From 3028d360bcf9c1ac9fdfb705fdcc2372b0d3ba47 Mon Sep 17 00:00:00 2001
From: Jorge Martinez <contact@jorgemartinez.space>
Date: Mon, 9 Sep 2024 09:05:21 +0200
Subject: [PATCH] doc: update

---
 README.md | 9 +++------
 1 file changed, 3 insertions(+), 6 deletions(-)

diff --git a/README.md b/README.md
index ed72e39..2aa35cd 100644
--- a/README.md
+++ b/README.md
@@ -95,13 +95,10 @@ Suppose you want to solve for the orbit of an interplanetary vehicle (that is
 Sun is the main attractor) form which you know that the initial and final
 positions are given by:
 
-$$
-\vec{r_1} = \begin{bmatrix} 0.159321004 \\ 0.579266185 \\ 0.052359607 \end{bmatrix} \text{ [AU]}
-$$
-
-$$
+```math
+\vec{r_1} = \begin{bmatrix} 0.159321004 \\ 0.579266185 \\ 0.052359607 \end{bmatrix} \text{ [AU]} \quad \quad
 \vec{r_2} = \begin{bmatrix} 0.057594337 \\ 0.605750797 \\ 0.068345246 \end{bmatrix} \text{ [AU] }
-$$
+```
 
 The time of flight is $\Delta t = 0.010794065 \text{[year]}$. The orbit is
 prograde and direct, thus $M=0$. Remember that when $M=0$, there is only one