an engine (9) with a nozzle and fuel tanks (10). The engine nozzle (9) is hidden by a cover (11) on the outside of the panel -X (4). Also installed on the -X panel (4) are solar panels (12), optical solar sensors (13), a transmitting antenna device (AU) (14) of the BSCU, AU (15) of navigation equipment, a receiving AU (not shown), a fluxgate analog magnetometer (16), and brackets with a transmitting AU (17) of the BSCU and an antenna (18) of a radio link for transmitting digital information are attached to the +X panel (1). The star trackers (19) are mounted so that their tops protrude from the +Y (2) and -Y (5) panels. The electromagnets (20) are installed on the outside on the +Y (2) and +Z (3) panels. Loop heat pipes (21) are also installed on each of the outer sides of the panels. The platform additionally includes a central honeycomb panel (22) installed as a load-bearing structure inside the platform. On the lower surface of the central panel (22) there is a block of automatic control, control and regulation (BAKUR) (23), an engine flywheel (24) and a uniaxial angular velocity meter (OIUS) (25). Under the center panel (22) on the -Y panel (5) is the lithium-ion battery (26). Above the central panel (22) on the -Z panel (6) there is a block of electronic magnetometers (27) and an engine flywheel (28). On the upper surface of the central panel (22) there are IMCS (29), a control multifunctional computer system (UMCS) (30), IMCS (31) and star trackers (19). Above the central panel (22) on the +Z panel (3) there is a data processing unit (32) and a remote control unit (33). Under the central panel (22) on the +Z panel (3) there is a BSCU block (34), and on the +Y panel (2) there is an onboard memory device (BZU) (35) and an onboard radio engineering complex (BRK) (36). The BSCU block (34) includes the BCC, the controller for telemetry measurements, the controller for battery charge and power distribution, the temperature control controller and the navigation and time controller. For the target equipment, an area (37) is provided inside the body of the space platform.

The space platform works as follows.

According to the provided average daily power consumption (table 1), 130 W is allocated to the target equipment, provided that the equipment for inter-satellite communication is organized on board.

The possible composition of the BA of the space platform with an indication of the mass of individual blocks is presented in Table 2.

The selection and installation of target equipment is carried out, for the operation of which sufficient power consumption is ensured, as well as weight and size characteristics are satisfied. Optoelectronic equipment (OEA) can be used as target equipment. To an orbit with an average altitude of 500 km, automatically, after the sensor of the contact of separation from the launch vehicles is triggered, using the RIMS (29), UMVS (30), magnetometers (16, 27), optical solar sensors (13), star sensors (19), complex flywheel control motors (24, 28), electromagnets (20), the spacecraft is brought into a uniaxial solar orientation and the panels of the photovoltaic battery (12) are unfolded. Upon receipt of a flight task for the next session of operation of the BSCU equipment, the spacecraft provides the supply voltage to the OEA installed in the area (37), the BZU (35) and the DBK (36) involved in this session.

The Earth remote sensing equipment is controlled according to the program-time principle. The supply voltage to the main or backup power supply units of the corresponding components of the equipment is carried out by the BSCU, which provides the issuance of arrays of control parameters and the receipt of operational control information via the CAN 2/0V control interface.

At the end of the period of the active existence of the spacecraft, according to the program stored in advance in the memory of the BSCU, with the help of a complex of control motors-flywheels, the spacecraft is transferred to the solar orientation. Then, at a predetermined moment of time, the remote control is turned on, which works for the time necessary to issue a braking impulse, and the spacecraft switches to the flight path to the Earth and burns up in the dense layers of the atmosphere.

Claims (2)

1. Small-sized space platform containing a non-pressurized body, which consists of a frame, four side panels, two end panels, one central panel and brackets, an onboard monitoring and control system, a motion control system, a power supply system and a thermal management system, while the panels The housings are a three-layer structure consisting of two aluminum alloy skins connected to each other through a honeycomb core, in which heat pipes are embedded, a thermoregulating coating is applied on the outer part of the panel surface, designed to dump heat into outer space, and on the outer part of the panel surface , not intended for heat dissipation, screen-vacuum thermal insulation is installed, and the platform also contains a thermal catalytic propulsion system operating on environmentally friendly monopropellants, the engine of which is installed on the outer side of the upper end panel of the spacecraft. the fuel tanks and the fuel supply system are made in the form of a monoblock and installed on the inner edge of the upper end panel, characterized in that the frame consists of metal profiles fastened together by means of a bolted connection, while the control, control and regulation automation unit mounted on the bottom surface of the center panel. 2. Small-scale space platform according to claim 1, characterized in that the frame profiles are fastened together using a riveted joint.

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