Research Article  Open Access
Quanwu Li, Manfeng Dou, Bo Tan, Haitao Zhang, Dongdong Zhao, "ElectromagneticThermal Integrated Design Optimization for Hypersonic Vehicle ShortTime Duty PM Brushless DC Motor", International Journal of Aerospace Engineering, vol. 2016, Article ID 9725416, 9 pages, 2016. https://doi.org/10.1155/2016/9725416
ElectromagneticThermal Integrated Design Optimization for Hypersonic Vehicle ShortTime Duty PM Brushless DC Motor
Abstract
High reliability is required for the permanent magnet brushless DC motor (PMBLDCM) in an electrical pump of hypersonic vehicle. The PMBLDCM is a shorttime duty motor with highpowerdensity. Since thermal equilibrium is not reached for the PMBLDCM, the temperature distribution is not uniform and there is a risk of local overheating. The winding is a main heat source and its insulation is thermally sensitive, so reducing the winding temperature rise is the key to the improvement of the reliability. In order to reduce the winding temperature rise, an electromagneticthermal integrated design optimization method is proposed. The method is based on electromagnetic analysis and thermal transient analysis. The requirements and constraints of electromagnetic and thermal design are considered in this method. The split ratio and the maximum flux density in stator lamination, which are highly relevant to the windings temperature rise, are optimized analytically. The analytical results are verified by finite element analysis (FEA) and experiments. The maximum error between the analytical and the FEA results is 4%. The errors between the analytical and measured windings temperature rise are less than 8%. It can be proved that the method can obtain the optimal design accurately to reduce the winding temperature rise.
1. Introduction
There are many kinds of permanent magnet brushless DC motor (PMBLDCM) in the engine of hypersonic vehicle to achieve fast, flexible, and precise thrust control [1–5]. These PMBLDCMs have different load profiles, which can be classified by the standard of IEC 600341:2010 as ten kinds of duty types: S1 to S10 [6]. The shorttime duty (S2) PMBLDCM in hypersonic vehicle can be used in pumps, actuators, fans, and so on. Reliability and powerdensity are the fundamental requirements for the hypersonic vehicle PMBLDCM [7–9]. Thermal equilibrium is not reached for shorttime duty PMBLDCM, so there is a risk of local overheating [10, 11]. Overheat can cause damage to those components which are sensitive to the temperature, especially, the winding insulation. As the temperature increases, the winding insulation lifetime is heavily reduced by the thermalaging degradation effect [12–14]. Reliability of the shorttime duty PMBLDCM is directly affected by the winding temperature rise. Therefore, reducing the winding temperature rise is the key to the improvement of the PMBLDCM’s reliability [15].
Both the electromagnetic and thermal designs need to be concerned for the PMBLDCM. The electromagnetic and thermal design parameters are coupled. The electromagneticthermal integrated design needs to be adopted to reduce the winding temperature rise. There are different types of electromagneticthermal integrated design methods proposed in the literatures. Nevertheless, these methods can be divided into two main categories: numerical methods and analytical methods [12, 15–21]. The two methods have their own advantages and disadvantages. There are also some approaches which combine the two methods [16, 17]. The numerical methods, which are based on the finite element analyses (FEA) and computational fluid dynamics (CFD), can get the accurate results intuitively. However, the numerical methods have high requirements in terms of model setup and computational time [19, 20]. The analytical methods, which are based on the electromagnetic and thermal parametric model, provide a fast and accurate solution for the electromagneticthermal integrated design optimization [20, 21]. In preceding publications, the electromagneticthermal integrated design optimization is based on the thermal steady state. However, the winding temperature is directly affected by the thermal transients for the shorttime duty PMBLDCM. Therefore, in this paper, an analytical electromagneticthermal integrated design optimization method, which is based on the thermal transients, is studied for the shorttime duty PMBLDCM.
Some main design parameters are highly relevant to the electromagnetic and thermal performance, such as the stator outer diameter , the stator inner diameter , and the motor active axial length [16–21]. The winding temperature rise can be decreased by optimizing the parameters. In some existing papers, there are too many variables involved and the optimization is complex [15, 19–21]. According to motor design theory, the main design parameters are determined by the electric load and magnetic load, which can be converted to the maximum flux density in the stator lamination , the stator inner diameter , and copper loss [22]. When two of , , and are determined, the dimensions of the PMBLDCM can be obtained. For lowspeed PMBLDCM, the copper loss is the only main loss, and so and are usually chosen to optimize [23–28]. For the highpowerdensity PMBLDCM with highspeed, and are suitable for the optimization. In order to make data comparable, is usually expressed as split ratio, which is the ratio of the stator inner diameter to the outer diameter . In this paper, the electromagnetic and thermal parameters are converted to the functions of the split ratio and . Only two variables are involved, so the optimization can be highly simplified.
The split ratio is an important design parameter since it has a significant influence on temperature rise, torque, loss, efficiency, and cost [23–27]. There are many investigations on the optimization of the split ratio in some existing papers. Different split ratio optimization methods for electrically excited motors, surface mounted PM motors, interior PM motors, external rotor PM motors, and so forth are presented in [23–25]. These methods are aimed at lowspeed motor and thermal limitation is achieved by limiting the copper loss. In [26], Tang et al. indicate that the split ratio has a significant influence on temperature rise of the shorttime duty PMBLDCM. In [27], Reichert et al. indicate that the local thermal situations should be considered, especially for the stator winding, which is one of the main heat sources; an analytical split ratio optimization method for lowspeed PMBLDCM is developed with global and local thermal limitations. In [23–27], the split ratio has been optimized for these PMBLDCMs whose losses are dominated by the copper loss, whereas other losses can be neglected. Speed has a significant influence on the optimal split ratios [28]. For the highpowerdensity PMBLDCM in this paper, the iron loss, the rotor eddy current loss, the rotor air friction loss, and the mechanical friction loss should be considered in the design optimization.
In this paper, an electromagneticthermal integrated design optimization method is proposed to reduce the winding temperature rise of the shorttime duty PMBLDCM. The analytical design model and electromagnetic torque equation are given in Section 2. The losses are calculated in Section 3. The thermal transient analysis and the optimal design determination method are presented in Section 4. Finally, the analytical optimization results are verified by FEA and experiments.
2. Electromagnetic Torque Calculation
The PMBLDCM intended to design is used in an electrical pump of hypersonic vehicle. High reliability and highpowerdensity are required. The PMBLDCM operates for a short time in a flight. Some constraints for the PMBLDCM are given as follows:(1)The motor is required to be able to operate 300 s per cycle with full load. The load profile is shown in Figure 1.(2)The rotational speed and torque under full load condition are 10000 r/min and 1.6 N·m, respectively.(3)Outer diameter and length of the motor are limited.(4)The operating altitude is 20 km.(5)The motor is cooled by natural cooling.(6)The maximum ambient temperature is 80°C.
The operation time of the PMBLDCM is far less than the time deenergized and at rest. There is enough time for it to reestablish motor temperatures within 2°C of the coolant temperature [6]. Therefore, the PMBLDCM is a shorttime duty motor.
Air density at altitude of 20 km is 0.0889 kg/m^{3}, which is 1/14 that of 0 km. At high altitudes, due to the thin air, the convection cooling capacity is reduced.
Some designs of the PMBLDCM prototype, such as 120° electrical conduction, inner rotor, surface mounted magnets, airgap width, slots number, poles number, outer stator diameter, and axial length, have been designed previously before optimization. Some requirements and design parameters are shown in Table 1.

The configuration and main geometric parameters of the PMBLDCM are shown in Figure 2, where is the stator tooth width; is the stator back iron width; is the toothtip height; and are the outer diameter and inner diameter of the stator core, respectively; is the stator slot area.
The split ratio is given as
The stator tooth width and the stator back iron width can be expressed aswhere is the airgap flux density, which is nearly a constant for surface mounted PM motors [24]; Q is the stator slots number; p is the poles number.
According to the geometric relationships and the expressions of and , the slot area can be obtained aswhere F(λ, ) is a function of λ and , shown aswhere ε is the ratio of 2 and :
The crosssectional area of a conductor is given aswhere is the slot fill factor; is the number of turns each phase.
The backEMF of a single conductor is given aswhere is the angular velocity of the rotor; is the active motor axial length.
The phase backEMF can be obtained aswhere is the winding factor.
The electromagnetic torque is given aswhere is the winding current.
3. Loss Calculation
Losses are the heat source that causes increase of motor temperature. Losses of the highpowerdensity PMBLDCM mainly include the copper loss, the iron loss, the rotor eddy current loss, the mechanical friction loss, and the rotor air friction loss [29].
3.1. Copper Loss
When the winding temperature of the PMBLDCM is ambient temperature , the winding temperature rise is 0, and the copper loss can be expressed aswhere is the resistivity of copper at ambient temperature ; is the winding phase resistance; is the average endwinding length, which is given aswhere is winding pitch.
According to (3)–(10), the copper loss expression in (10) can be rewritten aswith the constant :
3.2. Iron Loss
The iron loss in the stator lamination is given aswhere is the iron loss per unit mass (kg); is the mass of the stator back iron; is the mass of the stator teeth.
is separated into the hysteretic loss component , the classical eddy current loss component , and the excess eddy current losses component , and can be expressed as [30]where and α are the hysteretic loss constants; is the classical eddy current loss constant; is the excess eddy current losses constant; is the frequency.
Based on the analytical design model, the expressions of and can be obtained aswhere is the density of the stator lamination material.
3.3. Rotor Eddy Current Loss
Eddy current loss in the permanent magnets, the sleeve, and the rotor yoke is caused by the space MMF harmonics and time MMF harmonics. The eddy current loss mainly locates in the permanent magnets and the sleeve, and the loss in the rotor yoke can be ignored [31]. The rotor eddy current loss can be calculated by [32]where is outer diameter of sleeve or magnets; is inner diameter of sleeve or magnets; is the pole arc for magnets, and the value is π/p for sleeve; ρ is electrical conductivity of sleeve or magnets; is the current density in the sleeve or magnets.
3.4. Mechanical Friction Loss
The mechanical friction loss is caused by running of the bearing, and its expression can be expressed as [33]where is the coefficient determined by the type and lubrication of the bearing; is the kinematic viscosity of the lubricating oil; is the average diameter of the bearing; is the coefficient determined by the type and load of bearing; is the dynamic load of the bearing; a and are the coefficients depending on the type and load of the bearing.
3.5. Rotor Air Friction Loss
The rotor air friction loss is generated by the friction between rotor and air. According to [34], the rotor air friction loss can be obtained aswhere is the rotor surface roughness coefficient, and its value is 1 for smooth rotor surfaces; is air density; is air friction coefficient, and it can be expressed aswith the Couette Reynolds number beingwhere δ is the airgap width.
The rotor air friction loss is close related to the radius of the rotor , which can be expressed as a function of λ: r = .
4. Determination of the Optimal Design
In various components of the PMBLDCM, the winding and permanent magnet are the main heat sources and their reliabilities are sensitive to temperature. In order to increase the reliability of the PMBLDCM, high temperature materials are adopted besides decreasing the motor temperature. The grade of the enamel insulated wires intended to adopt is QY2/220 and its maximum operating temperature is 220°C. The permanent magnet material intended to adopt is Sm_{2}Co_{17}, and its grade is XGS239/199/350. The maximum operating temperature of the permanent magnet is 350°C. Temperature tolerance ability of the magnets is higher than that of winding. In addition, the life of winding decreases with temperature rises. In order to improve the reliability of the PMBLDCM, the winding temperature needs to be decreased.
The airgap thermal resistance is larger than other thermal resistances in the stator. Furthermore, the airgap thermal resistance increases with air density decreases. Therefore, the effect of the rotor temperature on the winding temperature can be ignored at the high altitude. The winding temperature rise is mainly determined by the copper and iron losses. The winding temperature rise can be calculated by the following equation:where is the heat transfer coefficient of the PMBLDCM; A is the cooling area of the PMBLDCM; is the thermal resistance between the windings and stator iron core.
The heat transfer coefficient of the PMBLDCM is the sum of the natural convection and radiation heat transfer coefficients. The natural convection heat transfer coefficient decreases with altitude rises. In order to improve the cooling capacity of the PMBLDCM at high altitude, the radiation heat transfer coefficient needs to be raised by increasing the emissivity of the motor surface.
The electromagnetic torque is the sum of the resistance torque and the output torque. The electromagnetic torque can be expressed aswhere is the output torque; is the sum of the rotor eddy current loss, the rotor air friction loss, and the mechanical friction loss, and it is expressed asAccording to (14)–(21), can be converted as a function of λ and .
Combining (12) and (23), the copper loss at ambient temperature can be obtained asThe copper loss increases with temperature rises. When the winding temperature rise is , the copper loss is given aswhere is resistivity temperature coefficient of copper.
Based on (22) and (26), the steady winding temperature rise can be obtained as
The winding transient temperature rise is given aswhere is time and is thermal time constant. Since is within 0 s–300 s, the temperature difference between the windings and stator iron core is negligible. It can be assumed that all parts of the stator have the same temperature. Therefore, can be obtained aswhere is the average specific heat capacity of the stator; is the mass of the stator.
The ratio of different losses in total losses and thermal time constant can be changed by adjusting and . In other words, the heat source and the rate of temperature rise can be changed by adjusting and . The variation of with and when t = 300 s is illustrated in Figure 3. It can be seen that can be reduced by optimizing and . There is an optimal combination of λ and to gain the minimum temperature rise. The optimal combination can be obtained by solving the equations group:
Using (30), the optimal and of the PMBLDCM in this paper are calculated as 0.44 and 2.02 T. However, 2.02 T of is hard to achieve for the stator lamination steel material DW31035. Figure 3 shows that should be close to 2.02 T to reduce the temperature rise. Considering the magnetic saturation point of the lamination steel of the prototype, 1.7 T of is chosen and the corresponding optimal is 0.43.
On the other hand, it should be noted that the optimal decreases with speed rises, and the value of may be less than the saturation point for some highspeed PMBLDCM. In this case, the actual value of optimal and should be chosen.
5. FEA and Experimental Verifications
The analytical results are verified by FEA and experiments. The verification purpose is to prove that the analytical optimal design is accurate and the optimization method can minimize the winding temperature rise.
In FEA verification, the air density at altitude 20 km and the ambient temperature of 80°C were considered. Different designs, which include the optimal design, are chosen to simulate. As shown in Figure 4, several motor designs with different combinations of and are chosen from the contour. The motor designs of C1, C2, C3, and C4 are designed by employing 0.43 of λ for the four specific 1.1 T, 1.3 T, 1.5 T, and 1.7 T, respectively. The motor designs of R1, R2, R3, R4, and R5 are designed by employing 1.7 T of for the five specific λ 0.25, 0.35, 0.43, 0.55, and 0.65, respectively. Among these designs, C4 (R3) is the optimal design in analytical prediction. Since C4 and R3 are the same design, there are eight designs for the FEA verification in total.
The analytical and FEA predicted winding temperature rises of the different designs are shown in Table 2. The FEA results are compared with analytical results in Figures 5 and 6. The maximum error, minimum error, and average error between analytical results and FEA results are 4.0%, 1.0%, and 2.3%. The FEA results agree well with the analytical results. The winding temperature rise of design C4 (R3) is proved to be the smallest. The 3D thermal field of C4 (R3) design at t = 300 s is shown in Figure 7.

As shown in Figure 8(a), a PMBLDCM prototype was manufactured according to the design C4 (R3). The prototype is driven by a pulsewidth modulation (PWM) inverter. The prototype and its controller are integrated to save the space. Surface of the prototype is painted black to increase the emissivity. Since there is no equipment to simulate the environment at the altitude of 20 km, the prototype was tested on the ground with normal temperature and normal atmospheric pressure, which are 19°C and 100.8 kPa. The experimental platform is shown in Figure 8(b). Total running time of the prototype is 300 s. In the running status of the prototype, the load torque and the speed were maintained as 1.6 N·m and 10000 rpm, respectively. The load torque is adjusted by the dynamometer (Magtrol). The speed was controlled by adjusting the voltage of the DC power source while the same PWM duty ratio was kept as 100%.
(a)
(b)
The winding temperature rise was measured by the resistance method [6]. The resistance values were measured by the LCR tester (HIOKI 352250). In order to measure the line resistance of the winding, the prototype was stopped for about 40 s after a 100 s running state. As shown in Figure 9, there are three resistance values , , and measured during the 40 s nonrunning state. The three measuring points are MP1, MP2, and MP3. Before the prototype runs, a line resistance value was measured when .
Using these measured resistances, the winding temperature rises are calculated by the following equation:where represent , , and ; represent , , and , which are the winding temperature rise at MP1, MP2, and MP3, respectively.
The measured winding temperature rises, together with analytical and FEA winding temperature rise, are given in Table 3 and Figure 10. The errors between measured and analytical winding temperature rises at points MP1, MP2, and MP3 are 5.8%, 3.0%, and 7.8%, respectively. The analytical result agrees well with the experimental result. The errors between measured and FEA results at points MP1, MP2, and MP3 are 10.5%, 1.6%, and 2.7%, respectively. The accuracy of the FEA simulation is also verified by experiments. Combining the FEA verification in Table 2, it can be proved that the optimal design is obtained accurately to minimize the winding temperature rise.

6. Conclusion
In order to improve the reliability of the shorttime PMBLDCM in hypersonic vehicle, an electromagneticthermal integrated design optimization method is proposed. This method can satisfy both the requirements and constraints of thermal and electromagnetic design aspects. The method is based on electromagnetic analysis and thermal transient analysis. The electromagnetic and thermal design parameters are represented as functions of split ratio and . The optimal design is determined after the optimal split ratio and are obtained. Since there are only two variables involved in the optimization, the analytical calculation of the optimization is highly simplified. The optimal design and the winding temperature rise are verified by the FEA and experiments. It can be proved that the optimal design is obtained accurately and the minimum winding temperature rise is achieved. The optimization method provides a fast and accurate solution for the electromagneticthermal integrated design of the shorttime duty PMBLDCM.
Competing Interests
The authors declare that there are no competing interests.
Acknowledgments
This work was supported by the National Natural Science Foundation of China (Grant no. 51507143), Specialized Research Fund for the Doctoral Program of Higher Education of China (Grant no. 20136102120055), and the Industry Science and Technology Research Foundation of Shaanxi Province, China (Grant no. 2015GY090).
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Copyright © 2016 Quanwu Li et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.