Navigation system, aerospace vehicle and optical marker
Simplify, downsize and reduce power of devices which comprise the satellite navigation system used in approach and docking in space. The navigation system 1 which estimates an attitude of a target object T in space comprises: an optical marker 10 that is attached to the target T and reflects light; a lighting device 20 that irradiates the target object T with light of a predetermined wavelength band; an image acquisition device 30 that acquires an image of the optical marker 10 which has reflected the light of the predetermined wavelength band; and an image processing device 40 that processes the image acquired by the image acquisition device 30 and thereby estimates the attitude of the target object T. The lighting device 20 and the image processing device 30 are loaded on an aerospace vehicle 2.
1. A navigation system which estimates an attitude of a target object in space comprising:
an optical marker that is attached to the target object and reflects light;
a lighting device that irradiates the target object with light of a predetermined wavelength band;
an image acquisition device that acquires an image of the optical marker which has reflected the light of the predetermined wavelength band; and
an image processing device that processes the image acquired by the image acquisition device and thereby estimates the attitude of the target object,
wherein the lighting device and the image acquisition device are loaded on an aerospace vehicle,
wherein the light of the predetermined wavelength band is absorbed by a heat insulation film which forms a surface of the target object.
2. The navigation system according to claim 1 , wherein the image processing device is loaded on the aerospace vehicle.
3. The navigation system according to claim 1 , wherein the image processing device is allocated on a ground station.
4. The navigation system according to claim 1 , wherein the lighting device includes a light emitting diode.
5. The navigation system according to claim 1 , wherein the optical marker includes a retroreflective material.
6. The navigation system according to claim 1 , wherein multiple optical markers are attached to a predetermined surface of the target object and are positioned rotationally asymmetrically with respect to a virtual axis which is vertical to the surface.
7. The navigation system according to claim 1 , wherein the image acquisition device includes an optical lens and an imaging sensor, and
wherein the optical lens is provided with an optical filter which transmits the light of the predetermined wavelength band.
8. An aerospace vehicle comprising:
a lighting device that irradiates an optical marker which is attached to a target object in space and reflects light with light of a predetermined wavelength band; and
an image acquisition device that acquires an image of the optical marker which has reflected the light of the predetermined wavelength band,
wherein the image which has been acquired by the image acquisition device is processed and whereby an attitude of the target object can be estimated, and
wherein the light of the predetermined wavelength band is absorbed by a heat insulation film which forms a surface of the target object.
9. An optical marker which is attached to a target object in space before the target object is launched into space,
wherein: the optical marker reflects light of a predetermined wavelength band which has been radiated from a lighting device of an aerospace vehicle; an image of the optical marker which has reflected the light of the predetermined wavelength band is acquired by an image acquisition device of the aerospace vehicle; and the image is processed by an image processing device and whereby an attitude of the target object can be estimated, and
wherein the light of the predetermined wavelength band is absorbed by a heat insulation film which forms a surface of the target object.