RU2640167C1 - Multifunctional space craft - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to equipment OF multifunctional space crafts (MSC), designed for calibration and alignment of radar stations (RS) and Earth's remote sensing (ERS). The MSC contains a housing with an instrument compartment, a propulsion system, orientation and stabilization systems, a thermal conditioning system, solar batteries. The housing of MSC is made in the form of a cube or a straight prism. On one of the facets of housing there is a V-shaped groove or a recess in which a corner reflector made of two flat plates is fixed. In MSC an additional module of equipment is introduced: target, transmitting, command radio link, navigation (for GLONASS and/or GPS systems) and other service systems.EFFECT: empowerment of multifunctional spacecraft by providing it with functions of orbital platform-carrier of tools for research of reflection characteristics of the atmosphere and ionosphere of the Earth, remote sensing of the Earth in optical or infrared range, enhancing the sustainability of corner reflector to thermal deformations.9 cl, 6 dwg

Description

Multifunctional spacecraft (MCA).

The invention relates to the design and equipment of spacecraft designed for calibration and alignment of radar stations, as well as remote sensing of the Earth (RS) in the optical and / or infrared range.

There are various versions of spacecraft (SC) designed for calibrating radar stations, for example, a spherical spacecraft with a reference reflective surface [1] p. 47-49. In the USA, starting in 1964, standard spherical artificial Earth satellites were launched to calibrate the radar [2] p. 37. In the USSR, Typhoon-2 spacecraft were created and used at various time periods. The spacecraft includes 24 shooting devices with spherical reference reflectors [3] p. 198-200.

Spheres are convenient reference scatterers, the effective scattering surface (EPR) of which can be calculated exactly [4] p. 204. The reference sphere has the advantage of calibrating the radar because, due to its symmetry, the EPR value is constant [4] p. 205.

A disadvantage of a spherical spacecraft with a reference reflective surface is the impossibility of using it for EPR calibration of radars operating on circular polarized waves during parallel reception of reflected signals, since a spherical reflector is invisible for such radars [5] p. 103.

Known spacecraft with reference reflectors - patent RU 2544908 "Spacecraft for calibrating a radar station by the magnitude of the effective scattering surface." This spacecraft is taken as a prototype.

The disadvantage of the prototype is that it is used solely for the purpose of calibrating the radar.

In addition, the design of the corner reflector of the prototype is insufficiently resistant to thermal deformations arising from the cyclic effects of temperature differences in space flight conditions.

The technical result consists in expanding the functionality: creating a multifunctional spacecraft, which along with the main target (calibration and adjustment of the radar) performs the functions of an orbital carrier platform for additional target equipment, for example, remote sensing of the Earth in the optical and / or infrared range. In addition, the technical result of the invention is to provide a stable value of the EPR by increasing the stability of the design of the corner reflector to thermal deformations arising from the cyclic effects of temperature differences in space flight.

The specified technical result is achieved in that the housing of the MCA is made in the form of a cube 1 or a direct prism. On one of the faces of a cube or a direct prism there is a V-shaped groove or depression of a V-shaped shape 2, in which a corner reflector 3 with faces 4, 5 of two flat radio-reflecting plates deployed at a fixed angle α is V-shapedly fixed. The angle α is in the range from (90-Δ) degrees to (90 + Δ) degrees, where Δ is determined from the ratio:

0 <Δ <18 λ / a,

λ is the wavelength of the calibrated radar;

and - the size of the face of the corner reflector (see. Fig. 3, Fig. 4, Fig. 5).

In this case, the bisector of the angle 8 between the faces in the plane perpendicular to the middle of the edge of the corner reflector from two flat radio-reflecting plates, deployed at a fixed angle α , coincides with the longitudinal axis 9 of the ICA case.

The technical result is also achieved by the fact that the MCA introduced a module for additional target equipment (MDCA), equipment for transmitting target information (ASCI), antenna ASCI, command radio link equipment (ACRL), transmitting and receiving antennas ACP L, navigation equipment for consumers (NAP) space GLONASS and / or GPS systems, on-board computer system (BVS), microcontroller, unit for interfacing an orientation and stabilization system with a microcontroller. Moreover, the input and output of the ARL is informationally connected to the BVS. The NAP output is connected to the first input of the on-board computer system, the first output of the on-board computer system is connected to the first input of the microcontroller. The first output of the microcontroller is connected to the first input of the interface unit. The first output of the interface unit is connected to the input of the orientation and stabilization system. The output of the orientation and stabilization system is connected to the input of the interface unit. The second output of the interface unit is connected to the second input of the microcontroller. The second output of the microcontroller is connected to the second input of the on-board computer system, which controls the process of orientation of the spacecraft relative to the calibrated (adjusted) radar or guidance module additional target equipment. In addition, the second output of the on-board computer system is connected to the input of the additional target equipment module, and the MDCA output is connected to the input of the target information transmission equipment (see Fig. 6).

In addition, the geometric dimensions of the flat radio-reflecting plates are larger than the geometric dimensions of the face of the cube or the side face of the direct prism of the ICA housing.

In addition, flat radio-reflecting plates have a radio-reflecting surface only on the inside of the formed dihedral corner reflector.

In addition, at least two faces of the cube or direct prism of the MCA housing are covered with photoelectric converters.

In addition, the European navigation system Galileo or the Galileo system together with the GLONASS or GPS navigation systems are used as consumer navigation equipment.

In addition, the module additional target equipment includes equipment for remote sensing of the Earth in the optical and / or infrared range.

In addition, the optical axis of the Earth remote sensing equipment in the optical and / or infrared range is parallel or aligned with the longitudinal axis of the MCA.

In addition, the edges of the corner reflector are made of honeycomb panels.

In addition, the honeycomb panels on the inside of the formed dihedral corner reflector have a radio-reflective surface.

The proposed multifunctional spacecraft is illustrated by the drawings of FIG. 1-fig. 6.

FIG. 1, FIG. 2 is a general view of a multifunctional spacecraft made in the form of a cube with an angular reflector.

FIG. 3 - multifunctional spacecraft in the form of a cube 1, top view, where 8 is the bisector of angle α ; 9 - the longitudinal axis of the multifunctional spacecraft; 10 - solar panels; 11 - engines of the orientation and stabilization system.

FIG. 4 - a multifunctional spacecraft in the form of a cube, rear view, where 12 is the camera lens of the module for additional target equipment; 13 - antenna transmitting target information; 14 - receiving antenna AKRL; 15 - transmitting antenna AKRL.

FIG. 5 is a cube-shaped multifunctional spacecraft, side view.

In FIG. 6 shows a block diagram of the informational relationship of the onboard equipment of a multifunctional spacecraft, where it is indicated:

16 - module additional target equipment (MDCA);

17 - equipment for the transmission of target information (ASCI);

18 - antenna ASCI;

19 - command radio link equipment (AKRL);

20 - receiving antenna AKRL (PRM AKRL);

21 - transmitting antenna AKRL (PRD AKRL);

22 - on-board computer system (BVS);

23 - consumer navigation equipment (NAP);

24 - microcontroller (MK);

25 - interface unit (BS);

26 - orientation and stabilization system (SOIS).

The information interconnection of the MDCA, target information transmitting equipment, ASCI antennas, receiving and transmitting antennas ARL, command radio line equipment, on-board computer system, consumer navigation equipment, microcontroller, interface unit, orientation and stabilization system is carried out via information exchange lines (in Fig. 6 are indicated thin solid line).

ACRL input and output are informationally connected to the BVS. The NAL output is connected to the first input of the on-board computer system, the first output of the on-board computer system is connected to the first input of the microcontroller, the first output of the microcontroller is connected to the first input of the interface unit, the first output of the interface unit is connected to the input of the orientation and stabilization system. The output of the orientation and stabilization system is connected to the second input of the interface unit, the second output of the interface unit is connected to the second input of the microcontroller, the second output of the microcontroller is connected to the second input of the on-board computer system, which controls the orientation or guidance of the module for additional target equipment of the MCA.

In addition, the second output of the on-board computer system is connected to the input of the additional target equipment module, and the MDCA output is connected to the input of the target information transmission equipment.

The antenna of the equipment for transmitting target information is connected to the output of the ASCI.

The transmitting and receiving antennas of the command radio equipment are connected to the output and input of the ARLA, respectively.

The proposed multifunctional spacecraft is made in the form of a cube or a direct prism.

The instrumentation compartment, the command radio line equipment, the on-board computer system, the GLONASS and / or GPS space system consumer navigation equipment, the microcontroller, the interface unit, the orientation and stabilization system, the additional target equipment module, and target information transmission equipment (in the drawing) are installed in the ICA case not shown).

On one of the faces of the cube 1 or a direct prism, a V-shaped groove or depression of a V-shaped 2 is made, in which a corner reflector 3 with faces 4, 5 of two flat radio-reflecting plates deployed at a fixed angle α is V-shaped. The angle α is in the range from (90-Δ) degrees to (90 + Δ) degrees, where Δ is determined from the ratio:

0 <Δ <18 λ / a,

λ is the wavelength of the calibrated radar;

and - the size of the face of the corner reflector (see Fig. 3, Fig. 4).

The edge 6 of the corner reflector 3 with faces 4, 5 of two flat radio-reflecting plates, deployed at a fixed angle α , is located at the intersection of two planes of symmetry of the cube 7. Moreover, the bisector of angle 8 between the faces in the plane perpendicular to the middle of the edge of the corner reflector of two flat radio-reflecting plates, deployed at a fixed angle α , coincides with the longitudinal axis 9 of the housing MKA.

On the side faces of the cube or prism are solar panels 10 (see Fig. 3).

The functioning of the MCA occurs in this sequence.

After the MCA is put into the target orbit, the ground-based control complex with the command radio line and the on-board equipment of the MCA command radio link are used to control the MCA. Moreover, the coordinates of the radar station to be calibrated by the magnitude of the effective scattering surface are transmitted to the MCA from the ground control complex via a command radio link. Then, using the receivers of the navigation system of the GLONASS and / or GPS type and the on-board computer system, the current coordinates of the center of mass of the MCA and the angles of the current spatial orientation of the MCA are determined. Using the onboard computer system, the position of the MCA center of mass relative to the coordinates of the calibrated radar station transmitted from the ground control complex is determined, as well as the orientation of the axes of the associated MCA coordinate system relative to the line of sight of the calibrated radar station. At the same time, the on-board computer system calculates and calculates the spatial position of the bisector of angle 8 of the dihedral angle reflector formed by two flat radio-reflecting plates relative to the line of sight of the calibrated radar at the current time. The calculation uses the coordinates (in the associated coordinate system of the MCA) of the middle of the rib and the position of the bisector of the angle of the dihedral angle reflector, entered into the on-board computer system before launching the MCA into orbit.

The calculated data from the first output of the on-board computer system are fed to the first input of the microcontroller, which forms control commands, which from the first output of the microcontroller go to the first input of the BS, and then from the first output of the BS arrive at the input of the SOIS. SOIS carries out a turn of the MCA and alignment of the position of the bisector of the angle of the dihedral angle reflector with the line of sight of the calibrated radar station.

The SOIS output is connected to the second input of the BS, the second output of the BS is connected to the second input of the microcontroller, the second output of the microcontroller is connected to the second input of the on-board computer system, which controls the process of orientation of the MCA relative to the calibrated radar in real time.

When combining the position of the bisector of the angle of the dihedral angular reflector with the line of sight of the calibrated spacecraft radar from the BVS, the MCLA receives a signal of readiness of the MCA for the calibration session, which is transmitted to the ground control complex.

In the future, the information interaction of the on-board computer system, consumer navigation equipment, microcontroller, interface unit, orientation and stabilization system of the MCA ensures that the angle bisector of the formed dihedral angle reflector is kept aligned with the sight line of the calibrated radar station until the end of the radar calibration session, the coordinates of which were transmitted from the ground-based complex ICA management.

Moreover, the main lobe of the scattering indicatrix of the dihedral corner reflector during the calibration session is directed to the calibrated radar station, and the maximum of the main lobe of the scattering indicatrix of the dihedral corner reflector coincides with the line of sight of the calibrated radar station.

For other tasks not related to radar calibration, the coordinates for guidance of the additional target equipment module are transmitted to the MCA from the ground control complex via a command radio link. Then, using the receivers of a navigation system of the GLONASS and / or GPS type and the on-board computer system, the current coordinates of the center of mass of the spacecraft and the angles of the current spatial orientation of the spacecraft are determined. In this case, the same receivers of the navigation system of the GLONASS and / or GPS type are used, the same on-board computer system used to calibrate the radar. Using the on-board computer system, the position of the center of mass of the MCA relative to the coordinates transmitted from the ground control complex is determined to guide the module of additional target equipment. Using BVS, the orientation of the axes of the associated MCA coordinate system relative to the optical axis of the Earth remote sensing equipment in the optical and / or infrared range is also determined. At the same time, the onboard computer system calculates and calculates the spatial position of the optical axis of the module of the additional target equipment relative to the direction to the nadir or other desired point, for example, to a star or space object, the coordinates of which are transmitted from the ground-based control complex.

In the calculation, the position of the optical axis of the module of the additional target equipment, introduced into the on-board computer system before the launch of the MCA into orbit, is used (in the associated coordinate system of the MCA).

The calculated data from the first output of the on-board computer system are fed to the first input of the microcontroller, which forms control commands, which from the first output of the microcontroller go to the first input of the BS, and then from the first output of the BS arrive at the input of the SOIS. SOIS carries out a turn of the MCA and guidance of the optical axis of the module of additional target equipment to a nadir or other desired point, for example, a star or a space object.

When combining the optical axis of the module of the additional target equipment with the direction to the nadir or with the coordinates on the Earth’s surface transmitted from the ground control complex, from the second output of the on-board computer system, the command to turn on the module of the additional target equipment is sent to the input of the MCA.

The observation results of the module additional target equipment using equipment for transmitting target information is transmitted to the ground control complex or ground receiving points of the target information. After reviewing the specified observation area from the ground control complex MCA via the command radio link or according to the specified flight program, the command to end the monitoring session of the MDCA is transmitted from the BVS to the ICA.

When a command arrives at the MCA from the ground control complex of pointing the module of additional target equipment to another desired point, for example, to a star or a space object, the orientation and stabilization system ensures that the position of the optical axis of the MDCA with a given direction is maintained during the entire observation session.

In the future, radar calibration (adjustment) sessions or monitoring sessions using MDCA are repeated according to commands from the ground control complex.

Execution corner reflector with facets of two flat radiootrazhayuschih plates deployed at a fixed angle α, specify the range from (90-Δ) degrees to (90 + Δ) degrees, allows for "flattening" form the main lobe of the scattering function of the angle of the reflector in the horizontal plane . Thus, the sector of the angles of the main lobe of the scattering indicatrix of the dihedral angular reflector in the horizontal plane, in which its EPR is almost constant, is 20 ° (± 10 °), [5] p. 150, fig. 4.7, curves 2, 3.

It should be noted that with an increase in the ESR of the reference reflector, the calibration efficiency increases [9] p. 65. So, as an example, the value of the ESR of the proposed MCA in the direction of the radar operating at a wavelength of 7 cm, taking into account a decrease in ESR by 3 dB due to deviation the angle between the faces of the MA from the straight for “flattening” the shape of the main lobe of the scattering indicatrix, when the face of the corner reflector is 100 cm, will be 2500 m ² , which is more than 800 times the EPR of a spherical reflector with a diameter of 200 cm [1] p. 49, table 2.1 .3. This size had the calibration spacecraft "South" as part of the RSC "Typhoon" [1] p. 49, [9] p. 65.

The use of MCA with UO significantly improves the calibration conditions of existing and future radar tools. Moreover, the proposed MCA with an angular reflector, the face of which is only 100 cm, allows you to increase the range at which it is possible to calibrate the radar by the magnitude of the EPR by 5.3 times. This will lead to the fact that MCA with SV will be steadily observed at small elevation angles: (3-5) degrees, at which it is necessary to calibrate high-potential early warning radars [1] p. 48.

At the same time, a significant increase in the ESR of the spacecraft will make it possible to increase the altitude of the orbit of the launched spacecraft, which in turn will significantly increase its lifetime in orbit [1] p. 48.

In addition, the V-shaped rigid fastening of the corner reflector into the V-shaped groove or the recess of the V-shaped body of the MCA in the form of a cube or a direct prism allows to ensure a stable EPR value by increasing the resistance of the design of the corner reflector to thermal deformations arising due to cyclic the effects of temperature differences in space flight.

Moreover, along with the main target (calibration and adjustment of the radar), the MCA performs the functions of an orbital carrier platform for additional target equipment for remote sensing of the Earth in the optical and / or infrared range.

At the same time, the use of existing small-sized on-board optoelectronic systems does not lead to a significant increase in the mass of on-board equipment of the MCA. For example, a 20-channel multispectral optoelectronic system with a telescope diameter of 5–7 cm, together with supporting equipment, has a mass of only 25–40 kg [1] p. 150.

Thus, the proposed MCA implements the integration of target equipment on one space platform and the creation of a dual-use spacecraft.

The proposed design of the MCA and the informational relationship of the equipment of the command radio line, the on-board computer system, the navigation equipment of the consumer, the microcontroller, the interface unit of the orientation and stabilization system of the MCA allow us to obtain properties that are different from the properties of known solutions, namely:

- flexibility in conducting radar calibration sessions in time and in space due to the prompt transfer from the ground control complex to the MCA of the coordinates of calibrated radars of both stationary and mobile land or sea based;

- the stable value of the ESR of the MCA with the UO in the direction of the calibrated radar due to the stability of the design of the angular reflector, used as the standard of the EPR, to thermal deformations arising due to temperature differences in space flight conditions;

- expanding the functionality of the spacecraft, which, along with the main target (calibration and adjustment of the radar), the MCA performs the functions of an orbital carrier platform for additional target equipment for remote sensing of the Earth in the optical and / or infrared range.

Moreover, the operation of additional target equipment for remote sensing of the Earth in the optical and / or infrared range is ensured by using the available resources of the MCA, namely: command radio link equipment, on-board computer system, consumer navigation equipment, orientation and stabilization system.

For example, the achievable accuracy of the orientation and stabilization system of 0.5 degrees [1] p. 259 allows you to use this MCA system in the radar calibration mode and in the guidance mode of the target equipment module for remote sensing of the Earth in the optical and / or infrared range [10] ] p. 31.

Therefore, the proposed MCA has significant differences from the known spacecraft and allows you to expand their functionality. In this case, the main purpose of the MCA is the calibration and alignment of radars both stationary based and mobile land or sea based, an additional purpose of the MCA is remote sensing of the Earth in the optical and / or infrared range.

Information sources

1. Small spacecraft information support / ed. Fateeva V.F. M .: Radio engineering. 2010.S. 47-50, p. 150, p. 259.

2. Leonov A.I., Leonov S.A., Nagulinko F.V. et al. Tests of the radar / ed. Leonova A.I. M .: Radio and communication. 1990.S. 37.

3. Missiles and spacecraft Design Bureau "South" / ed. Konyukhova S.N. Dnepropetrovsk. GKB "South" them. M.K. Yangel. 2000.S. 198-200.

4. Maisels E.N., Torgovanov V.A. Measurement of scattering characteristics of radar targets / ed. Kolosova M.A. M .: Soviet radio. 1972. S. 144-145, p. 193-194, p. 204-213.

5. Kobak V.O. Radar Reflectors / Ed. Leontievsky O.N. M .: Soviet radio. 1975.S. 103, p. 139, p. 144, p. 146, p. 150, p. 152, p. 235.

6. Bakitko R.V., Boldenkov E.N., Bulavsky N.T. and other GLONASS. The principles of construction and operation / ed. Perova A.I., Kharisova V.N. M .: Radio engineering. 2010.S. 412.

7. Maisenya L.I. Handbook of mathematics: basic concepts and formulas. Minsk: Ab. school 2011.S. 201-203.

8. Patent RU 2544908 "A spacecraft for calibrating a radar station by the magnitude of the effective scattering surface" / Poluyan A.P. Open Joint-Stock Company Specialized Space Systems Corporation Comet.

9. Fateev V.F. A modern view of the development of the space echelon of EKO information tools. Aerospace defense. 2014. No1. S. 65.

10. Afanasyev I. “In the interests of Japanese customers, Dnipro launched five satellites into orbit.” Cosmonautics News. 2015. No01. S. 30-33.

Claims (13)

1. A multifunctional spacecraft (MCA) comprising a housing with an instrument compartment, a propulsion system, orientation and stabilization systems, a thermal management system, solar panels, characterized in that the spacecraft’s housing is made in the form of a cube or a direct prism, moreover, on one of the faces a cube or a direct prism, there is a V-shaped groove or V-shaped recess in which a corner reflector with faces of two flat radio-reflecting plates deployed at a fixed angle α is V-shapedly fixed, and the magnitude and the angle α is in the range of (90-Δ) degrees to (90 + Δ) degrees, where Δ - is determined from the relationship: 0 <Δ <18λ / a, λ is the wavelength of the calibrated radar; a is the size of the face of the corner reflector, in this case, the bisector of the angle between the faces in the plane perpendicular to the middle of the corner of the corner reflector from two flat radio-reflecting plates deployed at a fixed angle α coincides with the longitudinal axis of the ICA body, in addition, the module of additional target equipment (MDCA), as well as equipment, are introduced into the MCA Target Information Transmission (ASCI), ASCI antenna, command radio link equipment (ACRL), receiving and transmitting ARL antenna, consumer navigation equipment (NAP) of GLONASS and / or GPS space systems a fuel system (BVS), a microcontroller, an interface unit for the orientation and stabilization system with a microcontroller, the ACRL input and output being informationally connected to the BVS, the NAP output is connected to the first input of the on-board computer system, the first output of the on-board computer system is connected to the first input of the microcontroller, the first output the microcontroller is connected to the first input of the interface unit, the first output of the interface unit is connected to the input of the orientation and stabilization system, the output of the orientation and stabilization system is connected to to the other input of the interface unit, the second output of the interface unit is connected to the second input of the microcontroller, the second output of the microcontroller is connected to the second input of the on-board computer system, which controls the orientation of the MCA relative to the calibrated radar or the guidance of the module of additional target equipment, in addition, the second output of the on-board computer system is connected to the input of the additional target equipment module, and the output of the additional target equipment module is connected to the input of the target transmission equipment th information. 2. The multifunctional spacecraft according to claim 1, characterized in that the geometric dimensions of the flat radio-reflecting plates are larger than the geometric dimensions of the face of the cube or the side face of the direct prism of the ICA body. 3. The multifunctional spacecraft according to claim 1, characterized in that the flat radio-reflecting plates have a radio-reflecting surface only from the inside of the formed dihedral corner reflector. 4. The multifunctional spacecraft according to claim 1, characterized in that at least two faces of the cube or direct prism of the spacecraft’s hull are covered with photoelectric converters. 5. The multifunctional spacecraft according to claim 1, characterized in that the European navigation system Galileo, or the Galileo system in conjunction with the GLONASS or GPS navigation systems is used as consumer navigation equipment. 6. The multifunctional spacecraft according to claim 1, characterized in that the additional target equipment module includes Earth remote sensing equipment in the optical and / or infrared range. 7. The multifunctional spacecraft according to claim 6, characterized in that the optical axis of the Earth remote sensing equipment in the optical and / or infrared range is parallel or aligned with the longitudinal axis of the MCA. 8. The multifunctional spacecraft according to claim 1, characterized in that the edges of the corner reflector are made of honeycomb panels. 9. The multifunctional spacecraft according to claim 8, characterized in that the honeycomb panels on the inside of the formed dihedral corner reflector have a radio-reflecting surface.

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