Variable power multi-path transmission system test bench and test method

Abstract

The application discloses a variable-power multi-path transmission system test bench and a test method, and belongs to the technical field of aero-engine transmission system tests. The test bench comprises an engine end, an aircraft end, a clutch and a start-up integrated motor which are provided with a tester loading system. The start-up integrated motor is embedded with a sensing and control system, which is used for monitoring the rotating speed of the tester loading system and controlling the on-off of the clutch. In normal operation, the tester loading system drives the engine end and the aircraft end accessories, and the start-up integrated motor generates electricity as a load; when simulating an engine fault, the start-up integrated motor is switched to a motor, the tester loading system simulates an engine, and an in-flight safety mode is simulated. Through integrated intelligent control and multi-path switching, the application can simulate in-flight engine faults and mode switching processes in ground tests, and can analyze the stability of a transmission system under normal working conditions or an engine fault condition.

Description

Technical Field

[0001] This invention relates to the field of mechanical transmission test bench technology, specifically to a test bench and test method for a variable power multipath transmission system. Background Technology

[0002] The function of an aero-engine transmission system is to extract power from the engine main shaft and drive various accessories through the accessory drive system to meet the needs of the engine and the aircraft. Conventional aero-engine transmission systems operate in a single mode. Under normal conditions, they extract power from the engine rotor to drive aircraft accessories and engine accessories (accessories refer to various pumps, motors, etc., used to maintain the operation of the aircraft and engine; those used for aircraft operation are called aircraft accessories, and those used for engine operation are called engine accessories), maintaining the normal operation of all related systems of the aircraft and engine. The entire system is strongly interconnected; when the engine fails, it directly causes the aircraft accessories to stop working, resulting in serious consequences. Variable power transmission systems are a new type of transmission system adapted to the intelligent characteristics and needs of engines. They have multiple power transmission paths and incorporate intelligent sensing systems, enabling them to identify and adjust operating modes during flight. When an engine fails at high altitude, power extraction becomes uncontrollable. To ensure the continued controllable operation of aircraft accessories and maintain normal aircraft functions, the accessory drive chain is disconnected from the main transmission system. This allows the aircraft to retain a certain degree of actuation and control capability even in the event of engine failure, reducing the dangers posed by engine failure.

[0003] Components on aero-engines have stringent reliability requirements, and related components must undergo thorough testing and verification before being installed in the engine. Traditional transmission system testing methods are only applicable to transmission systems operating in a single mode. To meet the testing needs of new transmission systems, new testing methods must be established. Therefore, a testing method for variable power transmission systems based on intelligent sensing and control is proposed. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a test bench and test method for a variable power multipath transmission system, solving the technical problem that existing transmission system test methods are only applicable to transmission systems with a single operating mode and cannot complete component tests of variable power multipath transmission systems based on intelligent sensing and control.

[0005] This application discloses a test bench for a variable power multi-path transmission system, including an engine end, an aircraft end, a clutch, and an integrated starter-generator motor; The engine end includes the drive shaft, engine accessories, and the test equipment loading system; The aircraft end includes the drive shaft and aircraft accessories; The tester loading system is used to simulate the engine under normal or fault conditions of the transmission system; The starter-generator integrated motor has an embedded sensing and control system, which is used to monitor the engine speed; The clutch is located between the engine end and the aircraft end, with one end connected to the aircraft accessory drive at the aircraft end and the other end connected to the engine accessory drive at the engine end; and is also connected to the integrated starter motor. During normal operation, the clutch is closed, and the integrated generator motor functions as a generator. When the sensing and control system detects a fault in the engine simulated by the tester loading system, it sends a disconnect signal to the clutch to disengage the clutch, thereby cutting off the power transmission path between the engine and the aircraft. At this time, the integrated generator motor switches to electric motor mode and serves as a backup power source to drive the aircraft accessories on the aircraft side.

[0006] Optionally, the integrated starter-generator motor is connected to a resistor box, which is used to consume the electrical energy generated by the integrated starter-generator motor when it is working as a generator.

[0007] Optionally, the engine end includes a first drive shaft, a second drive shaft, and a third drive shaft; the aircraft end includes a fifth drive shaft and a sixth drive shaft; the test bench also includes a fourth drive shaft, which is disposed between the engine end and the aircraft end and is connected to the integrated starter-generator motor.

[0008] Another aspect of the present invention discloses a test method for a variable power multipath transmission system, using the aforementioned test bench, comprising the following steps: Step 1: Start the loading system of the tester so that it simultaneously drives the engine accessory at the engine end and the aircraft accessory at the aircraft end to work and stabilizes at the preset speed. At this time, the integrated starter motor works as a generator. Step 2: Control the loading system of the tester to simulate an engine failure and reduce its speed. When the sensing and control system of the starter motor detects that the speed has dropped to the speed threshold, it sends a disconnection signal to the clutch to control the clutch to disengage. Step 3: After the clutch is disengaged, the power transmission path between the engine end and the aircraft end is cut off, the engine accessories at the engine end stop working, and at the same time, the integrated starter motor switches to electric motor mode to drive the aircraft accessories at the aircraft end to work, so that the transmission system enters the air safety mode. Step 4: Collect and record the operating parameters of the transmission system during the processes of Steps 1 to 3. Based on the collected operating parameters, perform stability analysis on the transmission system under normal operating conditions or engine failure conditions.

[0009] Optionally, in step 2, if the clutch cannot be disengaged smoothly, the integrated starter motor is controlled to switch from generator mode to electric motor mode to output a balanced torque to ensure that the clutch is disengaged smoothly.

[0010] Optionally, the operating parameters collected in step 4 may include at least: the output power and torque of engine accessories, the output power and torque of aircraft accessories, the rotational speed of each drive shaft, the vibration acceleration of the transmission system housing, and the clutch current.

[0011] Optionally, the sensing and control system establishes a signal interaction with the tester loading system to acquire the rotational speed signal of the tester loading system in real time.

[0012] Compared with the prior art, the present invention has at least the following beneficial effects: (1) The test method of the present invention is applicable to component testing of variable power transmission system based on intelligent perception control. The tester loading system simulates the high-pressure rotor of the engine as the power source under normal working conditions of the transmission system. It can avoid the direct use of expensive aero engines, reduce test costs and improve safety, and improve test efficiency.

[0013] (2) Realistic simulation of fault conditions: This invention simulates the fault state of a sudden drop in the high-pressure rotor speed of an engine through the tester loading system, breaking through the limitation of traditional tests that can only simulate steady-state operation, and can realistically reproduce the extreme conditions of engine failure in the air.

[0014] (3) Verification of intelligent mode switching: The test method uses an integrated motor with embedded sensing and control system, which can monitor the power source status in real time and control the clutch on and off autonomously. It fully simulates the intelligent switching process from "normal mode" to "air safety mode", and realizes a comprehensive assessment of the core control logic of the new transmission system.

[0015] (4) Verification of backup power intervention capability: The integrated starter-generator motor used in the test method of this invention can operate under load and can also switch modes to drive aircraft accessories as a backup power source; the integrated starter-generator motor has sensing and judgment capabilities and establishes signal interaction with the tester loading system. This test method can simulate the process of engine failure in flight and switching of operating modes, fully verify the life and reliability of the new transmission system, lay the foundation for verification and application on the engine as a whole, and provide key data support for evaluating the aircraft's operation and control capabilities after engine failure.

[0016] (5) Improve test reliability and efficiency: When mode switching is difficult, the starting motor outputs a balanced torque to assist the clutch to disengage, which avoids the risk of jamming during the test, improves the success rate and reliability of the test, and ensures the effective acquisition of test data. Attached Figure Description

[0017] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0018] Figure 1 This is a schematic diagram of the test bench for the variable power multipath transmission system of the present invention.

[0019] Explanation of reference numerals in the attached figures: 1. Testing apparatus loading system; 2. First drive shaft; 3. Second drive shaft; 4. Third drive shaft; 5. Fourth drive shaft; 6. Fifth drive shaft; 7. Sixth drive shaft; 8. Electromagnetic clutch; 9. First load; 10. Second load; 11. Third load; 12. Resistance box; 13. Starter motor; 14. High-voltage rotor. Detailed Implementation

[0020] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0021] A specific embodiment of the present invention, such as Figure 1 As shown, a test bench for a variable power multipath transmission system is disclosed, including a resistance box 12, a starter-generator integrated motor 13, an engine end, an aircraft end, and an electromagnetic clutch 8. The resistor box is connected to the starter-generator integrated motor and is used to consume the electrical energy generated by the starter-generator integrated motor; The electromagnetic clutch 8 is connected to the integrated starter motor, the aircraft end, and the engine end, respectively. Furthermore, one end of the electromagnetic clutch 8 is connected to the aircraft accessory drive at the aircraft end, and the other end is connected to the engine accessory drive at the engine end.

[0022] The engine end includes at least one drive shaft, at least one engine accessory, and a tester loading system 1; The aircraft end includes at least one drive shaft and at least one aircraft accessory; The drive shaft is connected to its corresponding accessory.

[0023] The tester loading system 1 is used to simulate the high-pressure rotor 14 of the engine under normal working conditions or fault conditions. When simulating the high-pressure rotor under normal working conditions, the tester loading system serves as the power input source under normal working conditions of the engine.

[0024] Understandably, an engine consists of a high-pressure rotor and blades, which are connected together.

[0025] The integrated starter motor has an embedded sensing and control system for monitoring the speed of the high-voltage rotor and controlling the on / off state of the electromagnetic clutch. When the tester loading system simulates normal engine operation, the integrated starter motor works as a load. When the tester loading system simulates a fault in the engine (high-voltage rotor), the integrated starter motor acts as a backup power source to drive aircraft accessories. During normal operation, the electromagnetic clutch is in the closed state. When a switch signal (disconnect signal) is received from the integrated starter motor, the electromagnetic clutch is energized and disengaged. When the electromagnetic clutch is disengaged, the first drive shaft 2 and the fourth drive shaft 5 are disconnected.

[0026] Furthermore, the electromagnetic clutch includes a toothed disc and a disc spring.

[0027] For example, the aircraft has two accessories, namely the first load 9 and the second load 10; the engine has one accessory, namely the third load 11.

[0028] The engine end is equipped with a first drive shaft 2, a second drive shaft 3, and a third drive shaft 4; The aircraft end is equipped with a fifth drive shaft 6 and a sixth drive shaft 7; The fourth drive shaft 5 is located between the engine end and the aircraft end, and is connected to the engine end, the aircraft end and the starter-generator integrated motor; The fifth drive shaft 6 is connected to the first load, the sixth drive shaft 7 is connected to the second load, and the third drive shaft 4 is connected to the third load. In this configuration, adjacent drive shafts are meshed together via gears. It should be understood that in other embodiments, the parallel shaft gear transmission mechanism can be arranged in a different manner as needed, for example, including more parallel shafts or fewer parallel shafts.

[0029] Another embodiment of the present invention also discloses a test method for a variable power multipath transmission system, which uses the aforementioned test bench for testing, and specifically includes the following steps: Step 1: The tester loading system simultaneously drives the aircraft accessories and engine accessories (each accessory is loaded according to the actual working load), and works stably at n speed. At this time, the integrated starter-generator motor works as a load generator. Understandably, the load is the attachment.

[0030] For example, when the load (attachment) is 3, the power output of the tester loading system is... for: (1) In the formula, This indicates the power output of the first load at the aircraft end; This indicates the power output of the second load at the aircraft end; This indicates the power output from the third load at the engine end; Indicates transmission efficiency.

[0031] Understandably, the load capacity is set according to the actual situation.

[0032] Step 2: The tester loading system simulates an engine malfunction, which is equivalent to an engine failure. At this time, the speed gradually decreases until it reaches the speed threshold (e.g., 20%). The sensing and control system of the starter motor recognizes the speed signal including the speed decrease and sends a switch signal (disconnect signal) to the electromagnetic clutch to control the electromagnetic clutch (which is normally closed by a disc spring) to be energized and disengaged.

[0033] Furthermore, the electromagnetic clutch needs to overcome friction and the elastic force of the disc spring to disengage smoothly. If the electromagnetic clutch cannot disengage at this time, the starter motor is switched from load to motor in advance to balance the driving torque and ensure that the electromagnetic clutch disengages smoothly. Furthermore, the magnitude of the frictional force is: (2) In the formula, The torque transmitted by the electromagnetic clutch; and These are the average diameter of the teeth and the shaft diameter of the dental insert. It is the tooth surface friction angle. , The total weight of the moving parts of the electromagnetic clutch; This represents the coefficient of friction of the tooth contact surface of a dental inlay. It represents the acceleration due to gravity.

[0034] Furthermore, the disengagement force of the electromagnetic clutch is: (3) In the formula, It is the number of coil turns. It's the magnitude of the current. It is the air gap permeability. It is the axial length of the air gap. It is the air gap area. It is the displacement during the disengagement process of the electromagnetic clutch.

[0035] Furthermore, the spring force of the disc spring is: (4) In the formula, and These are the elastic modulus and Poisson's ratio, respectively. For the thickness of the disc spring, and It is a coefficient related to the disc spring diameter ratio. The outer diameter of the disc spring. It is the amount of deformation under normal pressure. It is the deformation of the disc spring. It is the deformation amount when the electromagnetic clutch is in a stable disengagement state.

[0036] Furthermore, the maximum value of the frictional force is obtained according to formulas (2)-(4). Maximum value of disc spring force and the minimum value of electromagnetic force Thus, the motor balancing force of the starter-generator integrated motor is obtained. The expression is:

[0037] In the formula, This indicates the maximum value of the frictional force; This indicates the maximum value of the disc spring force; This represents the minimum value of the electromagnetic force.

[0038] Step 3: After the electromagnetic clutch is disengaged, the mechanical motion relationship between the first drive shaft 2 and the fourth drive shaft 5 is decoupled, the transmission system enters the air safety mode, the engine accessories stop working, and the integrated starter motor is converted from a load to a motor to drive the aircraft accessories until the transmission system reaches the specified speed and load, maintaining the aircraft accessories' actuation control capability.

[0039] The output power of the starter motor should be controlled as follows: .

[0040] Step 4: Collect data such as the power and torque output of all accessories, the speed of each shaft, the vibration acceleration on the transmission system housing, and the electromagnetic clutch current. Based on the collected data, perform stability analysis under normal operating conditions or engine failure conditions.

[0041] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A test bench for a variable power multipath transmission system, characterized in that, This includes the engine end, aircraft end, electromagnetic clutch, and integrated starter-generator motor; The engine end includes the drive shaft, engine accessories, and the test equipment loading system; The aircraft end includes the drive shaft and aircraft accessories; The tester loading system is used to simulate the engine under normal or fault conditions of the transmission system; The starter-generator integrated motor has an embedded sensing and control system, which is used to monitor the engine speed; An electromagnetic clutch is located between the engine end and the aircraft end, with one end connected to the aircraft accessory drive at the aircraft end and the other end connected to the engine accessory drive at the engine end; and is also connected to the integrated starter motor. The electromagnetic clutch includes a toothed disc and a disc spring; During normal operation, the electromagnetic clutch is closed, and the integrated generator motor functions as a generator. When the sensing and control system detects a fault in the engine simulated by the tester loading system, it sends a disconnect signal to the electromagnetic clutch to disconnect it, thereby cutting off the power transmission path between the engine and the aircraft. At this time, the integrated generator motor switches to electric motor mode and serves as a backup power source to drive the aircraft accessories on the aircraft side.

2. The test bench for a variable power multipath transmission system according to claim 1, characterized in that, The integrated generator motor is connected to a resistor box, which is used to consume the electrical energy generated by the integrated generator motor when it is working as a generator.

3. The test bench for a variable power multipath transmission system according to claim 1, characterized in that, The engine end includes a first drive shaft, a second drive shaft, and a third drive shaft; the aircraft end includes a fifth drive shaft and a sixth drive shaft; the test bench also includes a fourth drive shaft, which is located between the engine end and the aircraft end and is connected to the integrated starter-generator motor.

4. A test method for a variable power multipath transmission system, using the test bench as described in any one of claims 1-3, characterized in that, Includes the following steps: Step 1: Start the loading system of the tester so that it simultaneously drives the engine accessory at the engine end and the aircraft accessory at the aircraft end to work and stabilizes at the preset speed. At this time, the integrated starter motor works as a generator. Step 2: Control the loading system of the tester to simulate an engine failure and reduce its speed. When the sensing and control system of the starter motor detects that the speed has dropped to the speed threshold, it sends a disconnection signal to the electromagnetic clutch to control the electromagnetic clutch to disconnect. Step 3: After the electromagnetic clutch is disengaged, the power transmission path between the engine end and the aircraft end is cut off, the engine accessories at the engine end stop working, and at the same time, the integrated starter motor switches to electric motor mode to drive the aircraft accessories at the aircraft end to work, so that the transmission system enters the air safety mode. Step 4: Collect and record the operating parameters of the transmission system during the processes of Steps 1 to 3. Based on the collected operating parameters, perform stability analysis on the transmission system under normal operating conditions or engine failure conditions.

5. The test method for a variable power multipath transmission system according to claim 4, characterized in that, In step 2, if the electromagnetic clutch cannot be disengaged smoothly, the starting and starting motor is controlled to switch from generator mode to motor mode to output a balanced torque to ensure that the electromagnetic clutch is disengaged smoothly.

6. The test method for a variable power multipath transmission system according to claim 4, characterized in that, The operating parameters collected in step 4 include at least: the output power and torque of the engine accessories, the output power and torque of the aircraft accessories, the rotational speed of each drive shaft, the vibration acceleration of the transmission system housing, and the current of the electromagnetic clutch.

7. The test method for a variable power multipath transmission system according to claim 4, characterized in that, The sensing and control system establishes signal interaction with the tester loading system to acquire the rotational speed signal of the tester loading system in real time.

Images