A force measuring device for an aircraft straight elevator

Abstract

The utility model discloses a kind of force measuring devices for aircraft linear rudder engine, belong to aviation airborne technical field.By connecting one end of force sensor with on-board structure, the other end is rigidly fixed with linear rudder, both ensure that force measuring elastomer can accurately perceive push-pull force when rudder engine actuates, additional stress generated due to rudder movement is avoided in connecting part, and the stability of measurement reference is ensured.The oblique through hole, the first straight through hole and the second straight through plate formed in force measuring elastomer inside form interconnected signal line channel, cooperate with the sealing cover of top, both protect cable from vibration, impact, acceleration wear, and can also shield external electromagnetic interference, ensure voltage signal stable transmission.Signal amplifier is arranged on the side of force measuring elastomer, and force measuring elastomer is integrated, and signal transmission distance is shortened.The utility model solves the problem that existing aircraft linear rudder cannot detect force value state, and early warning fault is difficult, and flight safety of aircraft is significantly improved.

Description

Technical Field

[0001] This utility model belongs to the field of airborne technology, specifically relating to a force measuring device for an aircraft linear servo. Background Technology

[0002] In aviation flight control systems, linear servos are widely used as core actuating elements in aerodynamic surface control mechanisms such as flaps, spoilers, and ailerons. These servos adjust flight attitude and aerodynamic characteristics through precise linear reciprocating motion. These servos need to operate continuously under complex conditions, withstanding environmental loads such as high-frequency vibration, impact, acceleration, and sudden temperature changes, while also meeting millisecond-level response speed requirements. However, in actual use, linear servos often experience abnormal operating conditions due to factors such as mechanical wear, hydraulic system leaks, or control algorithm deviations. When the actual force is lower than the theoretical displacement value, the aerodynamic surface may fail to reach the expected adjustment angle, leading to loss of flight attitude control. Conversely, when the actual force is higher than the theoretical displacement value, or even when the servo output force exceeds the load limits of the onboard connecting structures, it can cause structural cracking, transmission rod deformation, and other damage, seriously threatening flight safety.

[0003] In existing technologies, force measurement of linear servos is mainly achieved through ground-based force-measuring fixtures. These fixtures are typically installed in series with the servo via flanges or bolts, and are only used to simulate and evaluate whether the output force and strength of the linear servo meet design requirements; they cannot be installed on the actual aircraft. Furthermore, traditional force-measuring devices usually employ a split design, with the force sensor installed in the force transmission system and the signal amplifier fixed in a nearby spare location, connected by cables. This design not only increases system weight but also results in a longer transmission path for the force signal, requiring multiple cable transfers. Microvolt-level strain signals are prone to signal distortion and data fluctuations during transmission, especially under high-frequency vibration, impact, and acceleration conditions, or in complex electromagnetic environments on board (such as those radiated by radar and communication equipment).

[0004] These technical bottlenecks make it difficult for flight control systems to achieve precise closed-loop control of force and displacement. Especially under extreme conditions, structural overload accidents caused by the lack of effective output force monitoring occur frequently. Such failures often pose a great risk to flight safety and prevent flight missions from being completed as expected. Summary of the Invention

[0005] The purpose of this invention is to overcome the problems of existing technologies, such as the inability to monitor force values ​​and provide early warnings of malfunctions due to the lack of force feedback signals in aircraft linear servos, as well as the complex separate installation, easy signal interference, and delayed response of traditional force measuring devices. This invention provides a force measuring device for aircraft linear servos, which significantly improves the flight safety of aircraft.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: This utility model provides a force measuring device for an aircraft linear servo, including a force sensor and a signal amplifier. The force sensor includes a force measuring elastomer, a wire guard plate and a sealing cover. One end of the force measuring elastomer is rotatably connected to the aircraft connection structure and the other end is fixedly connected to the linear servo. The force-measuring elastomer has a circular plate structure in the middle, and a cross beam is set inside the circular plate structure. A resistance strain gauge is set above the cross beam, and a sealing cover is set above the circular plate structure. The force-measuring elastomer has a continuously penetrating oblique through hole, a first straight through hole, and a second straight through hole inside. A wire guard plate is set on the opening surface of the first straight through hole. The oblique through hole is connected to the circular plate structure, and the second straight through hole is connected to a signal amplifier. The signal amplifier is located on the side of the force-measuring elastic body and is integrated with the force-measuring elastic body. Its input end is connected to the resistance strain gauge through a cable passing through the second through hole, the first through hole and the oblique through hole in sequence. Its output end is connected to an external cable interface.

[0007] A further improvement of this utility model is that the upper end of the force-measuring elastic body is provided with an ear fork hole, and the force-measuring elastic body is rotatably connected to the machine connection structure through the ear fork hole.

[0008] A further improvement of this utility model is that the ear fork hole is a through hole.

[0009] A further improvement of this utility model is that a boss is provided below the ear fork hole, and the sealing cover is fixedly mounted on the boss by welding.

[0010] A further improvement of this utility model is that the wire guard plate has a bent plate-like structure, and the welding surface matches the opening plane of the first through hole.

[0011] A further improvement of this invention is that the axes of the first through hole and the second through hole are perpendicular to each other.

[0012] A further improvement of this utility model is that the force-measuring elastic body is provided with six bolt through holes, and the force-measuring elastic body is fixedly connected to the linear servo through the bolt through holes.

[0013] A further improvement of this utility model is that the bolt through holes are distributed in a rectangular array, including holes at the four corners and on both sides of the middle.

[0014] A further improvement of this utility model is that the force-measuring elastic body is provided with two first inclined ribs and two second inclined ribs symmetrically distributed vertically, and the first inclined ribs and the second inclined ribs form an angle of 25~45° with the bottom surface of the force-measuring elastic body.

[0015] A further improvement of this utility model is that the two first inclined ribs and the two second inclined ribs are respectively connected to the four bolt through holes in the area where the circular plate structure is located.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This invention incorporates a force sensor and a signal amplifier. One end of the force sensor is rotatably connected to the machine structure, while the other end is rigidly fixed to a linear servo. This design ensures that the force-measuring elastic body undergoes regular deformation during servo operation to accurately sense push and pull forces, while avoiding additional stress on the connection point caused by servo movement, thus ensuring the stability of the measurement reference. The force-measuring elastic body's internal oblique through-hole, first straight through-hole, and second straight through-plate form a connected signal line channel. Combined with the top sealing cover, this protects the cable from vibration, impact, and acceleration wear, while also shielding it from external electromagnetic interference, ensuring stable voltage signal transmission. Furthermore, the signal amplifier is integrated into the side of the force-measuring elastic body, shortening the signal transmission distance. This invention converts the force value experienced by a linear servo during push-pull operation into a millivolt-level voltage signal. After being amplified by a signal amplifier, it is converted into a volt-level voltage signal that is linearly related to the push-pull force experienced by the linear servo. This signal is then provided to the aircraft linear servo controller. Combined with the signal feedback from the displacement sensor, it identifies faults such as the push-pull force output by the linear servo being too small or too large compared to the corresponding displacement. It also enables the linear servo to promptly stop operation or reverse operation when the output force exceeds the design load, thus preventing damage to the aircraft structure and transmission components.

[0017] Furthermore, the ear fork hole adopts a through-hole design, which can be rotated and connected to the machine structure to avoid the influence of excessive lateral force and additional torque.

[0018] Furthermore, the sealing cap is welded and fixed to the boss, and the sealing performance is enhanced through rigid connection, which completely isolates the external environment from the erosion and interference of the cross beam strain zone and ensures the sealing reliability under harsh working conditions.

[0019] Furthermore, the cable protection plate has a bent plate-like structure, and the welding surface matches the opening plane of the first through hole. Through structural adaptation, the welding sealing is enhanced, the risk of cable wear is reduced, and the resistance to vibration, impact, and acceleration and the reliability of protection are improved. Attached Figure Description

[0020] The accompanying drawings described herein are for illustrative purposes only and are not intended to limit the scope of the present invention in any way. Furthermore, the shapes and proportions of the components in the drawings are merely illustrative to aid in understanding the present invention and do not specifically limit the shapes and proportions of the components of the present invention.

[0021] Figure 1This is a schematic diagram of the force measuring device for an aircraft linear servo according to the present invention; Figure 2 This is a bottom view of the force-measuring elastic body of this utility model; Figure 3 This is a top view of the force-measuring elastic body of this utility model; Figure 4 This is an external view of the wire protection plate of this utility model; Figure 5 This is an external view of the sealing cap of this utility model; Figure 6 This is a schematic diagram illustrating the working principle of a force measuring device for an aircraft linear servo.

[0022] Among them: 1. Force measuring elastic body; 101. Ear fork hole; 102. Boss; 103. Oblique through hole; 104. First straight through hole; 105. Second straight through hole; 106. Signal amplifier; 107. Bolt through hole; 108. Circular plate structure; 109. First oblique rib; 110. Second oblique rib; 2. Wire guard plate; 3. Sealing cover. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0025] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0026] In the description of the embodiments of this utility model, it should be noted that if terms such as "upper," "lower," "horizontal," or "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the utility model product is in use, they are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the utility model. Furthermore, terms such as "first" and "second" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0027] Furthermore, the use of the term "horizontal" does not imply that the component must be absolutely horizontal, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0028] In the description of the embodiments of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0029] The present invention will now be described in further detail with reference to the accompanying drawings: like Figures 1 to 5 As shown, this utility model provides a force measuring device for an aircraft linear servo, including a force sensor and a signal amplifier 106. The input end of the signal amplifier 106 is connected to the force sensor via a cable, and the output end is connected to the aircraft linear servo controller via a cable. The force sensor includes a force measuring elastomer 1, a cable guard 2, and a sealing cover 3. The force measuring elastomer 1 and the signal amplifier 106 are integrated into a single unit design.

[0030] The force-measuring elastomer 1 has an ear fork hole 101 and a boss 102 at its upper end. The force-measuring elastomer 1 is rotatably connected to the machine connection structure through the ear fork hole 101. The force-measuring elastomer 1 has six bolt through holes 107, which are arranged in a rectangular array, including holes at the four corners and two sides in the middle. The force-measuring elastomer 1 is fixedly connected to the linear servo through the bolt through holes 107, and the other end of the linear servo is hinged to the machine body structure.

[0031] A circular plate structure 108 is provided in the middle of the force-measuring elastomer 1, which serves as a strain zone. A cross beam is provided inside the circular plate structure 108, and a resistance strain gauge is provided above the cross beam. A sealing cover 3 is provided on the boss 102 of the force-measuring elastomer 1 to seal the strain zone. The force-measuring elastomer 1 has a continuously penetrating oblique through hole 103, a first straight through hole 104, and a second straight through hole 105. A wire guard plate 2 is provided on the opening surface of the first straight through hole 104 to weld the exposed first straight through hole 104. The system is sealed to isolate the force sensor from the complex external natural and electromagnetic environment. The oblique through hole 103 connects to the circular plate structure 108, and the second straight through hole 105 connects to the signal amplifier 106, which is used to connect the signal amplifier 106 and the force sensor. The signal amplifier 106 is located on the side of the force-measuring elastic body 1. Its input end is connected to the resistance strain gauge on the circular plate structure 108 through the second straight through hole 105, the first straight through hole 104 and the oblique through hole 103 in sequence via a cable. Its output end is connected to an external cable interface.

[0032] As a preferred option, the cable guard plate 2 has a bent plate-like structure, and the welding surface matches the opening plane of the first through hole 104. The structural adaptation enhances the welding sealing performance, reduces the risk of cable wear, and improves the resistance to vibration, impact, and acceleration, as well as the reliability of protection.

[0033] As a preferred embodiment, the ear fork hole 101 is a through hole, and the boss 102 is located below the ear fork hole 101. The ear fork hole 101 adopts a through hole design, which allows for rotatable connection with the machine structure, avoiding the influence of excessive lateral forces and additional torques.

[0034] As a preferred option, the sealing cover 3 is fixedly installed on the boss 2 by welding, which isolates the inside of the force sensor from the external environment, completely isolates the external environment from the erosion and interference of the cross beam strain zone, and ensures the sealing reliability under harsh working conditions.

[0035] As a preferred option, the axes of the first through hole 104 and the second through hole 105 are perpendicular to each other, which optimizes the spatial layout of the cable routing, further realizes the physical isolation of the signal transmission path, and reduces the risk of electromagnetic interference.

[0036] As a preferred option, the middle part of the force-measuring elastic body 1 serves as the strain zone, and resistance strain gauges are respectively set on the cross beams inside the circular plate structure 108 of the strain zone. The symmetrical beam design enables uniform sensing of stress in multiple directions, while the internal embedded layout can effectively avoid external vibration, impact, and acceleration interference, ensuring the stability of signal acquisition.

[0037] The force-measuring elastic body 1 is provided with two first inclined ribs 109 and two second inclined ribs 110 symmetrically distributed vertically. The first inclined ribs 109 form a 35° angle with the bottom surface of the force-measuring elastic body 1, and the second inclined ribs 110 form a 25° angle with the force-measuring elastic body 1. The two first inclined ribs 109 and the two second inclined ribs 110 are respectively connected to four bolt through holes 107 in the area where the circular plate structure 108 is located. The external load is evenly transferred to the strain zone through the inclined support structure, which effectively improves the problem of uneven load distribution caused by the asymmetrical layout, makes the stress distribution in the strain zone more balanced, and is conducive to improving the force measurement accuracy and structural stability.

[0038] like Figure 6 As shown, the working principle of the force-measuring device for an aircraft linear servo is as follows: The force-measuring elastomer, as the core force-bearing component, is connected to the aircraft structure at one end via a rotating connection, and rigidly fixed to the linear servo at the other end. When the servo is actuated, the circular plate structure in the middle of the force-measuring elastomer undergoes regular deformation due to the push-pull force. The resistance strain gauges attached to the crossbeam inside the elastomer simultaneously undergo strain, converting the mechanical force value into a millivolt-level voltage signal. The signal cable is transmitted through a three-dimensional wiring channel formed by the pre-set oblique through-hole, the first straight through-hole, and the second straight through-hole inside the force-measuring elastomer, avoiding exposure of the cable to vibration, impact, acceleration wear, or electromagnetic interference. The signal amplifier integrated on the side of the elastomer receives weak signals and linearly amplifies them to the volt range (output range +1VDC±0.1VDC~+8VDC±0.1VDC). When the linear servo is not under force, it stably outputs +4.5VDC±0.05VDC. 35kN pressure corresponds to +1VDC±0.1VDC, and 35kN tension corresponds to +8VDC±0.1VDC, achieving a high-precision measurement of 0.3%F·S.

[0039] The amplified signal is transmitted to the servo controller. Combined with displacement data from the displacement sensor, the controller can determine the matching relationship between the push-pull force and the displacement in real time. When an excessive force or force-displacement anomaly is detected, the servo immediately triggers a stop protection or reverse action to prevent structural overload. Structurally, the first and second inclined ribs on the force-measuring elastomer form different angles with the bottom surface of the force-measuring elastomer, uniformly transferring the asymmetric load to the strain zone. Combined with the precise welding of the bent plate-shaped guard plate to the opening plane of the first through hole, both local stiffness is enhanced and sealing reliability is ensured. Finally, through mechanical-signal collaborative design, real-time linear monitoring of the servo force value and active safety protection are achieved.

[0040] This invention proposes a force measuring device for aircraft linear servos. By integrating the force sensor and signal amplifier into the servo actuation shaft system, and employing an elastic body mounting method combining rotational connection and rigid fixation, the accuracy of force transmission is ensured while avoiding interference from additional stress. The internally designed three-dimensional wiring channel (a combination of oblique and straight through holes) effectively protects the signal cable. Combined with the reinforcement structure of the first and second oblique ribs forming different angles with the bottom surface of the force measuring elastic body, the device significantly improves resistance to vibration, impact, and acceleration, as well as the uniformity of stress distribution. Simultaneously, through millivolt-to-volt signal conversion and real-time interaction with the controller, millisecond-level response protection for force over-limit is achieved. This solution fundamentally solves the problems of existing aircraft linear servos lacking force feedback signals, making it impossible to monitor force status and provide early warning of faults, as well as the complex separate installation, easily interfered signal, and delayed response of traditional force measuring devices, significantly improving aircraft flight safety.

[0041] Many embodiments and applications beyond the examples provided will be apparent to those skilled in the art upon reading the foregoing description. Therefore, the scope of this teaching should not be determined by reference to the foregoing description, but rather by reference to the foregoing claims and the full scope of their equivalents. For purposes of completeness, all articles and references, including patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended as a waiver of that subject matter, nor should it be construed as an indication that the applicant has not considered that subject matter as part of the disclosed utility model subject matter.

[0042] The above content provides a further detailed description of this utility model. It should not be considered that the specific embodiments of this utility model are limited to this. For those skilled in the art, several simple deductions or substitutions can be made without departing from the concept of this utility model, and all such deductions or substitutions should be considered to fall within the scope of protection of this utility model as defined by the submitted claims.

Claims

1. A force measuring device for an aircraft linear servo, characterized in that, It includes a force sensor and a signal amplifier (106). The force sensor includes a force-measuring elastomer (1), a wire guard plate (2), and a sealing cover (3). One end of the force-measuring elastomer (1) is rotatably connected to the on-board connection structure, and the other end is fixedly connected to the linear servo. The force-measuring elastomer (1) has a circular plate structure (108) in the middle, a cross beam inside the circular plate structure (108), a resistance strain gauge above the cross beam, and a sealing cap (3) above the circular plate structure (108); the force-measuring elastomer (1) has a continuously penetrating oblique through hole (103), a first straight through hole (104), and a second straight through hole (105); the opening surface of the first straight through hole (104) is provided with a wire guard plate (2); the oblique through hole (103) is connected to the circular plate structure (108), and the second straight through hole (105) is connected to the signal amplifier (106); The signal amplifier (106) is located on the side of the force measuring elastomer (1) and is integrated with the force measuring elastomer (1). Its input end is connected to the resistance strain gauge by passing through the second through hole (105), the first through hole (104) and the oblique through hole (103) in sequence with a cable. Its output end is connected to an external cable interface.

2. The force measuring device for an aircraft linear servo according to claim 1, characterized in that, The upper end of the force-measuring elastomer (1) is provided with an ear fork hole (101), and the force-measuring elastomer (1) is rotatably connected to the machine connection structure through the ear fork hole (101).

3. The force measuring device for an aircraft linear servo according to claim 2, characterized in that, The ear fork hole (101) is a through hole.

4. The force measuring device for an aircraft linear servo according to claim 2, characterized in that, A boss (102) is provided below the ear fork hole (101), and the sealing cover (3) is fixedly installed on the boss (102) by welding.

5. The force measuring device for an aircraft linear servo according to claim 1, characterized in that, The wire guard plate (2) is a bent plate structure, and the welding surface matches the opening plane of the first through hole (104).

6. The force measuring device for an aircraft linear servo according to claim 1, characterized in that, The axes of the first through hole (104) and the second through hole (105) are perpendicular to each other.

7. The force measuring device for an aircraft linear servo according to claim 1, characterized in that, The force-measuring elastic body (1) has six bolt through holes (107), and the force-measuring elastic body (1) is fixedly connected to the linear servo through the bolt through holes (107).

8. A force measuring device for an aircraft linear servo according to claim 7, characterized in that, The bolt through holes (107) are distributed in a rectangular array, including holes at the four corners and on both sides of the middle.

9. A force measuring device for an aircraft linear servo according to claim 1, characterized in that, The force-measuring elastic body (1) is provided with two first inclined ribs (109) and two second inclined ribs (110) symmetrically distributed vertically. The first inclined ribs (109) and the second inclined ribs (110) form an angle of 25~45° with the bottom surface of the force-measuring elastic body (1).

10. A force measuring device for an aircraft linear servo according to claim 9, characterized in that, The two first inclined ribs (109) and the two second inclined ribs (110) are respectively connected to the four bolt through holes (107) in the area where the circular plate structure (108) is located.

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