Advanced Station Keeping Delta V Calculator

Calculator Inputs

Mission Duration (years)

Initial Spacecraft Mass (kg)

Thruster Specific Impulse (s)

Radial Delta V per Burn (m/s)

Radial Burns per Year

In-Track Delta V per Burn (m/s)

In-Track Burns per Year

Cross-Track Delta V per Burn (m/s)

Cross-Track Burns per Year

Wheel Dump Delta V per Event (m/s)

Wheel Dump Events per Year

Extra Annual Delta V (m/s)

Maneuver Efficiency (%)

Contingency Margin (%)

Annual Budget Growth (%)

Reset

Example Data Table

Mission Years	Initial Mass (kg)	Isp (s)	Radial (m/s × burns/yr)	In-Track (m/s × burns/yr)	Cross-Track (m/s × burns/yr)	Wheel Dump (m/s × events/yr)	Extra Annual (m/s)	Efficiency (%)	Margin (%)	Growth (%)	Year 1 Budget (m/s)	Mission Total (m/s)	Propellant (kg)
5.00	1,200.00	220.00	0.180 × 12	0.220 × 12	0.350 × 6	0.050 × 24	1.200	96.00	15.00	2.00	11.141	57.976	31.817

Formula Used

1. Annual ideal delta v
ΔV_ideal = (ΔV_radial × N_radial) + (ΔV_in-track × N_in-track) + (ΔV_cross-track × N_cross-track) + (ΔV_wheel × N_wheel) + ΔV_extra

2. Efficiency adjusted annual delta v
ΔV_adjusted = ΔV_ideal ÷ (Efficiency ÷ 100)

3. Budgeted annual delta v
ΔV_budget,year1 = ΔV_adjusted × (1 + Contingency ÷ 100)

4. Year by year mission budget
ΔV_year,i = ΔV_budget,year1 × (1 + Growth ÷ 100)^i-1

5. Total mission delta v
ΔV_mission = Σ ΔV_year,i
Partial years are scaled by the fraction of the final year used.

6. Propellant estimate from the rocket equation
m_prop = m₀ × [1 - exp(-ΔV_mission ÷ (Isp × g₀))]
where g₀ = 9.80665 m/s²

This model is useful for preliminary engineering budgets, sensitivity checks, and propellant planning. Flight programs may use more detailed environmental, orbit, and control models.

How to Use This Calculator

Enter the full mission duration in years.
Provide the spacecraft initial mass and thruster specific impulse.
Enter per-burn delta v and yearly burn counts for radial, in-track, and cross-track control.
Include wheel dump delta v and wheel dump events if momentum management consumes propellant.
Add any extra annual delta v for drag, solar pressure, safe mode recovery, or operational reserves.
Set maneuver efficiency, contingency margin, and annual growth assumptions.
Click the calculate button to display the result above the form.
Review the summary cards, component table, and Plotly chart.
Use the CSV and PDF buttons to export the current results.

FAQs

1. What does station keeping delta v mean?

It is the velocity change budget needed to hold a spacecraft near its required orbit slot, attitude-control strategy, or pointing corridor over time.

2. Why separate radial, in-track, and cross-track components?

Each axis can have different disturbance sources, correction frequencies, and operational limits. Splitting them makes the budget easier to understand and defend.

3. What does maneuver efficiency change?

Lower efficiency increases the real propellant cost. It accounts for steering losses, finite burn effects, attitude errors, and practical execution losses.

4. Why include a contingency margin?

A contingency margin protects the mission against modeling uncertainty, environmental variation, unexpected recoveries, and operational changes later in life.

5. What is annual budget growth?

It represents a rising yearly delta v need. Teams may use it when disturbances, aging, mission complexity, or control effort are expected to increase.

6. Does this calculator replace a detailed orbit tool?

No. It is a planning calculator. Detailed mission design still needs high-fidelity orbit propagation, environmental models, and operations analysis.

7. How is propellant mass estimated here?

The page uses the classical rocket equation with your mission total delta v, initial spacecraft mass, and thruster specific impulse.

8. Can I use this for electric propulsion?

Yes, for early budgeting. Enter the appropriate specific impulse and realistic annual delta v assumptions, then validate the result with mission-specific thrust modeling.