Ram air turbine system

Abstract

The application discloses a ram air turbine system, comprising a turbine, an energy conversion unit, a support arm, an actuator cylinder, a recovery control switch, a quick connector and a hose; wherein the turbine, the energy conversion unit and the support arm are sequentially connected to form a ram air turbine device, the ram air turbine device rotates around the pivot of the support arm; the actuator cylinder is a pneumatic actuator cylinder; the rod end A of the pneumatic actuator cylinder is hinged with the support arm, and the tailstock end B is hinged with the fuselage; the control air channel in the actuator cylinder forms an air inlet and an air outlet through a recovery electromagnetic valve, the air inlet is connected with the connecting hose, and the air outlet is communicated with the atmosphere; the pneumatic actuator cylinder comprises the recovery electromagnetic valve, a piston cylinder, an upper lock, a lower lock, a damper, a lock piston, a piston rod, a spring, a disc spring set and a tailstock. The embodiment of the application solves the problems of the conventional ram air turbine system, such as pollution caused by easy oil leakage, unstable response time and the like.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of aviation emergency energy technology, and to a ram air turbine system. Background Technology

[0002] Traditional ram air turbine systems mainly consist of a ram air turbine unit and a hydraulic actuator. The retraction and extension of the ram air turbine unit are achieved by the hydraulic actuator.

[0003] Currently, the hydraulic actuators used in ram air turbine systems have two main drawbacks: 1) They are prone to oil leakage, causing pollution problems, and the oil is flammable, posing a risk of explosion; 2) The viscosity of the oil is greatly affected by temperature, and low temperature conditions severely affect the response time of the ram air turbine. Summary of the Invention

[0004] The purpose of this invention is to provide a ram air turbine system to solve the problems of existing ram air turbine systems, such as pollution caused by easy oil leakage and unstable response time.

[0005] The technical solution of the present invention: The present invention provides a ram air turbine system, including: turbine 1, energy conversion unit 2, support arm 3, actuator cylinder, recovery control switch 7, quick-change connector 12, and hose 13;

[0006] Among them, turbine 1, energy conversion unit 2 and support arm 3 are connected in sequence to form ram air turbine device, and ram air turbine device rotates around the pivot of support arm 3;

[0007] The actuator is configured as a pneumatic actuator; the rod end A of the pneumatic actuator 4 is hinged to the support arm 3, and the tailstock end B is hinged to the fuselage; the control air passage inside the actuator 4 forms an air inlet 14 and an exhaust port 15 through a recovery solenoid valve 5, the air inlet 14 is connected to the connecting hose 13, and the exhaust port 15 is connected to the atmosphere.

[0008] The pneumatic actuator 4 includes: a recovery solenoid valve 5, a piston cylinder 16, an upper lock 17, a lower lock 18, a damper 19, a locking piston 20, a piston rod 21, a spring 22, a disc spring assembly 23, and a tailstock 24.

[0009] The piston cylinder 16 has a closed end, which is rod end A. The piston cylinder 16 has an annular upper locking groove and a lower locking groove at both ends. The piston rod 21 and the locking piston 20 nested within the piston rod 21 are integrally nested within the piston cylinder 16. One end of the piston rod 21 extending out of the piston cylinder 16 is fixedly connected to the tailstock 24. The locking piston 20, located within the piston cylinder 16, has an axially arranged upper lock 17 and lower lock 18 with a convex ring structure. The upper lock 17 and lower lock 18 extend radially out of the piston rod 21. The upper lock 17 engages with the upper locking groove to lock the retracted state, and the lower lock 18 engages with the lower locking groove to lock the unfolded state. A spring 22 and a disc spring assembly 23 are arranged within the annular cavity formed by the piston rod 21 and the piston cylinder 16. An annular boss is provided on the outside of the piston cylinder 16, and the tailstock 24 is installed between the annular boss and the tailstock 24.

[0010] Alternatively, in the ram air turbine system described above,

[0011] The ram air turbine system is used in the air to push the ram air turbine device out of the cabin by the elastic force of the compression spring 22 built into the pneumatic actuator 4; it is also used during the push-out process to absorb the system impact load and reduce the structural impact force by using the damper 19 and disc spring assembly 23 in the cavity of the pneumatic actuator 4 when the pneumatic actuator 4 is close to being fully extended; after the ram air turbine device is fully extended, the turbine 1 rotates under the action of airflow, driving the energy conversion unit 2 to work and generate emergency energy for the aircraft; it is also used for ground recovery, whereby the pneumatic actuator 4 is connected to the air source 11 through the hose 13 and quick-connect coupling 12, so that the single piston rod cylinder in the pneumatic actuator 4 introduces high-pressure gas, generating a recovery pull force to retract the ram air turbine device into the cabin.

[0012] Alternatively, in the ram air turbine system described above,

[0013] The damper 19 and the disc spring assembly 23 work together to buffer the load transmitted by the piston cylinder 16. Their characteristics are as follows:

[0014] a) The damper 19 is arranged at the tail end of the piston rod 21 and along the axial direction of the piston rod 21. One end is connected to the inner cavity of the piston rod 21, and the other end is connected to the inner cavity of the piston cylinder 16. The inner cavity of the piston rod 21 is connected to the exhaust port 15 through the recovery solenoid valve 5, forming an exhaust passage from the inner cavity of the piston cylinder 16 through the damper (19) to the inner cavity of the piston rod 21 and then to the exhaust port 15. The exhaust passage is in a normally open state. When the pneumatic actuator 4 is extended to the piston cylinder 16 and close to the tail end of the piston rod 21, the flow area of ​​the damper 19 gradually decreases. The air in the inner cavity of the piston cylinder 16 is discharged from the remaining connected damper. During this process, the air volume is compressed, absorbing the load transmitted by the piston cylinder 16 and playing a buffering role.

[0015] b) The disc spring assembly 23 is composed of multiple disc springs connected in parallel. The disc spring assembly 23 is arranged in the cavity formed by the piston cylinder 16 and the piston rod 21, and is located at the end of the cavity away from the damper 19. When the ram air turbine device is close to the fully deployed state, the piston rod 21 and the piston cylinder 16 begin to squeeze the disc spring assembly 23. The disc spring assembly 23 deforms to absorb the load transmitted by the piston cylinder 16 and plays a buffering role.

[0016] Optionally, in the ram air turbine system described above, the upper lock and the lower lock are integrated into the pneumatic actuator 4;

[0017] When the upper lock 17 is in the locked position, it is used to lock the ram air turbine unit inside the engine room; when the lower lock 18 is in the locked position, it is used to lock the ram air turbine unit in the fully extended working position.

[0018] Alternatively, in the ram air turbine system described above,

[0019] The pneumatic actuator 4 has a built-in dual-redundant unlocking mechanism, including: a locking piston 20 and two deployable electromagnets 6 connected to the locking piston 20 respectively; when one of the electromagnets 6 is energized, it can pull the locking piston 20 to move and release the locking pin of the upper lock 17.

[0020] Optionally, the ram air turbine system described above also includes: an automatic release unit 9 connected to two deployment electromagnets 6 and a manual release button 10 respectively;

[0021] The automatic release unit 9 is used to perform logical judgment by collecting aircraft wheel signals, energy system signals, and airspeed signals to determine the timing of releasing the ram air turbine device; the three signals are AND gates, and when the triggering conditions are met simultaneously, the automatic release unit 9 sends a release command to the deployment electromagnet 6.

[0022] The manual release button 10 is designed in the cockpit and is manually triggered by the pilot or maintenance personnel. When triggered, it sends a working command to the deployment electromagnet 6.

[0023] Optionally, in the ram air turbine system described above, the tailstock 24 of the pneumatic actuator 4 is provided with an air hole connected to the inner cavity of the piston rod 21, and the air hole forms an air inlet 14 and an air outlet 15 through the recovery solenoid valve 5.

[0024] The air inlet 14 is connected to the quick-change interface 12 via a hose 13, and the exhaust port 15 is directly connected to the atmosphere. One half of the quick-change interface 12 is fixed to the aircraft structure and protected by a window cover, while the other half of the quick-change interface 12 is connected to the air source 11. When the ram air turbine is recovered on the ground, the window cover of the quick-change interface 12 of the aircraft is removed, and the air source 11 is connected to the air inlet 14.

[0025] Optionally, the ram air turbine system described above also includes: a recovery control switch 7 and a power supply 8;

[0026] The recovery solenoid valve 5 is integrated into the tailstock 24 of the pneumatic actuator cylinder 4. The recovery solenoid valve 5 is connected to the power supply 8 through the recovery control switch 7. The recovery solenoid valve 5 controls the opening and closing of the air intake passage between the inner cavity of the piston rod 21 and the air source 11 through the air inlet 14. The air intake passage is normally closed and is only opened when ground recovery is carried out and the recovery solenoid valve 5 is energized.

[0027] Optionally, in the ram air turbine system described above, the recovery control switch 7 is a push-button switch with a spring reset. When the switch is pressed, the circuit is connected, and when the switch is released, the circuit is automatically disconnected.

[0028] Beneficial effects of the present invention: The embodiments of the present invention provide a ram air turbine system, which has the following beneficial effects:

[0029] 1. In the ram air turbine system provided in this embodiment of the invention, a pneumatic retractable actuator is used, which can avoid the pollution problem of hydraulic actuators, and avoid the combustion and explosion problem caused by hydraulic leakage of hydraulic actuators; and avoid the problem that the hydraulic actuator deployment time is greatly affected by temperature, thereby improving the stability of system response time.

[0030] 2. In the ram air turbine system provided in this embodiment of the invention, a dual buffering method combining a damper and a disc assembly is adopted, which greatly absorbs the impact load, has a significant buffering effect, and improves reliability.

[0031] 3. In the ram air turbine system provided in this embodiment of the invention, the ram air turbine device uses the elastic force release of a compression spring, which does not rely on external energy sources of the aircraft, thus improving system reliability.

[0032] 4. In the ram air turbine system provided in this embodiment of the invention, a manual recovery control switch is used for recovery control, which improves maintenance safety;

[0033] 5. In the ram air turbine system provided in this embodiment of the invention, the upper lock, lower lock, recovery electromagnet, and deployment electromagnet are integrated into the retraction and extension actuator, which improves the system integration and reduces the system size and weight.

[0034] 6. The ram air turbine system provided in this embodiment of the invention consists of multiple replaceable field units, which can be replaced during field use and maintenance, thereby improving system maintainability. Attached Figure Description

[0035] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0036] Figure 1 This is a schematic diagram of the overall structure of a ram air turbine system provided in an embodiment of the present invention;

[0037] Figure 2 for Figure 1 The diagram shown illustrates the structure of the actuator cylinder upper lock in the ram air turbine system provided in the embodiment.

[0038] Figure 3 for Figure 1 The diagram shows a schematic representation of the actuator cylinder in the intermediate deployed state of the ram air turbine system provided in the embodiment shown.

[0039] Figure 4 for Figure 1 The diagram shown illustrates the structure of the actuator cylinder in the locked state of the ram air turbine system provided in the embodiment.

[0040] Figure 5 for Figure 1 The illustrated embodiment provides a schematic diagram of the actuator cylinder recovery solenoid valve in the energized state of the ram air turbine system.

[0041] Explanation of reference numerals in the attached figures:

[0042] 1-Turbine, 2-Energy conversion unit, 3-Support arm, 4-Actuator cylinder, 5-Recovery solenoid valve, 6-Deployment electromagnet, 7-Recovery control switch, 8-Power supply, 9-Automatic release unit, 10-Manual release button, 11-Air source, 12-Quick-change connector, 13-Hose, 14-Inlet, 15-Exhaust port, 16-Piston cylinder, 17-Upper position lock, 18-Lower position lock, 19-Damper, 20-Locking piston, 21-Piston rod, 22-Spring, 23-Disc spring assembly, 24-Tailstock. Detailed Implementation

[0043] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0044] As explained in the background section above, the retraction and extension of the ram air turbine device are achieved by a hydraulic actuator, and traditional ram air turbine systems suffer from problems such as pollution caused by easy oil leakage and unstable response time.

[0045] To address the aforementioned problems of traditional ram air turbine systems, this invention proposes a pollution-free ram air turbine system with relatively stable response time.

[0046] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0047] Figure 1 This is a schematic diagram of the overall structure of a ram air turbine system provided in an embodiment of the present invention. Figure 1 As shown, the main structure of the ram air turbine system provided in this embodiment of the invention includes: a turbine 1, an energy conversion unit 2, a support arm 3, an actuator 4, a recovery control switch 7, a quick-connect coupling 12, and a hose 13. The actuator 4 can be a pneumatic actuator 4. The turbine 1, energy conversion unit 2, and support arm 3 are sequentially connected to form a ram air turbine device, which rotates around the pivot of the support arm 3.

[0048] Figure 2 for Figure 1 The diagram shows the structure of the actuator cylinder upper lock in the ram air turbine system provided in the embodiment. Figure 3 for Figure 1 The illustrated embodiment provides a schematic diagram of the actuator cylinder in its intermediate deployed state within the ram air turbine system. Figure 4 for Figure 1 The illustrated embodiment provides a schematic diagram of the actuator cylinder in the locked state of the lower position lock in the ram air turbine system. Figure 5 for Figure 1 The illustrated embodiment provides a schematic diagram of the actuator cylinder recovery solenoid valve in the energized state of the ram air turbine system. The rod end A of the pneumatic actuator cylinder 4 is hinged to the support arm 3, and the tailstock end B is hinged to the fuselage. The control air passage inside the pneumatic actuator cylinder 4 forms an air inlet 14 and an exhaust port 15 via the recovery solenoid valve 5. The air inlet 14 is connected to the connecting hose 13, and the exhaust port 15 is open to the atmosphere.

[0049] Reference Figures 2 to 5 As shown, the structure of the actuator 4 in this embodiment of the invention may include: a recovery solenoid valve 5, a piston cylinder 16, an upper lock 17, a lower lock 18, a damper 19, a locking piston 20, a piston rod 21, a spring 22, a disc spring assembly 23, and a tailstock 24.

[0050] The actuator 4 has the following structure: the closed end of the piston cylinder 16 is the rod end A, and the piston cylinder 16 has an annular upper locking groove and a lower locking groove at both ends. The piston rod 21 and the locking piston 20 nested in the inner cavity of the piston rod 21 are nested in the inner cavity of the piston cylinder 16. The end of the piston rod 21 that extends out of the piston cylinder 16 is fixedly connected to the tail seat 24. The end of the locking piston 20 located in the piston cylinder 16 has an upper lock 17 and a lower lock 18 with a convex ring structure along the axial direction. The upper lock 17 and the lower lock 18 extend radially out of the piston rod 21. The upper lock 17 locks the retracted state by cooperating with the upper locking groove, and the lower lock 18 locks the unfolded state by cooperating with the lower locking groove. A disc spring assembly 23 is provided in the annular cavity formed by the piston rod 21 and the piston cylinder 16. An annular boss is provided on the outside of the piston cylinder 16. A spring 22 is installed between the annular boss and the end face of the tail seat 24.

[0051] Based on the structure of the ram air turbine system provided in the above embodiments of the present invention, the working principle of the ram air turbine system is as follows:

[0052] When used in the air, the ram air turbine is pushed out of the cabin by the elastic force of the compression spring 22 built into the actuator 4. During the push-out process, when the actuator 4 is close to being fully extended, the damper 19 and disc spring assembly 23 inside the actuator 4 absorb the system's impact load and reduce the structural impact force.

[0053] After the ram air turbine is fully extended into position, as Figure 3 As shown, turbine 1 rotates under the action of airflow, driving energy conversion unit 2 to generate emergency energy for the aircraft.

[0054] During ground recovery, the actuator 4 is connected to the air source 11 through the hose 13 and quick-change connector 12, which introduces high-pressure gas into the single piston rod cylinder inside the actuator 4, generating a recovery pull force to retract the ram air turbine device into the cabin.

[0055] In this embodiment of the invention, the damper 19 and the disc spring assembly 23 simultaneously function as a buffer, absorbing the load transmitted by the piston cylinder 16. Their characteristics are as follows:

[0056] a) The damper 19 is arranged at the tail end of the piston rod 21 (i.e., the end of the piston rod 21 close to the upper lock), along the axial direction of the piston rod 21. One end is connected to the inner cavity of the piston rod 21, and the other end is connected to the inner cavity of the piston cylinder 16. The inner cavity of the piston rod 21 is connected to the exhaust port 15 through the recovery solenoid valve 5, forming an exhaust passage from the inner cavity of the piston cylinder 16 through the damper (19) to the inner cavity of the piston rod 21, and then to the exhaust port 15. The exhaust passage is in a normally open state. When the pneumatic actuator 4 is extended to the piston cylinder 16 close to the tail end of the piston rod 21, the flow area of ​​the damper 19 gradually decreases, and the air in the inner cavity of the piston cylinder 16 is discharged from the remaining connected damper. During this process, the air volume is compressed, absorbing the load transmitted by the piston cylinder 16 and playing a buffering role.

[0057] b) The disc spring assembly 23 is composed of multiple disc springs connected in parallel. The disc spring assembly 23 is arranged in the cavity formed by the piston cylinder 16 and the piston rod 21, and is located at the end of the cavity away from the damper 19. When the ram air turbine device is close to the fully deployed state, the piston rod 21 and the piston cylinder 16 begin to squeeze the disc spring assembly 23. The disc spring assembly 23 deforms to absorb the load transmitted by the piston cylinder 16 and plays a buffering role.

[0058] The ram air turbine system provided in this embodiment of the invention integrates an upper lock and a lower lock within a pneumatic actuator 4; wherein, when the upper lock 17 is in the locked position, the ram air turbine device is locked inside the engine compartment, such as... Figure 2 As shown in the diagram; when the lower lock 18 is in the locked position, the ram air turbine device is locked in the fully extended working position, as shown. Figure 4 The state shown;

[0059] In the ram air turbine system provided in this embodiment of the invention, the actuator 4 has a built-in dual-redundant unlocking mechanism, including: a locking piston 20 and two deploying electromagnets 6 respectively connected to the locking piston 20; when either deploying electromagnet 6 is energized, it can pull the locking piston 20 to move and release the locking pin of the upper lock 17.

[0060] In one implementation provided by an embodiment of the present invention, such as Figure 1 As shown, the ram air turbine system also includes an automatic release unit 9 and a manual release button 10, which are respectively connected to two deployment electromagnets 6.

[0061] In this implementation, the automatic release unit 9 is used to perform logical judgments by collecting aircraft wheel signals, energy system signals, and airspeed signals to determine the timing for releasing the ram air turbine device. The three signals are connected in an AND gate relationship. When the triggering conditions are met simultaneously, the automatic release unit 9 sends a release command to the deployment electromagnet 6. The manual release button 10 is designed in the cockpit and is manually triggered by the pilot or maintenance personnel. When triggered, it sends a mode operation command to the deployment electromagnet 6.

[0062] In a specific implementation of this invention, the tailstock 24 of the pneumatic actuator 4 is provided with an air hole connected to the inner cavity of the piston rod 21. The air hole forms an air inlet 14 and an exhaust outlet 15 through the recovery solenoid valve 5. The air inlet 14 is connected to the quick-change interface 12 via a hose 13, and the exhaust outlet 15 is directly connected to the atmosphere. One half of the quick-change interface 12 is fixed to the aircraft structure and protected by a window cover. The other half of the quick-change interface 12 is connected to the air source 11. When the ram air turbine device is recovered on the ground, the window cover of the quick-change interface 12 of the aircraft is removed, and the air source 11 is connected to the air inlet 14.

[0063] Furthermore, such as Figure 1 As shown, the ram air turbine system provided in this embodiment of the invention further includes: a recovery control switch 7 and a power supply 8.

[0064] The recovery solenoid valve 5 is integrated on the tailstock 24 of the pneumatic actuator cylinder 4. The recovery solenoid valve 5 is connected to the power supply 8 through the recovery control switch 7. The recovery solenoid valve 5 controls the opening and closing of the air intake passage between the inner cavity of the piston rod 21 and the air source 11 through the air inlet 14. The air intake passage is normally closed and is only opened when ground recovery is carried out and the recovery solenoid valve 5 is energized.

[0065] In practical applications, the recycling control switch 7 is a push-button switch with spring reset. When the switch is pressed, the circuit is connected, and when the switch is released, the circuit is automatically disconnected.

[0066] The ram air turbine system provided in this embodiment of the invention has the following beneficial effects:

[0067] 1. In the ram air turbine system provided in this embodiment of the invention, a pneumatic retractable actuator is used, which can avoid the pollution problem of hydraulic actuators, and avoid the combustion and explosion problem caused by hydraulic leakage of hydraulic actuators; and avoid the problem that the hydraulic actuator deployment time is greatly affected by temperature, thereby improving the stability of system response time.

[0068] 2. In the ram air turbine system provided in this embodiment of the invention, a dual buffering method combining a damper and a disc assembly is adopted, which greatly absorbs the impact load, has a significant buffering effect, and improves reliability.

[0069] 3. In the ram air turbine system provided in this embodiment of the invention, the ram air turbine device uses the elastic force release of a compression spring, which does not rely on external energy sources of the aircraft, thus improving system reliability.

[0070] 4. In the ram air turbine system provided in this embodiment of the invention, a manual recovery control switch is used for recovery control, which improves maintenance safety;

[0071] 5. In the ram air turbine system provided in this embodiment of the invention, the upper lock, lower lock, recovery electromagnet, and deployment electromagnet are integrated into the retraction and extension actuator, which improves the system integration and reduces the system size and weight.

[0072] 6. The ram air turbine system provided in this embodiment of the invention consists of multiple replaceable field units, which can be replaced during field use and maintenance, thereby improving system maintainability.

[0073] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A ram air turbine system, characterized in that, include: Turbine (1), energy conversion unit (2), support arm (3), actuator cylinder, recovery control switch (7), quick-connect coupling (12), hose (13); Among them, the turbine (1), the energy conversion unit (2) and the support arm (3) are connected in sequence to form a ram air turbine device, and the ram air turbine device rotates around the pivot of the support arm (3); The actuator is configured as a pneumatic actuator; the rod end A of the pneumatic actuator (4) is hinged to the support arm (3), and the tailstock end B is hinged to the fuselage; the control air passage inside the actuator (4) forms an air inlet (14) and an exhaust port (15) through a recovery solenoid valve (5), the air inlet (14) is connected to the connecting hose (13), and the exhaust port (15) is connected to the atmosphere; The pneumatic actuator (4) includes: a recovery solenoid valve (5), a piston cylinder (16), an upper lock (17), a lower lock (18), a damper (19), a locking piston (20), a piston rod (21), a spring (22), a disc spring assembly (23), and a tailstock (24); The piston cylinder (16) has a closed end at rod end A, and the piston cylinder (16) has an annular upper locking groove and a lower locking groove at both ends. The piston rod (21) and the locking piston (20) nested in the inner cavity of the piston rod (21) are integrally nested in the inner cavity of the piston cylinder (16). The end of the piston rod (21) extending out of the piston cylinder (16) is fixedly connected to the tailstock (24). The end of the locking piston (20) located in the piston cylinder (16) has an upper locking (17) with a convex ring structure along the axial direction. The lower lock (18), upper lock (17) and lower lock (18) extend the piston rod (21) radially. The upper lock (17) locks the retracted state by cooperating with the upper lock groove, and the lower lock (18) locks the unfolded state by cooperating with the lower lock groove. A spring (22) and a disc spring assembly (23) are provided in the annular cavity formed by the piston rod (21) and the piston cylinder (16). An annular boss is provided on the outside of the piston cylinder (16), and a tail seat (24) is installed between the annular boss and the tail seat (24).

2. The ram air turbine system according to claim 1, characterized in that, The ram air turbine system is used in the air to push the ram air turbine device out of the cabin by the elastic force of the compression spring (22) built into the pneumatic actuator (4); it is also used in the process of pushing out the ram air turbine device to absorb the system impact load and reduce the structural impact force by using the damper (19) and disc spring group (23) in the cavity of the pneumatic actuator (4) when the pneumatic actuator (4) is close to the fully extended state; after the ram air turbine device is fully pushed out, the turbine (1) rotates under the action of airflow, drives the energy conversion unit (2) to work, and generates emergency energy for the aircraft; it is also used in the ground recovery process, the pneumatic actuator (4) is connected to the air source (11) through the hose (13) and quick-connect coupling (12), so that the single piston rod cylinder in the pneumatic actuator (4) introduces high pressure gas, generates recovery pull force, and pulls the ram air turbine device back into the cabin.

3. The ram air turbine system according to claim 1, characterized in that, The damper (19) and the disc spring assembly (23) work together to buffer the load transmitted by the piston cylinder (16). The characteristics of both are as follows: a) The damper (19) is arranged at the tail end of the piston rod (21) along the axial direction of the piston rod (21). One end is connected to the inner cavity of the piston rod (21), and the other end is connected to the inner cavity of the piston cylinder (16). The inner cavity of the piston rod (21) is connected to the exhaust port (15) through the recovery solenoid valve (5), forming an exhaust passage from the inner cavity of the piston cylinder (16) through the damper (19) to the inner cavity of the piston rod (21) and then to the exhaust port (15). The exhaust passage is in a normally open state. When the pneumatic actuator (4) is extended to the piston cylinder (16) and close to the tail end of the piston rod (21), the flow area of ​​the damper (19) gradually decreases. The air in the inner cavity of the piston cylinder (16) is discharged from the remaining connected damper. During this process, the air volume is compressed, absorbing the load transmitted by the piston cylinder (16) and playing a buffering role. b) The disc spring assembly (23) is composed of multiple disc springs connected in parallel. The disc spring assembly (23) is arranged in the cavity formed by the piston cylinder (16) and the piston rod (21), and is located at the end of the cavity away from the damper (19). When the ram air turbine device is close to the fully deployed state, the piston rod (21) and the piston cylinder (16) begin to squeeze the disc spring assembly (23). The disc spring assembly (23) deforms to absorb the load transmitted by the piston cylinder (16) and plays a buffering role.

4. The ram air turbine system according to claim 1, characterized in that, The upper lock and the lower lock are integrated in the pneumatic actuator (4); When the upper lock (17) is in the locked position, it is used to lock the ram air turbine device inside the engine room; when the lower lock (18) is in the locked position, it is used to lock the ram air turbine device in the fully extended working position.

5. The ram air turbine system according to claim 1, characterized in that, The pneumatic actuator (4) has a built-in dual-redundant unlocking mechanism, including: a locking piston (20) and two deployable electromagnets (6) respectively connected to the locking piston (20); when one of the electromagnets (6) is energized, it can pull the locking piston (20) to move and release the locking pin of the upper lock (17).

6. The ram air turbine system according to claim 5, characterized in that, Also includes: The automatic release unit (9) and the manual release button (10) are respectively connected to the two unfolding electromagnets (6); The automatic release unit (9) is used to make logical judgments by collecting aircraft wheel signals, energy system signals and airspeed signals to determine the timing of releasing the ram air turbine device; the three signals are AND gates, and when the triggering conditions are met at the same time, the automatic release unit (9) sends a release command to the deployment electromagnet (6); The manual release button (10) is designed to be located in the cockpit and is manually triggered by the pilot or maintenance personnel. When triggered, it sends a working command to the deployment electromagnet (6).

7. The ram air turbine system according to claim 1, characterized in that, The tailstock (24) of the pneumatic actuator (4) is provided with an air hole connected to the inner cavity of the piston rod (21). The air hole forms an air inlet (14) and an air outlet (15) through the recovery solenoid valve (5). The air inlet (14) is connected to the quick-connect interface (12) via a hose (13), and the exhaust port (15) is directly connected to the atmosphere. One half of the quick-connect interface (12) is fixed to the aircraft structure and protected by a window cover. The other half of the quick-connect interface (12) is connected to the air source (11). When the ram air turbine is recovered on the ground, the window cover of the quick-connect interface (12) of the aircraft is removed, and the air source (11) is connected to the air inlet (14).

8. The ram air turbine system according to claim 7, characterized in that, Also includes: Recycle control switch (7) and power supply (8); The recovery solenoid valve (5) is integrated into the tailstock (24) of the pneumatic actuator (4). The recovery solenoid valve (5) is connected to the power supply (8) through the recovery control switch (7). The recovery solenoid valve (5) controls the opening and closing of the air intake passage between the inner cavity of the piston rod (21) and the air source (11) through the air inlet (14). The air intake passage is normally closed. It is only opened when the ground is being recovered and the recovery solenoid valve (5) is energized.

9. The ram air turbine system according to claim 1, characterized in that, The recycling control switch (7) is a push-button switch with spring reset. When the switch is pressed, the circuit is connected, and when the switch is released, the circuit is automatically disconnected.

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