Circular Deorbit Interface Burn
Calculate an impulsive retrograde burn from a circular orbit to a supplied interface periapsis in consistent km/s units; no atmospheric landing path is inferred.
Description
An impulsive retrograde burn from a circular orbit can lower the opposite apsis to a specified interface radius.
An impulsive retrograde burn from a circular orbit can lower the opposite apsis to a specified interface radius. The resulting ellipse defines an orbital geometry rather than an atmospheric landing path.1
Calculate an impulsive retrograde burn from a circular orbit to a supplied interface periapsis in consistent km/s units; no atmospheric landing path is inferred.
When to use Circular Deorbit Interface Burn
Use this tool to calculate an impulsive retrograde burn from a circular orbit to a supplied interface periapsis in consistent km/s units; no atmospheric landing path is inferred.
Prepare the orbital state or model parameters in one reference frame. Confirm compatible distance/time units and the stated angular and gravitational-parameter conventions.
How to use Circular Deorbit Interface Burn and understand its results
- Prepare the orbital state or model parameters in one reference frame. Confirm compatible distance/time units and the stated angular and gravitational-parameter conventions.
- Enter mu, initialOrbitRadius, targetPeriapsisRadius using the field table and calculation rules, then run the tool.
- Read retrogradeDeltaV, transferSemimajorAxis. The explanation below defines the units, signs, ordering and any flags or placeholder values.
- If the tool reports an input issue, correct the values and run it again. Apply the stated assumptions when interpreting a successfully returned result.
| Input field | Meaning | Value type; see rules below | Requirement |
|---|---|---|---|
| mu | Gravitational parameter, using the same distance and time units throughout; km³/s² for km and seconds. | number | Required |
| initialOrbitRadius | Initial orbit radius | number | Required |
| targetPeriapsisRadius | Target periapsis radius | number | Required |
Enter positive μ and center-referenced radii, with target periapsis no larger than the initial circular radius. Using km and seconds yields deltaV in km/s and axis in km. The tool returns the retrograde burn magnitude and transfer axis. Equal radii require zero burn.
aTransfer = (initialRadius+targetPeriapsis)/2; deltaV = sqrt(μ/initialRadius)−visViva(initialRadius,aTransfer) Units, indexing, boundary conditions and exceptional cases are defined in the calculation rules above.
| Output field | Meaning | Value type |
|---|---|---|
| retrogradeDeltaV | Retrograde delta v | number |
| transferSemimajorAxis | Transfer semimajor axis | number |
{
"input": {
"mu": 1,
"initialOrbitRadius": 2,
"targetPeriapsisRadius": 1
},
"output": {
"retrogradeDeltaV": 0.12975651199692173,
"transferSemimajorAxis": 1.5
}
}Limitations and assumptions
It does not check a body's radius, atmospheric corridor, entry timing, heating or landing location. Surface altitudes must first be converted to center-referenced radii.
Numeric inputs must be finite. Follow the calculation-specific rules for overflow, underflow and exceptional cases. Missing required fields, extra fields, wrong value types and violations of the calculation rules are input errors.
Alternative or Complementary methods
Use Hohmann Transfer Budget: Compute both coplanar Hohmann burn magnitudes, total impulse, and half-period coast time for circular endpoints. For a complementary task, use Aerocapture Corridor Margin: Audit a predicted entry-angle uncertainty band against a supplied aerocapture corridor; no atmosphere-specific corridor is embedded.
References
-
Circular Deorbit Interface Burn — tool.io
Similar or alternative tools
- Hohmann Transfer Budget
Compute both coplanar Hohmann burn magnitudes, total impulse, and half-period coast time for circular endpoints.
- Aerocapture Corridor Margin
Audit a predicted entry-angle uncertainty band against a supplied aerocapture corridor; no atmosphere-specific corridor is embedded.