Data Provider Groups | Data Provider Elements
SEET Debris Flux
Computes the total debris flux of all particulates. The debris model is valid only for near-circular orbits at altitudes between roughly 300 km and 2250 km. Because the model was created using averages over long time periods (e.g., many months or a few years), it is not appropriate to output a flux value at any given time - there really is no information in different evaluations of the model over short time spans. Hence, the debris flux is evaluated at just 1 sample per requested time interval, at the midpoint of the interval. Valid for vehicles whose central body is earth.Available for these objects: LaunchVehicle, Missile, Satellite
Type: Interval data given specified evaluation intervals and step sizes. Intended to be used only with elements from this same data provider.
Availability: Reports | Graphs
Data Provider Groups
| Name | Description |
|---|---|
| Impacts | Computes the total debris flux of all particulates, at the midpoint of the given interval. |
| Damaging Impacts | Computes the total debris flux of all particulates that cause damage. |
Data Provider Elements
| Name | Dimension | Type | Description |
|---|---|---|---|
| Time | Date | Real Number or Text | Time. |
| Impact mass flux | MassFlux | Real Number or Text | The total impact mass flux from all particulates, found as the integral of the particle impact flux distribution with respect to mass. If the mean altitude is below the minimum of the model, the value will be "BelowMinAltitude"; if the mean altitude is above the maximum of the model, the value will be "AboveMaxAltitude"; if the orbit is too eccentric for the model to be valid, the value will be "OrbitTooEccentric"; if mean elements could not be computed the value will be "CannotComputeMeanElements"; the value will be "CannotComputeValue" is some other error occurs. |
| Impact mass rate | Mass Per Time | Real Number or Text | The rate of total debris impact mass, computed by multiplying the cross sectional area by the impact mass flux. If the mean altitude is below the minimum of the model, the value will be "BelowMinAltitude"; if the mean altitude is above the maximum of the model, the value will be "AboveMaxAltitude"; if the orbit is too eccentric for the model to be valid, the value will be "OrbitTooEccentric"; if mean elements could not be computed the value will be "CannotComputeMeanElements"; the value will be "CannotComputeValue" if some other error occurs. |
| Impact flux | Flux | Real Number or Text | The total impact flux from all particulates, found as a simple sum of the impact flux of all particulates. If the mean altitude is below the minimum of the model, the value will be "BelowMinAltitude"; if the mean altitude is above the maximum of the model, the value will be "AboveMaxAltitude"; if the orbit is too eccentric for the model to be valid, the value will be "OrbitTooEccentric"; if mean elements could not be computed the value will be "CannotComputeMeanElements"; the value will be "CannotComputeValue" if some other error occurs. |
| Impact rate | Unitless Per Time | Real Number or Text | The rate of total debris impacts, computed by multiplying the cross sectional area by the impact flux. If the mean altitude is below the minimum of the model, the value will be "BelowMinAltitude"; if the mean altitude is above the maximum of the model, the value will be "AboveMaxAltitude"; if the orbit is too eccentric for the model to be valid, the value will be "OrbitTooEccentric"; if mean elements could not be computed the value will be "CannotComputeMeanElements"; the value will be "CannotComputeValue" if some other error occurs. |
| MeanAltitude | Distance | Real Number | The approximate mean altitude of the vehicle used to evaluate the debris model. |
| MeanInclination | Angle | Real Number or Text | The approximate mean inclination of the vehicle used to evaluate the debris model. |
| 13 month Avg F10 | Unitless | Real Number | The average F10.7 value of the trailing 13 months prior to the sampled time. |