A rotor engine oil metering redundancy control system and method for a low altitude aircraft
Patent Information
- Application Number
- CN202611403769.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-09-10
- Publication Date
- 2026-10-30
AI Technical Summary
其中，机械式计量泵调节精度较差，难以精准匹配发动机不同转速、负荷工况下的润滑供油需求；单一电磁阀控制系统则缺少闭环反馈与安全冗余设计
1.本发明在机油计量泵总成上集成主电磁阀与冗余备份电磁阀，二者油路并联布置，当主电磁阀出现故障导致供油异常时，可切换至冗余备份电磁阀接替供油，避免转子发动机因单路电磁阀失效发生机油供给中断，提升低空飞行器转子发动机机油供油工作可靠性。
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Figure CN123006435A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of rotary engine technology, specifically a redundant control system and method for oil metering of rotary engines suitable for low-altitude aircraft. Background Technology
[0002] To adapt to the development of the low-altitude economy, the trend towards miniaturized aircraft rotary engines is increasing. Currently, most rotary engine cylinder lubrication systems use mechanical plunger pumps or single electronically controlled solenoid valves to control the oil supply. Among these, mechanical metering pumps have poor adjustment accuracy, making it difficult to precisely match the lubrication supply requirements under different engine speeds and load conditions; while single solenoid valve control systems lack closed-loop feedback and safety redundancy design.
[0003] In low-altitude flight conditions, if the oil metering valve becomes stuck, the drive circuit fails, or the oil supply line is abnormal, the sudden drop in oil pressure cannot be detected and dealt with in time. This can easily cause dry friction in core friction pairs such as the triangular rotor and radial seals, resulting in rapid wear or even jamming, which can further lead to loss of power in the air and seriously threaten flight safety. Summary of the Invention
[0004] To address the problems existing in the background art, the present invention provides a redundant control system and method for oil metering of a rotor engine suitable for low-altitude aircraft.
[0005] To achieve the above objectives, the present invention adopts the following technical solution: a redundant control system for oil metering of a rotor engine suitable for low-altitude aircraft, comprising an oil metering pump assembly, a main solenoid valve, a redundant backup solenoid valve, an oil pressure sensor, and an electronic control unit; The oil metering pump assembly is provided with an oil inlet, an oil outlet, and an oil drain hole. The main solenoid valve and the redundant backup solenoid valve are both mounted on the oil metering pump assembly and are independently configured. The oil pressure sensor is mounted on the oil outlet side of the oil metering pump assembly, and the sensor's detection end is connected to the oil passage of the oil outlet. The oil inlet is used to connect to an external oil supply source, the oil outlet is used to connect to the cylinder lubrication oil passage of the rotary engine, and the oil drain hole is used to connect to the return oil line. The main solenoid valve, the redundant backup solenoid valve, and the oil pressure sensor are all electrically connected to the electronic control unit (ECU). The ECU outputs a switching control signal to the main solenoid valve and the redundant backup solenoid valve based on the oil outlet pressure signal collected by the oil pressure sensor, thereby controlling their switching operation.
[0006] Both the main solenoid valve and the redundant backup solenoid valve are on / off metering valves with the same structure. The oil volume output by each solenoid valve core in a single opening and closing action is a fixed value. The electronic control unit adjusts the opening and closing frequency of the solenoid valves to change the total amount of oil output per unit time.
[0007] The main solenoid valve and the redundant backup solenoid valve are arranged in parallel in the internal oil circuit of the oil metering pump assembly. The oil input through the oil inlet can be supplied to the oil chamber of the main solenoid valve and the oil chamber of the redundant backup solenoid valve respectively, and the output ends of the main solenoid valve and the redundant backup solenoid valve are connected to the oil passage of the oil outlet.
[0008] The drain holes are connected to the drain channels of the main solenoid valve and the redundant backup solenoid valve, respectively, and the excess oil generated by the depressurization of each solenoid valve can flow back through the drain holes.
[0009] The method includes the following steps: S1: Under normal operating conditions, the electronic control unit drives the main solenoid valve to work and keeps the redundant backup solenoid valve in a dormant standby state. The oil output is controlled by adjusting the opening and closing frequency of the main solenoid valve. S2: The oil pressure signal on the oil outlet side is collected in real time by the oil pressure sensor and the pressure signal is fed back to the electronic control unit; S3: The electronic control unit judges the oil pressure signal. If the pressure signal is in the normal range, it maintains the current working state. If the oil pressure signal is detected to be lower than the preset threshold, it outputs an alarm signal and a switching control signal. The switching control signal is used to control the main solenoid valve to be cut off and the redundant backup solenoid valve to be activated so as to continue to supply lubricating oil to the rotor engine cylinder.
[0010] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention integrates a main solenoid valve and a redundant backup solenoid valve into the oil metering pump assembly. The two are arranged in parallel oil circuits. When the main solenoid valve fails and causes abnormal oil supply, it can switch to the redundant backup solenoid valve to take over the oil supply, thereby avoiding oil supply interruption of the rotor engine due to the failure of a single solenoid valve and improving the reliability of oil supply in the rotor engine of low-altitude aircraft.
[0011] 2. The oil pressure sensor is directly installed on the oil outlet side to monitor the actual output oil pressure in real time. Based on the oil outlet pressure signal, the oil supply condition is judged, which can accurately reflect the actual oil supply status and reduce misjudgment.
[0012] 3. The drain holes are connected to the drain channels of the two solenoid valves respectively. The oil overflowing from the solenoid valves can flow back smoothly, maintaining the stability of the internal oil pressure of the system and reducing the adverse effects of abnormal oil pressure on the service life of the solenoid valves.
[0013] 4. The electronic control unit uses existing mature control devices, and only utilizes its existing signal acquisition, logic judgment and drive output functions to realize switching control. There is no need to modify the electronic control hardware itself, and the solution is easy to implement.
[0014] In summary, the present invention has a compact structure, integrating the main and backup solenoid valves on the oil metering pump assembly. It relies on oil pressure monitoring on the oil outlet side to achieve fault identification and oil supply switching, effectively improving the fault tolerance capability of oil supply for the rotor engine of low-altitude aircraft. The structure is simple and easy to assemble and manufacture. Attached Figure Description
[0015] Figure 1 This is a three-dimensional structural schematic diagram of the present invention; Figure 2 This is a three-dimensional structural schematic diagram from another perspective of the present invention. Detailed Implementation
[0016] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.
[0017] This embodiment discloses a redundant control system for oil metering of a rotor engine suitable for low-altitude aircraft, such as... Figure 1 , Figure 2 As shown, the system includes an oil metering pump assembly 1, a main solenoid valve 2, a redundant backup solenoid valve 3, an oil pressure sensor 4, and an electronic control unit (ECU). The oil metering pump assembly 1 has an oil inlet 5, an oil outlet 6, and a drain hole 7. The main solenoid valve 2 and the redundant backup solenoid valve 3 are both mounted on the oil metering pump assembly 1, arranged independently. The oil pressure sensor 4 is installed on the oil outlet side of the oil metering pump assembly 1, and its detection end is connected to the oil passage of the oil outlet 6. The oil inlet 5 connects to an external oil supply source, the oil outlet 6 connects to the cylinder lubrication oil passage of the rotary engine, and the drain hole 7 connects to the return oil line. The main solenoid valve 2, the redundant backup solenoid valve 3, and the oil pressure sensor 4 are all electrically connected to the ECU.
[0018] Both the main solenoid valve 2 and the redundant backup solenoid valve 3 are on / off metering valves with identical structures. Each time the solenoid valve core completes its opening and closing action, it outputs a fixed volume of oil. The electronic control unit adjusts the oil output per unit time by changing the opening and closing frequency of the solenoid valves, thus matching the oil supply requirements of the rotary engine under different operating conditions. The main solenoid valve 2 and the redundant backup solenoid valve 3 are arranged in parallel within the oil metering pump assembly 1. After external oil supply enters the pump body through the oil inlet 5, the oil can enter the oil chambers of the main solenoid valve 2 and the redundant backup solenoid valve 3 respectively. The oil outlets of the main solenoid valve 2 and the redundant backup solenoid valve 3 converge and connect to the oil passage of the oil outlet 6. The drain hole 7 connects to the drain channels of the main solenoid valve 2 and the redundant backup solenoid valve 3 respectively. Excess oil overflowing during solenoid valve operation can flow back to the return oil line through the drain hole 7.
[0019] In this embodiment, the electronic control unit is a single-chip microcontroller commonly used in the field of rotary engine electronic control, which is a mature existing hardware device. This invention does not modify the hardware circuitry or chip model of the electronic control unit itself, but only utilizes its existing signal acquisition, logic comparison, and signal output functions to implement the redundant switching control logic of this application. The electronic control unit hardware includes an analog signal acquisition port and a multi-channel drive output port; the analog signal acquisition port is electrically connected to the oil pressure sensor 4 to receive the pressure analog signal output by the oil pressure sensor 4; the multi-channel drive output port is electrically connected to the main solenoid valve 2 and the redundant backup solenoid valve 3 respectively, for outputting drive signals, switching control signals, and alarm signals.
[0020] During operation, the oil pressure sensor 4 collects the oil pressure in the oil passage of the oil outlet 6 in real time and transmits the pressure analog signal to the electronic control unit (ECU). The ECU performs analog-to-digital conversion and compares the collected actual oil pressure value with the preset oil pressure threshold within the ECU. Under the normal operating conditions of the low-altitude aircraft rotor engine, the ECU outputs a drive signal to the main solenoid valve 2, controlling the main solenoid valve 2 to reciprocate opening and closing at the opening and closing frequency corresponding to the operating conditions, thereby achieving a quantitative oil supply. At this time, the ECU does not output a drive signal to the redundant backup solenoid valve 3, and the redundant backup solenoid valve 3 remains in a dormant closed state and does not participate in oil metering and supply.
[0021] When the main solenoid valve 2 malfunctions, becomes stuck, or experiences an abnormality in the oil circuit, causing a drop in oil pressure at the oil outlet 6 and the collected oil pressure falls below the preset threshold inside the electronic control unit (ECU), a signal anti-jitter delay logic can be configured inside the ECU to prevent erroneous switching caused by instantaneous oil pressure disturbances. Only after the oil pressure falls below the preset threshold and remains below the set anti-jitter duration will the ECU output an alarm signal and a switching control signal. The alarm signal can be connected to an external alarm indicator light or the aircraft's onboard alarm bus to report the oil metering system malfunction to the entire aircraft. The switching control signal cuts off the drive output of the main solenoid valve 2, stopping its operation. Simultaneously, it outputs a drive signal to the redundant backup solenoid valve 3, waking it up and putting it into operation. The redundant backup solenoid valve 3 then takes over the oil metering supply, continuously delivering lubricating oil to the rotor engine cylinders, achieving oil supply redundancy and ensuring that the rotor engine on the low-altitude aircraft will not directly lose its oil supply due to a single solenoid valve malfunction.
[0022] The aforementioned logic for pressure signal acquisition, analog-to-digital conversion, threshold comparison, anti-shake delay judgment, drive signal output, fault alarm, and solenoid valve operation switching all fall under conventional technical means in the field of engine electronic control. Those skilled in the art, combining the hardware connection relationships and control logic described in this application, can implement all the above functions using a commercially available microcontroller controller without any creative effort. The specific pressure values for the preset thresholds and the anti-shake delay duration can be adaptively calibrated according to the rotor engine model and the operating conditions of the low-altitude aircraft. These calibration parameters do not constitute an improvement of this invention and are not specifically limited here.
[0023] This embodiment also discloses a redundant control method for oil metering in a rotor engine suitable for low-altitude aircraft. Employing the aforementioned redundant oil metering control system, the method includes the following steps: S1: Under normal operating conditions, the electronic control unit (ECU) drives the main solenoid valve 2 and keeps the redundant backup solenoid valve 3 in standby mode. The oil output is controlled by adjusting the opening and closing frequency of the main solenoid valve 2. S2: The oil pressure signal from the oil outlet port 6 is collected in real time by the oil pressure sensor 4 and fed back to the ECU. S3: The ECU judges the oil pressure signal. If the pressure signal is within the normal range, the current operating state is maintained. If the oil pressure signal is detected to be below a preset threshold, an alarm signal and a switching control signal are output. The switching control signal is used to control the shut-off of the main solenoid valve 2 and the activation of the redundant backup solenoid valve 3 to continue supplying lubricating oil to the rotor engine cylinder.
[0024] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of the equivalent features of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.
Claims
1. A redundant control system for oil metering of a rotary engine suitable for low-altitude aircraft, characterized in that: It includes an oil metering pump assembly (1), a main solenoid valve (2), a redundant backup solenoid valve (3), an oil pressure sensor (4), and an electronic control unit; The oil metering pump assembly (1) is provided with an oil inlet (5), an oil outlet (6), and an oil drain (7); the main solenoid valve (2) and the redundant backup solenoid valve (3) are both installed on the oil metering pump assembly (1) and are set independently of each other; the oil pressure sensor (4) is installed on the oil outlet side of the oil metering pump assembly (1), and the detection end of the oil pressure sensor (4) is connected to the oil passage of the oil outlet (6); the oil inlet (5) is used to connect to the external oil supply source, the oil outlet (6) is used to connect to the cylinder lubrication oil circuit of the rotary engine, and the oil drain (7) is used to connect to the return oil pipeline; the main solenoid valve (2), the redundant backup solenoid valve (3), and the oil pressure sensor (4) are all electrically connected to the electronic control unit; the electronic control unit is used to output a switching control signal to the main solenoid valve (2) and the redundant backup solenoid valve (3) according to the oil outlet pressure signal collected by the oil pressure sensor (4) to control the switching operation of the two.
2. The redundant control system for rotor engine oil metering in low-altitude aircraft according to claim 1, characterized in that: The main solenoid valve (2) and the redundant backup solenoid valve (3) are both on / off metering valves with the same structure. The oil volume output by each solenoid valve core in a single on / off action is a fixed value. The electronic control unit adjusts the opening and closing frequency of the solenoid valve to change the total amount of oil output per unit time.
3. The redundant control system for rotor engine oil metering in low-altitude aircraft according to claim 1, characterized in that: The main solenoid valve (2) and the redundant backup solenoid valve (3) are arranged in parallel in the internal oil circuit of the oil metering pump assembly (1). The oil input through the oil inlet (5) can be supplied to the oil chamber of the main solenoid valve (2) and the oil chamber of the redundant backup solenoid valve (3) respectively. The output ends of the main solenoid valve (2) and the redundant backup solenoid valve (3) are connected to the oil passage of the oil outlet (6).
4. The redundant control system for rotor engine oil metering in low-altitude aircraft according to claim 1, characterized in that: The drain hole (7) is connected to the drain channels of the main solenoid valve (2) and the redundant backup solenoid valve (3), respectively, and the excess oil generated by the depressurization of each solenoid valve can flow back through the drain hole (7).
5. A method for redundant control of oil metering in a rotor engine suitable for low-altitude aircraft according to any one of claims 1-4, characterized in that, The method includes the following steps: S1: Under normal operating conditions, the electronic control unit drives the main solenoid valve (2) to work and keeps the redundant backup solenoid valve (3) in hibernation standby. The oil output is controlled by adjusting the opening and closing frequency of the main solenoid valve (2). S2: The oil pressure signal on the oil outlet (6) side is collected in real time by the oil pressure sensor (4), and the pressure signal is fed back to the electronic control unit; S3: The electronic control unit judges the oil pressure signal. If the pressure signal is in the normal range, it maintains the current working state. If the oil pressure signal is detected to be lower than the preset threshold, it outputs an alarm signal and a switching control signal. The switching control signal is used to control the main solenoid valve (2) to be cut off and the redundant backup solenoid valve (3) to continue to supply lubricating oil to the rotor engine cylinder.