diff --git a/AstroLib/Src/AsOrbitParam.cpp b/AstroLib/Src/AsOrbitParam.cpp
index a737c6bf956a5acf481ac51d56a7d4d12dec158b..70b4357ad3b17d39c4369dcac03614a802e17daa 100644
--- a/AstroLib/Src/AsOrbitParam.cpp
+++ b/AstroLib/Src/AsOrbitParam.cpp
@@ -34,13 +34,13 @@ CCartState::CCartState(double xPos, double yPos, double zPos, double xVel, doubl
 {
 }
 
-//重载求负运算
+//閲嶈浇姹傝礋杩愮畻
 const CCartState CCartState::operator -() const
 {
 	return CCartState(-m_Pos, -m_Vel);
 }
 
-//重载相减运算
+//閲嶈浇鐩稿噺杩愮畻
 const CCartState& CCartState::operator -=(const CCartState& state)
 {
 	m_Pos -= state.m_Pos;
@@ -107,12 +107,12 @@ COrbElem::COrbElem(double sMajAx, double ecc, double i,
 
 
 //********************************************************************
-/// 从位置和速度矢量得到飞行器的轨道角速度
+/// 浠庝綅缃拰閫熷害鐭㈤噺寰楀埌椋炶鍣ㄧ殑杞ㄩ亾瑙掗�熷害
 /// @Author	Wang Hua
 /// @Date	2005.3.4
 /// @Input
-/// @Param	pos			飞行器位置
-/// @Param	vel			飞行器速度
+/// @Param	pos			椋炶鍣ㄤ綅缃�
+/// @Param	vel			椋炶鍣ㄩ�熷害
 /// @Output
 /// @Param	orbAngVel	orbit angular velocity			
 /// @Return			
@@ -128,18 +128,18 @@ bool AsCartStateToOrbAngVel(
 
 
 //********************************************************************
-/// 由惯性系中的绝对速度和位置计算目标VVLH坐标系(x指向前，z指向地心，
-///   y垂直轨道面)中的相对位置坐标和速度矢量
+/// 鐢辨儻鎬х郴涓殑缁濆閫熷害鍜屼綅缃绠楃洰鏍嘨VLH鍧愭爣绯�(x鎸囧悜鍓嶏紝z鎸囧悜鍦板績锛�
+///   y鍨傜洿杞ㄩ亾闈�)涓殑鐩稿浣嶇疆鍧愭爣鍜岄�熷害鐭㈤噺
 /// @author	Wang Hua
 /// @Date	2005.12.22
 /// @Input
-/// @Param	assocPos	绝对位置，即追踪飞行器位置
-/// @Param	assocVel	绝对速度，即追踪飞行器速度
-/// @Param	basePos		参考飞行器位置，即目标飞行器位置
-/// @Param	baseVel		参考飞行器速度，即目标飞行器速度
+/// @Param	assocPos	缁濆浣嶇疆锛屽嵆杩借釜椋炶鍣ㄤ綅缃�
+/// @Param	assocVel	缁濆閫熷害锛屽嵆杩借釜椋炶鍣ㄩ�熷害
+/// @Param	basePos		鍙傝�冮琛屽櫒浣嶇疆锛屽嵆鐩爣椋炶鍣ㄤ綅缃�
+/// @Param	baseVel		鍙傝�冮琛屽櫒閫熷害锛屽嵆鐩爣椋炶鍣ㄩ�熷害
 /// @Output
-/// @Param	relPos		目标轨道坐标系中的相对位置
-/// @Param	relVel		目标轨道坐标系中的相对速度
+/// @Param	relPos		鐩爣杞ㄩ亾鍧愭爣绯讳腑鐨勭浉瀵逛綅缃�
+/// @Param	relVel		鐩爣杞ㄩ亾鍧愭爣绯讳腑鐨勭浉瀵归�熷害
 //********************************************************************
 void AsStateToVVLHRelState(
             const CCoord& assocPos, const CCoord& assocVel,
@@ -160,18 +160,18 @@ void AsStateToVVLHRelState(
 
 
 //********************************************************************
-/// 由目标VVLH坐标系(x指向前，z指向地心，y垂直轨道面)中的相对位置坐标和
-///    速度矢量计算惯性系中的绝对速度和位置
+/// 鐢辩洰鏍嘨VLH鍧愭爣绯�(x鎸囧悜鍓嶏紝z鎸囧悜鍦板績锛寉鍨傜洿杞ㄩ亾闈�)涓殑鐩稿浣嶇疆鍧愭爣鍜�
+///    閫熷害鐭㈤噺璁＄畻鎯�х郴涓殑缁濆閫熷害鍜屼綅缃�
 /// @author	Wang Hua
 /// @Date	2005.12.22
 /// @Input
-/// @Param	relPos		目标轨道坐标系中的相对位置
-/// @Param	relVel		目标轨道坐标系中的相对速度
-/// @Param	basePos		参考飞行器位置，即目标飞行器位置
-/// @Param	baseVel		参考飞行器速度，即目标飞行器速度
+/// @Param	relPos		鐩爣杞ㄩ亾鍧愭爣绯讳腑鐨勭浉瀵逛綅缃�
+/// @Param	relVel		鐩爣杞ㄩ亾鍧愭爣绯讳腑鐨勭浉瀵归�熷害
+/// @Param	basePos		鍙傝�冮琛屽櫒浣嶇疆锛屽嵆鐩爣椋炶鍣ㄤ綅缃�
+/// @Param	baseVel		鍙傝�冮琛屽櫒閫熷害锛屽嵆鐩爣椋炶鍣ㄩ�熷害
 /// @Output
-/// @Param	assocPos	绝对位置，即追踪飞行器位置
-/// @Param	assocVel	绝对速度，即追踪飞行器速度
+/// @Param	assocPos	缁濆浣嶇疆锛屽嵆杩借釜椋炶鍣ㄤ綅缃�
+/// @Param	assocVel	缁濆閫熷害锛屽嵆杩借釜椋炶鍣ㄩ�熷害
 //********************************************************************
 void AsVVLHRelStateToState(
             const CCoord& relPos, const CCoord& relVel,
@@ -188,4 +188,64 @@ void AsVVLHRelStateToState(
     AsCartStateToOrbAngVel(basePos, baseVel, angVel);
     assocVel += baseVel+angVel*assocPos;
     assocPos += basePos;
+}
+
+/// 淇杞ㄩ亾鏍规暟杞崲涓轰綅缃�熷害/modified orbit element to cartesian state element.
+/// @Author	Zhang Yu
+/// @Date	2023/4/2
+/// @Input
+/// @Param	modOrb	淇杞ㄩ亾鏍规暟
+/// @Param	gm		涓績浣撳紩鍔涘父鏁�
+/// @Output
+/// @Param	pos		浣嶇疆
+/// @Param	vel		閫熷害
+/// @Return			true=鎴愬姛; false=杈撳叆閿欒
+//********************************************************************
+bool AsModOrbElemToCart(const CModOrbElem& modOrb, double gm, CCoord3& pos, CCoord3& vel)
+{
+	double m_PeriRad = modOrb.m_PeriRad;		///<杩戞嫳鐐瑰崐寰� periapsis radius in m   (0,鈭�)
+	double m_Ecc = modOrb.m_Ecc;				///<鍋忓績鐜� eccentricity   [0,鈭�)
+	double m_I = modOrb.m_I;					///<杞ㄩ亾鍊捐 inclination in radians [0,pi]
+	double m_RAAN = modOrb.m_RAAN;				///<鍗囦氦鐐硅丹缁� right ascension of ascending node  [-pi,2pi]
+	double m_ArgPeri = modOrb.m_ArgPeri;		///<杩戞嫳鐐硅 arg of periapsis in rad   [0,2pi]
+	double m_TrueA = modOrb.m_TrueA;			///<鐪熻繎鐐硅 true anomaly in radians   [-pi,2pi]
+	if ( gm <= 0 || m_PeriRad <= 0 || m_Ecc < 0 || m_I<0 || m_I>AsCPI || m_RAAN < -AsCPI || m_RAAN>2 * AsCPI || m_ArgPeri < 0 || m_ArgPeri>2 * AsCPI || m_TrueA < -AsCPI || m_TrueA>2 * AsCPI||(m_Ecc>=1&& m_TrueA>=AsCPI-acos(1.0/m_Ecc)&& m_TrueA<= AsCPI + acos(1.0 / m_Ecc)))
+	{
+		return 0;
+	}
+	else {
+		double p = m_PeriRad * (1 + m_Ecc);		///<鍗婇�氬緞 
+		double miudh = sqrt(gm / p);			///<甯告暟
+
+		double sinf = sin(m_TrueA);
+		double cosf = cos(m_TrueA);
+		double cosi = cos(m_I);
+		double sini = sin(m_I);
+		double cosAr = cos(m_ArgPeri);
+		double sinAr = sin(m_ArgPeri);
+		double cosRA = cos(m_RAAN);
+		double sinRA = sin(m_RAAN);
+		double cosRAsinAr = cosRA * sinAr;
+		double sinRAsinAr = sinRA * sinAr;
+		double cosRAcosAr = cosRA * cosAr;
+		double sinRAcosAr = sinRA * cosAr;
+
+		double r = p / (1 + m_Ecc * cosf);		///<鍦板績璺濆ぇ灏�
+		double rcosf = r * cosf;
+		double rsinf = r * sinf;
+
+		double iex = cosRAcosAr - sinRAsinAr * cosi;	
+		double iey = sinRAcosAr + cosRAsinAr * cosi;
+		double iez = sini * sinAr;
+		double ipx = -cosRAsinAr - sinRAcosAr * cosi;
+		double ipy = -sinRAsinAr + cosRAcosAr * cosi;
+		double ipz = sini * cosAr;
+		pos[0] = rcosf * iex + rsinf * ipx;
+		pos[1] = rcosf * iey + rsinf * ipy;
+		pos[2] = rcosf * iez + rsinf * ipz;
+		vel[0] = -miudh * sinf * iex + miudh * (m_Ecc + cosf) * ipx;
+		vel[1] = -miudh * sinf * iey + miudh * (m_Ecc + cosf) * ipy;
+		vel[2] = -miudh * sinf * iez + miudh * (m_Ecc + cosf) * ipz;
+		return 1;
+	}
 }
\ No newline at end of file