US 2026/0217387 A1 · Generalized Method for Orbital Launch Trajectories

Abstract

The method launches a satellite as high as a first height (rh), with respect to the center of the Earth given as rh1=sf·aORBIT (or sf·rORBIT) where 1.1<sf<2 where aORBIT is the semi-major axis of the stable elliptical orbit (rORBIT for circular orbits). Then the descent stage, with satellite, starts free-fall in response to a gravitational pull of the Earth along with the assistance of the rocket propulsion applied in the direction of the selected orbital injection point, into the stable orbit. An analytical formulation is derived using the conservation of energy principle equating the total energy in the stable orbit to the first total energy, adjusted due to propellant consumed during the descent given below, providing the ability to launch satellites from any point on earth to any orbital inclination directly with no launch azimuth restrictions using less propellant or larger payloads with the same propellant, r h = 1 1 2 ⁢ GM [ v e ⁢ l ⁢ n ⁡ ( 1 + m PROP m ORBIT ) ] 2 + 1 2 ⁢ a ORBIT .

Claims29

Dependent claims

A system for launch trajectories into one of a plurality of potential orbital configurations, the system comprising:

a booster rocket, a satellite, and an Orbit Designer software program controller:
the controller providing a calculation of a launch of the satellite to a target height (rh1), as high as a first height (rh), defined with respect to the center of the Earth;
the controller providing a calculation of a gravitational first potential energy at the target height;
the controller providing a calculation of a decrease in the satellite height in response to a gravitational pull of the Earth;
the controller providing a calculation of the satellite attaining a stable orbit around the Earth defined by the formula:
x
1
2
a
2
+
y
1
2
b
2
=
1
;
where a is a semi-major axis along a x1 axis passing through the Earth;
and,
where b is a semi-minor axis along a y1 axis, orthogonal to the x1 axis.

19 more elements

A method for launch trajectories into one of a plurality of potential orbital configurations, the method comprising:

launching a payload including a descent rocket, a satellite, and a first amount of descent rocket propellant from a surface of the Earth;
the payload attaining a non-orbiting target height (rh1), defined with respect to the center of the Earth;
the payload attaining a gravitational first potential energy and a first kinetic energy at the target height, where the first gravitational energy is greater than the first kinetic energy;
decreasing the payload height in response to the Earth's gravitational pull;
creating a first angle of descent tangential to a stable orbit around the Earth, responsive to a velocity adjustment thrust;
and,
after burning the first amount of propellant, the satellite attaining the stable orbit defined by the formula:
x
1
2
a
2
+
y
1
2
b
2
=
1
;
where a is a semi-major axis along a x1 axis passing through the Earth;
and,
where b is a semi-minor axis along a y1 axis, orthogonal to the x1 axis.

21 more elements

A method of obtaining launch trajectories for one of a plurality of potential orbital configurations, the method comprising:

for a payload including a descent rocket, a satellite, and a first amount of propellant, an Orbit Designer software program identifying a target height (rh1) with respect to the center of the Earth;
the Orbit Designer software program identifying a stable orbit around the Earth defined by the formula:
x
1
2
a
2
+
y
1
2
b
2
=
1
;
where a is a semi-major axis along a x1 axis passing through the Earth;
where b is a semi-minor axis along a y1 axis, orthogonal to the x1 axis;
the Orbit Designer software program identifying a height difference between the target height and a;
the Orbit Designer software program, identifying a direction αF, thrust FD, and descent burn time TBD from the target height;
the Orbit Designer software program identifying a decrease in the payload height in response to the pull of gravity;
the Orbit Designer software program identifying a tangential alignment of the payload with the stable orbit in response to the height difference, direction αF, thrust FD, and descent burn time TBD;
and,
the Orbit Designer software program identifying an attainment of a stable orbit subsequent to burning the first amount of propellant.

21 more elements

A method of obtaining launch trajectories for one of a plurality of potential orbital configurations using Orbital Designer computer processor instructions stored on a non-transitory memory, the instructions comprising:

for a payload including a descent rocket, a satellite, and a first amount of propellant, calculating a target height (rh1) with respect to the center of the Earth;
calculating a stable orbit around the Earth defined by the formula:
1
2
⁢
m
ORBIT
[
v
e
⁢
ln
⁢
(
m
0
m
ORBIT
)
]
2
-
G
⁢
Mm
0
r
h
⁢
1
=
-
G
⁢
Mm
ORBIT
2
⁢
a
r
h
⁢
1
=
1
1
2
⁢
GM
[
v
e
⁢
ln
⁢
(
1
+
m
PROP
m
ORBIT
)
]
2
+
1
2
⁢
a
where a is a semi-major axis along a x1 axis passing through the Earth;
where b is a semi-minor axis along a y1 axis, orthogonal to the x1 axis;
calculating a height difference between the target height and a;
calculating a direction αF, thrust FD, and descent burn time TBD from the target height;
calculating a decrease in the payload height in response to the pull of gravity;
calculating a tangential alignment of the payload with the stable orbit in response to the height difference, direction αf, thrust FD, and descent burn time TBD;
and,
calculating an attainment of the satellite in a stable orbit subsequent to burning the first amount of propellant.

75 more elements

Dependencies are inferred from the claim text.

Generalized Method for Orbital Launch Trajectories

Life of this patent

Generalized Method for Orbital Launch Trajectories

Life of this patent

Abstract

Claims29