System and Method for Assessing the Risk of Conjunction of a Rocket Body with Orbiting and Non-Orbiting Platforms
First Claim
Patent Images
1. A target access volume determination apparatus comprising:
- a rocket processing unit, wherein the rocket processing unit comprises a first processor and wherein the first processor is configured with software executable instructions to cause the rocket processing unit to perform operations comprising;
receiving a latitude and an altitude of a launcher from which the rocket will be launched and a rocket velocity and a specified trajectory;
receiving a target altitude (altsat) and a topocentric firing azimuth (AZtopocentric) from a set of desired target altitudes and topocentric firing azimuths;
initializing the processor with values for a launcher firing angle relative to a horizon (φ
), wherein φ
is small and positive, an increment of φ
(dφ
), a range of the rocket (cc) equal to zero, and an altitude at burnout (altbo) equal to the altitude of the rocket launcher (altlauncher);
for each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric), determining;
a magnitude of a rotating earth rocket velocity (Vsez);
whether the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit;
when the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit;
determining a value of the rocket'"'"'s angular range α and
an eccentricity (ecc);
determining the rocket'"'"'s a, ecc, α
, β
, and TOF in an inertial frame, wherein a is the semi-major axis, β
is a target'"'"'s off-nadir angle to the rocket launcher, and TOF is a time of flight of the rocket from the rocket launcher to the target;
determining when the current value of α
is greater than a previous value of α
;
when the current α
is less than or equal to the previous value of α
, then setting α
MAX equal to the previous value of α and
aMAX, eccMAX, β
MAX, and TOFMAX equal to the previous values of a, ecc, β
, and TOF; and
when the current α
is greater than the previous value of α
, then incrementing φ
by dφ and
determine a next value of α
; and
an access volume processing unit, wherein the access volume processing unit comprises a second processor and wherein the second processor is configured with software executable instructions to cause the access volume processing unit to perform operations comprising;
for each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric);
receiving α
MAX aMAX, eccMAX, β
MAX, and TOFMAX;
determining a latitude of the satellite latsat and a longitudinal offset (Δ
N) corresponding to α
MAX aMAX, eccMAX, β
MAX, and TOFMAX;
identifying a point defined by altsat, latsat, and Δ
N in an inertial frame relative to a launcher location; and
defining a volume surface from the points determined for each altsat and AZtopocentric in the set of desired target altitudes and topocentric firing azimuths; and
a display and alert processing unit, wherein display and alert processing unit comprises a third processor and wherein the third processor is configured with software executable instructions to cause the display and alert processing unit to perform operations comprising;
receiving the volume surface from the access volume processing unit;
generating a visual representation of a access volume; and
sending the visual representation to a display device for display.
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Abstract
A system and method for assessing the risk of conjunction of a rocket body with orbiting and non-orbiting platforms. Two-body orbital dynamics are used to initially determine the kinematic access for a ballistic vehicle. The access may be represented in two ways: as a volume relative to its launcher and also as a geographical footprint relative to a target position that encompasses all possible launcher locations.
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Citations
20 Claims
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1. A target access volume determination apparatus comprising:
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a rocket processing unit, wherein the rocket processing unit comprises a first processor and wherein the first processor is configured with software executable instructions to cause the rocket processing unit to perform operations comprising; receiving a latitude and an altitude of a launcher from which the rocket will be launched and a rocket velocity and a specified trajectory; receiving a target altitude (altsat) and a topocentric firing azimuth (AZtopocentric) from a set of desired target altitudes and topocentric firing azimuths; initializing the processor with values for a launcher firing angle relative to a horizon (φ
), wherein φ
is small and positive, an increment of φ
(dφ
), a range of the rocket (cc) equal to zero, and an altitude at burnout (altbo) equal to the altitude of the rocket launcher (altlauncher);for each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric), determining; a magnitude of a rotating earth rocket velocity (Vsez); whether the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit; when the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit; determining a value of the rocket'"'"'s angular range α and
an eccentricity (ecc);determining the rocket'"'"'s a, ecc, α
, β
, and TOF in an inertial frame, wherein a is the semi-major axis, β
is a target'"'"'s off-nadir angle to the rocket launcher, and TOF is a time of flight of the rocket from the rocket launcher to the target;determining when the current value of α
is greater than a previous value of α
;when the current α
is less than or equal to the previous value of α
, then setting α
MAX equal to the previous value of α and
aMAX, eccMAX, β
MAX, and TOFMAX equal to the previous values of a, ecc, β
, and TOF; andwhen the current α
is greater than the previous value of α
, then incrementing φ
by dφ and
determine a next value of α
; andan access volume processing unit, wherein the access volume processing unit comprises a second processor and wherein the second processor is configured with software executable instructions to cause the access volume processing unit to perform operations comprising; for each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric); receiving α
MAX aMAX, eccMAX, β
MAX, and TOFMAX;determining a latitude of the satellite latsat and a longitudinal offset (Δ
N) corresponding to α
MAX aMAX, eccMAX, β
MAX, and TOFMAX;identifying a point defined by altsat, latsat, and Δ
N in an inertial frame relative to a launcher location; anddefining a volume surface from the points determined for each altsat and AZtopocentric in the set of desired target altitudes and topocentric firing azimuths; and a display and alert processing unit, wherein display and alert processing unit comprises a third processor and wherein the third processor is configured with software executable instructions to cause the display and alert processing unit to perform operations comprising; receiving the volume surface from the access volume processing unit; generating a visual representation of a access volume; and sending the visual representation to a display device for display. - View Dependent Claims (2, 3, 4, 5, 7, 8, 9, 10)
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6. A method for determining the accessibility of a target to an earth-launched rocket for a specified trajectory comprising:
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receiving at a rocket processing unit a latitude and an altitude of a launcher from which the rocket will be launched and a velocity of the rocket, wherein the rocket processing unit comprises a first processor; receiving at the rocket processing unit a target altitude (altsat) and a topocentric firing azimuth (AZtopocentric) from a set of desired target altitudes and topocentric firing azimuths; initializing the first processor with values for a launcher firing angle relative to a horizon (φ
), wherein φ
is small and positive, an increment of φ
(dφ
), a range of the rocket (α
) equal to zero, and an altitude at burnout (altbo) equal to the altitude of the rocket launcher (altlauncher);for each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric); using the first processor to determine a magnitude of a rotating earth rocket velocity (Vsez); and using the first processor to determine whether the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit; when the rocket has sufficient energy to reach altsat and insufficient energy to achieve orbit; using the first processor to determine a value of the rocket'"'"'s angular range α and
an eccentricity (ecc);using the first processor to determine the rocket'"'"'s a, ecc, α
, β
, and TOF in an inertial frame, wherein a is the semi-major axis, β
is a target'"'"'s off-nadir angle to the rocket launcher, and TOF is a time of flight of the rocket from the rocket launcher to the target; andusing the first processor to determine when the current value of α
is greater than a previous value of α
;when the current α
is less than or equal to the previous value of α
, then using the first processor for setting α
MAX equal to the previous value of α and
aMAX, eccMAX, β
MAX, and TOFMAX equal to the previous values of a, ecc, β
, and TOF; andwhen the current α
is greater than the previous value of α
, then using the first processor for incrementing φ
by dφ and
for determining a next value of α
; andfor each desired target altitude (altsat) and topocentric firing azimuth (AZtopocentric); receiving at an access volume processing unit α
MAX aMAX, eccMAX, β
MAX, and TOFMAX, wherein the access volume processing unit comprises a second processor;using the second processor to determine a latitude of the satellite latsat and a longitudinal offset (Δ
N) corresponding to α
MAX aMAX, eccMAX, β
MAX, and TOFMAX;using the second processor to identify a point defined by altsat, latsat, and Δ
N in an inertial frame relative to a launcher location; andusing the second processor to define a volume surface from the points determined for each altsat and AZtop ocentric; and receiving the volume surface from the access volume processing unit at a display and alert processing unit, wherein the display and alert processing unit comprises a third processor; using the third processor to generate a visual representation of a access volume; and using the third processor to send the visual representation to a display device for display.
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11. A target access volume determination apparatus comprising:
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a rocket processing unit, wherein the rocket processing unit comprises a first processor and wherein the first processor is configured with software executable instructions to cause the rocket processing unit to perform operations comprising; receiving a set of desired arrival azimuths of a rocket y, a muzzle velocity Vm of the rocket, an altitude of the rocket launcher (altlauncher) from which the rocket will be launched, a specific launch trajectory, and a target altitude altsat; initializing the first processor by setting a value for a rotating earth rocket velocity (Vsez) to Vm; for each desired arrival azimuth of a rocket γ
at the target altitude altsat;(a) determining the rocket'"'"'s a, ecc, α
, β
, and TOF in an inertial frame, wherein a is the semi-major axis, γ
is a target'"'"'s off-nadir angle to the rocket launcher, and TOF is a time of flight of the rocket from the rocket launcher to the target; and(b) determining a current value of the rocket'"'"'s angular range α
;(c) when the current α
is not equal to π
or to 0, then determining a current value of the rotating earth rocket velocity (Vsez); and(d) determining when the current value of Vsez is approximately equal to a just previous value of Vsez; when the current value of Vsez is not approximately equal to a just previous value of Vsez, then initializing the first processor with the current Vsez and performing operations (a)-(d); and when the current value of Vsez is approximately equal to the just previous value of Vsez, then determining latlauncher and longitudinal offset (Δ
N); andan access volume processing unit, wherein the access volume processing unit comprises a second processor and wherein the second processor is configured with software executable instructions to cause the access volume processing unit to perform operations comprising; receiving the latlauncher and longitudinal offset (Δ
N), wherein latlauncher and longitudinal offset (Δ
N) determine a point in an inertial frame relative to the target; andidentifying a accessibility region constructed from points determined for the selected altsat over the set of desired arrival azimuths γ
; anda display and alert processing unit, wherein display and alert processing unit comprises a third processor and wherein the third processor is configured with software executable instructions to cause the display and alert processing unit to perform operations comprising; receiving the region from the access accessibility processing unit; using the third processor to generate a visual representation of a accessibility region; and using the third processor to send the visual representation to a display device for display. - View Dependent Claims (12, 13, 14, 15, 17, 18, 19, 20)
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16. A method for determining the accessibility of a target to an earth-launched rocket comprising:
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receiving at a rocket processing unit a set of desired arrival azimuths of a rocket y, a muzzle velocity Vm of the rocket, an altitude of the rocket launcher (altlauncher) from which the rocket will be launched, and a target altitude altsat, wherein the rocket processing unit comprises a first processor; initializing the first processor by setting a value for a rotating earth rocket velocity (Vsez) to Vm; for each desired arrival azimuth of a rocket γ
at the target altitude altsat;(a) using the first processor to determine the rocket'"'"'s a, ecc, α
, β
, and TOF in an inertial frame, wherein a is the semi-major axis, β
is a target'"'"'s off-nadir angle to the rocket launcher, and TOF is a time of flight of the rocket from the rocket launcher to the target; and(b) using the first processor to determine a current value of the rocket'"'"'s angular range α
;(c) when the current α
is not equal to π
or to 0, then using the first processor to determine a current value of the rotating earth rocket velocity (Vsez); and(d) using the first processor to determine when the current value of Vsez is approximately equal to a just previous value of Vsez; when the current value of Vsez is not approximately equal to a just previous value of Vsez, then initializing the first processor with the current Vsez and performing steps (a)-(d); when the current value of Vsez is approximately equal to the just previous value of Vsez, then using the first processor to determine latlauncher and longitudinal offset (Δ
N);receiving at a accessibility processing unit the latlauncher and longitudinal offset (Δ
N), wherein the access volume processing unit comprises a second processor and wherein latlauncher and longitudinal offset (Δ
N) determine a point in an inertial frame relative to the target;using the second processor to identify a accessibility region constructed from points determined for the selected altsat over the set of desired arrival azimuths γ
;receiving the region from the access accessibility processing unit at a display and alert processing unit, wherein the display and alert processing unit comprises a third processor; using the third processor to generate a visual representation of a accessibility region; and using the third processor to send the visual representation to a display device for display.
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Specification