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operations
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state-vectors
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latest
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{
  "id": "SV-123",
  "spacecraftId": "550e8400-e29b-41d4-a716-446655440000",
  "spacecraftName": "GS002",
  "epoch": "2024-06-15T12:00:00Z",
  "position": [
    42164,
    0,
    0
  ],
  "velocity": [
    0,
    3.075,
    0
  ],
  "referenceFrame": "EME2000",
  "mass": 1500,
  "originator": "VALAR",
  "creationDate": "2024-06-15T12:30:00Z",
  "sourceType": "OPM_IMPORT",
  "orbitSolutionId": null,
  "hasCovariance": false
}

Documentation Index

Fetch the complete documentation index at: https://docs.valar.space/llms.txt

Use this file to discover all available pages before exploring further.

Authorizations

​
Authorization
string
header
required

API Key (format: vsp_sk_...)

Query Parameters

​
spacecraftId
string
required

Spacecraft identifier

​
includeNonConverged
boolean
default:false

Include non-converged OD results (default: false)

Response

Successfully retrieved the latest state vector

State vector representation with position, velocity, and metadata

​
covariance
object

State covariance data including 6x6 matrix and standard deviations. Null if covariance is not available.

​
creationDate
string

Creation timestamp when this state vector was created/imported in ISO-8601 format

Example:

"2024-01-15T12:30:00Z"

​
epoch
string

Epoch timestamp of the state vector in ISO-8601 format

Example:

"2024-01-15T12:00:00Z"

​
hasCovariance
boolean

Whether covariance data is available for this state vector

Example:

true

​
id
string

Unique identifier for the state vector (format: SV-{sequence})

Example:

"SV-123"

​
keplerianElements
object

Mean Keplerian orbital elements derived via DSST averaging of the osculating state. Null when the DSST conversion fails (e.g., highly perturbed orbits).

​
mass
number<double>

Spacecraft mass in kilograms

Example:

1500

​
meanElementTheory
enum<string> | null

Theory used to produce meanElements. 'DSST' on success, null when meanElements is null.

Available options:
DSST
Example:

"DSST"

​
meanElements
object

Mean Keplerian orbital elements derived via DSST averaging of the osculating state. Null when the DSST conversion fails (e.g., highly perturbed orbits).

​
orbitSolutionId
string | null

ID of the associated OrbitSolution if this state vector was produced by orbit determination. Null for imported state vectors.

Example:

"GS002-559"

​
originator
string

Originator or source of this state vector data

Example:

"VALAR"

​
position
number<double>[]

Position vector [x, y, z] in kilometers

Position vector [x, y, z] in kilometers

Example:
[42164, 0, 0]
​
referenceFrame
string

Reference frame of the state vector (e.g., EME2000, GCRF, TEME)

Example:

"EME2000"

​
sourceType
enum<string>

Source type indicating how this state vector was created. OPM_IMPORT for imported OPMs, ORBIT_DETERMINATION for OD results, MANUAL for manually entered.

Available options:
OPM_IMPORT,
ORBIT_DETERMINATION,
MANUAL
Example:

"OPM_IMPORT"

​
spacecraftId
string

ID of the spacecraft this state vector belongs to

Example:

"spacecraft-abc-123"

​
spacecraftName
string

Name of the spacecraft

Example:

"GS002"

​
velocity
number<double>[]

Velocity vector [vx, vy, vz] in km/s

Velocity vector [vx, vy, vz] in km/s

Example:
[0, 3.075, 0]