RO134961A2 - Guiding device for space rendezvous operations - Google Patents

Abstract

The invention relates to a guiding device for space rendezvous operations, by determining the motion of the image of the vehicle to be met, illuminated with a high-power laser beam in the near infrared range, image which is formed on a high-resolution CCD sensor. According to the invention, the device consists of a pulsed laser diode (1) which emits a laser beam (2) with a power of 20...30 W, at a wavelength of 850 nm or 905 nm, which passes through the cutout zone of a mirror (3) and is collimated by an objective lens (4) in the focus of which the laser diode (1) is placed, thereby illuminating a target (5), the beam (6) reflected by it being focused by the same objective (4) on the active surface of a high-resolution CCD sensor (8) after being reflected by the mirror (3) and passing through an interference filter (7) operating at the same wavelength with the radiation emitted by the laser diode (1), in order to eliminate the background noise, the data provided by the CCD sensor (8) being transmitted to a control and guiding unit (9) consisting of a microcontroller (10) which processes the image data, an auto-pilot (11) which generates the controls necessary for the rendezvous operation and some actuators (12) which perform the rendezvous operation.

Description

Starting from the date of publication of the patent application, the application provisionally provides the applicant with the protection conferred according to the provisions of art. 32 of Law no. 64/1991, except in cases where the patent application has been rejected, withdrawn or considered as withdrawn, the extent of the protection conferred by the patent application is determined by the claims contained in the application published in accordance with art. 23 par. (1) - (3).

IIIIIIIIIIIIIIIIIIIIIIIIIIIIIIH

ΙΙΙΙΙΗΙΙΙΙίΙΙΙΗ

OHUU DE STAT Ρ & ΝΊ KU iNVSNîO _Λ _ Patent application for resurrectionI0134961 A2 xț .. a cr> 42K Date of denunciation. · .. îZ λΙΙλίΗΠΟ. ţ

GUIDANCE DEVICE FOR SPACE MEETING OPERATIONS

The invention relates to a guidance device for space encounter operations by determining the displacement of the image of the vehicle with which the encounter operation is performed, illuminated with a laser beam of power in the near infrared field, image formed on a high resolution CCD sensor.

The invention is relevant in the context of space missions and can offer a lower cost alternative compared to current systems.

the space meeting is important for complex collaborative space missions involving multiple vehicles. This operation is also important in the context of the foreseeable future of both cubic and standard size satellite vehicles.

An example of this is the formation of a 50 cubesat formation. To achieve this formation in space requires an advanced but inexpensive control of altitude and position that can be adapted for a mission of cubed dimensions. Another example is the synthetic diaphragm radio telescope, which consists of a large number of small satellites, each representing an individual fragment of a large antenna. In order to make a useful antenna, each satellite must determine and control with high precision its own altitude and position in relation to the other satellites. the space encounter is also important in the context of the repair of a satellite made in orbit by a "repair" satellite. The repair satellite must be able to meet with a potentially uncooperative target satellite, which must receive the repair operations.

A solution for such a guidance device was described in US patent application 2007/0129879 Al, which proposes the use of the global navigation satellite system (GNSS) and ultra-wideband technology (UWB). The main disadvantage of this solution is the low accuracy of position determination, especially when the target is close, and approach maneuvers require a better determination of the target position.

The device according to the invention removes the disadvantage shown above in that it allows the determination of the relative position of the target with a very high precision, while allowing the automation of the coupling process.

The technical problem that the present invention aims to solve consists in determining the relative position of the target and guiding the spacecraft to achieve the meeting in good conditions with the target.

The device according to the invention has as main element the sensor unit, consisting of a laser diode emitter, which realizes the illumination of the target, and a receiver, which uses

EN 134961 Α2 ^ ί / a high-resolution CCD sensor, which achieves the target image and transmits it to the control and guidance unit, which generates the guidance signals and performs the necessary maneuvers.

The transmitter and receiver have a common path, this being a requirement imposed by the need to eliminate the blind spot near the target. The transmitter uses a power laser diode (20 - 30 W), which generates radiation in the near infrared range, with a wavelength of 850 or 905 nm, radiation collimated by a lens, in whose focus the laser diode is placed. The emitted laser beam passes through the cut-out central area of a 45 ° inclined plane mirror (used at the reception). The target is illuminated with a laser beam to ensure the highest possible signal-to-noise ratio: the laser radiation, with a very narrow spectral bandwidth, will pass unattended through the interference filter (very narrow band) mounted on the reception path before the CCD sensor , unlike the background radiation (parasitic light), which, having a very high spectral width, will be drastically attenuated by the interference filter. The beam reflected by the target will be focused by the lens and will be deflected towards the sensor by the 45 ° inclined flat mirror. The high-resolution CCD sensor (48 MPixels) will digitize the image formed on its active surface and will transmit the data to the control and guidance unit, which generates the guidance signals and performs the necessary maneuvers.

The invention has the following advantages:

- It is achievable using relatively inexpensive components.

- Provides high accuracy in determining the relative position of the target.

- Allows automation of the process of guiding the spacecraft to the target.

A preferred embodiment of the invention is set forth below in connection with FIG. 1. The guide device for rendez-vous operations in space determines the movement of the image of the object with which the rendez-vous operation is performed (target). For this, a pulse laser diode (1) is used which emits a laser beam (2) with a power of 20 - 30 W at a wavelength of 850 or 905 nm, the beam passing through the cut-off area of the mirror (3) and is collimated by the objective (4), in the focus of which the laser diode (1) is placed, achieving the illumination of the target (5). The beam reflected (6) by it is focused by the same lens (4) on the active surface of a high-resolution CCD sensor (8) (48 Mpixel), after being reflected by the mirror (3) and passed through a filter interference (7), working on the same wavelength as the laser radiation emitted by the diode (1), in order to remove the background noise (radiation other than the laser used). The data provided by the CCD sensor (8) is then sent to a control and guidance unit (9), consisting of a microcontroller (10), which processes the image, an autopilot (11), which generates the commands necessary for the rendez-vous operation and actuating elements (12), which perform the rendez-vous operation.

Claims (1)

Guidance device for rendezvous operations in space by determining the movement of the image of the object with which the rendezvous operation is performed (target), illuminated with a laser beam of power in the near infrared range, image formed on a high-resolution CCD sensor , characterized in that it consists of a pulsed laser diode (1) emitting a laser beam (2) with a power of 20-30 W at a wavelength of 850 or 905 nm, passing through the cut-off area of the the mirror (3) and is collimated by the objective (4), in the focus of which the laser diode is placed, illuminating the target (5), the beam reflected (6) by it being focused by the same objective (4) on the active surface of a CCD sensor (8) high resolution (48 Mpixel), after being reflected by the mirror (3) and passed through an interference filter (7), working on the same wavelength as the laser radiation emitted by the diode (1), in order to remove background noise (radiation other than laser used), the data provided by the CCD sensor (8) is then sent to a control and guidance unit (9), consisting of a microcontroller (10), which processes the image, an autopilot (11), which generates the commands necessary for the rendering operation -vous and actuators (12), which perform the rendez-vous operation.