초록 ▼

A control device (D), for a spacecraft (S1) of a group of spacecraft moving in formation, comprises i) an assembly consisting of three antennas (A1-A3) installed on a face of the spacecraft (S1) and capable of emitting and/or receiving first and second RF signals exhibiting first and second frequenc

A control device (D), for a spacecraft (S1) of a group of spacecraft moving in formation, comprises i) an assembly consisting of three antennas (A1-A3) installed on a face of the spacecraft (S1) and capable of emitting and/or receiving first and second RF signals exhibiting first and second frequencies spaced apart by a chosen frequency gap, ii) first measurement means (M1) charged with determining first and second differences in path length between antennas (A1-A3), corresponding to the first frequency and to the frequency gap, on the basis of the first and second signals received by the antennas and originating from another spacecraft, iii) second measurement means (M2) charged with delivering measurements of rotation undergone by the spacecraft (S1), and iv) processing means (MT) a) charged with coarsely estimating the direction of transmission of the signals received on the basis of first and second initial path length differences, b) with ordering the positioning of the spacecraft (S1) so that a chosen axis of a frame of reference tied to said spacecraft is aligned with respect to the coarse direction of transmission, c) with ordering the rotational turning of the spacecraft (S1) about the chosen axis, d) with precisely estimating the direction of transmission of the signals emitted by the other spacecraft (Si′) on the basis of the rotation measurement and of a measurement of variation of the first path length difference induced by this rotation.

대표청구항 ▼

1. A control device (D), for a spacecraft (Si) of a group of spacecraft intended to move according to a chosen formation, comprising: at least one assembly including an emission/reception antenna (A1) and of two receiving antennas (A2, A3) installed at chosen locations on a face of said spacecraft (

1. A control device (D), for a spacecraft (Si) of a group of spacecraft intended to move according to a chosen formation, comprising: at least one assembly including an emission/reception antenna (A1) and of two receiving antennas (A2, A3) installed at chosen locations on a face of said spacecraft (Si) and able to emit and/or receive radiofrequency signals,processing means (MT) designed to estimate the directions of transmission of the signals emitted by other spacecraft of the group on the basis of said signals received by said antennas (A1-A3),each antenna (A1-A3) of said assembly is designed to emit and/or receive first and second signals exhibiting first and second chosen frequencies spaced apart by a chosen frequency gap,first measurement means (M1) designed to determine first and second differences in path length between antennas (A1-A3), corresponding to the first or second chosen frequencies and to said frequency gap, on the basis of the first and second signals received by each of said antennas of said assembly originating from another spacecraft (Si′) of said group,attitude measurement means (M2) designed to deliver measurements of rotation undergone by said spacecraft (Si),wherein said processing means (MT) are designed to a) coarsely estimate the direction of transmission of the signals emitted by said other spacecraft (Si′) on the basis of first and second initial path length differences, b) order a coarse positioning of said spacecraft (Si) so that a chosen axis (X) of a frame of reference tied to said spacecraft is substantially aligned with respect to said coarsely estimated direction of transmission, c) order at least one chosen rotational turning of said spacecraft (Si) about said chosen axis (X), d) precisely estimate said direction of transmission of the signals emitted by said other spacecraft (Si′) on the basis of the rotation measurement delivered by said attitude measurement means (M2) and of a measurement of variation of the first or second initial path length differences induced by said rotation, performed by said first measurement means (M1). 2. The device as claimed in claim 1, wherein said processing means (MT) generate, before ordering said rotational turning, instructions intended to order a stabilization of the coarse positioning at near-zero speed of said spacecraft (Si), on the basis of said measurement of variation of one of the first and second path length differences performed by said first measurement means (M1). 3. The device as claimed in claim 2, wherein said processing means are designed to retain a precise knowledge of said direction of transmission, on the basis of said measurements of variation of one of the first and second path length differences. 4. The device as claimed in claim 2, wherein said first measurement means (M1) are designed to i) determine the first and second phases of the first and second signals received by each of said antennas (A1-A3) of said assembly originating from said other spacecraft (Si′), ii) deduce from said first and second phases first and second differences in phase between said emission/reception antenna (A1) and each of said receiving antennas (A2, A3), iii) deduce from said first and second phase differences third phase differences corresponding to said frequency gap, iv) deduce from first or second consecutive phase differences and from third consecutive phase differences measurements of variation of first or second path length difference, and v) deduce from the measurements of variation of first or second path length difference non-ambiguous measurements of said first and second path length differences corresponding to the first or second frequency. 5. The device as claimed in claim 2, comprising second measurement means (M3) designed to estimate the distance separating their spacecraft (Si) from said other spacecraft (Si′) of the group, on the basis of said first and/or second signals received by at least one of said antennas (A1-A3) originating from said other spacecraft (Si′), and in that said processing means (MT) are designed to determine the relative positions of said spacecraft (Si′) with respect to their spacecraft (Si), on the basis of said estimated distances and of said precise estimated direction of transmission. 6. The device as claimed in claim 1, wherein said processing means are designed to retain a precise knowledge of said direction of transmission, on the basis of said measurements of variation of one of the first and second path length differences. 7. The device as claimed in claim 6, wherein said first measurement means (M1) are designed to i) determine the first and second phases of the first and second signals received by each of said antennas (A1-A3) of said assembly originating from said other spacecraft (Si′), ii) deduce from said first and second phases first and second differences in phase between said emission/reception antenna (A1) and each of said receiving antennas (A2, A3), iii) deduce from said first and second phase differences third phase differences corresponding to said frequency gap, iv) deduce from first or second consecutive phase differences and from third consecutive phase differences measurements of variation of first or second path length difference, and v) deduce from the measurements of variation of first or second path length difference non-ambiguous measurements of said first and second path length differences corresponding to the first or second frequency. 8. The device as claimed in claim 1, wherein said first measurement means (M1) are designed to i) determine the first and second phases of the first and second signals received by each of said antennas (A1-A3) of said assembly originating from said other spacecraft (Si'), ii) deduce from said first and second phases first and second differences in phase between said emission/reception antenna (A1) and each of said receiving antennas (A2, A3), iii) deduce from said first and second phase differences third phase differences corresponding to said frequency gap, iv) deduce from first or second consecutive phase differences and from third consecutive phase differences measurements of variation of first or second path length difference, and v) deduce from the measurements of variation of first or second path length difference non-ambiguous measurements of said first and second path length differences corresponding to the first or second frequency. 9. The device as claimed in claim 1, comprising second measurement means (M3) designed to estimate the distance separating their spacecraft (Si) from said other spacecraft (Si′) of the group, on the basis of said first and/or second signals received by at least one of said antennas (A1-A3) originating from said other spacecraft (Si′), and in that said processing means (MT) are designed to determine the relative positions of said spacecraft (Si′) with respect to their spacecraft (Si), on the basis of said estimated distances and of said precise estimated direction of transmission. 10. The device as claimed in claim 9, wherein said second measurement means (M3) are designed to estimate the distance separating their spacecraft (Si) from said other spacecraft (Si′) of the group, on the basis of said first and/or second signals received by at least one of said antennas (A1-A3) originating from said other spacecraft (Si′), and of auxiliary signals transmitted by said other spacecraft (Si′) and representative of the distance separating it from said spacecraft (Si). 11. The device as claimed in claim 9, wherein said processing means (MT) are designed to correct said distance measurement and/or said measurement of precise direction of transmission of an effect induced by multi-paths, on the basis of stored cartographic data and of said direction of transmission of the signals. 12. The device as claimed in claim 10, wherein said processing means (MT) are designed to correct said distance measurement and/or said measurement of precise direction of transmission of an effect induced by multi-paths, on the basis of stored cartographic data and of said direction of transmission of the signals. 13. The device as claimed in claim 1, comprises comprising at least two antenna assemblies on at least two faces of different orientations. 14. The device as claimed in claim 1, comprising at least one complementary emission/reception antenna (A4) on at least one face devoid of any assembly of antennas. 15. The device as claimed in claim 1, wherein said antennas (A1-A3) are able to emit and/or receive first and second radiofrequency signals taking the form of first and second carriers, at least one of which is modulated by a chosen pseudo-random code. 16. The device as claimed in claim 1, wherein said frequency gap corresponds to a wavelength of length at least equal to twice the distance separating said emission/reception antenna (A1) from each of said receiving antennas (A2, A3). 17. The device as claimed in claim 1, wherein said antennas (A1-A3) are designed to emit/receive first and second carriers exhibiting first and second frequencies belonging to a frequency band chosen from a group comprising the S, SHF and EHF bands. 18. The device as claimed in claim 17, wherein said frequency band is the S band. 19. A spacecraft (S1) intended to move in formation within a group of spacecraft, comprising a control device (D) as claimed in claim 1. 20. A group of space craft (Si), intended to move according to a chosen formation, wherein at least one of said spacecraft (S1) comprises at control device (D) as claimed in claim 1, and in that at least some of the other spacecraft (S2, S3) comprises at least one emission/reception antenna (A1) installed on at least one chosen face.