Laser observation space instrument and a space vehicle including it

• US 5,726,743 A
• Filed: 05/08/1995
• Issued: 03/10/1998
• Est. Priority Date: 05/27/1994
• Status: Expired due to Fees

• Current Assignee: Aerospatiale Societe Nationale Industrielle
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Krawczyk, Rodolphe
• Primary Examiner(s): Buczinski, Stephen C.
• Application Number:
  US08/438,100
• Time in Patent Office: 1,037 Days
• Field of Search: 356/28.5, 356/5.09, 356/342
• US Class Current: 356/28.5
• CPC Class Codes: G01S 17/95 for meteorological use
• CPC Class Codes: G01S 7/4811 common to transmitter and receiver
• CPC Class Codes: G01S 7/4817 relating to scanning
• CPC Class Codes: Y02A 90/10 Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

Abstract

A laser observation space instrument for the quantitative characterization by DOPPLER effect of movements within a fluid mass carried by a planet having a reference axis locally parallel to its trajectory and including a laser generator, a frequency measuring unit, first and second sighting elements aligned on the reference axis and having first and second lines of sight of non-null inclinations with respect to the reference axis and intended for emitting and receiving laser beams, a single telescope with its axis merged with the reference axis in order to send beams emitted by the laser generator to the sighting elements and to apply laser beams received by these sighting elements to the measuring unit, and rotating means for rotating the sighting elements with respect to the panel about the reference axis. The first sighting element, disposed between the telescope and the second sighting element, is adapted to transmit, to the second sighting element, along the reference axis, laser beams sent by the telescope, and vice versa.

Claims

1. A laser observation space instrument for the quantitative characterization by DOPPLER effect of movements within a fluid mass carried by a planet, said laser observation space instrument capable of being moved by a carrier vehicle along a trajectory above said fluid mass, said laser observation space instrument comprising:

a reference axis capable of being oriented locally parallel to said trajectory;

a panel for mounting said laser observation space instrument to said carrier vehicle;

a laser generator mounted on said panell

a frequency measuring unit mounted on said panel;

first and second sighting elementsl mounted on said panel and aligned on said reference axis, having first and second lines of sight of non-null inclinations with respect to said reference axis, said first and second lines of sight capable of being oriented toward said planet for the emission and reception of laser beams and having projections of opposite directions on said reference axis;

means for rotating said first and second sighting elements about said reference axis, said rotating means mounted on said panel; and

a telescope device, with its having an axis collinear with said reference axis, for sending laser beams emitted by said laser generator to said first and second sighting elements and for applying laser beams received by said first and second sighting elements to said frequency measuring unit, said telescope device including a single telescope, said first sighting element of said first and second sighting elements disposed between said telescope device and said second sighting element of said first and second sighting elements, said first sighting element adapted to transmit, to said second sighting element, along said reference axis, at least a part of said laser beams sent by said telescope device at a predetermined frequency and to transmit, to said telescope device, along said reference axis, laser beams received by said second sighting element.

2. The laser observation space instrument according to claim 1, wherein said first sighting element comprises a diffractive transmission optical element, coaxial with said telescope device, having a diameter equal to the optical diameter of said telescope device and having two transmission axes, the first transmission axis of said two transmission axes positioned collinear with said reference axis and the second transmission axis of said two transmission axes positioned collinear with said first line of sight, and wherein said second sighting element comprises a reflection optical element.

3. The laser observation space instrument according to claim 2, wherein said second sighting element comprises a mirror inclined with respect to said reference axis.

4. The laser observation space instrument according to claim 2, wherein said second sighting element comprises a diffractive reflection optical element, coaxial with said telescope device, having a diameter equal to the optical diameter of said telescope device and has a reflection axis collinear with said second line of sight.

5. The laser observation space instrument according to claim 2, wherein said laser generator has a single emission frequency at which said diffractive transmission optical element transmits a laser beam emitted from said laser generator partly along said reference axis and partly along said first line of sight, said first and second lines of sight having different inclinations with respect to said reference axis.

6. The laser observation space instrument according to claim 2, wherein said laser generator has a first emission frequency at which said diffractive transmission optical element transmits the whole of a laser beam emitted from said laser generator along said reference axis, and wherein said laser generator has a second emission frequency at which said diffractive transmission optical element transmits the whole of a laser beam emitted from said laser generator along said first line of sight.

7. The laser observation space instrument according to claim 6, wherein said first and second lines of sight have equal inclinations with respect to said reference axis.

8. The laser observation space instrument according to claim 1, wherein said first and second lines of sight have, with respect to said reference axis, inclinations between about 20°

and about 80°

.

9. The laser observation space instrument according to claim 8, wherein said inclinations are between about 40°

and about 50°

.

10. An observation space vehicle for the quantitative characterization, by DOPPLER effect, of movements within a fluid mass carried by a planet, said observation space vehicle comprising:

a platform capable of following an orbit around said planet;

a roll axis capable of being oriented parallel to said orbit;

a yaw axis perpendicular to said roll axis, said yaw axis capable of being oriented toward the center of said planet; and

the laser observation space instrument, in accordance with claim 1, fixed to said platform such that said reference axis of said laser observation space instrument is parallel to said roll axis.

11. A laser observation space instrument for the quantitative characterization by DOPPLER effect of movements within a fluid mass carried by a planet, said laser observation space instrument capable of being moved by a carrier vehicle along a trajectory above said fluid mass, said laser observation space instrument comprising:

a reference axis capable of being oriented locally parallel to said trajectory;

a panel for mounting said laser observation space instrument to said carrier vehicle;

a laser generator mounted on said panel;

a frequency measuring unit mounted on said panel;

sighting means, mounted on said panel and aligned on said reference axis, having at least first and second lines of sight of non-null inclinations with respect to said reference axis, said at least first and second lines of sight capable of being oriented toward said planet for the emission and reception of laser beams, said sighting means having a diffractive optical element; and

a telescope device having an axis collinear with said reference axis, for sending laser beams emitted by said laser generator to said sighting means and for applying laser beams received by said sighting means to said frequency measuring unit, said telescope device including a single telescope, said diffractive optical element of said sighting means being adapted to split laser beams sent by said telescope device at a predetermined frequency into at least two beams having different directions and to send to said telescope device, along said reference axis, laser beams received by said sighting means along said different directions.

12. The laser observation space instrument according to claim 11, wherein said sighting means comprises a diffractive reflecting optical element adapted to reflectively split a laser beam into different laser reflected beams.