RU2014111007A - METHOD FOR DETERMINING ATEROID MOTION PARAMETERS AND A DEVICE FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. The method of determining the parameters of the motion of an asteroid, which consists in irradiating the asteroid with electromagnetic energy, characterized in that they receive continuous signals with frequency modulation reflected from the asteroid according to a one-sided ramp law (NLFM signal) with at least four receiving antennas PRA1, PRA2, PRA3 and PRA4 installed on the Earth, on a circle, at equal distance from each other around the circle, with basic L distances between diametrically opposite PRA1 and PRA2, as well as PRA3 and PRA4, and they teach the NLFM signal to the side of an asteroid approaching the Earth through a transmitting antenna (PDA) installed in the center of the circumference of the PRA installation, and the signals reflected from the asteroid and the emitted NLFM are multiplied in four mixers (SM1, CM2, CM3 and CM4) with the first inputs connected , respectively, to the outputs of PRA1, PRA2, PRA3, PRA4 and second inputs connected to the low-power output of the NLFM transmitter combined with PDA in order to receive and detect four signals with a specific difference frequency: Fp ÷ Fp = [(Di + Dj) Fm × dfm / C] - (2 × Vi × f / C) = Fp, where Di, Dj is the tech the distance from the asteroid to, respectively, the PRA and PDA, C, Vi, respectively, the speed of light and the asteroid, f, Fm, dfm are the frequency, modulation frequency, and frequency deviation of the NLFM signal, after which, in sequence of the moments of detection of signals with frequencies Fp and Fp, as well as Fp and Fp and the values of the time intervals t and t, respectively, between the moments of detection of signals with frequencies Fp and Fp, as well as Fp and Fp, determine the cells of the permanent storage device (YaPZU1 ÷ YaPZU4), in which the previously calculated data on the values are stored: azimuth , elevation and range

Claims (2)

1. The method of determining the parameters of the motion of an asteroid, which consists in irradiating the asteroid with electromagnetic energy, characterized in that they receive continuous signals with frequency modulation reflected from the asteroid according to a one-sided ramp law (NLFM signal) with at least four receiving antennas PRA1, PRA2, PRA3 and PRA4 installed on the Earth, on a circle, at equal distance from each other around the circle, with basic L distances between diametrically opposite PRA1 and PRA2, as well as PRA3 and PRA4, and they teach the NLFM signal to the side of an asteroid approaching the Earth through a transmitting antenna (PDA) installed in the center of the circumference of the PRA installation, and the signals reflected from the asteroid and the emitted NLFM are multiplied in four mixers (SM1, CM2, CM3 and CM4) with the first inputs connected , respectively, to the outputs of PRA1, PRA2, PRA3, PRA4 and second inputs connected to the low-power output of the NLFM transmitter combined with the PDA in order to receive and detect four signals with a specific differential frequency: Fp ₁ ÷ Fp ₄ = [(Di + Dj) Fm × dfm / C] - (2 × Vi × f / C) = Fp, where Di, Dj are the current distances from the asteroid to, respectively, PRA and PDA, C, Vi - respectively, the speed of light and an asteroid, f, Fm, dfm - frequency, modulation frequency and frequency deviation of the LFLM signal, after which, according to the sequence of moments of the start of detection of signals with frequencies Fp ₁ and Fp ₂ , as well as Fp ₃ and Fp ₄ and the values of time intervals t ₁ and t ₂ , respectively, between the moments of detection of signals with frequencies Fp ₁ and Fp ₂ , and Fp ₃ and Fp ₄ , determine the cells of the permanent storage device (YaPZU1 ÷ YaPZU4), which store pre-calculated data on the values: azimuth, elevation angle and distance to the region of the hemisphere above the PDA in which the asteroid is detected, then, after repeated multiplication of the reflected from an asteroid and an emitted NLChM signal s receive and detect again four signal frequency Fp ^1:

where $$Di>D_i^{\mathrm{one}}$$

and $$Dj>D_j^{\mathrm{one}}$$

- current distances from the asteroid to, respectively, ballasts and PDA, after which, in sequence of moments of the beginning of detection of signals with frequencies $$F{p}_{\mathrm{one}}^{\mathrm{one}}$$

and $$F{p}_2^{\mathrm{one}}$$

, as well as $$F{p}_3^{\mathrm{one}}$$

and $$F{p}_{\mathrm{four}}^{\mathrm{one}}$$

and values of time intervals $$t_{\mathrm{one}}^{\mathrm{one}}$$

and $$t_2^{\mathrm{one}}$$

, respectively, between the moments of detection of signals with frequencies $$F{p}_{\mathrm{one}}^{\mathrm{one}}$$

and $$F{p}_2^{\mathrm{one}}$$

, a also $$F{p}_3^{\mathrm{one}}$$

and $$F{p}_{\mathrm{four}}^{\mathrm{one}}$$

, determine YaPZU ¹ 1 ÷ YaYaU ¹ 4, which stores pre-calculated data on the values of: azimuth, elevation angle and distance to the region of the hemisphere part above the PDA in which the asteroid is detected again, then, using the known data on the removal of asteroid detection areas, calculate, using the expression Vi = (Fp-Fp ¹ ) C / 2t ₃ , the speed of the asteroid, where t ₃ is the value of the time interval between the moments of detection of signals with frequencies Fp ₁ and $$F{p}_{\mathrm{one}}^{\mathrm{one}}$$

and the direction coinciding with the vector drawn from the center of the first to the center of the second areas of its detection is taken as the direction of movement of the asteroid. 2. A device for determining the parameters of motion of an asteroid containing a frequency radar, characterized in that the frequency radar is made in the form of one transmitting module (PDM) and four identical receiving modules (PRM1 ÷ PRM4), each of which is connected in series: a receiving antenna (PRA ); a mixer (SM) with a second input, through one of four high-frequency cables (VCHK1 ÷ VChK4) connected to the low-power output of the PDM transmitter; a difference frequency filter (HPF) and a narrow-band frequency spectrum signal detector (GPRS) and an output bus, and a PDM combined with: first and second phase detectors (FD1 and FD2); four information display units (BOI1 ÷ BOI4); the shift register (Rg) and the asteroid velocity calculation unit (BVCA), contains a continuous signal transmitter with frequency modulation according to a one-sided sawtooth linearly increasing law (NLCM signal), the high-power output of which is connected to the transmitting antenna (PDA), and the outputs PRM1, PRM2, PRM3 and PRM4, each, through one of the four VCHK (VChK5 ÷ VChK8), are connected, respectively, to the first and second inputs of PD1 and to the first and second inputs of PD2, and the first output of PD1 is connected to the first inputs of BOI1 and BOI4, the second output of PD1 is connected to the first inputs of BOI2 and BOI 3, the first output of PD2 is connected to the second inputs of BOI1 and BOI2, the second output of PD2 is connected to the second inputs of BOI3 and BOI4, and the output of PRM1 is connected to the input Rg, the first output of which is connected: to the third inputs of BOI; the input of the MENA, the second output of Pr is connected to the fourth inputs of the BOI.