Test flight test modification method and system for ram air turbine system

Abstract

The invention belongs to the technical field of aircraft test flight verification, and discloses a test flight test modification method and system for a ram air turbine system, and the method comprises the steps: modifying an aircraft employing the ram air turbine system as an emergency hydraulic energy source; a hydraulic pump outlet guide pipe of the ram air turbine system is disconnected from the hydraulic source system, the rear end of a hydraulic pump of the ram air turbine system is connected with a hydraulic oil tank through a one-way throttle valve, and a pressure sensor is installed at the rear end of the hydraulic pump. According to the invention, the internal leakage of the system under the emergency energy working condition can be simulated, the working states such as the pressure and the rotating speed of the ram air turbine can be monitored, and the verification of the emergency energy in the flight verification test can be realized, including the pressure building time, the capacity and the rotating speed of the ram air turbine system under the airplane emergency state. And a normal hydraulic source system can still be used during test flight.

Description

Technical Field

[0001] This invention belongs to the field of aircraft flight test verification technology, and relates to a modification method and system for flight test of an aircraft hydraulic power source system, specifically to a modification method and system for flight test of a ram air turbine system. Background Technology

[0002] The ram air turbine system is an emergency power source for aircraft. When the aircraft is in an emergency, it can absorb the energy of ram air and convert it into emergency hydraulic energy or emergency electrical energy.

[0003] Hydraulic emergency power systems for aircraft typically consist of a ram air turbine system, pressure and oil suction lines integrated onboard to achieve system functionality. The ram air turbine system providing emergency hydraulic power usually comprises a hydraulic pump, retraction / extension actuator, deployment solenoid, hydraulically controlled directional valve, turbine blades, etc. Figure 1 As shown, in non-emergency mode, the aircraft's hydraulic power is provided by EDP #2, EDP #3 and one DC electric pump EMP connected in parallel. In emergency mode, if the hydraulic power source system fails, the aircraft's hydraulic power is provided by the ram air turbine system.

[0004] Therefore, the operating envelope of the ramjet turbine system needs to coincide with the aircraft's flight envelope, and it should be able to provide sufficient power under all flight altitude and speed conditions. To meet this requirement, in-flight verification of the ramjet turbine system under full operating envelope conditions is necessary. However, verifying the ramjet turbine system's capability under conditions where the engine or normal hydraulic power sources have all failed has a significant impact on aircraft safety, and currently, there are no mature flight test verification methods available in China.

[0005] Ground-based testing methods are difficult to simulate real flight environments, and using wind tunnels for verification is both too costly and has limited resources. Summary of the Invention

[0006] To address the aforementioned issues, this invention provides a method and system for flight test modification of a ram air turbine system. By decomposing the onboard functional verification of the ram air turbine system, i.e. verifying in the air whether the pressure build-up time, capacity, and speed of the ram air turbine system meet the requirements, the remaining functional performance is verified through ground tests and simulations, significantly reducing the risks and technical difficulties of flight test verification.

[0007] The technical solution of the present invention is as follows: A method for flight testing and modification of a ram air turbine system, modifying an aircraft that uses a ram air turbine system as an emergency hydraulic power source, includes the following steps: S1, disconnect the hydraulic pump outlet pipe of the ram air turbine system from the hydraulic power source system; S2 connects the rear end of the hydraulic pump of the ram air turbine system to the hydraulic oil tank via a one-way throttle valve, and installs a pressure sensor at the rear end of the hydraulic pump.

[0008] Furthermore, after S1, a plug is used to seal the connection between the hydraulic pump outlet conduit and the hydraulic power source system.

[0009] A flight test system for a ram air turbine system includes a hydraulic power source system, a ram air turbine system, a one-way throttle valve, a hydraulic oil tank, and a pressure sensor. The oil outlet of the hydraulic oil tank is connected to the inlets of the hydraulic power source system and the ram air turbine system, respectively. The hydraulic power source system and the ram air turbine system are connected in parallel. The outlet of the hydraulic power source system supplies pressure to the system. The outlet of the ram air turbine system is connected to the oil inlet of the hydraulic oil tank through a one-way throttle valve. The pressure sensor measures the outlet pressure of the ram air turbine system.

[0010] Furthermore, it also includes a data recording module, which is connected to a pressure sensor and records the pressure sensor's data, and a data recording module is connected to a speed sensor of the ram air turbine system and records the speed sensor's data.

[0011] Furthermore, it also includes an accumulator and a priority valve. The hydraulic oil tank is a piston-type booster tank. The accumulator is connected to the high-pressure chamber of the hydraulic oil tank. The accumulator is also connected to the outlet of the hydraulic power source system through the priority valve.

[0012] A flight test method for a ram air turbine system, comprising the following steps: conducting flight tests on an aircraft modified using a ram air turbine system flight test modification method, or conducting flight tests on an aircraft equipped with the aforementioned ram air turbine system flight test system. Step 1: During flight, the hydraulic power system normally provides hydraulic pressure to the aircraft systems; Step 2: Start the ram air turbine system and use ram air to drive the ram air turbine system, which generates hydraulic pressure. Step 3: Collect and record the hydraulic pressure and flow rate generated by the ram air turbine system; Step four: The liquid supply at the rear end of the ram air turbine system is returned to the hydraulic oil tank to eliminate the impact of starting the ram air turbine system on the oil level in the hydraulic oil tank.

[0013] Furthermore, the internal leakage of the hydraulic power source system under emergency energy working conditions was simulated using a one-way throttle valve.

[0014] Furthermore, the flow rate in step three is calculated by using the rotational speed collected by the rotational speed sensor of the hydraulic pump installed in the ram air turbine system.

[0015] Technical effects: 1. This invention provides a method and system for flight test modification of a ram air turbine system. The method simulates the internal leakage of the system under emergency power conditions using a simulation device, and monitors the working status of the ram air turbine, such as pressure and speed, using pressure acquisition devices and speed acquisition devices. This method can realize the verification of emergency power in flight verification tests, including the pressure build-up time, capacity and speed of the ram air turbine system in emergency conditions of the aircraft, and the normal hydraulic power source system can still be used during flight tests.

[0016] 2. This method greatly reduces the risks and technical difficulties of flight testing and verification of ram air turbine systems. Moreover, the modification method is relatively simple, saving flight testing time and costs, and has good application prospects and economic benefits.

[0017] 3. This invention enables real-world testing and verification through airborne trials, resulting in more reliable and accurate conclusions compared to purely ground-based testing. Compared to wind tunnel testing, it is significantly less expensive and avoids utilizing scarce wind tunnel resources, thus improving testing efficiency. Attached Figure Description

[0018] Figure 1 This is the original schematic diagram of the present invention.

[0019] Figure 2 This is a schematic diagram of the pipeline removal process according to the present invention.

[0020] Figure 3 This is a schematic diagram of the modification principle of the present invention.

[0021] Among them, 1—hydraulic pump outlet conduit, 2—hydraulic source system, 3—ram air turbine system, 4—one-way throttle valve, 5—hydraulic oil tank, and 6—pressure sensor. Detailed Implementation

[0022] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0023] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0024] Example 1: A method for flight testing and modification of a ram air turbine system, modifying an aircraft that uses a ram air turbine system as an emergency hydraulic power source, includes the following steps: S1, disconnect the hydraulic pump outlet pipe of the ram air turbine system from the hydraulic power source system; S2 connects the rear end of the hydraulic pump of the ram air turbine system to the hydraulic oil tank via a one-way throttle valve, and installs a pressure sensor at the rear end of the hydraulic pump.

[0025] After S1, a plug is used to seal the connection between the hydraulic pump outlet conduit and the hydraulic power source system.

[0026] A flight test system for a ram air turbine system includes a hydraulic power source system 2, a ram air turbine system 3, a one-way throttle valve 4, a hydraulic oil tank 5, and a pressure sensor 6. The oil outlet of the hydraulic oil tank 5 is connected to the inlet of both the hydraulic power source system 2 and the ram air turbine system 3. The hydraulic power source system 2 and the ram air turbine system 3 are connected in parallel. The outlet of the hydraulic power source system 2 supplies pressure to the system. The outlet of the ram air turbine system 3 is connected to the oil inlet of the hydraulic oil tank 5 through a one-way throttle valve 4. The pressure sensor 6 measures the outlet pressure of the ram air turbine system 3.

[0027] It also includes a data recording module, which is connected to the pressure sensor 6 and records the data of the pressure sensor 6, and the data recording module is connected to the speed sensor of the ram air turbine system 3 and records the data of the speed sensor.

[0028] It also includes an accumulator and a priority valve. The hydraulic oil tank 5 is a piston-type oil tank. The accumulator is connected to the high-pressure chamber of the hydraulic oil tank 5. The accumulator is also connected to the outlet of the hydraulic power source system 2 through the priority valve.

[0029] A flight test method for a ram air turbine system, comprising the following steps: conducting flight tests on an aircraft modified using a ram air turbine system flight test modification method, or conducting flight tests on an aircraft equipped with the aforementioned ram air turbine system flight test system. Step 1: During flight, the hydraulic power system normally provides hydraulic pressure to the aircraft systems; Step 2: Start the ram air turbine system and use ram air to drive the ram air turbine system, which generates hydraulic pressure. Step 3: Collect and record the hydraulic pressure and flow rate generated by the ram air turbine system; Step four: The liquid supply at the rear end of the ram air turbine system is returned to the hydraulic oil tank to eliminate the impact of starting the ram air turbine system on the oil level in the hydraulic oil tank.

[0030] The internal leakage of the hydraulic power source system under emergency energy working conditions was simulated using a one-way throttle valve.

[0031] The flow rate in step three is calculated by using the rotational speed collected by the speed sensor of the hydraulic pump installed in the ram air turbine system.

[0032] Example 2: A method and system for flight testing and modification of a ram air turbine system, characterized in that the method and system include the following steps: Step 1: Disconnect the hydraulic pump outlet conduit (pressure line) of the ram air turbine system from the hydraulic power source system, and seal the connection between the hydraulic pump outlet conduit and the hydraulic power source system with a plug cap; Step 2: Connect the ram air turbine system, the one-way throttle valve, and the hydraulic oil tank. Install a pressure acquisition device at the rear end of the hydraulic pump of the ram air turbine system.

[0033] See Figure 1 This is an original schematic diagram of one embodiment of this application. In this schematic diagram, the power source of the medium hydraulic power system 2 consists of 2#EDP, 3#EDP and a DC electric pump (EMP) connected in parallel. 2#EDP and 3#EDP draw oil from the hydraulic oil tank 5 through the oil suction pipe. The high-pressure oil output goes one way to the high-pressure port of the self-supplying booster hydraulic oil tank 5; the other way goes to the control valves of each functional system. The DC electric pump is used to supplement the system's short-term high flow demand and serves as a backup power source after the main pump fails. The emergency energy system is connected in parallel with the medium hydraulic power system 2. The emergency energy system is integrated on the aircraft by the ram air turbine system 3, pressure pipelines and oil suction pipelines. When the normal hydraulic power system fails, the ram air turbine system 3 draws oil from the hydraulic oil tank 5 and then supplies pressure to the flight control system.

[0034] In one implementation, such as Figure 2 As shown, it was confirmed that the hydraulic power source system 2 was not pressurized and the accumulator was in an unloaded state. The connection between the hydraulic pump outlet pipe 1 of the ram air turbine system 3 and the hydraulic power source system 2 was disconnected and sealed with a plug.

[0035] Figure 3This is a schematic diagram of one embodiment of the present application, showing the connection of a ram air turbine system 3, a one-way throttle valve 4, and a hydraulic oil tank 5. A pressure sensor 6 is installed at the rear end of the hydraulic pump of the ram air turbine system 3. The hydraulic oil tank of the intermediate hydraulic power source, connected through the added one-way throttle valve, is used to simulate the internal leakage of the intermediate hydraulic power source system 2 under emergency energy working conditions. Its main performance indicators are: rated flow rate: 4L / min, inlet and outlet pressure difference: 13MPa~15MPa.

[0036] Based on the above test modifications, after the ram air turbine system 3 is lowered from the aircraft and starts working in the air, it draws oil from the hydraulic oil tank 5. The high-pressure oil output returns to the hydraulic oil tank 5 through the one-way throttle valve 4. The pressure output by the ram air turbine system 3 is collected by the pressure sensor 6, and its output speed is measured by its built-in speed sensor. The data recording module will synchronously store the pressure and speed data.

[0037] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A method for flight testing and modification of a ramjet turbine system, characterized in that, The modification of aircraft that use ram air turbine systems as emergency hydraulic power sources includes the following steps: S1, disconnect the hydraulic pump outlet pipe of the ram air turbine system from the hydraulic power source system; S2 connects the rear end of the hydraulic pump of the ram air turbine system to the hydraulic oil tank via a one-way throttle valve, and installs a pressure sensor at the rear end of the hydraulic pump.

2. The method for flight testing and modification of a ramjet turbine system according to claim 1, characterized in that, After S1, a plug is used to seal the connection between the hydraulic pump outlet conduit and the hydraulic power source system.

3. A flight test system for a ramjet turbine system, characterized in that, The system includes a hydraulic power source system (2), a ram air turbine system (3), a one-way throttle valve (4), a hydraulic oil tank (5), and a pressure sensor (6). The oil outlet of the hydraulic oil tank (5) is connected to the inlet of the hydraulic power source system (2) and the ram air turbine system (3), respectively. The hydraulic power source system (2) and the ram air turbine system (3) are connected in parallel. The outlet of the hydraulic power source system (2) supplies pressure to the system. The outlet of the ram air turbine system (3) is connected to the oil inlet of the hydraulic oil tank (5) through a one-way throttle valve (4). The pressure sensor (6) measures the outlet pressure of the ram air turbine system (3).

4. The flight test system for a ramjet turbine system according to claim 3, characterized in that, It also includes a data recording module, which is connected to the pressure sensor (6) and records the data of the pressure sensor (6), and the data recording module is connected to the speed sensor of the ram air turbine system (3) and records the data of the speed sensor.

5. The flight test system for a ramjet turbine system according to claim 3, characterized in that, It also includes an accumulator and a priority valve. The hydraulic oil tank (5) is a piston-type oil tank. The accumulator is connected to the high-pressure chamber of the hydraulic oil tank (5). The accumulator is also connected to the outlet of the hydraulic power source system (2) through the priority valve.

6. A method for flight testing of a ramjet turbine system, comprising conducting flight tests on an aircraft modified using the method described in claim 1, or conducting flight tests on an aircraft equipped with the flight test system described in claim 3, characterized in that... Includes the following steps: Step 1: During flight, the hydraulic power system normally provides hydraulic pressure to the aircraft systems; Step 2: Start the ram air turbine system and use ram air to drive the ram air turbine system, which generates hydraulic pressure. Step 3: Collect and record the hydraulic pressure and flow rate generated by the ram air turbine system; Step four: The liquid supply at the rear end of the ram air turbine system is returned to the hydraulic oil tank to eliminate the impact of starting the ram air turbine system on the oil level in the hydraulic oil tank.

7. The flight test method for a ramjet turbine system according to claim 6, characterized in that, The internal leakage of the hydraulic power source system under emergency energy working conditions was simulated using a one-way throttle valve.

8. The flight test method for a ramjet turbine system according to claim 6, characterized in that, The flow rate in step three is calculated by using the rotational speed collected by the speed sensor of the hydraulic pump installed in the ram air turbine system.

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