A buck-boost starter generator controller and control method for aviation high-voltage direct current

Abstract

A controller and control method for a step-up / step-down starter generator for aviation high voltage DC. The controller mainly includes power tubes Q1 to Q6, Q 1A ~Q 6A The three-phase bridge arm circuit structure is the same. For the A-phase bridge arm, the A-phase input terminal is connected to the emitter of Q1 and the collector of Q2. The collector of Q1 is connected to Q 1A The collector connection, Q 1A The emitter of Q2 is connected to the positive pole of the high voltage DC bus, and the emitter of Q 2A The emitter E is connected, Q 2A The collector of the power transistor is connected to the negative terminal of the high-voltage DC bus. During power generation, the power tube operates at a low frequency, resulting in low high-frequency ripple and low high-frequency electromagnetic interference. Because the power tube operates at a low frequency during power generation, high-current-tolerant but high-loss power tubes can be used, giving the starter generator controller excellent overload resistance. Furthermore, the switching between boost and buck regulation during power generation is smooth, resulting in a continuous output voltage, making it suitable for parallel operation of multiple units and ideal for aviation high-voltage DC power systems.

Description

Technical Field

[0001] The present invention relates to a step-up / step-down starter generator controller and a control method for aviation high-voltage direct current. Background Art

[0002] For military aviation power systems with power exceeding 12kW, using 270V high-voltage DC (HVDC) to power onboard equipment is the optimal solution. Aviation power systems typically require an overload capacity of 1.5 times the rated current for 5 minutes and 2 times the rated current for 5 seconds during normal power generation and regulated output. They also need to be able to output 3 times the short-circuit current. High-frequency ripple must be kept to a minimum to minimize electromagnetic interference.

[0003] The permanent magnet starter generator power system consists of two parts: the permanent magnet starter generator and the starter generator controller. The permanent magnet starter generator is used to convert mechanical energy into variable-voltage and variable-frequency AC power. In the starting state, the starter generator controller converts the DC power provided by the starting power supply into variable-voltage and variable-frequency AC power to power the permanent magnet starter generator, driving the motor from a standstill to the engine ignition speed. In the generating state, the starter generator controller converts the variable AC voltage output by the permanent magnet starter generator into a regulated 270V DC voltage to power aircraft equipment.

[0004] Currently, starter-generator controllers for low-voltage DC power systems generally use a three-phase fully controlled full-bridge as hardware, with both starting and generating using SVPWM control, and generating using PWM rectification technology. However, PWM rectification technology has the following shortcomings:

[0005] 1) PWM rectification belongs to boost control. The peak value of the motor line voltage is not allowed to exceed the desired output voltage under any circumstances. This makes the phase current too large during low-speed power generation and starting, resulting in low efficiency of the starter generator controller.

[0006] 2) When generating electricity, the switching frequency of the power tube is one order of magnitude higher than the frequency of the starter generator, resulting in large switching losses;

[0007] 3) For permanent magnet starter generators for aviation with high speed, the high frequency and small inductance of the starter generator make it very difficult to use PWM rectification technology to stabilize the voltage.

[0008] 4) During power generation, when switching from uncontrolled rectification to PWM rectification, it is easy to form DC bus overvoltage;

[0009] 5) When using PWM rectification technology, the excessively high switching frequency causes the output voltage high-frequency ripple to be too high, making it difficult to meet relevant standard requirements;

[0010] 6) In order to meet the demand for high switching frequency, the power tubes usually use fast and low-loss power tubes, which have a weak ability to withstand overload current;

[0011] 7) When the output is short-circuited, the three-phase full-bridge circuit controlled by PWM rectification does not have the ability to limit the short-circuit current.

[0012] Patent CN108712093 A, a power converter for a high-speed permanent magnet starter generator and its control method, provides a starter generator control method with buck-boost functionality in the power generation state. The hardware utilizes a three-phase full-bridge and an SCR phase-controlled full-bridge in parallel. At low speeds, the three-phase full-bridge is used for boost stabilization, while at high speeds, the SCR phase-controlled full-bridge is used for buck stabilization. This technology has the following deficiencies:

[0013] 1) The three-phase fully controlled full bridge and the SCR phase-controlled full bridge are in parallel. To ensure compatibility between boost and buck regulation, the boost regulation value needs to be about 10V lower than the buck regulation value, resulting in discontinuous output voltage. This cannot be used in applications where multiple starter generator controllers are connected in parallel.

[0014] 2) The maximum operating temperature of SCR is lower than that of IGBT, which reduces the maximum operating temperature that the starter generator controller can withstand;

[0015] 3) The rapid switching of the three-phase fully controlled full bridge will cause the SCR phase-controlled full bridge to be mis-conducted. To avoid this problem, an isolation saturation inductor needs to be added between the SCR phase-controlled full bridge and the three-phase winding of the starter generator, which increases the difficulty of engineering implementation and adds additional weight.

[0016] In addition, some applications add a DC / DC power converter after rectification to achieve step-down or step-up / step-down stabilization. However, the method of adding a DC / DC power converter has the following shortcomings:

[0017] 1) In addition to the rectified AC / DC, it also includes DC / DC, which is a two-stage converter, usually with low efficiency and large weight;

[0018] 2) The DC / DC converter requires the addition of independent magnetic components, which makes the DC / DC stage heavier. Summary of the Invention

[0019] To solve the above technical problems, the present invention provides a controller and control method for a step-up / step-down starter generator for aviation high voltage direct current.

[0020] The present invention is achieved through the following technical solutions.

[0021] The present invention provides a step-up / step-down starter generator controller for aviation high voltage direct current, which is characterized by comprising power tubes Q1 to Q6, Q1A ~Q 6A , diodes D1~D6, capacitor C A 、C B 、C C 、C s 、C dc , discharge resistor R s And permanent magnet starter generator; the A phase input terminal of the permanent magnet starter generator is connected to the emitter E of Q1 and the collector C of Q2, and the collector of Q1 is connected to Q 1A The collector of diode D1 is connected to the anode of Q 1A The emitter E of Q2 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 2A The emitter E of the diode D2 is connected to the cathode, Q 2A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C A The two ends of are connected to the collector C of Q1 and the emitter of Q2 respectively; the B phase input end of the permanent magnet starter generator is connected to the emitter of Q3 and the collector of Q4, and the collector of Q3 is connected to Q 3A The collector of diode D3 is connected to the anode of Q 3A The emitter E of Q4 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 4A The emitter of diode D4 is connected to the cathode of diode D4, Q 4A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C B The two ends of the permanent magnet starter generator are connected to the collector of Q3 and the emitter E of Q4 respectively; the C phase input end of the permanent magnet starter generator is connected to the emitter of Q5 and the collector C of Q6, and the collector of Q5 is connected to the emitter of Q5 and the collector C of Q6. 5A The collector of diode D5 is connected to the anode of Q 5A The emitter E of Q6 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 6A The emitter of diode D6 is connected to the cathode of diode D6, Q 6A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C C The two ends of are connected to the collector of Q3 and the emitter of Q6 respectively, and the cathodes of diodes D1, D3 and D5 are connected to the capacitor C s One end and the discharge resistor R s One end of the diode D2, D4 and D6 is connected to the anode of the capacitor C s The other end and the discharge resistor R s The other end of the capacitor C dc The two ends of the MOSFET are connected to the positive and negative poles of the high-voltage DC bus respectively.

[0022] Furthermore, the power tubes Q1 to Q6, Q 1A ~Q 6AAll use Infineon's single-bridge-arm IGBT tube module FF600R12KE4.

[0023] Furthermore, the capacitor C A 、C B and C C This is achieved by connecting 15 ceramic capacitors in parallel.

[0024] Furthermore, the capacitor C s It is realized by connecting three film capacitors in parallel.

[0025] Furthermore, the capacitor C dc Use 24 film capacitors in parallel to achieve

[0026] Furthermore, the film capacitor is an SHB-500-90-4G# film capacitor from EACO.

[0027] A control method for a boost / buck starter generator controller for aviation high voltage direct current includes the following steps:

[0028] Step 1: The position signal θ = 0° corresponds to the zero-crossing point of the voltage drop section of phase A of the main motor under no-load conditions;

[0029] Step 2: During the starting process, the starter generator controller drives the permanent magnet starter generator from rest to the engine ignition speed;

[0030] Step 3: After the engine reaches the power generation speed, it enters the power generation process;

[0031] Step 4: During power generation, when the line voltage amplitude of the permanent magnet starter generator does not reach the desired output voltage, the voltage is stepped up and stabilized;

[0032] Step 5: During power generation, when the line voltage amplitude of the permanent magnet starter generator exceeds the desired output voltage, the voltage is stepped down and stabilized;

[0033] Step 6: When generating electricity, according to the output DC current I dc , determine the desired output voltage V ref , assuming the rated current is I N , in I dc <2I N When V ref =270V, at I dc By 2I N to 3I N When the V ref Reduced from 270V to 0V.

[0034] Furthermore, the startup process described in step 2 includes the following steps:

[0035] Step 21: Close the power tube Q1A ~Q 6A , the power tubes Q1 to Q6 form an IGBT three-phase full bridge, and the high-voltage DC bus supplies power to the IGBT three-phase full bridge;

[0036] Step 22: The control circuit adopts a quasi-speed outer loop and current inner loop control strategy, generates drive signals G1 to G6 for the three-phase full-bridge IGBT tubes through sinusoidal space vector pulse width modulation (SVPWM) control, and sends the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively;

[0037] Step 23: The starter generator controller outputs variable voltage and variable frequency AC power.

[0038] Furthermore, the voltage boosting and stabilizing in step 4 includes the following steps:

[0039] Step 41: According to the DC voltage V dc and position signal θ, determine the driving signals G1~G6 of the boost voltage regulation control, define the angle of the falling edge hysteresis θ=180° of the driving signal G2 as δ1, and the high level pulse width of the driving signal G2 as δ2. dc Less than the desired output voltage V ref When the active current i is increased by increasing the width of δ2 q Make the DC voltage stable at the desired output voltage, and adjust δ1 to make the reactive current i d =0, reducing δ1 corresponds to reducing the demagnetization reactive current i d , the adjustment range of δ1 is 0~60°, the adjustment range of δ2 is 0~90°, G1~G6 have the same positive pulse width, and the boost voltage regulation control drive signals G1~G6 are formed in a manner that G2, G5, G4, G1, G6, and G3 lag 60° in sequence;

[0040] Step 42: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ;

[0041] Step 43: According to the driving signals G1 to G6 and the signal G 1Ai ~G6Ai , determine the driving signal G for boost voltage regulation control 1A ~G 6A , G 1A =G2|G 1Ai , G 6A =G5|G 6Ai , G 3A =G4|G 3Ai , G 2A =G1|G 2Ai , G 5A =G6|G 5Ai , G 4A =G3|G 4Ai ;

[0042] Step 44: Send the drive signals G1 to G6 to the power transistors Q1 to Q6 respectively. 1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

[0043] Furthermore, the step 5 of step 5 includes the following steps:

[0044] Step 51: Set the drive signals G1 to G6 to all 0, and send the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively, so that the power tubes Q1 to Q6 are all turned off;

[0045] Step 52: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ;

[0046] Step 53: Let the driving signal G 1A ~G 6A Lag signal G 1Ai ~G 6Ai The angle is δ3, when the DC voltage V dc Greater than the desired output voltage V ref When , the DC voltage is stabilized at the desired output voltage by increasing the width of δ3;

[0047] Step 54: Set the drive signal G1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

[0048] The beneficial effects of the present invention are: 1) the proposed controller and control method for a step-up / step-down starter generator for aviation high-voltage direct current (HVDC) are suitable for aviation high-voltage direct current (HVDC) power supply systems;

[0049] 2) During power generation, it belongs to step-up and step-down voltage stabilization control. The voltage range of step-up voltage stabilization and the range of step-down voltage stabilization are both narrow, so the power generation efficiency is high;

[0050] 3) Compared with the starter generator with pure boost control, the starter generator with buck-boost control has a higher back EMF coefficient, which reduces the starting current corresponding to the same starting torque and reduces the current stress that the power tube in the starter generator controller needs to bear;

[0051] 4) When generating electricity, the switching between step-up and step-down voltage regulation is smooth, the output voltage is continuous, and it can be used for parallel operation of multiple machines;

[0052] 5) The inductance of the starter generator is used to achieve starting and power generation voltage stabilization functions, without the need to add magnetic components, and the weight is light;

[0053] 6) When generating electricity, the operating frequency of the power tube is the same as the electrical frequency of the starter generator. Compared with PWM rectification control, the frequency is one order of magnitude lower, the switching loss is significantly reduced, and the efficiency is significantly improved;

[0054] 7) When generating electricity, the operating frequency of the power tube is low, which makes the high-frequency ripple smaller and the high-frequency electromagnetic interference smaller;

[0055] 8) When generating electricity, the operating frequency of the power tube is low, so the power tube can be a power tube that can withstand large current but has relatively large loss, so that the starter generator controller has good anti-overload ability;

[0056] 9) By reducing the regulated current value as the output current increases, the output short-circuit current can be controlled within a reasonable range;

[0057] 10) When there is a fault in the starter generator controller or the starter generator, the fault isolation can be achieved by disconnecting all power tube drives. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] Figure 1 This is a block diagram of the starter generator controller of the present invention;

[0059] Figure 2 is a relationship diagram between the position signal and the three-phase no-load voltage of the present invention;

[0060] Figure 3This is a schematic diagram of the starting control principle of the present invention;

[0061] Figure 4 This is a schematic diagram of the boost and voltage stabilization control principle of the present invention;

[0062] Figure 5 This is a schematic diagram of the buck and voltage stabilization control principle of the present invention. DETAILED DESCRIPTION

[0063] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0064] This embodiment is a 40kW starter-generator controller. The permanent magnet starter synchronous generator has 3 pole pairs, and the peak no-load line voltage at 18,000 r / min is 270V. The starting power supply is 270V DC, and the starting torque is 60N·m (0-3500 r / min). When operating as a generator, the output is 270VDC, the output power is 40kW (12,000 r / min-24,000 r / min), and it has an overload capacity of 150% rated load for 5 minutes and 200% rated load for 5 seconds; and a short-circuit capacity of not less than 300% rated current within 5 seconds. The application background of this embodiment is a 270V high-voltage DC power supply system.

[0065] Figure 1 The figure shows the block diagram of the starter generator controller. A step-up / step-down starter generator controller device for aviation high voltage DC includes power tubes Q1~Q6, Q 1A ~Q 6A , diodes D1~D6, capacitor C A 、C B 、C C 、C s 、C dc , discharge resistor R s The A phase input terminal of the permanent magnet starter generator is connected to the emitter E of Q1 and the collector C of Q2. The collector C of Q1 is connected to Q 1A The collector C of diode D1 is connected to the anode of Q 1A The emitter E of Q2 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 2A The emitter E of the diode D2 is connected to the cathode, Q 2A The collector C is connected to the negative electrode of the high voltage DC bus, and the capacitor C A The two ends of the permanent magnet starter generator are connected to the collector C of Q1 and the emitter E of Q2, and the B phase input end of the permanent magnet starter generator is connected to the emitter E of Q3 and the collector C of Q4. 3A The collector C of diode D3 is connected to the anode of Q 3A The emitter E of Q4 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q4A The emitter E of the diode D4 is connected to the cathode, Q 4A The collector C is connected to the negative electrode of the high voltage DC bus, and the capacitor C B The two ends of are connected to the collector C of Q3 and the emitter E of Q4 respectively. The C phase input end of the permanent magnet starter generator is connected to the emitter E of Q5 and the collector C of Q6. The collector C of Q5 is connected to the emitter E of Q5 and the collector C of Q6. 5A The collector of C, the anode of diode D5 is connected, Q 5A The emitter E of Q6 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 6A The emitter E of the diode D6 is connected to the cathode, Q 6A The collector C is connected to the negative electrode of the high voltage DC bus, and the capacitor C C The two ends of the diodes D1, D3 and D5 are connected to the collector C of Q3 and the emitter E of Q6 respectively, and the cathodes of the diodes D1, D3 and D5 are connected to the capacitor C s One end and the discharge resistor R s One end of the diode D2, D4 and D6 is connected to the anode of the capacitor C s The other end and the discharge resistor R s The other end of the capacitor C dc The two ends of the circuit are connected to the positive and negative poles of the high-voltage DC bus respectively.

[0066] The power tube adopts the single-bridge-arm IGBT tube module FF600R12KE4 from Infineon. For the A-phase bridge arm, Q1 and Q2, Q 1A and D1, Q 2A The capacitor C and D2 are both FF600R12KE4, and the diodes D1 and D2 are IGBT tubes connected in reverse parallel. The power devices used in phases B and C are the same as those in phase A. A 、C B and C C 15 ceramic capacitors CT45-T-X5R-500V-105M are connected in parallel. The single capacitor CT45-T-X5R-500V-105M has a withstand voltage of 500V and a capacity of 1μF. s Use 3 EACO SHB-500-90-4G# film capacitors in parallel. Capacitor C dc 24 SHB-500-90-4G# film capacitors are connected in parallel. The withstand voltage of a single SHB-500-90-4G# capacitor is 500V and the capacity is 90μF. The three-phase AC current i A 、i B and i C and DC current I dcThe control circuit adopts DSP+FPGA structure, with TI's TMS320F28335PGFA as DSP and Altera's EP3C25E114CN as FPGA.

[0067] The inductance of the starter generator is used to achieve starting and power generation voltage stabilization functions, without adding magnetic components and with a light weight.

[0068] When a fault occurs in the starter generator controller or the starter generator, the fault isolation can be achieved by disconnecting all power tube drives.

[0069] A control method for a boost / buck starter generator controller for aviation high voltage direct current includes the following steps:

[0070] Step 1: The position signal θ = 0° corresponds to the zero-crossing point of the voltage drop section of phase A of the main motor under no-load conditions;

[0071] Step 2: During the starting process, the starter generator controller drives the permanent magnet starter generator from rest to the engine ignition speed;

[0072] Step 3: After the engine reaches the power generation speed, it enters the power generation process;

[0073] Step 4: During power generation, when the line voltage amplitude of the permanent magnet starter generator does not reach the desired output voltage, the voltage is stepped up and stabilized;

[0074] Step 5: During power generation, when the line voltage amplitude of the permanent magnet starter generator exceeds the desired output voltage, the voltage is stepped down and stabilized;

[0075] Step 6: When generating electricity, according to the output DC current I dc , determine the desired output voltage V ref , assuming the rated current is I N , in I dc <2I N When V ref =270V, at I dc By 2I N to 3I N When the V ref Reduced from 270V to 0V.

[0076] Figure 2 The figure shows the relationship between the position signal and the three-phase no-load voltage. In step 1, the relationship between the position signal θ=0° and the no-load main motor phase A voltage is clarified, which should also be equivalent to clarifying the relationship between the position signal and the three-phase voltage.

[0077] It can be seen from steps 5 and 6 that during power generation, it belongs to buck-boost voltage regulation control. The voltage range of the boost voltage regulation and the voltage range of the buck voltage regulation are both narrow, so the power generation efficiency is high.

[0078] In step 6, the output short-circuit current can be controlled within a reasonable range by reducing the regulated current value as the output current increases.

[0079] Combine Figure 3 The starting control principle diagram shown in FIG. 1 illustrates the starting process control described in step 2, which includes the following steps:

[0080] Step 21: Close the power tube Q 1A ~Q 6A , the power tubes Q1 to Q6 form an IGBT three-phase full bridge, and the high-voltage DC bus supplies power to the IGBT three-phase full bridge;

[0081] Step 22: The control circuit adopts a quasi-speed outer loop and current inner loop control strategy, generates drive signals G1 to G6 for the three-phase full-bridge IGBT tubes through sinusoidal space vector pulse width modulation (SVPWM) control, and sends the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively;

[0082] Step 23: The starter generator controller outputs variable voltage and variable frequency AC power.

[0083] Compared with the starter generator that uses pure boost control for power generation, the starter generator that uses boost-buck control has a higher back electromotive force coefficient, which reduces the starting current corresponding to the same starting torque and reduces the current stress that the power tube in the starter generator controller needs to withstand.

[0084] Combine Figure 4 The boost and voltage stabilization control principle diagram shown in FIG. 1 illustrates the power generation boost and voltage stabilization control described in step 4, which includes the following steps:

[0085] Step 41: According to the DC voltage V dc and position signal θ, determine the driving signals G1~G6 of the boost voltage regulation control, define the angle of the falling edge hysteresis θ=180° of the driving signal G2 as δ1, and the high level pulse width of the driving signal G2 as δ2. dc Less than the desired output voltage V ref When the active current i is increased by increasing the width of δ2 q Make the DC voltage stable at the desired output voltage, and adjust δ1 to make the reactive current i d =0, reducing δ1 corresponds to reducing the demagnetization reactive current i d, the adjustment range of δ1 is 0~60°, the adjustment range of δ2 is 0~90°, G1~G6 have the same positive pulse width, and the boost voltage regulation control drive signals G1~G6 are formed in a manner that G2, G5, G4, G1, G6, and G3 lag 60° in sequence;

[0086] Step 42: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ;

[0087] Step 43: According to the driving signals G1 to G6 and the signal G 1Ai ~G 6Ai , determine the driving signal G for boost voltage regulation control 1A ~G 6A , G 1A =G2|G 1Ai , G 6A =G5|G 6Ai , G 3A =G4|G 3Ai , G 2A =G1|G 2Ai , G 5A =G6|G 5Ai , G 4A =G3|G 4Ai ;

[0088] Step 44: Send the drive signals G1 to G6 to the power transistors Q1 to Q6 respectively. 1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

[0089] Combine Figure 5 The buck-voltage stabilization control principle diagram shown in FIG. 1 illustrates the power generation boost-voltage stabilization control described in step 5, which includes the following steps:

[0090] Step 51: Set the drive signals G1 to G6 to all 0, and send the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively, so that the power tubes Q1 to Q6 are all turned off;

[0091] Step 52: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ;

[0092] Step 53: Let the driving signal G 1A ~G 6A Lag signal G 1Ai ~G 6Ai The angle is δ3, when the DC voltage V dc Greater than the desired output voltage V ref When , the DC voltage is stabilized at the desired output voltage by increasing the width of δ3;

[0093] Step 54: Set the drive signal G 1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

[0094] During power generation, the generator controller of the present invention operates at a relatively low power tube operating frequency, resulting in low high-frequency ripple and low high-frequency electromagnetic interference. Because the power tube's operating frequency is relatively low during power generation, it can utilize high-current-tolerant but high-loss power tubes, giving the starter generator controller excellent overload resistance. Furthermore, the switching between boost and buck regulation during power generation is smooth, resulting in a continuous output voltage, making it suitable for parallel operation of multiple machines. The proposed boost-buck starter generator controller and control method for aviation high-voltage DC power systems are suitable for aviation high-voltage DC power supply systems.

Claims

1. A control method for a step-up / step-down starter generator controller for aviation high voltage direct current. The aviation high voltage direct current step-up / step-down starter generator controller includes power tubes Q1 to Q6, Q 1A ~Q 6A , diodes D1~D6, capacitor C A 、C B 、C C 、C s 、C dc , discharge resistor R s And the permanent magnet starter generator; the A phase input terminal of the permanent magnet starter generator is connected to the emitter E of Q1 and the collector C of Q2, and the collector of Q1 is connected to Q 1A The collector of diode D1 is connected to the anode of Q 1A The emitter E of Q2 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 2A The emitter E of the diode D2 is connected to the cathode, Q 2A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C A The two ends of are connected to the collector C of Q1 and the emitter of Q2 respectively; the B phase input end of the permanent magnet starter generator is connected to the emitter of Q3 and the collector of Q4, and the collector of Q3 is connected to Q 3A The collector of diode D3 is connected to the anode of Q 3A The emitter E of Q4 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 4A The emitter of diode D4 is connected to the cathode of diode D4, Q 4A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C B The two ends of the permanent magnet starter generator are connected to the collector of Q3 and the emitter E of Q4 respectively; the C phase input end of the permanent magnet starter generator is connected to the emitter of Q5 and the collector C of Q6, and the collector of Q5 is connected to Q 5A The collector of diode D5 is connected to the anode of Q 5A The emitter E of Q6 is connected to the positive pole of the high voltage DC bus, and the emitter E of Q 6A The emitter of diode D6 is connected to the cathode of diode D6, Q 6A The collector is connected to the negative electrode of the high voltage DC bus, and the capacitor C C The two ends of are connected to the collector of Q3 and the emitter of Q6 respectively, and the cathodes of diodes D1, D3 and D5 are connected to the capacitor C s One end and the discharge resistor R s One end of the diode D2, D4 and D6 is connected to the anode of the capacitor C s The other end and the discharge resistor R s The other end of the capacitor C dc The two ends are connected to the positive and negative poles of the high-voltage DC bus respectively; It is characterized by The following steps are involved: Step 1: The position signal θ = 0° corresponds to the zero-crossing point of the voltage drop section of phase A of the main motor under no-load conditions; Step 2: During the starting process, the starter generator controller drives the permanent magnet starter generator from rest to the engine ignition speed; Step 3: After the engine reaches the power generation speed, it enters the power generation process; Step 4: During power generation, when the line voltage amplitude of the permanent magnet starter generator does not reach the desired output voltage, the voltage is stepped up and stabilized; Step 5: During power generation, when the line voltage amplitude of the permanent magnet starter generator exceeds the desired output voltage, the voltage is stepped down and stabilized; Step 6: When generating electricity, according to the output DC current I dc , determine the desired output voltage V ref , assuming the rated current is I N , in I dc <2I N When V ref =270V, at I dc By 2I N to 3I N When the V ref Reduce from 270V to 0V; The step 4 includes the following steps: Step 41: According to the DC voltage V dc and position signal θ, determine the driving signals G1~G6 of the boost voltage regulation control, define the angle of the falling edge hysteresis θ=180° of the driving signal G2 as δ1, and the high level pulse width of the driving signal G2 as δ2. dc Less than the desired output voltage V ref When the active current i is increased by increasing the width of δ2 q Make the DC voltage stable at the desired output voltage, and adjust δ1 to make the reactive current i d =0, reducing δ1 corresponds to reducing the demagnetization reactive current i d , the adjustment range of δ1 is 0~60°, the adjustment range of δ2 is 0~90°, G1~G6 have the same positive pulse width, and the boost voltage regulation control drive signals G1~G6 are formed in a manner that G2, G5, G4, G1, G6, and G3 lag 60° in sequence; Step 42: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ; Step 43: According to the driving signals G1 to G6 and the signal G 1Ai ~G 6Ai , determine the driving signal G for boost voltage regulation control 1A ~G 6A , G 1A =G2|G 1Ai , G 6A =G5|G 6Ai , G 3A =G4|G 3Ai , G 2A =G1|G 2Ai , G 5A =G6|G 5Ai , G 4A =G3|G 4Ai ; Step 44: Send the drive signals G1 to G6 to the power transistors Q1 to Q6 respectively. 1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

2. The control method of the aviation HVDC buck-boost starter generator controller according to claim 1, characterized in that: The starting process described in step 2 includes the following steps: Step 21: Close the power tube Q 1A ~Q 6A , the power tubes Q1 to Q6 form an IGBT three-phase full bridge, and the high-voltage DC bus supplies power to the IGBT three-phase full bridge; Step 22: The control circuit adopts a quasi-speed outer loop and current inner loop control strategy, generates drive signals G1 to G6 for the three-phase full-bridge IGBT tubes through sinusoidal space vector pulse width modulation (SVPWM) control, and sends the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively; Step 23: The starter generator controller outputs variable voltage and variable frequency AC power.

3. The control method of the aviation high voltage direct current buck-boost starter generator controller according to claim 1, characterized in that: The step 5 of step 5 of step 5 includes the following steps: Step 51: Set the drive signals G1 to G6 to all 0, and send the drive signals G1 to G6 to the power tubes Q1 to Q6 respectively, so that the power tubes Q1 to Q6 are all turned off; Step 52: Determine the boost voltage regulation control signal G according to the position signal θ 1Ai ~G 6Ai , when θ=210°~360° and 0°~30°, make G 1Ai =1, for other θ values, make G 1Ai =0, press G 1Ai , G 6Ai , G 3Ai , G 2Ai , G 5Ai , G 4Ai The boost voltage control signal G is formed by lagging 60 degrees in sequence. 1Ai ~G 6Ai ; Step 53: Let the driving signal G 1A ~G 6A Lag signal G 1Ai ~G 6Ai The angle is δ3, when the DC voltage V dc Greater than the desired output voltage V ref When , the DC voltage is stabilized at the desired output voltage by increasing the width of δ3; Step 54: Set the drive signal G 1A ~G 6A respectively sent to the power tube Q 1A ~Q 6A .

4. The aviation high voltage direct current buck-boost starter generator controller according to claim 1, characterized in that: The power tubes Q1 to Q6, Q 1A ~Q 6A All use Infineon's single-bridge-arm IGBT tube module FF600R12KE4.

5. The aviation high voltage direct current buck-boost starter generator controller according to claim 1, characterized in that: The capacitor C A 、C B and C C This is achieved by connecting 15 ceramic capacitors in parallel.

6. The aviation high voltage direct current buck-boost starter generator controller according to claim 1, characterized in that: The capacitor C s It is realized by connecting three film capacitors in parallel.

7. The aviation high voltage direct current buck-boost starter generator controller according to claim 1, characterized in that: The capacitor C dc It is realized by connecting 24 film capacitors in parallel.

8. The step-up / step-down starter generator controller for aviation high voltage direct current according to any one of claims 6 or 7, characterized in that: The film capacitor is an SHB-500-90-4G# film capacitor produced by EACO.

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