Airplane configured with a high intensity pulse laser generation system and method
In an example, the present invention provides an airplane or aerospace vehicle system configured with a high intensity pulse laser generation system.
1 . An airplane or aerospace vehicle system, the system comprising:
a cockpit section;
a fuselage section having a first end and a second end, the first end coupled to the cockpit section;
a tail section coupled to the second end of the fuselage section;
an optical aperture coupled to the fuselage;
a high intensity pulse laser generation system configured in the fuselage between the first end and the second end, the system comprising:
a light source configured to generate a pulse of a laser beam having a pulse energy power of 0.01 Joule to 10 Mega Joule an optical cavity maintained in a vacuum of 300 Torr or less and characterized by a length of free space, the optical cavity being configured to increase an intensity of the pulse from a first energy power intensity to a second higher energy power intensity propagating on a first optical path located within the optical cavity by circulating or reciprocating the pulse along the first optical path;
an optical path modification device coupled to the optical cavity, the optical path modification device configured to repeatedly change a spatial direction of the pulse propagating on the first optical path at a predetermined timing ranging from 20 milliseconds to 3 seconds, the optical path modification device configured to cause the pulse propagating on the first optical path to change from the first optical path to a second optical path that is outside of the first optical path, wherein the optical path modification device is configured to change a direction of the pulse to the second optical path when the pulse has reached the second higher density thereby generating a high intensity pulse laser beam, and a response time to change to the second optical path is from 0.01 microsecond to 30 microseconds; and
wherein the second optical path traverses through the optical aperture and outside of the airplane or aerospace vehicle.
2 . The system of claim 1 wherein the pulse of the laser beam has a wavelength range from 1020 nm to 1070 nm.
3 . The system of claim 1 , wherein each of the mirror devices has a reflectance to the laser beam of 99.99% or more.
4 . The system of claim 1 wherein each of the mirror devices comprises a dielectric multilayer mirror surface that includes a fluorine compound.
5 . The system of claim 1 wherein the pulse of the laser beam from the light source comprises a pulsed laser with a frequency of more than 100 kHz.
6 . The system of claim 1 wherein the pulse of the laser beam from the light source is a single-mode laser.
7 . The system of claim 1 wherein the light source comprises a semiconductor laser light source containing an AlInGaN-based compound.
8 . The system of claim 1 wherein the pulse intensity of laser beam generated is at least 10 3 times greater than a pulse intensity of the laser beam from the light source.
9 . An airplane or aerospace vehicle system, the system comprising:
a cockpit section;
a fuselage section having a first end and a second end, the first end coupled to the cockpit section;
an optical aperture coupled to the fuselage section;
a tail section coupled to the second end of the fuselage section;
a high intensity pulse laser generation system configured in the fuselage between the first end and the second end, the system comprising:
an optical cavity maintained in a vacuum, the optical cavity being configured to increase an intensity of a pulse from a laser beam from a first energy power intensity to a second higher energy power intensity propagating on a first optical path configured within the optical cavity by circulating or reciprocating the pulse from a light source having a pulse energy power on the first optical path;
an optical path modification device coupled to the optical cavity, the optical path modification device configured to repeatedly change a spatial direction of the laser beam propagating on the first optical path at a predetermined timing with the response time to cause the laser beam propagating on the first optical path to change a direction from the first optical path to a second optical path that is outside of the first optical path, wherein the optical path modification device is configured to change a direction of the pulse to the second optical path when the pulse has reached the second higher energy density thereby generating a high intensity pulse laser beam;
at least a pair of mirror devices, each of the mirror devices provided within the first optical path, at least one of the pair of mirror devices configured to change a position of the mirror; and
wherein the second optical path traverses through the optical aperture and outside of the airplane or aerospace vehicle.
10 . The airplane or aerospace vehicle system of claim 9 , wherein the pulse of the laser beam has a wavelength range from 1020 nm to 1070 nm.
11 . The airplane or aerospace vehicle system of claim 9 , wherein each of the mirror devices has a reflectance to the laser beam of 99.99% or more.
12 . The airplane or aerospace vehicle system of claim 9 , wherein each of the mirror devices comprises a dielectric multilayer mirror surface that includes a fluorine compound.
13 . The airplane or aerospace vehicle system of claim 9 , wherein the pulse of the laser beam from the light source comprises a pulsed laser with a frequency of more than 100 kHz.
14 . The airplane or aerospace vehicle system of claim 9 , wherein the pulse of the laser beam from the light source is a single-mode laser.
15 . The airplane or aerospace vehicle system of claim 9 , wherein the light source comprises a semiconductor laser light source containing an AlInGaN-based compound.
16 . The airplane or aerospace vehicle system of claim 9 , wherein the pulse intensity of the laser beam generated has a second pulse intensity that is at least 10 3 times greater than a first pulse intensity of the laser beam from the light source.