RU2271317C1 - Spacecraft and jet engine module - Google Patents

Abstract

FIELD: construction of spacecraft and arrangement of engine plants on them.

SUBSTANCE: proposed spacecraft includes load-bearing cylindrical body of central compartment with radial sheathing panels connected to it. Mounted on "north" and "south" sides of spacecraft are thermal panels for payload instruments and spacecraft service systems. Solar batteries are mounted on their outsides. Connected to central compartment on "zenith" and "ground" sides of spacecraft are package panels. Connected to package and thermal panels and to sheathing panels on " west" and "east" sides of spacecraft are engine panels. Mounted symmetrically on engine panels are sections of engines of equal thrust. Each section includes electrical jet engine (traction engine, for example stationary plasma engine) and gas jet engine (for dampening spacecraft after separation and relief of flywheels). Lines of action of engine thrust are inclined at different angles relative to spacecraft body axes and are shifted relative to center of mass of spacecraft.

EFFECT: possibility of using proposed spacecraft with engine module as accompanying payload at twin injection into space of main payload.

5 cl, 7 dwg

Description

The invention relates to space technology and can be used in the development of spacecraft and their propulsion systems, in particular to spacecraft, designed for continuous round-the-clock relay of information flows for various purposes in the satellite communications and broadcasting systems.

The prior art spacecraft (SC), containing a cylindrical body of the Central compartment, panels for mounting equipment, propulsion system, control system, solar panels, antennas, batteries (see, for example, US patent No. 5979833, CL 244 / 158 R, B 64 G 1/00, dated 09.11.99).

A jet engine block is also known from the prior art, comprising equally-drawn sections of electric jet engines mounted equally in two planes equidistant from the base plane Y0Z with the axes Y and Z of the associated coordinate system placed therein and parallel to this base plane, angled to the aforementioned the Y and Z axes and the lines of action of the rods displaced relative to the center of mass of the spacecraft (see, for example, RF patent No. 2142461, class B 64 G 1/26, 1/24, 1/40, dated 12.11.97).

The disadvantages of these prototypes include the following. For example, the well-known spacecraft is not adapted to install a more powerful payload on it (from the side of the head part) without its additional rather serious refinement, because its body of the central compartment is designed for installation of tanks of the propulsion system inside the cylinder and is not intended to carry this more powerful additional, and maybe even the main, load. Also, console fixing of dashboards will not allow to provide the required levels of stiffness for some spacecraft equipment. An open, external arrangement of instruments will require additional measures and mass for the organization of micrometeorite, radiation and electrostatic protection of electronic and other spacecraft equipment.

As for the propulsion system (jet engine block), in the known block all control efforts and moments are created due to only electric jet engines, which is not always efficient, fast, accurate and economical during the operation of the spacecraft in orbit.

The objective of these inventions is to create a spacecraft and a block of jet engines to it with the achievement of a technical result in the form of the ability to use the claimed spacecraft in the form of a passing load with the joint launch of the main payload into space, as well as expanding the arsenal of technical equipment for a specific purpose.

The solution to this problem is achieved by the fact that in a spacecraft containing a cylindrical body of the central compartment, panels for mounting equipment, a propulsion system, control system, solar panels, antennas, batteries, in accordance with the invention, to the housing of the central compartment performing the function of a power element providing the transfer of loads from the main payload to the upper stage at the withdrawal section, four auxiliary connections are connected from the outside along the generatrices of the cylinder e-wiring panels to increase the rigidity of the spacecraft structure and for additional mounting on the ends of the motor panels at their ends distant from the cylindrical body, all panels of the spacecraft are made three-layer on the basis of aluminum sheets, two instrument panels are made with the function of thermal panels, thermal panels are connected to the central compartment of the spacecraft along two planes of stabilization opposite to the axis of the central compartment, forming the "northern" and "southern" spacecraft panels, aggregate panels are connected to the central compartment ku - one in the plane of the technological junction of the spacecraft with the transition system, forming an “anti-aircraft” panel, and the other in the plane below the plane of the technological junction of the spacecraft with the payload separation device, forming the “earth” panel, the motor panels are attached to auxiliary radial panels - sewing on the central compartment and aggregate panels in planes perpendicular to the aggregate panels and perpendicular to the thermal panels, respectively, from the "western" and "eastern" sides, and made in the form of strips, parallel axes of the spacecraft, between which a zonal disclosed antenna of the onboard repeater is installed on the spacecraft’s central compartment, and on the engine panels themselves, the jet engine blocks are fixedly mounted in sections located in two parallel planes equally spaced from the center of mass, each engine section includes a gas engine and traction module based on a stationary plasma engine, the axis of the chambers of which are located at different angles to each other, modular and thermal panels, with an external Rhone from the heat panels are placed solar panels on the inside of the thermal panels payload payload instruments are placed, and the inside of the heat panels are placed side service equipment service of the spacecraft systems and motors, flywheels.

At the same time, locks and pushers installed on the transitional system are interfaced with structural elements on the cylindrical part of the spacecraft’s central compartment to provide access to them from the inside of the transitional system and the spacecraft’s central compartment, heat pipes can be glued over the entire area of the payload thermal panel, and rechargeable batteries are installed on the aggregate "earth" panel along the plane of installation of the thermal panel of the payload with the ability to move the batteries to adjust the center position masses of spacecraft.

The solution to this problem is also achieved by the fact that in the block of jet engines containing equal-draft sections of electric jet engines installed equally in two planes equidistant from the base plane Y0Z and parallel to the base plane with the axes Y and Z of the associated coordinate system with directional at an angle to the said Y and Z axes and displaced by the thrust action lines relative to the center of mass of the spacecraft, in accordance with the invention, the engine sections are mounted on auxiliary radars In addition to electric jet engines, in each section, in addition to electric jet engines, a gas engine with a thrust action line directed at an angle to the Y and X axes of the associated coordinate system is additionally installed, with the following installed: electric jet engines with the function of generating thrust impulses for orbit correction and unloading of flywheel engines, and gas engines with the function of generating thrust impulses when damping residual angular velocities after separation of the spacecraft from the upper stage, unloading of flywheel engines before starting the operation of electric jet engines and in emergency cases.

The invention is further explained using the accompanying graphic materials.

Figure 1 presents the claimed spacecraft in disassembled form (main elements); figure 2 presents the KA - configuration when displayed in the composition of the space head part (KGCH); figure 3 - presents the working (orbital) configuration of the spacecraft; figure 4-6 presents certain types of spacecraft, allowing better to understand the essence of the invention; 7 shows the layout of gas engines and traction modules relative to the associated coordinate system.

The spacecraft will restrain the cylindrical body of the central compartment 1 with four auxiliary radial panels-covers 2 attached to the body from the outside along the generatrix of the cylinder of the body.

Two dashboards are installed along two opposite planes of stabilization relative to the axis of the central compartment, which act as thermal panels, forming the "northern" and "southern" spacecraft panels: the "northern" panel is the service side thermal panel 3 for accommodating service board instruments and equipment and the southern "payload thermal panel 4 for placement of payload instruments and equipment.

Aggregate panels are connected to the central compartment - one in the plane of the technological interface of the spacecraft with the transition system, forming an “anti-aircraft” panel 5, the other in the plane below the plane of the technological interface of the spacecraft with the separation device 6 of the main payload, forming the “earth” panel 7.

To the aggregate and thermal panels in planes perpendicular to the aggregate panels and thermal panels, as well as to the auxiliary radial panels-stitching of the central compartment, from the "western" and "eastern" sides attached motor panels 8, made in the form of strips parallel to the axis of the spacecraft.

Between the engine panels in the central compartment of the spacecraft, a zonal disclosed antenna of the onboard repeater (BRTK) 9 is installed. The engine sections 10 are fixed on the engine panels, each engine section includes a gas engine 11 (for example, K10P) and a traction module 12 based on a stationary a plasma engine (for example, SPD-70), the axis of the chambers of which are located at different angles to each other, aggregate and thermal panels (see figure 5, 6).

On the outside of the thermal panels are solar panels 13.

On the inside of the heat panel of the payload, payload devices are placed, and on the inside of the heat panel of the service side there are devices of the spacecraft service systems.

Locks and pushers installed on the transition system 14 are interfaced with structural elements on the cylindrical part of the central compartment of the spacecraft with access to them from the inside of the transition system and the central compartment of the spacecraft.

Heat pipes are glued over the entire area of the payload thermal panels.

On the aggregate "earth" panel along the plane of installation of the thermal payload panel mounted batteries 15 with the ability to move the batteries to adjust the position of the center of mass (CM) of the spacecraft. The flywheel engines 16 are installed on the heat board of the service board.

Jet engines mounted on a spacecraft make up a block of jet engines containing equal-draft sections, each of which includes an electric jet engine (traction module) and a gas engine. These sections are installed equally in two planes equidistant from the base plane Y0Z and parallel to the base plane with the Y and Z axes of the associated coordinate system with the action lines of the thrusts of electric jet engines (traction modules) directed at an angle to the said Y and Z axes and under angle to the X and Y axes with the action lines of the thrusts of gas engines.

The action lines of the thrusts of all jet engines are shifted relative to the center of mass of the spacecraft (see figure 5-7).

The following were installed: electric jet engines with the function of generating thrust impulses during orbit correction and unloading of the spacecraft flywheel engines, and gas engines with the function of creating thrust impulses when damping the residual angular velocities after separating the spacecraft from the booster booster block, unloading the flywheel engines to start-up of electric jet engines and in emergency cases.

The operation of the said spacecraft with the jet engine block installed on this apparatus is performed, for example, as follows.

After launching the launch vehicle into orbit of the spacecraft as a part of the KCH, along with the main payload and separation of the main payload, the spacecraft is separated from the upper stage of the launch vehicle. After separation, the spacecraft damps the residual angular velocity (stops its rotation relative to all axes) and stabilizes with the help of flywheel engines. At the same time, the flywheel engines are unloaded with the help of gas engines, which continues after the spacecraft is stabilized until the flywheel engines are completely unloaded. During stabilization, flywheel engines create control moments around all the SC axes (relative to the SC center of mass). Gas engines are switched on in pairs to create unloading moments (rather than control moments) and unload the flywheel engines. The installation scheme of gas engines (see Fig. 7) allows you to create moments of unloading relative to all the axes of the spacecraft, even if one gas engine fails. Before turning on the electric jet engines, the unloading of the flywheel engines occurs with the help of gas engines. After turning on the electric jet engines, gas engines are not used in the further operation of the spacecraft, except in emergency situations.

After the electric jet engines are ready for operation, the spacecraft performs orbit correction and switches to the required position in the orbit with the help of traction pulses issued by the electric jet engines. Maintaining the required position in orbit - correcting the orbit (both in latitude and longitude), as well as unloading the flywheel engines using electric jet engines (traction modules). The installation diagram of these engines (see Fig. 7) allows for simultaneous orbit correction and unloading of flywheel engines, creating unloading moments around the Z and Y axes of the spacecraft, which allows more efficient use of the fuel supply. The unloading moment around the X axis is created separately from the orbit correction.

For example, by issuing traction pulses by two traction modules located on the side of the spacecraft Z and X axis (see Fig. 7), the orbit is corrected in latitude and the moment of unloading is created around the spacecraft's Y axis. By alternating the inclusion of the corresponding pairs of electric jet engines and selecting the appropriate duration of each pair, the required corrective impulse is provided and the flywheel engines are unloaded in the K and Y channels. In this case, stabilization of the spacecraft relative to the center of mass is carried out by flywheel engines.

Thus, the spacecraft has three different types of engines, each of which is used for its own purposes.

Flywheel engines are used to create control moments around the axes of the associated coordinate system (relative to the center of mass) at all stages of the spacecraft flight. These engines do not spend fuel during operation and do not affect the spacecraft’s own external atmosphere, and are also capable of very accurately fulfilling the required control torque of various sizes.

Gas engines are used to unload flywheel engines in the initial portion of the spacecraft flight before turning on the electric jet engines. These motors create a fixed moment of discharging torque, do not require large electric power for operation, and can be used when solar panels are not directed at the Sun. Also, these engines can be used to control spacecraft in emergency situations.

Electric jet engines (traction modules) are used to correct the orbit and unload the flywheel engines. These engines require significant electrical power for their operation and therefore are used only when there is power from solar panels. Electric jet engines have a very high specific impulse, which allows you to perform orbit correction with minimal fuel consumption. The instability of the engine thrust in size and direction, as well as some other characteristics of the engine make it difficult to use as a device that creates control moments for stabilization of the spacecraft.

Claims (5)

1. A spacecraft containing a cylindrical body of the central compartment, panels for mounting various equipment, a propulsion system, a control system, solar panels, antennas, batteries, characterized in that the housing of the central compartment, made with the function of a power element for transmission on the site removal of loads from the main payload to the booster block, four auxiliary radial panels-sewing are attached from the outside along the generatrices of the cylinder to increase stiffness the design of the spacecraft and for mounting on their remote ends of the motor panels, all the spacecraft panels are made three-layer on the basis of aluminum sheets, two dashboards are designed as thermal panels, while the thermal panels are connected to the central compartment along two opposite to its axis to the stabilization planes, forming the "northern" and "southern" sides of the spacecraft, the aggregate panels are connected to the central compartment: one in the technological plane the junction of the spacecraft with the transition system, forming the “anti-aircraft” panel, and the other in the plane located below the plane of the technological junction of the spacecraft with the main payload separation device, forming the “earth” panel, the motor panels are attached to the indicated radial wiring panels and aggregate panels in planes perpendicular to the aggregate and thermal panels respectively from the "western" and "eastern" sides, and are made in the form of strips parallel to the axis of the spacecraft, and between In the central compartment, the zonal disclosed antenna of the onboard repeater is installed in the central compartment, and the jet engine blocks are mounted on the engine panels motionlessly by sections located in two parallel planes equally spaced from the center of mass of the spacecraft, with each section including a gas engine and a traction module based on a stationary plasma engine, the axis of the chambers of which are located at different angles to each other, aggregate and thermal panels, solar panels are placed On the outside of the heat panels, on the inside of one of the heat panels are placed payload devices, and on the inside of the other heat panel are devices of the service systems of the spacecraft and flywheel engines. 2. The spacecraft according to claim 1, characterized in that the locks and pushers mounted on the transition system are associated with structural elements on the cylindrical part of the central compartment of the spacecraft with access to them from the inside of the transition system and the central compartment of the spacecraft. 3. The spacecraft according to claim 1, characterized in that heat pipes are glued over the entire surface of the payload thermal panel. 4. The spacecraft according to claim 1, characterized in that the batteries are mounted on an aggregate "earth" panel along the plane of installation of the thermal payload panel with the ability to move the batteries to adjust the position of the center of mass of the spacecraft when installing the engines. 5. The jet engine block of the spacecraft according to claim 1, comprising equally-drawn sections of electric jet engines installed equally in two planes equidistant from the base plane (YOZ) of the spacecraft and parallel to this plane, the thrust lines of these engines being directed at an angle to the axes Y and Z of the associated coordinate system and are displaced relative to the center of mass of the spacecraft, characterized in that the said sections are mounted on auxiliary radial panels-covers, while in each section, in addition to electric jet engines, is additionally installed along a gas engine with a thrust action line directed at an angle to the Y and X axes of the associated coordinate system, where the X axis is perpendicular to the specified reference plane, while the electric jet engines are capable of generating thrust impulses for orbit correction and unloading the flywheel engines of the spacecraft, and gas engines with the possibility of creating thrust pulses for damping the residual angular velocities after being separated spacecraft from the booster block of the launch vehicle, for unloading flywheel engines before the start of operation of electric jet engines, as well as for use in emergency cases.

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