Here you can approximately estimate an orbit from two position vectors and time. The orbital estimate will be more accurate for smaller time intervals. For example, for a 700 Km altitude orbit, 5 second time interval between position vectors will give good accuracy.

Enter the necessary inputs below.

First position vector at t₀
x1
y1
z1

Second position vector at t₁
x2
y2
z2

after seconds

Velocity vector at t₀
v_x
v_y
v_z

The Keplerian orbital elements at t₀ are

Semi-major axis(Kms): Eccentricity:
Inclination: Arg of Perigee:
Right Asc of Asc Node: Mean Anomaly:
True Anomaly: Eccentric Anomaly:

---

Questions? ContactSheela V.Belur at bvsheela@yahoo.com

---