1. A scan apparatus comprising:
a CCD sensor to receive reflected light from a document, wherein the CCD sensor includes a red line sensor array having a red filter layer configured to pass red light and a plurality of red photodiodes to receive light passing through the red filter layer, a green line sensor array having a green filter layer configured to pass green light and a plurality of green photodiodes to receive light passing through the green filter layer, and a blue line sensor array having a blue filter layer configured to pass blue light and a plurality of blue photodiodes to receive light passing through the blue filter layer,
a thickness of the red filter layer is a value except the integral multiple of a wavelength at which sensitivity of the red photodiodes becomes maximum in a wavelength region of the red light,
a thickness of the green filter layer is a value except the integral multiple of a wavelength at which sensitivity of the green photodiodes becomes maximum in a wavelength region of the green light, and
a thickness of the blue filter layer is a value except the integral multiple of a wavelength at which sensitivity of the blue photodiodes becomes maximum in a wavelength region of the blue light.
2. The apparatus of claim 1, wherein
the red filter layer passes the red light of a wavelength in a visible light region,
the green filter layer passes the green light of a wavelength in the visible light region, and
the blue filter layer passes the blue light of a wavelength in the visible light region.
3. The apparatus of claim 1, wherein
the red photodiodes are arranged in a line, receive the light passing through the red filter layer and perform photoelectric conversion,
the green photodiodes are arranged in a line, receive the light passing through the green filter layer and perform photoelectric conversion, and
the blue photodiodes are arranged in a line, receive the light passing through the blue filter layer and perform photoelectric conversion.
4. The apparatus of claim 1, wherein
the red photodiodes have sensitivity to a wavelength \u03bbr in a specified range of red light wavelengths in a visible light region, and have maximum sensitivity to a wavelength \u03bbrp in the wavelength \u03bbr,
the green photodiodes have sensitivity to a wavelength \u03bbg in a specified range of green light wavelengths in the visible light region, and have maximum sensitivity to a wavelength \u03bbgp in the wavelength \u03bbg, and
the blue photodiodes have sensitivity to a wavelength \u03bbb in a specified range of blue light wavelengths in the visible light region, and have maximum sensitivity to a wavelength \u03bbbp in the wavelength \u03bbb.
5. The apparatus of claim 1, wherein
the CCD sensor includes a transparent base layer provided on the red photodiodes, the green photodiodes and the blue photodiodes, and the red filter layer, the green filter layer and the blue filter layer are provided on the base layer.
6. The apparatus of claim 5, wherein
the CCD sensor includes a transparent cover glass to cover the base layer, the red filter layer, the green filter layer and the blue filter layer.
7. The apparatus of claim 1, further comprising:
a transparent document plate on which the document is set; and
an exposure lamp configured to expose the document on the document plate.
8. The apparatus of claim 7, wherein
the CCD sensor receives the reflected light from the document by the exposure.
9. An image forming apparatus comprising:
a transparent document plate on which a document is set;
an exposure lamp configured to expose the document on the document plate;
a CCD sensor which receives reflected light from the document generated by exposing and includes a red line sensor array having a red filter layer configured to pass red light and a plurality of red photodiodes to receive light passing through the red filter layer, a green line sensor array having a green filter layer configured to pass green light and a plurality of green photodiodes to receive light passing through the green filter layer, and a blue line sensor array having a blue filter layer configured to pass blue light and a plurality of blue photodiodes to receive light passing through the blue filter layer; and
a color printer configured to print a color image corresponding to an output of the CCD sensor; wherein
a thickness of the red filter layer is a value except the integral multiple of a wavelength at which sensitivity of the red photodiodes becomes maximum in a wavelength region of the red light,
a thickness of the green filter layer is a value except the integral multiple of a wavelength at which sensitivity of the green photodiodes becomes maximum in a wavelength region of the green light, and
a thickness of the blue filter layer is a value except the integral multiple of a wavelength at which sensitivity of the blue photodiodes becomes maximum in a wavelength region of the blue light.
10. The apparatus of claim 9, wherein
the red filter layer passes the red light of a wavelength in a visible light region,
the green filter layer passes the green light of a wavelength in the visible light region, and
the blue filter layer passes the blue light of a wavelength in the visible light region.
11. The apparatus of claim 9, wherein
the red photodiodes are arranged in a line, receive the light passing through the red filter layer and perform photoelectric conversion,
the green photodiodes are arranged in a line, receive the light passing through the green filter layer and perform photoelectric conversion, and
the blue photodiodes are arranged in a line, receive the light passing through the blue filter layer and perform photoelectric conversion.
12. The apparatus of claim 9, wherein
the red photodiodes have sensitivity to a wavelength \u03bbr in a specified range of red light wavelengths in a visible light region, and have maximum sensitivity to a wavelength \u03bbrp in the wavelength \u03bbr,
the green photodiodes have sensitivity to a wavelength \u03bbg in a specified range of green light wavelengths in the visible light region, and have maximum sensitivity to a wavelength \u03bbgp in the wavelength \u03bbg, and
the blue photodiodes have sensitivity to a wavelength \u03bbb in a specified range of blue light wavelengths in the visible light region, and have maximum sensitivity to a wavelength \u03bbbp in the wavelength \u03bbb.
13. The apparatus of claim 9, wherein
the CCD sensor includes a transparent base layer provided on the red photodiodes, the green photodiodes and the blue photodiodes, and the red filter layer, the green filter layer and the blue filter layer are provided on the base layer.
14. The apparatus of claim 13, wherein
the CCD sensor includes a transparent cover glass to cover the base layer, the red filter layer, the green filter layer and the blue filter layer.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A system for controlling deployment of at least two spacecraft which are provided with maneuvering means and are intended to move according to a chosen formation, comprising:
a control device having i) first measurement means designed to determine substantially simultaneously and with high precision the orbital positions of said spacecraft, and ii) first calculation means designed to determine for each of said spacecraft, as a function of said orbital positions, maneuvers intended to position each of them at a chosen instant substantially in a chosen position with respect to a reference trajectory, having regard to a time law of a reference craft on said reference trajectory, so as to place said formation in a chosen configuration.
2. The system as claimed in claim 1, wherein said reference craft is one of said spacecraft of said formation, said other spacecraft of the formation then being a follower craft.
3. The system as claimed in claim 1, said reference craft is a dummy craft representative of the said formation as a whole.
4. The system as claimed in claim 1, wherein said first calculation means are designed to determine maneuvers intended to substantially position each craft at a chosen instant in a chosen position with respect to said reference trajectory and with a chosen relative speed with respect to said reference craft, having regard to said time law of said reference craft on its reference trajectory.
5. The system as claimed in claim 4, wherein said first calculation means are designed to determine maneuvers intended to substantially position each craft with a substantially zero relative speed with respect to said reference craft.
6. The system as claimed in claim 1, comprising i) second means of relative metrology installed on each of said craft and designed to perform at least measurements of relative positions between their craft and some at least of said other spacecraft when the latter are placed in a rendezvous space, and to deduce at least from said measurements some at least of the relative positions of their spacecraft with respect to said other spacecraft, and ii) second calculation means installed on each of said craft and designed to estimate risks of collision with some at least of the other spacecraft on the basis at least of said measurements of relative position, and, in the event of risk of collision exceeding a chosen value, to determine local and fleeting avoidance maneuvers.
7. The system as claimed in claim 6, said second means of relative metrology are designed to perform estimations of relative speed of their spacecraft with respect to some at least of the other spacecraft, and in that said second calculation means are designed to estimate said risks of collision with some at least of the other spacecraft on the basis at least of said measurements of relative position andor of said measurements of relative speed.
8. The system as claimed in claim 6, wherein said second means of relative metrology and said second calculation means are suitable for being put into operation at the latest during the separation of their respective spacecraft with respect to a launcher.
9. The system as claimed in claim 1, wherein said first measurement means comprise at least two measurement stations installed on the ground at chosen spots and each designed to measure substantially simultaneously at least the distances which separate them from said spacecraft, and processing means designed to determine said orbital positions of said spacecraft on the basis at least of said substantially simultaneous distance measurements.
10. The system as claimed in claim 1, wherein said first measurement means are designed to determine said orbital positions of the spacecraft by means of a Delta DOR technique.
11. The system as claimed in claim 1, wherein said control device is installed on the ground.
12. A control device, it is suitable for forming part of a deployment control system as claimed in claim 1.
13. A spacecraft, comprising maneuvering means and intended to move in formation within a group of spacecraft of the same type, comprising second means of relative metrology and second calculation means of a deployment control system as claimed in claim 1.
14. The spacecraft as claimed in claim 13, wherein the spacecraft is devised in the form of a satellite.
15. The system as claimed in claim 2, wherein said first calculation means are designed to determine maneuvers intended to substantially position each craft at a chosen instant in a chosen position with respect to said reference trajectory and with a chosen relative speed with respect to said reference craft, having regard to said time law of said reference craft on its reference trajectory.
16. The system as claimed in claim 3, wherein said first calculation means are designed to determine maneuvers intended to substantially position each craft at a chosen instant in a chosen position with respect to said reference trajectory and with a chosen relative speed with respect to said reference craft, having regard to said time law of said reference craft on its reference trajectory.
17. The system as claimed in claim 2, comprising i) second means of relative metrology installed on each of said craft and designed to perform at least measurements of relative positions between their craft and some at least of said other spacecraft when the latter are placed in a rendezvous space, and to deduce at least from said measurements some at least of the relative positions of their spacecraft with respect to said other spacecraft, and ii) second calculation means installed on each of said craft and designed to estimate risks of collision with some at least of the other spacecraft on the basis at least of said measurements of relative position, and, in the event of risk of collision exceeding a chosen value, to determine local and fleeting avoidance maneuvers.
18. The system as claimed in claim 3, comprising i) second means of relative metrology installed on each of said craft and designed to perform at least measurements of relative positions between their craft and some at least of said other spacecraft when the latter are placed in a rendezvous space, and to deduce at least from said measurements some at least of the relative positions of their spacecraft with respect to said other spacecraft, and ii) second calculation means installed on each of said craft and designed to estimate risks of collision with some at least of the other spacecraft on the basis at least of said measurements of relative position, and, in the event of risk of collision exceeding a chosen value, to determine local and fleeting avoidance maneuvers.
19. The system as claimed in claim 4, comprising i) second means of relative metrology installed on each of said craft and designed to perform at least measurements of relative positions between their craft and some at least of said other spacecraft when the latter are placed in a rendezvous space, and to deduce at least from said measurements some at least of the relative positions of their spacecraft with respect to said other spacecraft, and ii) second calculation means installed on each of said craft and designed to estimate risks of collision with some at least of the other spacecraft on the basis at least of said measurements of relative position, and, in the event of risk of collision exceeding a chosen value, to determine local and fleeting avoidance maneuvers.
20. The system as claimed in claim 6, wherein said second means of relative metrology and said second calculation means are suitable for being put into operation at the latest during the separation of their respective spacecraft with respect to a launcher.