Systems and methods for satellite constellation launch using air-launched vehicles

1. A method for determining aerial launch sites for establishing a satellite constellation using an aircraft configured to carry and deploy a plurality of satellite air-launch vehicles, the method comprising:

receiving an indication of a desired satellite constellation, wherein the desired satellite constellation comprises a first satellite traveling in a first orbit and a second satellite traveling in a second orbit, and wherein the first orbit comprises first orbit parameters and the second orbit comprises second orbit parameters, the first and second orbit parameters each respectively comprising at least: a semi-major axis, an inclination, and a longitude of an ascending node;

determining, based on information about an accessible range of an aircraft configured to carry a first satellite launch vehicle and a second launch vehicle, a geographical area that the aircraft can access without landing, the first launch vehicle including the first satellite and the second launch vehicle including the second satellite;

determining, based on the first orbit parameters, a first aerial launch site for launching the first satellite from the aircraft into the first orbit, the first aerial launch site comprising a first geographical position and a first launch time, the first geographical position within the geographical area that the aircraft can access without landing;

receiving mission parameters indicating one or more of flight conditions for the aircraft and launch conditions of air-launch, via the first launch vehicle, of the first satellite at the first aerial launch site;

determining, based on the second orbit parameters and the received mission parameters, a second aerial launch site for launching the second satellite from the aircraft into the second orbit, the second aerial launch site comprising a second geographical position and a second launch time, the second geographical position within the geographical area that the aircraft can access without landing.

2. The method of claim 1 , further comprising determining a time that the aircraft can maintain flight without landing, and wherein a time period between the first launch time and the second launch time is less than the calculated time that the aircraft can maintain flight without landing.

3. The method of claim 1 , wherein the information about the accessible range of the aircraft comprises one or more of: a fuel capacity of the aircraft, a maximum speed of the aircraft, a cruising speed of the aircraft, a cruising altitude of the aircraft, and a cargo capacity of the aircraft.

4. The method of claim 1 , wherein determining the geographical area that the aircraft can access without landing comprises calculating the geographical area based on information about at least one of the following: weather conditions within the geographical area, wind conditions within the geographical area, flight altitude within the geographical area, flight plan or terrain restrictions within the geographical area, and accessible airports within the geographical area.

5. The method of claim 1 , wherein the orbit parameters further include at least one of the following: an altitude, an eccentricity, an argument of perigee, a radius of perigee, a radius of apogee, and a time of perigee passage.

6. The method of claim 1 , wherein the first orbit is different than the second orbit.

7. The method of claim 1 , wherein the mission parameters indicating one or more of flight conditions for the aircraft and launch conditions of air-launch include one or more of: weather conditions within the geographical area, wind conditions within the geographical area, flight altitude within the geographical area, flight plan or terrain restrictions within the geographical area, and accessible airports within the geographical area.

8. The method of claim 1 , further comprising:

transmitting the second aerial launch site for launching the second satellite to the aircraft.

9. A method for determining aerial launch sites for establishing a satellite constellation using an aircraft configured to carry and deploy a plurality of satellite aerial launch vehicles, the method comprising:

determining a first geographical area that an aircraft can access without landing based on an accessible range of the aircraft, the aircraft configured to launch a first satellite into a first orbit and a second satellite into a second orbit via deployment of a first and second satellite aerial launch vehicle, wherein each of the first orbit and the second orbit comprise orbit parameters comprising at least a semi-major axis, an inclination, and a longitude of an ascending node;

determining a first launch site for launching the first satellite into the first orbit and a second launch site for launching the second satellite into the second orbit, wherein the first launch site comprises a first geographical position within the first geographical area and a first launch time, and wherein the second launch site comprises a second geographical position within the first geographical area and a second launch time;

subsequent to determining the first launch site and the second launch site, receiving mission information indicating one or more of flight conditions for the aircraft, the mission information affecting the accessible range of the aircraft;

determining, based on the received information, a second geographical area that the aircraft can access without landing, the second geographical area different than the first geographic area;

determining, based on the received information, that one of the first launch site and second launch site is not suitable for aerial launching the first satellite into the first orbit or the second satellite into the second orbit, respectively;

in response to determining that one of the first launch site and second launch site is not suitable for aerial launching determining a third launch site for launching the first satellite into the first orbit or the second satellite into the second orbit, respectively, wherein the third launch site comprises a third geographical position within the second geographical area and a third launch time.

10. The method of claim 9 , wherein determining that one of the first launch site and second launch site is not suitable for aerial launching comprises determining that the one of the first launch site and second launch site is not within the second geographical area.

11. The method of claim 9 , wherein the accessible range of the aircraft is determined based on one or more of a fuel capacity of the aircraft, a maximum speed of the aircraft, a cruising speed of the aircraft, a cruising altitude of the aircraft, and a cargo capacity of the aircraft.

12. The method of claim 9 , wherein mission information indicating one or more of flight conditions for the aircraft includes one or more of the following: weather conditions within the geographical area, wind conditions within the geographical area, altitude within the geographical area, flight plan or terrain restrictions within the geographical area, and accessible airports within the geographical area.

13. The method of claim 9 , wherein the orbit parameters further include at least one of the following: an altitude, an eccentricity, an argument of perigee, a radius of perigee, a radius of apogee, and a time of perigee passage.

14. The method of claim 9 , wherein the first orbit is different than the second orbit.

15. The method of claim 9 , further comprising:

transmitting the third launch site to the aircraft.

16. A computer program product for determining aerial launch sites for establishing a satellite constellation using an aircraft configured to carry and deploy a plurality of satellite air-launch vehicles, the computer program product comprising a non-transitory computer readable storage medium having instructions stored therein, the instructions when executed by a processor, are configured to cause the processor to:

receive an indication of a desired satellite constellation, wherein the desired satellite constellation comprises a first satellite traveling in a first orbit and a second satellite traveling in a second orbit, and wherein the first orbit comprises first orbit parameters and the second orbit comprises second orbit parameters, the first and second orbit parameters each respectively comprising at least: a semi-major axis, an inclination, and a longitude of an ascending node;

determine, based on information about an accessible range of an aircraft configured to carry a first satellite launch vehicle and a second launch vehicle, a geographical area that the aircraft can access without landing, the first launch vehicle including the first satellite and the second launch vehicle including the second satellite;

determine, based on the first orbit parameters, a first aerial launch site for launching the first satellite from the aircraft into the first orbit, the first aerial launch site comprising a first geographical position and a first launch time, the first geographical position within the geographical area that the aircraft can access without landing;

receive mission parameters indicating one or more of flight conditions for the aircraft and launch conditions of air-launch, via the first launch vehicle, of the first satellite at the first aerial launch site;

determine, based on the second orbit parameters and the received mission parameters, a second aerial launch site for launching the second satellite from the aircraft into the second orbit, the second aerial launch site comprising a second geographical position and a second launch time, the second geographical position within the geographical area that the aircraft can access without landing.

17. The computer program product of claim 16 , wherein the instructions, when executed by a processor, are configured to further cause the processor to:

determine a time that the aircraft can maintain flight without landing, and wherein a time period between the first launch time and the second launch time is less than the calculated time that the aircraft can maintain flight without landing.

18. The computer program product of claim 16 , wherein the information about the accessible range of the aircraft comprises one or more of: a fuel capacity of the aircraft, a maximum speed of the aircraft, a cruising speed of the aircraft, a cruising altitude of the aircraft, and a cargo capacity of the aircraft.

19. The computer program product of claim 16 , wherein being configured to determine the geographical area that the aircraft can access without landing comprises calculating the geographical area based on information about at least one of the following: weather conditions within the geographical area, wind conditions within the geographical area, flight altitude within the geographical area, flight plan or terrain restrictions within the geographical area, and accessible airports within the geographical area.

20. The computer program product of claim 16 , wherein the mission parameters indicating one or more of flight conditions for the aircraft and launch conditions of air-launch include one or more of: weather conditions within the geographical area, wind conditions within the geographical area, flight altitude within the geographical area, flight plan or terrain restrictions within the geographical area, and accessible airports within the geographical area.