Satellite constellation for measuring atmospheric wind speeds using doppler lidar

• US 6,634,600 B2
• Filed: 08/01/2001
• Issued: 10/21/2003
• Est. Priority Date: 08/02/2000
• Status: Expired due to Fees

• Current Assignee: Alcatel SA (Nokia Corporation)
• Original Assignee: Alcatel SA (Nokia Corporation)
• Inventors: Plantier, Jean-François, Krawczyk, Rodolphe
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/918,502
• Publication Number:
  US 20020036766A1
• Time in Patent Office: 811 Days
• Field of Search: 244/158.R, 701/226, 356/28.5, 356/139.03, 342/352, 342/354, 731/701.6, 731/702.8, 702/3
• US Class Current: 244/158.4
• CPC Class Codes: B64G 1/1021 Earth observation satellites
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2423 Sun-synchronous orbits
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: G01S 17/95 for meteorological use
• 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 constellation of satellites comprising at least two satellites in the same orbit is used to measure atmospheric wind speeds by means of a spatial wind lidar; each satellite carries a Doppler lidar, with a fixed sight axis. The orbit is a polar or quasi-polar orbit, with an orbital altitude from 350 to 500 km. The sight angles and the distribution of the satellites in the orbit are chosen so that the tracks on the surface of the Earth of the sight axes of the satellites of the constellation are substantially coincident over half of the surface of the Earth and regularly distributed over the other half of the surface of the Earth.

Claims

1. A constellation of satellites for measuring atmospheric wind speeds, said constellation including at least two satellites distributed over the same non-geosynchronous orbit and each carrying a Doppler lidar, wherein the tracks on the surface of the Earth of said sight axis of said satellites of said constellation are substantially coincident in a first area of the surface of the Earth, and are substantially regularly distributed in a second area of the surface of the Earth.

3. The constellation claimed in claim 1 wherein said orbit is a polar or quasi-polar orbit.

4. The constellation claimed in claim 1 wherein the orbital altitude is from 350 km to 500 km.

5. The constellation claimed in claim 4 including three satellites and in which the orbital altitude is from 400 km to 500 km.

6. The constellation claimed in claim 1 wherein said sight angle of one satellite relative to the nadir is from 30°

to 50° and

is preferably 45°

.

7. The constellation claimed in claim 1 wherein said satellites of said constellation have different angles between the projection of said sight axis on the surface of the Earth and the projection of the speed of said satellite on the Earth.

8. The constellation claimed in claim 7 including two satellites and in which the difference between said angles is from 75°

to 105° and

is preferably about 90°

.

9. The constellation claimed in claim 8 including three satellites and in which the difference between said angles is from 90°

to 150° and

is preferably about 120°

.

2. A constellation of satellites for measuring atmospheric wind speeds, said constellation including at least two satellites distributed over the same non-geosynchronous orbit and each carrying a Doppler lidar, wherein the sight axis of said Doppler lidar of at least one of said two satellites is fixed.

10. A constellation of satellites for measuring atmospheric wind speeds, said constellation including at least two satellites distributed over the same non-geosynchronous orbit and each carrying a Doppler lidar, wherein said constellation satisfies the condition:

$\frac{2<br><br>\mathrm{\pi <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>T_S}{n<br><br>\text{\hspace{1em}<br><br>}<br><br>T}<br><br>R<<br><br>\frac{H}{\cos <br><br>\text{\hspace{1em}<br><br>}<br><br>\mathrm{\gamma <br><br>}}<br><br><br><br>\tan <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\alpha <br><br>}}_{i+1}<br><br>\sin <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\varphi <br><br>}}_{i+1}-\tan <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\alpha <br><br>}}_i<br><br>\sin <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\varphi <br><br>}}_i<br><br>+\frac{T_S}{T}<br><br>R<br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\psi <br><br>}}_{i,i+1}\le <br><br>a+\frac{2<br><br>\text{\hspace{1em}<br><br>}<br><br>\mathrm{\pi <br><br>}<br><br>\text{\hspace{1em}<br><br>}<br><br>T_S}{n<br><br>\text{\hspace{1em}<br><br>}<br><br>T}<br><br>R$

where n is the number of satellites in the constellation, T is the period of rotation of the Earth, T_S is the orbital period, R is the radius of the Earth, H is the orbital altitude, γ

is the angle between the projection of the speed of satellite i on the surface of the Earth on passing over the equator and the rotation speed of the Earth at the equator, α

_i is the angle between the sight axis of satellite i and the nadir, φ

_i is the angle between the projection on the Earth of the sight axis of satellite i and the projection on the Earth of the speed of said satellite, ψ

_i,i+1 is the angle measured in the plane of the orbit between satellites i and i+1, and a parameter analogous to a distance and is less than 500 km.

11. The constellation claimed in claim 10 wherein said parameter a has a value less than 100 km and preferably less than 50 km.

12. A constellation of satellites for measuring atmospheric wind speeds, said constellation including at least two satellites distributed over the same non-geosynchronous orbit and each carrying a Doppler lidar, wherein the angle between said two satellites of said constellation in the plane of said orbit satisfies the condition:

$\frac{T_S}{T}<br><br>R<br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\psi <br><br>}}_{i,i+1}\le <br><br>\frac{H}{\cos <br><br>\text{\hspace{1em}<br><br>}<br><br>\mathrm{\gamma <br><br>}}<br><br><br><br>\tan <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\alpha <br><br>}}_i<br><br>\sin <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\varphi <br><br>}}_i-\tan <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\alpha <br><br>}}_{i+1}<br><br>\sin <br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\varphi <br><br>}}_{i+1}<br><br>\le <br><br>\frac{T_S}{T}<br><br>R<br><br>\text{\hspace{1em}<br><br>}<br><br>{\mathrm{\psi <br><br>}}_{i,i+1}+b$

where T is the rotation period of the Earth, T_S is the orbital period, R is the radius of the Earth, H is the orbital altitude, γ

is the angle between the projection of the speed of satellite i on the surface of the Earth on crossing the equator and the rotation speed of the Earth at the equator, α

_i is the angle between the sight axis of satellite i and the nadir, φ

_i is the angle between the projection of the sight axis of satellite i on the Earth and the projection of the speed of said satellite on the Earth, ψ

_i,i+1 is the angle measured in the plane of the orbit between satellites i and i+1, and b parameter analogous to a distance and is less than 200 km.

13. The constellation claimed in claim 12 wherein said parameter b has a value less than 20 km and preferably less than 10 km.