From b06f8146e16d993b6ce5d315c29b437d351c108c Mon Sep 17 00:00:00 2001
From: varadk2612 <82491758+varadk2612@users.noreply.github.com>
Date: Thu, 11 Apr 2024 16:42:43 -0500
Subject: [PATCH] Update Tuning.md

---
 docs/Electrical/Tuning.md | 3 +++
 1 file changed, 3 insertions(+)

diff --git a/docs/Electrical/Tuning.md b/docs/Electrical/Tuning.md
index daf60aaa..ca915cdb 100644
--- a/docs/Electrical/Tuning.md
+++ b/docs/Electrical/Tuning.md
@@ -9,8 +9,11 @@ We have been using the same guidelines as [PX-4's Tuning Guide](https://docs.px4
 In a UAS, a PID controller ensures that the UAS responds the way the pilot expects it to. A PID controller takes in the error signal in roll, pitch, or yaw (i.e. the difference between the pilot's input command and the actual behavior) and then performs some calculations so that the error is minimized.
 
 The PID controller has gains, or constant multipliers, corresponding to three calculations:
+
 *Proportional*: This gain is proportional to the error signal. Increasing the P gain will proportionally send a larger correcting signal if there is a large current error.
+
 *Integral*: This gain is proportional to the *integral* of the error signal. Essentially it corresponds to a large signal if the cumulative error is large.
+
 *Derivative*: This gain is proportional to the derivative of the error. It contributes to a signal that is proportional to the instantaneous rate of change of error which it finds as the difference between the current and previous error.