Probability of Conjunction Estimation for Analyzing the Electromagnetic Environment Based on a Space Object Conjunction Methodology

The introduction of the space object conjunction method in electromagnetic compatibility modeling and simulation is quite a novel concept. It is useful for the stochastic analysis of an electromagnetic (EM) environment which is based on the probability of conjunction assessment. The space conjunction methodology is anticipated as the frontline defense for the protection of active satellites in space. EM congestion occurs in an environment with the increase in the number of operational EM devices. In a theoretical sense, this congestion is analogous to the space conjunction. Therefore, the space conjunction model can be applied in the EM scenarios. In this paper, we have investigated the application of the defined conjunction model by using the analytical expression of the probability of electromagnetic conjunction, which is based on the orbital parameters of the system under test. Additionally, we have elaborated the influence of these orbital parameters on the probability of conjunction. The simulations have been performed by considering different EM scenarios and the results are validated by using Monte Carlo simulations. The results show that errors in the analytical and Monte Carlo simulations are within a 1% range, which makes the analytical model effective. Computationally, the proposed analytical model is cost effective as compared to the numerical method, i.e., Monte Carlo. Moreover, from the results, it has been validated that the probability of conjunction increases with the increase in transmitted power and decreases with the compatible threshold limit of the receiving system, thus, making this method useful for analyzing the electromagnetic environment and as a frontline safety tool for electromagnetic systems.


Introduction
Radio interference has a great influence on the overall performance of wireless communication systems. Figure 1 shows the environment where different EM communication links may cause EM interferences witheach other. This has been studied for decades and spectrum management is also well in use to solve the problems of radio interference to a large extent. However, with the increase in the number of electronic transmission systems, like navigation radars, mobile stations, and smart vehicles, especially in the electronic battlefield where many communication systems are operating in considerably small areas, the performance prediction of such systems and devices nearby is still a topic of greater importance. Traditionally, the electromagnetic compatibility (EMC) topic of greater importance. Traditionally, the electromagnetic compatibility (EMC) evaluation of a system is done by finding the radar cross-section (RCS) and with the performance evaluation of the system under test (SUT) in the presence of electromagnetic sources in EM anechoic chambers. Probabilistic methods are also being used for electromagnetic compatibility/electromagnetic interference (EMC/EMI) evaluation in communication systems. They are primarily based on the amplitude probability distribution (APD) in which the probability of interference noise is measured as the sum of the intervals during which signal samples exceed a certain threshold, normalized by the total measurement time [1,2]. This method is quite suitable for intra-system level EMC evaluation, but for the characterization of a complete EM environment, where platforms are stationary or moving in trajectories, the prediction of the EM interference in that situation is quite complex. For intersystems EMI evaluation, the performance of the SUT is typically predicted in the presence of EM sources, as mentioned earlier. It can be carried out in EM chambers in far-field regions, and the SUT is considered as the receiver in this evaluation [3] and [4] (pp. [1][2][3][4][5][6][7][8][9][10][11][12]. For the transmitters, MIL-STD 464C [4] (pp. 14-36) and [5] regulations are applicable, in which there are defined power levels to limit its interference with other electronic devices nearby. However, these tests and measurements are carried out for static systems without considering the motion uncertainties. For moving platforms different types of uncertainties, like position, velocity, and angular uncertainties, are associated with the motion of the platform. Therefore, the main objective of this article is to analyze the EMC/EMI situation for any platform and evaluate the probability of interference among them, as it is difficult to quantify the actual strength of EMI in these situations. This is because of the behavior of EM waves in the presence of multiple sources, reflections from buildings, mountains, and terrain, is difficult to analyze. Since most of the systems/sensors are mounted on the moving platforms, this makes the situation complex enough and hard to predict with the traditional methods. Recently, Baqar et al. [6] presented an idea of EM conjunction in such scenarios and its evaluation based on the space conjunction method. As stated earlier, the present description of radio interference needs to be updated to a more generalized version. Space conjunction, which is the first line of defense for all objects in space, is the methodology that is well being studied regarding conjunction and collision risk management of space objects [7]. This method is based on finding orbital parameters and, by using those parameters, the probability of conjunction is estimated. Space orbital conjunction methods are being used in collision detection analysis of space satellites with debris. The density of space debris is increasing with the increase in space missions. This is because some of the spacecraft and rocket bodies will fail and, As stated earlier, the present description of radio interference needs to be updated to a more generalized version. Space conjunction, which is the first line of defense for all objects in space, is the methodology that is well being studied regarding conjunction and collision risk management of space objects [7]. This method is based on finding orbital parameters and, by using those parameters, the probability of conjunction is estimated. Space orbital conjunction methods are being used in collision detection analysis of space satellites with debris. The density of space debris is increasing with the Symmetry 2018, 10, 255 3 of 16 increase in space missions. This is because some of the spacecraft and rocket bodies will fail and, hence, will not be able to leave their orbits-even if this was initially intended, as in case of Intelsat2, for example [8]. The remains resulting from such failed missions will not always naturally decay due to very little atmospheric drag that is present in some orbital regimes. Figure 2 shows the density of debris and spacecraft in orbits. The parameters, like density, speed, position, and rate of conjunction, have a greater influence on the conjunction analysis of space objects. The conjunction probability (P c ) is the fundamental concept for the conjunction assessment and collision avoidance of space objects. The algorithms used to compute P c are based on state vectors of positions and velocities of the objects.
Symmetry 2018, 10, x FOR PEER REVIEW 3 of 16 hence, will not be able to leave their orbits-even if this was initially intended, as in case of Intelsat2, for example [8]. The remains resulting from such failed missions will not always naturally decay due to very little atmospheric drag that is present in some orbital regimes. Figure 2 shows the density of debris and spacecraft in orbits. The parameters, like density, speed, position, and rate of conjunction, have a greater influence on the conjunction analysis of space objects. The conjunction probability ( ) is the fundamental concept for the conjunction assessment and collision avoidance of space objects. The algorithms used to compute are based on state vectors of positions and velocities of the objects. The conjunction idea can be introduced in the field of EMC/EMI modeling or predicting. In the EMC/EMI model, the platforms can be airplanes, ships, and cars, which are all moving in their own trajectories, called their orbits. If a radiation source on one platform has some interference on any devices on other platforms, it can be considered as a conjunction in the sense of electromagnetics. The method to judge whether the EM conjunction has happened or not, we usually adopt the concept of space debris as EM congestion. If talking particularly in terms of dense electromagnetic scenarios, like in electronic warfare, where many tactical movements are going on, all systems remain in some orbits (trajectories) and have associated orbital parameters (orbital parameters details are discussed in next section). An overview of the orbital parameters and their influence on the orbital conjunction analysis for EMC/EMI evaluation is given by Baqar et al. [6]. If information of the radiation source is given, its interference orbit can be found. When all orbital parameters of interference sources are known, it is not so difficult to predict the conjunction of two radio systems. The predicted results will help in analyzing the EM situation. This helps in taking precautionary measures for avoiding EM interference, hence resulting in improving the effectiveness of the systems. Since all platforms are well equipped with sophisticated EM sensors, this makes the environment electromagnetically dense. The increase of commercial platforms, like airplanes, cargo ships, and mobile stations, make the EM environment even more congested. The overview of such an EM-dense scenario, where multiple platforms are moving in their respective orbits and having particular EM power contours, can be seen in Figure 3. The power distribution of these EM sources is analogous to the size of space objects and the rate of EM conjunction can be treated as the rate of space conjunction. Based on these analogies, we can presume that the protection methods used in space conjunction can also be applied in electromagnetic situations, which gives a better situational analysis of the scenario. This paper is organized as follows: Section 2 gives the details of the conjunction prediction method; Section 3 describes the probability of the EM conjunction ( ) estimation; Section 4 shows the associated simulation results; Section 5 presents the discussion; and Section 6 offers conclusions and related future work. The conjunction idea can be introduced in the field of EMC/EMI modeling or predicting. In the EMC/EMI model, the platforms can be airplanes, ships, and cars, which are all moving in their own trajectories, called their orbits. If a radiation source on one platform has some interference on any devices on other platforms, it can be considered as a conjunction in the sense of electromagnetics. The method to judge whether the EM conjunction has happened or not, we usually adopt the concept of space debris as EM congestion. If talking particularly in terms of dense electromagnetic scenarios, like in electronic warfare, where many tactical movements are going on, all systems remain in some orbits (trajectories) and have associated orbital parameters (orbital parameters details are discussed in next section). An overview of the orbital parameters and their influence on the orbital conjunction analysis for EMC/EMI evaluation is given by Baqar et al. [6]. If information of the radiation source is given, its interference orbit can be found. When all orbital parameters of interference sources are known, it is not so difficult to predict the conjunction of two radio systems. The predicted results will help in analyzing the EM situation. This helps in taking precautionary measures for avoiding EM interference, hence resulting in improving the effectiveness of the systems. Since all platforms are well equipped with sophisticated EM sensors, this makes the environment electromagnetically dense. The increase of commercial platforms, like airplanes, cargo ships, and mobile stations, make the EM environment even more congested. The overview of such an EM-dense scenario, where multiple platforms are moving in their respective orbits and having particular EM power contours, can be seen in Figure 3. The power distribution of these EM sources is analogous to the size of space objects and the rate of EM conjunction can be treated as the rate of space conjunction. Based on these analogies, we can presume that the protection methods used in space conjunction can also be applied in electromagnetic situations, which gives a better situational analysis of the scenario. This paper is organized as follows: Section 2 gives the details of the conjunction prediction method; Section 3 describes the probability of the EM conjunction (P cEM ) estimation; Section 4 shows the associated simulation results; Section 5 presents the discussion; and Section 6 offers conclusions and related future work.

Conjunction Prediction
For the conjunction prediction of any device or system, it is important to know the concept of the orbit and its associated parameters, these parameters will be called orbital parameters later in this article. The orbital parameters for the EM scenario can be written as ( , , , , , , ). These parameters are ( , , )-system's position, -the time of operation, -operational frequency, -power density, and -spatial coverage (directional or omnidirectional). How are these parameters expressed for finding ? This is a question of interest. In this paper, we attempt to formulate an analytical expression of based on these orbital parameters. It is not easy to find the exact numerical solution. However, it is possible to approximate the solution and obtain the results within error limits. Conjunction assessment and its avoidance is of great importance considering in space or EMC/EMI conjunctions. For defining conjunction, we first consider the physical trajectory of the system and find the expression of . Then we apply a radio propagation model for complete elaboration of . While considering the trajectory of the system, the description of for such a scenario is defined as follows: the state vector (position and velocity) of system 1 (S 1 ) is Ω 1 with the covariance matrix ∁ 1 . It is assumed that at 10 the state and covariance matrix is known for S 1 . is the time of closest approach where the conjunction is likely to occur. Similarly, for system 2 (S 2 ), the state and covariance vectors, Ω 2 and ∁ 2 are known at 20 . By using the closest approach analysis, at the time of closest approach ( ), corresponding state and covariance matrices are Ω 1 ( ), Ω 2 ( ), ∁ 1 (τ), and ∁ 2 (τ), respectively. The safety radii of the two systems are 1 and 2 , respectively. This is illustrated in Figure 4 which shows the positioning error ellipsoid in the trajectory and associated state parameters at the initial and closest approach times. All of these above parameters are used to compute , which is considered as a significant parameter in finding the occurrence of conjunction. The trajectory estimation model and the covariance must be computed accurately as it may cause false alarms in the calculation.

Conjunction Prediction
For the conjunction prediction of any device or system, it is important to know the concept of the orbit and its associated parameters, these parameters will be called orbital parameters later in this article. The orbital parameters for the EM scenario can be written as O(x, y, z, t, f c , PD, ψ). These parameters are P(x, y, z)-system's position, t-the time of operation, f c -operational frequency, PD-power density, and ψ-spatial coverage (directional or omnidirectional). How are these parameters expressed for finding P cEM ? This is a question of interest. In this paper, we attempt to formulate an analytical expression of P cEM based on these orbital parameters. It is not easy to find the exact numerical solution. However, it is possible to approximate the solution and obtain the results within error limits. Conjunction assessment and its avoidance is of great importance considering in space or EMC/EMI conjunctions. For defining conjunction, we first consider the physical trajectory of the system and find the expression of P c . Then we apply a radio propagation model for complete elaboration of P cEM . While considering the trajectory of the system, the description of P c for such a scenario is defined as follows: the state vector (position and velocity) of system 1 (S 1 ) is Ω 1 with the covariance matrix 1 . It is assumed that at t 10 the state and covariance matrix is known for S 1 .
τ is the time of closest approach where the conjunction is likely to occur. Similarly, for system 2 (S 2 ), the state and covariance vectors, Ω 2 and 2 are known at t 20 . By using the closest approach analysis, at the time of closest approach (τ), corresponding state and covariance matrices are Ω 1 (τ), Ω 2 (τ), 1 (τ), and 2 (τ), respectively. The safety radii of the two systems are r 1 and r 2 , respectively. This is illustrated in Figure 4 which shows the positioning error ellipsoid in the trajectory and associated state parameters at the initial and closest approach times. All of these above parameters are used to compute P c , which is considered as a significant parameter in finding the occurrence of conjunction. The trajectory estimation model and the covariance must be computed accurately as it may cause false alarms in the P cEM calculation.

Analytical Expression of the Probability of EM Conjunction
In this section, we will derive an analytical expression for . We start by defining the conjunction definition for two objects and compute the probability of conjunction ( ), and then modify the parameters for finding the . There are various methods to calculate the probability of conjunction given by [9][10][11][12]. In this article, we used the method given by Chan [9] and Alfano et al. [11], due to its accuracy and less computational cost. As discussed in Section 2, if the state covariance matrix is given at each instance and is assumed to be statistically independent then we can combine the covariance matrix [9]. If ∁ is the combined covariance matrix, then the probability density function (PDF) for the relative position X between the both objects will be as follows [13]: where: Therefore, the probability of conjunction ( ) at any instant of time is defined as: where is the volume of the overlap region of the distributions. For simplification, let us assume both objects are spheres with as the total safety radius i.e., = 1 + 2 , then the volume , swept by the sphere centered at the primary (origin) is given as: The closed form solution for the above 3-D integral is difficult to find. Chan [9] modified the integral to 2-D by taking the following assumptions: the relative velocity of two space objects are very high and they contribute to much less time in the conjunction instance, so the relative velocity can be assumed rectilinear. He then further reduced the integral to an isotropic distribution for which it is easy to obtain the solution via numerical expansion. Alfano, in [14], said that the same 3-D to 2-D integral transformation can be directly used in 2-D problems without any approximation. Therefore, EMC evaluation for moving platforms, and considering most of the platforms in the real-world as 2-D, we consider only 2-D cases in this paper and derive the expression of . The joint PDF of the relative position coordinates (assumed uncorrelated) for the two objects (primary and secondary objects) will be bivariate Gaussian. If they are correlated, then the transformation of the principal axis can be applied [9].
can be defined as the surface integral of a bivariate PDF which is centered at , and has a combined standard deviations in and as and , respectively. The surface integral is over a circular cross-section area of combined radius ,

Analytical Expression of the Probability of EM Conjunction
In this section, we will derive an analytical expression for P cEM . We start by defining the conjunction definition for two objects and compute the probability of conjunction (P c ), and then modify the parameters for finding the P cEM . There are various methods to calculate the probability of conjunction given by [9][10][11][12]. In this article, we used the method given by Chan [9] and Alfano et al. [11], due to its accuracy and less computational cost. As discussed in Section 2, if the state covariance matrix is given at each instance and is assumed to be statistically independent then we can combine the covariance matrix [9]. If is the combined covariance matrix, then the probability density function (PDF) for the relative position X between the both objects will be as follows [13]: where: Therefore, the probability of conjunction (P c ) at any instant of time is defined as: where V is the volume of the overlap region of the distributions. For simplification, let us assume both objects are spheres with R as the total safety radius i.e., R = r 1 + r 2 , then the volume V, swept by the sphere R centered at the primary (origin) is given as: The closed form solution for the above 3-D integral is difficult to find. Chan [9] modified the integral to 2-D by taking the following assumptions: the relative velocity of two space objects are very high and they contribute to much less time in the conjunction instance, so the relative velocity can be assumed rectilinear. He then further reduced the integral to an isotropic distribution for which it is easy to obtain the solution via numerical expansion. Alfano, in [14], said that the same 3-D to 2-D integral transformation can be directly used in 2-D problems without any approximation. Therefore, EMC evaluation for moving platforms, and considering most of the platforms in the real-world as 2-D, we consider only 2-D cases in this paper and derive the expression of P cEM .
The joint PDF of the relative position coordinates (assumed uncorrelated) for the two objects (primary and secondary objects) will be bivariate Gaussian. If they are correlated, then the Symmetry 2018, 10, 255 6 of 16 transformation of the principal axis can be applied [9]. P c can be defined as the surface integral of a bivariate PDF which is centered at µ x , µ y and has a combined standard deviations in x and y as σ x and σ y , respectively. The surface integral is over a circular cross-section area of combined radius R, as shown in Figure 5. The integral parameters on the conjunction plane are µ x , µ y , σ x , σ y , and R. The P c can be written mathematically as the total area laying inside the circular cross-section: Symmetry 2018, 10, x FOR PEER REVIEW 6 of 16 as shown in Figure 5. The integral parameters on the conjunction plane are , , , , and . The can be written mathematically as the total area laying inside the circular cross-section: Chan [9] and Xian et al. [15] presented an improved analytical expression for computing by solving and replacing the two-dimensional integral by a one-dimensional Rician PDF, which can be evaluated in the form of a convergent infinite series. Chen [7] did the analogous work in which he presented the first term and the recursive expression of the infinite series, which is helpful for the programing of analytical expression due to its simplification.
The variables in Equation (3) can be parameterized as: by integration of over a circular region from 0 to 2π, the 2-D integral is converted to 1-D. After some mathematical simplification, Pc is given as: where 0 is the modified Bessel function. This PDF arises in most signal detection problems. The transformation was obtained by Rice [16], hence, it is called Rician PDF. The solution for the above Bessel function can be written as an infinite convergent series: Therefore: Chan [9] and Xian et al. [15] presented an improved analytical expression for computing P c by solving and replacing the two-dimensional integral by a one-dimensional Rician PDF, which can be evaluated in the form of a convergent infinite series. Chen [7] did the analogous work in which he presented the first term and the recursive expression of the infinite series, which is helpful for the programing of analytical expression due to its simplification.
The variables in Equation (3) can be parameterized as: by integration of θ over a circular region from 0 to 2π, the 2-D integral is converted to 1-D. After some mathematical simplification, Pc is given as: where I 0 is the modified Bessel function. This PDF arises in most signal detection problems. The transformation was obtained by Rice [16], hence, it is called Rician PDF. The solution for the above Bessel function can be written as an infinite convergent series: Therefore: We can write: where: The first term in the series is: By integration and simplification, we have: Substituting µ r : Assuming w and z as dimensionless quantities as: The expression in Equation (12) reduces to: The n th and (n − 1) th terms can be expressed recursively as: Defining a new variable as: Therefore, the recursive expression of Equation (14) can be written as: Thus, any term of P n can be obtained from the above recursive expression for all n ≥ 1. To approximate it, let us assume first that k + 1 terms can give P c , the probability of conjunction, so we may write: Xian et al. [11] state that in conjunction analysis of space objects, where R is considered relatively smaller than the position uncertainties σ x and σ y , then the truncation error is reduced to 10 −5 if considered only the first term as P c . The truncation error is reduced further to 10 −9 if the first two terms are considered. Thus, the higher sums contribute a negligible difference in summation of P c . Therefore, considering only the first term yields the error in the 3rd significant digit. By substituting the values of w and z in Equation (13), the estimated analytical expression of P c is obtained as: where R is the total size of the objects i.e., the size of transmitter and receiver systems, and is given as: σ 2 x and σ 2 y are the diagonal elements of the combined covariance matrix, which is: µ x (t) and µ y (t) are the difference of the mean trajectory paths of the two platforms, i.e.,: Although Equation (18) serves as the basic formula to analyze the probability of conjunction, if the cross-sectional radius and the miss distance is greater than σ x or σ y , then one might have to consider more terms to compute P c accurately [7]. Since R is the total size of the conjunction radius, for EM systems, considering an isotropic antenna, the propagation distance is analogous to the radius of the object. In this case, P c calculations by using Equation (17) will give accurate results as in the EMC scenario R is usually greater (depending upon the operating frequency) than σ x or σ y . We may write R t , the size of the transmitter, as a maximum of physical and EM size, i.e.,: Since we are concerned with the EM conjunction, therefore, Equation (19) becomes: where R t EM and R r EM are the EM sizes of the transmitter and receiver, respectively. For EMC evaluation, the receiver, which is the system under test, has its own compatibility threshold and is considered passive during the testing. This makes the R r EM = 0, Therefore, the conjunction probability in Equation (18) can be written as: The size R t EM depends on the compatibility threshold limit (η r ) of the receiver [5]. η r is the maximum threshold for any electronic system at which it remains electromagnetically compatible. We can find R t EM by using Friis Equation, considering free space path loss [17]: where P t is the transmitted power, η r is the threshold limit of the system under test (SUT-receiver), G t , G r are the antenna gains of the transmitter and the receiver, respectively, f is the operating frequency, and c is the velocity of electromagnetic waves. Considering the scenario where both platforms have transmitting systems installed, then R t EM1 of system 1 depends on η 2 (the threshold of receiver system 2). Similarly, the R t EM2 of system 2 is associated with η 1 and can be calculated by using Equation (26). Therefore, having P c1 and P c2 as their respective probabilities of conjunction, as shown in the schematic in Figure 6, the total probability of conjunction (P ctotal ) can be realized as a parallel system scenario. Therefore, from the theory of reliability, the total probability of conjunction P ctotal in terms of an individual system probability [18] can be written as: P ctotal = Prob (at least one system working) Using the complementary approach, we can write: Prob (at least one system working) = 1 − Prob (all system not working) For a transceiver case the transmitter and the receiver systems are independent of each other, therefore: Equation (27) is the analytical expression of total P c for the scenario where both platforms have transmitters. The EM size P c1 depends on the threshold limit of system 2 while the EM size used for P c2 expression depends on the threshold value of system 1. Using the complementary approach, we can write: For a transceiver case the transmitter and the receiver systems are independent of each other, therefore: Equation (27) is the analytical expression of total for the scenario where both platforms have transmitters. The EM size 1 depends on the threshold limit of system 2 while the EM size used for 2 expression depends on the threshold value of system 1.

Simulation Results
For the simulations, we consider two platforms, assuming transmitter ( ) (a radar system) on one platform and the receiver ( ) on the other. Both systems are installed on a platform having rectilinear motion and moving in a trajectory that has random perturbations in the and coordinates. We assume the perturbations are due to external factors, like weather, turbulence, and efficiency of the positioning devices, hence, causing random errors in the positioning of the platforms/systems since, for an unbiased estimator, the root mean square error (RMSE) is the standard deviation [19]. Horizontal positioning accuracy of a GPS systems is normally within the range of 2-8 m [20], so the mean square error would be in the range of 4-64 m 2 . In all simulations, we take the variance from this range. We further assumed the positioning errors in and are uncorrelated, i.e., = 0, having a mean value equal to zero. Both antennas are assumed to be omnidirectional with unity gains. Since navigational radars are operating at high frequency, mainly in GHz, we assume the frequency of operation is 8 GHz. Due to the high power of the radars, transmitted power is taken from the range 60-66 dBm, while the threshold of ( ) is taken from 0-10 dBm, which is the upper limit assumed for impeccable and linear functionality of the system. This range threshold is taken as microware amplifiers in EM receivers usually get saturated at these values, however, this threshold limit can be adjusted depending upon the type of EMI evaluation to be performed, e.g., EM interference from a jamming perspective, saturation, or burnout, etc. To compute the probability of EM conjunction, we neglect the effect of the physical size of the platforms. We further assumed that both platforms are moving with the same velocity. These initial conditions

Simulation Results
For the simulations, we consider two platforms, assuming transmitter (Tx) (a radar system) on one platform and the receiver (Rx) on the other. Both systems are installed on a platform having rectilinear motion and moving in a trajectory that has random perturbations in the x and y coordinates. We assume the perturbations are due to external factors, like weather, turbulence, and efficiency of the positioning devices, hence, causing random errors in the positioning of the platforms/systems since, for an unbiased estimator, the root mean square error (RMSE) is the standard deviation [19]. Horizontal positioning accuracy of a GPS systems is normally within the range of 2-8 m [20], so the mean square error would be in the range of 4-64 m 2 . In all simulations, we take the variance from this range. We further assumed the positioning errors in x and y are uncorrelated, i.e., ρ xy = 0, having a mean value equal to zero. Both antennas are assumed to be omnidirectional with unity gains. Since navigational radars are operating at high frequency, mainly in GHz, we assume the frequency of operation is 8 GHz. Due to the high power of the radars, transmitted power is taken from the range 60-66 dBm, while the threshold of Rx (η r ) is taken from 0-10 dBm, which is the upper limit assumed for impeccable and linear functionality of the Rx system. This range threshold is taken as microware amplifiers in EM receivers usually get saturated at these values, however, this threshold limit can be adjusted depending upon the type of EMI evaluation to be performed, e.g., EM interference from a jamming perspective, saturation, or burnout, etc. To compute the probability of EM conjunction, we neglect the effect of the physical size of the platforms. We further assumed that both platforms are moving with the same velocity. These initial conditions are applied in all simulations. Simulations are performed for three different trajectories. All three scenarios are shown in Figures 7-9. First is the straight-line scenario where systems are moving close and crossing each other, second case is of a circular trajectory (tangent) scenario in which they make a tangent at the time of closest approach. The third case is also circular trajectory (crossing) scenario, but moving close and crossing each other at two different instances. P cEM is computed for all simulation scenarios by using Equation (17), written P cEM analy , and the results are validated with Monte Carlo simulations, and written as P cEM MC .

Discussions
The analytical expression of shows that it depends on the four orbital parameters, e.g.., position coordinates (trajectory mean), error covariance, transmitted power, and receiver threshold. Therefore, simulations are conducted in four groups and the results are compiled to see the effect of trajectory, transmitted power ( ), receiver threshold ( ), and position covariance on . The effect of trajectory is shown in Figures 10-12, while the rest of the results are organized in Tables 1-3. Figures 10-12 show the effect of trajectories on the . In all three trajectories, all variables are kept as mean: , = 0, variance: 2 , 2 = 10 m 2 , cov: = 0, = 60 dBm, and =10 dBm. In a straight line trajectory, Figure 10, it can be seen that is increasing as both platforms are approaching close to each other. The number of peaks are also significant as it gives the number of instances at which systems are in relatively EMC incompatible zones. In Figure 10 only one peak exists for a small duration. This means that, in the whole trajectory, there exists only a single instance of closest approach ( ) where conjunction probability is high. The width of the peak shows the duration for which is subjected to the relatively high power in the whole trajectory. In Figure 11, the duration of is greater as the platforms are in close vicinity to each other for a longer duration (making tangent). In Figure 12, there are two closest approach instances ( 1 , 2 ), which shows there are two possible instances of EM conjunction in that trajectory. . Circular trajectory (Crossing): P t = 60 dBm; η r = 10 dBm; error parameters: mean: µ x , µ y = 0, variance: σ 2 x , σ 2 y = 10 m 2 , cov: ρ xy = 0.

Discussions
The analytical expression of P cEM shows that it depends on the four orbital parameters, e.g., position coordinates (trajectory mean), error covariance, transmitted power, and receiver threshold. Therefore, simulations are conducted in four groups and the results are compiled to see the effect of trajectory, transmitted power (P t ), receiver threshold (η r ), and position covariance on P cEM . The effect of trajectory is shown in Figures 10-12, while the rest of the results are organized in Tables 1-3.

Discussions
The analytical expression of shows that it depends on the four orbital parameters, e.g.., position coordinates (trajectory mean), error covariance, transmitted power, and receiver threshold. Therefore, simulations are conducted in four groups and the results are compiled to see the effect of trajectory, transmitted power ( ), receiver threshold ( ), and position covariance on . The effect of trajectory is shown in Figures 10-12, while the rest of the results are organized in Tables 1-3. Figures 10-12 show the effect of trajectories on the . In all three trajectories, all variables are kept as mean: , = 0, variance: 2 , 2 = 10 m 2 , cov: = 0, = 60 dBm, and =10 dBm. In a straight line trajectory, Figure 10, it can be seen that is increasing as both platforms are approaching close to each other. The number of peaks are also significant as it gives the number of instances at which systems are in relatively EMC incompatible zones. In Figure 10 only one peak exists for a small duration. This means that, in the whole trajectory, there exists only a single instance of closest approach ( ) where conjunction probability is high. The width of the peak shows the duration for which is subjected to the relatively high power in the whole trajectory. In Figure 11, the duration of is greater as the platforms are in close vicinity to each other for a longer duration (making tangent). In Figure 12, there are two closest approach instances ( 1 , 2 ), which shows there are two possible instances of EM conjunction in that trajectory.    . from the Monte Carlo simulation and analytical method, at the time of closest approach, is shown in Table 1. We can see that has a direct relation with (Figure 13a), which means as the transmitter power is increased, the probability of conjunction is also increased, which validates the concept of EMI in any electronic system. The percentage error in between simulated and analytical methods at the time of closest approach is calculated in the last column, showing the effectiveness of the analytical method.
Keeping the same position uncertainty values and fixed at 60 dBm , the effect of is summarized in Table 2. It can be seen that the increase in the compatibility threshold of the receiver   . from the Monte Carlo simulation and analytical method, at the time of closest approach, is shown in Table 1. We can see that has a direct relation with (Figure 13a), which means as the transmitter power is increased, the probability of conjunction is also increased, which validates the concept of EMI in any electronic system. The percentage error in between simulated and analytical methods at the time of closest approach is calculated in the last column, showing the effectiveness of the analytical method.
Keeping the same position uncertainty values and fixed at 60 dBm , the effect of is summarized in Table 2. It can be seen that the increase in the compatibility threshold of the receiver . P cEM and error in P cEM (Monte Carlo and Analytical) for circular trajectory (crossing); P t = 60 dBm; η r = 10 dBm; error parameters: mean: µ x , µ y = 0, variance: σ 2 x , σ 2 y = 10 m 2 , cov: ρ xy = 0. Figures 10-12 show the effect of trajectories on the P cEM . In all three trajectories, all variables are kept as mean: µ x , µ y = 0, variance: σ 2 x , σ 2 y = 10 m 2 , cov: ρ xy = 0, P t = 60 dBm, and η r = 10 dBm. In a straight line trajectory, Figure 10, it can be seen that P cEM is increasing as both platforms are approaching close to each other. The number of peaks are also significant as it gives the number of instances at which systems are in relatively EMC incompatible zones. In Figure 10 only one peak exists for a small duration. This means that, in the whole trajectory, there exists only a single instance of closest approach (τ) where conjunction probability is high. The width of the peak shows the duration for which Rx is subjected to the relatively high power in the whole trajectory. In Figure 11, the duration of τ is greater as the platforms are in close vicinity to each other for a longer duration (making tangent). In Figure 12, there are two closest approach instances (τ 1 , τ 2 ), which shows there are two possible instances of EM conjunction in that trajectory.
For all three trajectories, the effects of P t , η r , and the position error variance on P cEM are simulated and the results are arranged in Tables 1-3. The maximum value of P cEM is taken at the time of closest approach (τ). Simulations are done with initial conditions of position uncertainty as mean: µ x , µ y = 0, variance: σ 2 x , σ 2 y = 10 m 2 , cov: ρ xy = 0. For analyzing the effect of P t , we keep η r fixed at 10 dbm. P cEM from the Monte Carlo simulation and analytical method, at the time of closest approach, is shown in Table 1. We can see that P cEM has a direct relation with P t (Figure 13a), which means as the transmitter power is increased, the probability of conjunction is also increased, which validates the concept of EMI in any electronic system. The percentage error in P cEM between simulated and analytical methods at the time of closest approach is calculated in the last column, showing the effectiveness of the analytical method.
Keeping the same position uncertainty values and P t fixed at 60 dBm, the effect of η r is summarized in Table 2. It can be seen that the increase in the compatibility threshold of the receiver system results in the deterioration of the probability of conjunction exponentially (Figure 13b), hence, making the system more likely EM compatible.
Finally, to see the effect of variance on P cEM , we keep P t and η r of the systems fixed at 60 dBm and 10 dBm, respectively. The results in Table 3 show the inverse relation of variance with P cEM . This is because, if perturbations are high, there is a more likely chance to miss the collision. These results are useful in predicting the EM environment. By applying the threshold limit on P cEM , we can set different electromagnetic compatible levels in the whole trajectory of any platform.

Conclusions
Space orbital conjunction analysis is one of the critical aspects in orbital conjunctions. As the EM environment is also becoming dense, the concept of space orbital conjunction is quite appealing to cope with EMC/EMI problems. The space conjunction method based on the probability of conjunction estimation is applied, and the orbital parameters are modified according to the EMI scenario. By knowing the prior information of the trajectory, error covariance matrix, and the specifications of transmitter and receiver systems, the analysis can give the EMC compatibility of the systems on the platform in a specific trajectory. The results based on the analytical expression of are validated by using Monte Carlo simulations. The percentage errors between Monte Carlo and analytical expressions lie within a 1% range, which authenticates the effectiveness of the proposed analytical expression with less computational cost. The method is of great importance and well suited

Conclusions
Space orbital conjunction analysis is one of the critical aspects in orbital conjunctions. As the EM environment is also becoming dense, the concept of space orbital conjunction is quite appealing to cope with EMC/EMI problems. The space conjunction method based on the probability of conjunction estimation is applied, and the orbital parameters are modified according to the EMI scenario. By knowing the prior information of the trajectory, error covariance matrix, and the specifications of transmitter and receiver systems, the P cEM analysis can give the EMC compatibility of the systems on the platform in a specific trajectory. The results based on the analytical expression of P cEM are validated by using Monte Carlo simulations. The percentage errors between Monte Carlo and analytical expressions lie within a 1% range, which authenticates the effectiveness of the proposed analytical expression with less computational cost. The method is of great importance and well suited for moving platforms to analyze the electromagnetic compatibility in their orbit. However, the proposed model is limited to 2-D scenarios and considering omnidirectional transmitters only, i.e., making the EM shape spherical or circular (considering a 2-D or 3-D antenna pattern). These limitations simplify the calculations, but decrease their accuracy when quantifying the level of EMI. The P cEM analysis is also significant in a way that we can set the protection threshold to take precautionary measures for the safety of onboard electronic devices. Moreover, for all transmitters (Tx) in a vicinity, conjunction probabilities can be computed and, based on the protection threshold limit, it is easy to indicate the trajectory or path which is considered more EM compatible. Additionally, this method is of key importance in electronic warfare scenarios, where different platforms are moving in a close vicinity creating more chances of interference among them. Since the current proposed model has some limitations that are mentioned above, for future work we will try to investigate those limitations to make the model robust for any real-time situations (2-D or 3-D). In the future, we will also try to perform a sensitivity analysis of the parameters that are used in the conjunction model.