Ram air turbine system release device and ram air turbine system

Abstract

The present invention relates to a ram air turbine system release device, comprising: a ram air turbine bearing shaft, a ram air turbine is fixed to the first end of the ram air turbine bearing shaft, and the second end of the ram air turbine bearing shaft is pivotally attached to the fuselage of the aircraft, wherein the ram air turbine bearing shaft can pivot around the pivot; and a first connecting rod, a first end of the first connecting rod is pivotally attached to the ram air turbine bearing shaft, and the second end of the first connecting rod is pivotally attached to the cabin door, wherein the first connecting rod is a telescopic connecting rod, and can be retracted to facilitate the closure of the cabin door, and can be extended to facilitate the opening of the cabin door. The device achieves a good balance between increasing the force acting on the cabin door and increasing the opening angle of the cabin door. In addition, the present invention also relates to a ram air turbine system.

Description

Technical Field

[0001] The present invention relates to a ram air turbine system release device. In addition, the present invention also relates to a ram air turbine system comprising the ram air turbine system release device. Background Art

[0002] In the design process of the ram air turbine (RAT) system of civil aircraft, there are many factors affecting the release of the RAT system, among which the connection position of the door link is the main factor. The door link acts as an intermediate hub to transmit the actuator's operating force (such as elastic force) to the door to push the RAT out. Under emergency conditions, the release time of the RAT system determines the power supply interval from the failure of all engines of the aircraft (i.e., failure of both engines) and the failure of the backup power supply to the re-powering of the emergency power generation system. The RAT starts to rotate after being released to a certain angle. The design of the door link largely determines the RAT release time and release safety (whether the RAT interferes with adjacent components during operation). In the early design process, if the structure and position of each part are uncertain, it is easy to cause the RAT release time to be too long or there is interference error in the later stage, resulting in frequent rework of the system or cutting of blades. Changes to the system (such as blades) will lead to changes in the center of gravity in the later stage, which will lead to strength problems, and then lead to huge change costs and may delay the delivery of the aircraft.

[0003] Based on previous engineering experience, the RAT system release process has a great impact on aircraft safety, and the door linkage design is also related to the release time and release safety distance (interference).

[0004] Figure 1 FIG. 4 shows a recovery state of a ram air turbine system release device 100 of the prior art. Figure 2 The figure shows the kinematic mechanics analysis of the door release of the ram air turbine system. As shown in the figure, the F2a / F2b direction is the door connecting rod direction. In the structure of the prior art, since the connecting rod 30 is relatively long, and when the RAT is in the recovery position, the door 300 is already closed at this time, the distance between the door connecting rod 30 and the door 300 at the RAT cabin installation point is too short, resulting in a large axial installation angle between the RAT door connecting rod 30 and the RAT door 300. Too large an angle will cause the effective force on the RAT door to be too small when it is opened, and most of the force is used to squeeze the door 300 with the door frame in the horizontal direction, which in turn causes stress deformation of the door 300, and is not used to open the door 300, resulting in a prolonged opening time of the RAT door.

[0005] If you follow directly Figure 2The door connecting rod is installed in the direction shown by F3 in FIG. 1 . At this time, compared with the above-described situation, the angle between the axial direction of the RAT door connecting rod and the normal direction of the RAT door 300 is reduced, thereby increasing the effective force component of the RAT door 300 and making it easier (and faster) to release the RAT. However, this structure has a too small opening angle of the door 300 after release, which easily causes the swept surface of the RAT blade to interfere with the door 300 after it starts to rotate.

[0006] In addition, if the structure and position of the door link 30 are uncertain during the early design process, it is easy to cause interference errors or long release time in the later stage, which may lead to the risk of hydraulic system pressure cut-off under severe working conditions (extreme cold) and aircraft loss of control. The system will be frequently reworked, and changes to the system (such as blades) will lead to changes in the center of gravity in the later stage, which will lead to huge change costs. There is currently no good way to avoid this problem.

[0007] Therefore, there is an urgent need to provide an improved ram air turbine system release device, which can overcome one or more disadvantages existing in the prior art. Summary of the invention

[0008] The purpose of the present invention is to provide a ram air turbine system release device applicable to a ram air turbine (hereinafter referred to as RAT) system. The release speed of the RAT system is related to the door opening speed. The faster the RAT door opens, the shorter the release time is. The interference position of the RAT system can be determined by a model, thereby reducing the probability of interference in the RAT system and improving the safety of the system. In combination with the above description, this paper proposes a RAT release device, which can be used to optimize the release time of the RAT system and avoid interference problems, and can improve the economy and safety of the RAT system of civil aircraft.

[0009] According to one aspect of the present invention, a ram air turbine system release device is provided, which may include:

[0010] a ram air turbine carrier shaft having a ram air turbine fixed to a first end thereof and a ram air turbine being pivotally attached to a fuselage of the aircraft at a second end thereof, wherein the ram air turbine carrier shaft is pivotable about a pivot axis; and

[0011] a first link, a first end of the first link being pivotally attached to the ram air turbine carrier shaft and a second end of the first link being pivotally attached to the door, such that pivoting of the ram air turbine carrier shaft opens or closes the door via the first link,

[0012] The first connecting rod is a retractable connecting rod, which can be retracted to facilitate the closing of the hatch, and can be extended to facilitate the opening of the hatch.

[0013] The ram air turbine system release device of the present invention further reduces the RAT release time and increases the door opening angle by mainly improving the door link during the RAT release process, and achieves a good balance between increasing the force on the door and increasing the door opening angle. The design of the retractable link shortens the release time and ensures that the RAT door is opened to a sufficient angle.

[0014] The design of the retractable rod form of the door link and its design that can be retracted to achieve a smaller installation angle can reduce the direct release time of the RAT to a certain extent. Under non-harsh working conditions, this solution can increase the safety margin of RAT release. Under harsh working conditions of the aircraft envelope (high altitude, low speed, low temperature, etc.), when the aircraft's dual engines and backup power supply fail, this technical solution can restore power and pressure to the aircraft more quickly, ensure the stability of aircraft operation and improve aircraft safety.

[0015] According to the above aspects of the present invention, preferably, the connection between the first connecting rod and the hatch can be arranged to ensure that the hatch is opened at a sufficient angle when the first connecting rod is fully extended, for example, the opening angle is greater than 90 degrees, and preferably greater than 110 degrees (for example, about 120 degrees, etc.), thereby ensuring that the RAT blades will not interfere with the hatch when they start to rotate, and ensuring that the RAT can generate electricity normally.

[0016] According to the above aspect of the present invention, preferably, the ram air turbine system release device may further include a second link, a first end of the second link is pivotally attached to the ram air turbine bearing shaft, and a second end of the second link is pivotally attached to the cabin door.

[0017] This double-link mode can increase the safety margin in the event of mechanical failure, while the design of the retractable link makes the release time shorter. In addition, by properly selecting the cross-sectional shape and size of the two links, it can be ensured that the overall weight of the system will not be significantly increased.

[0018] According to the above aspect of the present invention, preferably, the second end of the first link and the second end of the second link may be attached to the door at a side away from the rotation axis of the door.

[0019] Through this arrangement, the torque for opening the hatch can be further increased, so that the hatch can be opened faster under the same actuating force.

[0020] According to the above aspect of the present invention, preferably, the second end of the first link and the second end of the second link may be spaced apart from each other, while the first end of the first link and the first end of the second link are close to each other.

[0021] According to the above aspect of the present invention, preferably, the first end of the first link and the first end of the second link may be arranged close to an end of the ram air turbine carrying shaft away from the pivot axis.

[0022] This arrangement makes it possible to achieve a greater opening angle of the door by means of the length and pivoting of the ram air turbine bearing shaft.

[0023] According to the above aspect of the present invention, preferably, at least one pivot mounting portion may be provided on at least one of the ram air turbine bearing shaft and the cabin door, the pivot mounting portion being provided with a socket, and the corresponding ends of the first link and / or the second link being provided with a spherical joint, the spherical joint being arranged in the socket and freely rotating. For example,

[0024] The pivot mounting portion can ensure a rotation margin within a certain spatial angle, and the rotatable characteristic of the sphere can be utilized to meet the rotation angle requirement.

[0025] According to the above aspects of the present invention, preferably, the first connecting rod may include a first rod body and a second rod body, the first rod body includes a cylinder body, and the second rod body includes a piston and a piston rod connected to the piston, wherein the piston can move under force to achieve contraction or extension of the first connecting rod.

[0026] Through this arrangement, the contraction or extension of the first connecting rod can be reliably achieved, and automatic control can be realized.

[0027] According to the above aspects of the present invention, preferably, the ram air turbine system release device may further include an actuating mechanism, which is retractable and can be connected to the ram air turbine bearing shaft for releasing or retracting the ram air turbine. Preferably, the actuating mechanism may include, for example, an actuating cylinder, a linear spring, or a conical spring.

[0028] According to another aspect of the present invention, a ram air turbine system is proposed. The ram air turbine system may include the ram air turbine system release device of the above aspect, and a ram air turbine. The ram air turbine may be fixed to the ram air turbine bearing shaft at the end of the ram air turbine bearing shaft away from the pivot, so that the ram air turbine can generate electricity through the ram air turbine under emergency working conditions to provide emergency energy for the aircraft.

[0029] Therefore, the ram air turbine system release device of the present invention can meet the use requirements, overcome the shortcomings of the prior art and achieve the predetermined purpose. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to further clearly describe the ram air turbine system release device according to the present invention, the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. In the accompanying drawings:

[0031] Figure 1 A schematic diagram showing a retracted state of a ram air turbine system release device of the prior art;

[0032] Figure 2 A schematic diagram showing the kinematics analysis of the ram air turbine system release hatch;

[0033] Figure 3 is a schematic diagram of a ram air turbine system release device according to a non-limiting embodiment of the present invention, wherein the ram air turbine system release device is in a retracted state;

[0034] Figure 4 is a schematic diagram of a ram air turbine system release device according to a non-limiting embodiment of the present invention, wherein the ram air turbine system release device is in a released state;

[0035] Figure 5 is a schematic diagram of a first link of a ram air turbine system release device according to a non-limiting embodiment of the present invention, wherein the first link is in a compressed state;

[0036] Figure 6 is a schematic diagram of a first link of a ram air turbine system release device according to a non-limiting embodiment of the present invention, wherein the first link is in an extended state; and

[0037] Figure 7 It is a schematic diagram of the installation of the pivotal mounting portion on the cabin door and an enlarged diagram of the structure according to a non-limiting embodiment of the present invention.

[0038] The above drawings are merely schematic and are not drawn strictly to scale.

[0039] List of reference numerals in the figures and embodiments:

[0040] 100 - Ram air turbine system release device, including:

[0041] 10- Ram air turbine bearing shaft, including:

[0042] 10A-pivot;

[0043] 11- first end;

[0044] 12- second end;

[0045] 20-First connecting rod, including:

[0046] 21 - first end;

[0047] 22- second end;

[0048] 23- first rod body;

[0049] 23A-cylinder body;

[0050] 24- The second rod body comprises:

[0051] 24A-piston;

[0052] 24B-piston rod;

[0053] 30-Second connecting rod, including:

[0054] 31 - first end;

[0055] 32 - second end;

[0056] 40- Pivot mounting portion, comprising:

[0057] 41- socket;

[0058] 42-ball joint;

[0059] 50-actuating mechanism;

[0060] 200 - Ram air turbine;

[0061] 300-Hatch door, including:

[0062] 301- shaft. DETAILED DESCRIPTION

[0063] It should be understood that, unless expressly stated otherwise, the present invention may adopt various alternative orientations and step sequences. It should also be understood that the specific devices shown in the drawings and described in the specification are merely exemplary embodiments of the inventive concepts disclosed and defined herein. Therefore, unless otherwise expressly stated, the specific orientations, directions or other physical characteristics of the various embodiments disclosed should not be considered as limiting.

[0064] The Ram Air Turbine (RAT) is an emergency turbine generator set used by an aircraft when the dual generators fail. It is driven by the aerodynamic force generated by the flow field when the aircraft is in flight and supplies power to the aircraft's important loads.

[0065] The RAT system uses the aircraft's aerodynamic energy to work. In emergency conditions, a ram air turbine is released from the aircraft. The ram air turbine uses rapid air flow to drive the turbine blades. The turbine is connected to a generator through a gearbox, thereby providing power to the aircraft's important loads.

[0066] The RAT system is arranged in a non-airtight cabin. In order to obtain better aerodynamic load and release angle, the RAT system of large civil aircraft is usually arranged in an area with good aerodynamic performance. Its specific layout location requires weighing multiple factors such as blade size and layout space to ultimately come up with the optimal solution.

[0067] The ram air turbine system may generally include a ram air turbine system release device and a ram air turbine, a ram air turbine generator controller, and a recovery control device. The ram air turbine system release device is used to release the ram air turbine in an emergency, and at the same time, the cabin door is opened with the help of the cabin door linkage, and the RAT is released into the airflow to provide electrical energy in an emergency and ensure the normal operation of important loads on the aircraft. The key performance indicators of the ram air turbine system release device involve the release time of the RAT and the cabin door deployment angle at which the rotation of the RAT blades will not be interfered.

[0068] As used herein, the term "cabin door" refers to a door used to enclose a RAT in a RAT compartment (i.e., a RAT accommodation compartment). Therefore, when releasing the RAT, the door needs to be opened first to allow the RAT to come out of the RAT compartment, and when stowing the RAT, the door needs to be closed to enclose the RAT in the RAT compartment, thereby ensuring flight safety and reducing the aerodynamic drag of the aircraft.

[0069] Figure 1 FIG. 4 is a schematic diagram showing a retracted state of a ram air turbine system release device 100 in the prior art.

[0070] As described in the background technology section of the present application, in the prior art structure, the setting of the connecting rod 30 cannot balance the two requirements of quickly opening the RAT door 300 and opening the door 300 at a sufficiently large angle to avoid the problem of interference between the RAT blade and the door 300.

[0071] Figure 2 The mechanics analysis of the ram air turbine system release hatch is shown in Figure 2, where for simplification, Figure 2 Two different installation positions of the connecting rod 30 are shown in FIG. Figure 2 As shown, during the opening of the hatch 300, the force condition when the connecting rod 30 is only installed at the right side of the hatch 300 can be expressed by the following equation:

[0072]

[0073] Where G is gravity, the angle between the direction of action and the vertical line of the hatch surface is μ, and the distance from the hatch rotation axis is L l , F t is the aerodynamic load, and other parameters are independent of the door linkage. The force related to the door linkage is F 2a cos(β), F 2a is the force transmitted to the door by the RAT system, and β is the angle between the door connecting rod direction and the door vertical direction. The moment received by the door 300 is the left part of the equation. From the above analysis, it can be concluded that the smaller the angle β is, the greater the moment received by the door 300 is. doorWhen the force remains constant, the greater the angular acceleration, the faster the hatch opens.

[0074] In addition, since the hatch 300 is opened by means of the connecting rod 30, the greater the length of the connecting rod 30, the greater the angle at which the hatch 300 can be opened.

[0075] To this end, the present invention proposes a ram air turbine system release device 100 , which can increase the opening angle of the door 300 while meeting the opening speed requirement of the door 300 .

[0076] Figure 3 is a schematic diagram of a ram air turbine system release device 100 according to a non-limiting embodiment of the present invention, wherein the ram air turbine system release device 100 is in a retracted state; and Figure 4 is a schematic diagram of a ram air turbine system release device 100 according to a non-limiting embodiment of the present invention, wherein the ram air turbine system release device 100 is in a released state.

[0077] As shown and as a non-limiting example, the ram air turbine system release device 100 may mainly include a ram air turbine carrier shaft 10 and a first link 20 .

[0078] The ram air turbine carrier shaft 10 may have a first end 11 and a second end 12. The first end 11 of the ram air turbine carrier shaft may be fixed with the ram air turbine 200, and the second end 12 of the ram air turbine carrier shaft may be pivotally attached to the fuselage of the aircraft. For example, the second end 12 of the ram air turbine carrier shaft 10 is pivotally fixed to the fuselage and can pivot about the pivot axis 10A.

[0079] The structure and working principle of the ram air turbine bearing shaft 10 are known in the art, and thus the present invention will not describe them in detail.

[0080] The release speed of the RAT system is related to the door opening speed. The faster the RAT door opens, the shorter the release time. The interference position of the RAT system can be determined through the force analysis model, thereby reducing the probability of interference in the RAT system and improving system safety.

[0081] In combination with the above description, the inventor of the present invention analyzes the stress of the connecting rod 30 during the opening of the hatch 300. Based on the stress analysis, the inventor finds that the smaller the angle β between the hatch connecting rod and the hatch vertical angle is, the faster the hatch opens. However, after the RAT is released, the hatch 300 opens at a too small angle, which easily causes the swept surface of the RAT blade to interfere with the hatch 300 after it starts to rotate. Therefore, the inventor designs a retractable connecting rod mechanism, namely the first connecting rod 20 shown in the drawings, and adopts this retractable connecting rod in the ram air turbine system release device 100 to obtain the desired performance.

[0082] pass Figure 3 and Figure 4 It can be seen from the comparison that when the hatch 300 is closed, the first link 20 is in a retracted state, and when the hatch 300 is opened, the first link 20 is in an extended state. At this time, due to the existence of the non-retractable second link 30, the hatch 300 has a larger deployment angle when it is opened, and the retractable first link 20 can be extended to adapt to the opening or deployment angle of the hatch 300.

[0083] Figure 5 is a schematic diagram of a first link 20 of a ram air turbine system release device 100 according to a non-limiting embodiment of the present invention, wherein the first link 20 is in a compressed state; and Figure 6 is a schematic diagram of a first link 20 of a ram air turbine system release device 100 according to a non-limiting embodiment of the present invention, wherein the first link 20 is in an extended state.

[0084] like Figure 3-6 As shown and as a non-limiting example, a first end 21 of the first link 20 may be pivotally attached to the ram air turbine carrier shaft 10 , while a second end 22 of the first link 20 may be pivotally attached to the door 300 .

[0085] The ram air turbine system release device 100 may include an actuation mechanism 50 (see Figure 3 ), the actuating mechanism 50 is connected to the ram air turbine carrier shaft 10, for example, pivotally connected between the fuselage and the ram air turbine carrier shaft 10, for releasing (for example, quickly releasing) or retracting the ram air turbine 200. The actuating mechanism 50 may include, for example, a retractable actuating cylinder, such as a hydraulic cylinder / pneumatic cylinder, one or more linear springs and conical springs (such as mechanical springs, pneumatic springs, etc.), etc. The structure of the actuating mechanism 50 and its connection relationship with the ram air turbine carrier shaft 10 are known in the art, and therefore will not be described in detail herein.

[0086] The actuating mechanism 50 can actuate the ram air turbine carrier shaft 10 so that it can pivot about the pivot axis 10A, such as Figure 3 and 4In this process, the first connecting rod 20 can also be pushed and moved by the ram air turbine bearing shaft 10, thereby pushing the cabin door 300 to open.

[0087] Preferably, the installation position of the first link 20 on the ram air turbine bearing shaft 10 and the door 300 can be adjusted, and the length of the first link 20 is selected so that when the first link 20 is fully extended, the door 300 is opened at an angle greater than 90 degrees. That is, from the door 300 being fully closed to the door 300 being fully opened, the door 300 pivots around the rotation axis 301 at an angle greater than 90 degrees. And more preferably, the door 300 is opened at an angle greater than 120 degrees to ensure that the blades of the RAT do not interfere with adjacent structural components. In other embodiments, the door 300 can be opened at a larger or smaller angle.

[0088] like Figure 5 and 6 As shown in detail in FIG. 1 , the first connecting rod 20 is in the form of a segment of a telescopic rod and may include a first rod body 23 and a second rod body 24. The first rod body 23 may include a cylinder body 23A, and the second rod body 24 may include a piston 24A and a piston rod 24B connected to the piston. The piston 24A may be fitted in the cylinder body 23A to achieve the contraction or extension of the first connecting rod 20. Preferably, in order to reduce the resistance during the contraction or extension process, the piston 24A may be provided with a vent (not shown).

[0089] Return to reference Figure 3 and Figure 4 As shown in the figure, the ram air turbine system release device 100 according to the present invention may further include a second link 30. The second link 30 may have the same structure and arrangement as the link in the prior art. For example, the first end 31 of the second link 30 may be pivotally attached to the ram air turbine bearing shaft 10, and the second end 32 of the second link 30 may be pivotally attached to the cabin door 300.

[0090] As is known, the cross-sectional area of ​​the door link (e.g., the first link 20 and the second link 30) determines the strength of the link. In the present application, the two links in the non-limiting example of the present application can be distributed according to the force ratio based on the cross-sectional area of ​​the cylindrical link used in the prior art, that is, the sum of the cross-sectional areas of the first link 20 and the second link 30 is approximately equal to the cross-sectional area of ​​a single link in the prior art. Therefore, the total weight of the door link including two links according to the non-limiting embodiment of the present invention is almost not increased. In addition, preferably, the second link 30 can be a solid link, such as a cylindrical solid link with a circular cross-section.

[0091] As shown in the drawings, the second end 22 of the first link 20 and the second end 32 of the second link may be attached to the hatch 300 at a side away from the rotation shaft 301 of the hatch 300 .

[0092] Preferably, the second end 22 of the first link 20 and the second end 32 of the second link 30 are spaced apart from each other, while the first end 21 of the first link 20 and the first end 31 of the second link 30 are close to each other. In an embodiment not shown, the first end 21 of the first link 20 and the first end 31 of the second link 30 may be stacked together, for example, pivotally coupled to the end of the ram air turbine carrier shaft 10 by means of the same pivot axis.

[0093] As a preferred embodiment, the first end 21 of the first link 20 and the first end 31 of the second link 30 may be arranged close to the end of the ram air turbine carrier shaft 10 away from the pivot axis 10A, that is, close to the second end 12 of the ram air turbine carrier shaft 10 .

[0094] exist Figure 3 and 4 In the example shown, at the beginning of the release of the hatch 300, the first link 20 bears most of the RAT cabin's push-opening pressure, and the angle β between the axial direction of the first link 20 and the normal direction of the hatch 300 is smaller, so under the same actuating force input, the hatch 300 obtains a greater effective thrust, and thus the hatch 300 opens faster. In addition, the double-rod mode including the first link 20 and the second link 30 can increase the safety margin of the hatch door link, and the design of the second link 30 with a relatively long rod length can further ensure that the hatch 300 is opened at a sufficiently large angle during the RAT release process.

[0095] During the opening stage of the door 300 (the first connecting rod 20 is in a compressed state), the first connecting rod 20 bears most of the force, so the door 300 is released faster. When the RAT release is nearly finished, under the action of the pulling force, the second rod 24 of the first connecting rod 20 moves away from the first rod 23, so that the first connecting rod 20 is in an extended state, and the connecting rod is extended to ensure that the RAT door is opened at a sufficient angle, thereby ensuring that there is no interference when the RAT blades start to rotate. Preferably, a buffer pad can be provided at one or both ends of the piston 24A of the second rod 24 to reduce the impact during the extension process.

[0096] Figure 7 is a schematic diagram of the installation of the pivoting mounting portion 40 on the cabin door 300 and an enlarged structural diagram according to a non-limiting embodiment of the present invention, wherein: Figure 7 The illustration on the right side of the figure is an enlarged view of the portion in the dotted circle in the illustration on the left side.

[0097] As shown in the figure, the pivot mounting portion 40 may be provided on at least one of the ram air turbine carrier shaft 10 and the cabin door 300 , and preferably, all connection portions / mounting points between the first link 20 and the second link 30 and the ram air turbine carrier shaft 10 and the cabin door 300 are provided with such a pivot mounting portion 40 .

[0098] As an example, the pivoting mounting portion 40 may be a mechanism that allows spatial angle rotation, and may be provided with a socket 41, and the corresponding ends of the first link 20 and / or the second link 30 (e.g., the corresponding first end and second end thereof) may be provided with a ball joint 42, and the ball joint 42 is matched and arranged in the socket 41 to achieve free rotation at a large angle. In this way, the rotation angle requirement is met by designing a pivoting mounting portion with a rotation margin within a certain spatial angle and utilizing the rotatable characteristics of the sphere.

[0099] As used herein, the terms "side", "end" and "first", "second" and the like, which indicate the position or orientation, and the terms "first", "second" and the like, which indicate the order, are intended only to enable those skilled in the art to better understand the concept of the present invention as shown in the form of a preferred embodiment, and are not intended to limit the present invention. Unless otherwise specified, all orders, positions or orientations are only used for the purpose of distinguishing one element / component / structure from another element / component / structure, and do not represent any particular order, sequence of operations, direction or orientation unless otherwise specified. For example, in alternative embodiments, the "first connecting rod" may be the "second connecting rod", and the "first rod body" may alternatively refer to the "second rod body".

[0100] The technical solution of the present invention further reduces the RAT release time by improving the door connecting rod during the RAT release process. The double-rod mode can increase the safety margin of mechanical failure, and the design of the retractable / variable connecting rod can shorten the release time. This method can streamline the design cost, simplify the test or assembly steps, and effectively save manpower and material costs.

[0101] The beneficial technical effects of the present application may include but are not limited to the following aspects:

[0102] First, the retractable or slidable rod design of the door link and its smaller installation angle design further reduce the RAT direct release time.

[0103] This can be obtained from Figure 2 The force analysis of the hatch connecting rod can be concluded.

[0104] Secondly, the existence of the dual-link mode further improves the safety margin or redundancy when the hatch is released.

[0105] Compared with the single door connecting rod design in the prior art, the double rod structure of the present application has certain backup characteristics in terms of system margin or redundancy. The device can improve the economy and safety of the RAT system of civil aircraft.

[0106] In summary, the ram air turbine system release device 100 according to the embodiment of the present invention overcomes the shortcomings of the prior art and achieves the intended purpose of the invention.

[0107] Although the ram air turbine system release device of the present invention is described above in conjunction with the preferred embodiments, those skilled in the art should recognize that the above examples are only for illustration and cannot be used as limitations of the present invention. Therefore, various modifications and variations can be made to the present invention within the spirit of the claims, and these modifications and variations will fall within the scope of the claims of the present invention.

Claims

1. A ram air turbine system release device (100), the ram air turbine system release device include: A ram air turbine carrier shaft (10), a first end (11) of the ram air turbine carrier shaft having a ram air turbine (200) fixed thereto and a second end (12) of the ram air turbine carrier shaft being pivotally attached to a fuselage of an aircraft, wherein the ram air turbine carrier shaft (10) is pivotable about a pivot axis (10A); and a first link (20), a first end (21) of the first link being pivotally attached to the ram air turbine carrier shaft (10), and a second end (22) of the first link being pivotally attached to a door (300), The first connecting rod (20) is a retractable connecting rod, and is capable of contracting to facilitate closing of the hatch (300), and is capable of extending to facilitate opening of the hatch (300).

2. The ram air turbine system release device (100) according to claim 1, It is characterized in that The connection between the first connecting rod (20) and the cabin door (300) is arranged so that when the first connecting rod (20) is fully extended, the cabin door (300) is opened at an angle greater than 110 degrees.

3. The ram air turbine system release device (100) according to claim 1, It is characterized in that Also included is a second link (30), a first end (31) of the second link being pivotally attached to the ram air turbine bearing shaft (10), and a second end (32) of the second link being pivotally attached to the door (300).

4. The ram air turbine system release device (100) according to claim 3, It is characterized in that The second end (22) of the first link (20) and the second end (32) of the second link are attached to the hatch (300) at a side away from a rotation axis (301) of the hatch (300).

5. The ram air turbine system release device (100) according to claim 4, It is characterized in that The second end (22) of the first link (20) and the second end (32) of the second link (30) are spaced apart from each other, while the first end (21) of the first link (20) and the first end (31) of the second link (30) are close to each other.

6. The ram air turbine system release device (100) according to claim 4, It is characterized in that The first end (21) of the first connecting rod (20) and the first end (31) of the second connecting rod (30) are arranged close to the end of the ram air turbine bearing shaft (10) away from the pivot shaft (10A).

7. The ram air turbine system release device (100) according to claim 3, It is characterized in that At least one pivot mounting portion (40) is provided on at least one of the ram air turbine bearing shaft (10) and the cabin door (300), and the pivot mounting portion is provided with a socket (41), and the corresponding ends of the first connecting rod (20) and / or the second connecting rod (30) are provided with a spherical joint (42), and the spherical joint (42) is arranged in the socket (41) to rotate freely.

8. The ram air turbine system release device (100) according to any one of claims 1 to 7, It is characterized in that The first connecting rod (20) includes a first rod body (23) and a second rod body (24), wherein the first rod body includes a cylinder body (23A), and the second rod body (24) includes a piston (24A) and a piston rod (24B) connected to the piston, so as to realize the contraction or extension of the first connecting rod (20).

9. The ram air turbine system release device (100) according to any one of claims 1 to 7, It is characterized in that Also included is an actuating mechanism (50) which is retractable and coupled to the ram air turbine bearing shaft (10) for releasing or retracting the ram air turbine (200).

10. A ram air turbine system, comprising a ram air turbine system release device (100) according to any one of claims 1 to 9, and a ram air turbine (200) fixed to the ram air turbine carrier shaft (10) at an end of the ram air turbine carrier shaft (10) remote from the pivot shaft (10A).

Images