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param remove empty @unit

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This commit is contained in:
Daniel Agar
2016-03-14 09:12:34 +01:00
committed by Lorenz Meier
parent 146cdf578a
commit 7a9427bc34
27 changed files with 0 additions and 195 deletions
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src/modules/fw_att_control/fw_att_control_params.c
-18
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@@ -83,7 +83,6 @@ PARAM_DEFINE_FLOAT(FW_P_TC, 0.4f);
* This defines how much the elevator input will be commanded depending on the
* current body angular rate error.
*
* @unit
* @min 0.005
* @max 1.0
* @group FW Attitude Control
@@ -96,7 +95,6 @@ PARAM_DEFINE_FLOAT(FW_PR_P, 0.08f);
* This gain defines how much control response will result out of a steady
* state error. It trims any constant error.
*
* @unit
* @min 0.005
* @max 0.5
* @group FW Attitude Control
@@ -135,7 +133,6 @@ PARAM_DEFINE_FLOAT(FW_P_RMAX_NEG, 60.0f);
* The portion of the integrator part in the control surface deflection is
* limited to this value
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control
@@ -148,7 +145,6 @@ PARAM_DEFINE_FLOAT(FW_PR_IMAX, 0.4f);
* This defines how much the aileron input will be commanded depending on the
* current body angular rate error.
*
* @unit
* @min 0.005
* @max 1.0
* @group FW Attitude Control
@@ -161,7 +157,6 @@ PARAM_DEFINE_FLOAT(FW_RR_P, 0.05f);
* This gain defines how much control response will result out of a steady
* state error. It trims any constant error.
*
* @unit
* @min 0.005
* @max 0.2
* @group FW Attitude Control
@@ -173,7 +168,6 @@ PARAM_DEFINE_FLOAT(FW_RR_I, 0.01f);
*
* The portion of the integrator part in the control surface deflection is limited to this value.
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control
@@ -199,7 +193,6 @@ PARAM_DEFINE_FLOAT(FW_R_RMAX, 70.0f);
* This defines how much the rudder input will be commanded depending on the
* current body angular rate error.
*
* @unit
* @min 0.005
* @max 1.0
* @group FW Attitude Control
@@ -212,7 +205,6 @@ PARAM_DEFINE_FLOAT(FW_YR_P, 0.05f);
* This gain defines how much control response will result out of a steady
* state error. It trims any constant error.
*
* @unit
* @min 0.0
* @max 50.0
* @group FW Attitude Control
@@ -225,7 +217,6 @@ PARAM_DEFINE_FLOAT(FW_YR_I, 0.0f);
* The portion of the integrator part in the control surface deflection is
* limited to this value
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control
@@ -251,7 +242,6 @@ PARAM_DEFINE_FLOAT(FW_Y_RMAX, 0.0f);
* This defines how much the wheel steering input will be commanded depending on the
* current body angular rate error.
*
* @unit
* @min 0.005
* @max 1.0
* @group FW Attitude Control
@@ -264,7 +254,6 @@ PARAM_DEFINE_FLOAT(FW_WR_P, 0.5f);
* This gain defines how much control response will result out of a steady
* state error. It trims any constant error.
*
* @unit
* @min 0.0
* @max 50.0
* @group FW Attitude Control
@@ -277,7 +266,6 @@ PARAM_DEFINE_FLOAT(FW_WR_I, 0.1f);
* The portion of the integrator part in the control surface deflection is
* limited to this value
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control
@@ -304,7 +292,6 @@ PARAM_DEFINE_FLOAT(FW_W_RMAX, 0.0f);
* to obtain a tigher response of the controller without introducing
* noise amplification.
*
* @unit
* @min 0.0
* @max 10.0
* @group FW Attitude Control
@@ -316,7 +303,6 @@ PARAM_DEFINE_FLOAT(FW_RR_FF, 0.5f);
*
* Direct feed forward from rate setpoint to control surface output
*
* @unit
* @min 0.0
* @max 10.0
* @group FW Attitude Control
@@ -328,7 +314,6 @@ PARAM_DEFINE_FLOAT(FW_PR_FF, 0.5f);
*
* Direct feed forward from rate setpoint to control surface output
*
* @unit
* @min 0.0
* @max 10.0
* @group FW Attitude Control
@@ -340,7 +325,6 @@ PARAM_DEFINE_FLOAT(FW_YR_FF, 0.3f);
*
* Direct feed forward from rate setpoint to control surface output
*
* @unit
* @min 0.0
* @max 10.0
* @group FW Attitude Control
@@ -472,7 +456,6 @@ PARAM_DEFINE_FLOAT(FW_MAN_P_MAX, 45.0f);
/**
* Scale factor for flaps
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control
@@ -482,7 +465,6 @@ PARAM_DEFINE_FLOAT(FW_FLAPS_SCL, 1.0f);
/**
* Scale factor for flaperons
*
* @unit
* @min 0.0
* @max 1.0
* @group FW Attitude Control