Air Data Probe Arm and Air Data Detection System

Abstract

The present invention discloses an air data probe support arm and an air data detection system, belonging to the field of aerospace. An air data probe is installed through an installation interface, and through the cooperation of a bistable structure and a steady-state transition driving mechanism, the bistable structure is switched between various steady-state structures, thereby driving the installation interface to communicate with the air data probe for reciprocating movement, achieving the effects of ice breaking and de-icing. The structure of the air data probe support arm is novel and reasonable. Compared with the traditional anti-icing method of welding heating wires inside the air data probe, this support arm supports the air data probe externally and will not affect the structure and performance of the air data probe itself. It has the advantages of simple processing and manufacturing, convenient use, strong ice-breaking ability of the support arm, and good insulation. The anti-icing ability of the air data probe support arm can be adjusted by the pilot or the air data computer according to the actual situation, ensuring the service life of the air data probe and reducing the energy consumption of the bistable structure at the same time.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace, relates to atmospheric data detection technology, and particularly relates to an atmospheric data probe arm and an atmospheric data detection system Background Art

[0002] An aircraft completes flight maneuvers relying on the real-time relative motion between itself and the surrounding airflows. At various stages such as takeoff, climb, cruise, and landing of the aircraft, a large amount of accurate information is provided by the atmospheric data system, such as barometric altitude, rate of climb, calibrated airspeed, true airspeed, Mach number, angle of attack, sideslip angle, static air temperature, and atmospheric density ratio, etc. This is crucial for ensuring flight safety and is also the information required by many key avionics subsystems for pilots to perform flight missions. Therefore, on modern civil and military aircraft, the atmospheric data system itself is one of the key avionics systems and an indispensable core element for other avionics subsystems

[0003] For example, when an aircraft flies in clouds with a temperature below freezing point and containing supercooled water droplets, icing will occur after the supercooled water droplets impact the surface of the aircraft components, seriously affecting the flight safety of the aircraft. The atmospheric data probe installed outside the fuselage is an extremely important core component of the atmospheric data system. Taking the pitot tube as an example, since the pitot tube is exposed outside the aircraft and relatively fixed in position relative to the fuselage, under icing flight conditions, the probe lip and the external support tube sleeve of the pitot tube are extremely prone to icing, and in severe cases, even the pitot tube may be blocked. The icing of the pitot tube will directly affect the indication of flight data inside the aircraft and may lead to catastrophic consequences. Therefore, it is crucial to carry out anti-icing work on the pitot tube

[0004] The existing atmospheric data probes mainly use the method of heating wire heating to prevent and remove ice, and this method requires welding heating wires inside the atmospheric data probes. However, the existing atmospheric data probes have a small diameter and a narrow internal space. In addition to arranging heating wires, devices such as total pressure, static pressure, upper surface pressure, lower surface pressure pipelines, and cavity isolation covers also need to be arranged, which makes the originally narrow space even more tense. Even if special wall-mounted welding processes and jigs for heating wires are used, it is easy to cause phenomena such as heating wire cracking, poor insulation of the probe, and low qualification rate of the probe. In addition, due to the heating wire itself having a certain volume, installing it inside the probe will instead affect the size and aerodynamic characteristics of the probe air pipeline and cavity, resulting in problems such as a larger probe volume and poorer aerodynamic characteristics. Moreover, the heating wire heating method can only control by turning on and off the current of the heating wire, and cannot adjust the anti-icing ability of the atmospheric data probe according to the actual situation, making the atmospheric data probe always in the heating state, not only with high energy consumption but also reducing the service life of the probe

[0005] In summary, the air data probe is a very important aviation equipment. However, the existing anti-icing methods for the probe have problems such as poor insulation of the probe, low qualification rate, short service life, and high anti-icing energy consumption. Therefore, it is very urgent and meaningful to propose a new anti-icing solution for the air data probe. Summary of the Invention

[0006] The purpose of the present invention is to provide an air data probe arm and an air data detection system to solve the problems that the existing anti-icing methods for the probe need to install heating wires inside the probe, resulting in poor insulation of the probe, low qualification rate, short service life, and high anti-icing energy consumption.

[0007] To achieve the above object, the present invention provides the following solutions:

[0008] The present invention provides an air data probe arm, including:

[0009] A support member;

[0010] A multi-stable structure, the multi-stable structure includes a plurality of bistable unit models. Any one of the bistable unit models includes a parallelogram frame and a "Y"-shaped bracket arranged inside the parallelogram frame. The first end of the "Y"-shaped bracket is connected to the vertex angle of a set of diagonals of the parallelogram frame. The second end and the third end of the "Y"-shaped bracket are respectively connected to the two sides of the base angle in the set of diagonals. The vertex angle of the parallelogram frame can approach or move away from the base angle under the action of an external force to realize the conversion of the bistable unit model between the first stable structure and the second stable structure; all the bistable unit models are stacked from top to bottom and connected end to end in sequence to form a multi-stable parallelogram frame. The vertex angle of the bistable unit model located at the top of the multi-stable parallelogram frame is the external force application point, and the bottom side of the bistable unit model located at the bottom of the multi-stable parallelogram frame is connected to the support member;

[0011] An installation interface, the installation interface is connected to the top side of the bistable unit model located at the top of the multi-stable parallelogram frame, and the installation interface is used to install the air data probe;

[0012] A stable state transition driving mechanism, the stable state transition driving mechanism includes a transmission device and a driving device connected to the transmission device. The transmission device is connected to the external force application point, and the transmission device is used to apply an external force to the external force application point under the drive of the driving device, so that the bistable unit models in the multi-stable parallelogram frame sequentially undergo the conversion between the first stable structure and the second stable structure from top to bottom.

[0013] Optionally, the multi-stable structure includes two bistable unit models stacked vertically. The parallelogram frame of any one of the bistable unit models is a rhombus frame. Among them, the top side of the rhombus frame located above is connected to the mounting interface, the bottom side of the rhombus frame located above is connected to the top side of the rhombus frame located below, and the bottom side of the rhombus frame located below is connected to the support member.

[0014] Optionally, the mounting interface is a columnar structure with an installation space opened inside, and the atmospheric data probe is installed in the installation space.

[0015] Optionally, the columnar structure includes a head mounting section, a middle connecting section, and a tail section arranged in sequence along its axis, where:

[0016] The head mounting section is a conical section, and a head cylindrical hole penetrating through both axial ends of the head mounting section is opened inside the head mounting section;

[0017] The middle connecting section is a cylindrical section, and a middle cylindrical hole penetrating through both axial ends of the middle connecting section is opened inside the middle connecting section. One axial end of the middle connecting section is connected to the large-head end of the head mounting section, and the middle cylindrical hole is communicated with the head cylindrical hole;

[0018] The tail section is bullet-shaped, and a tail hole is opened inside the tail section. One end of the tail hole penetrates through the large-head end of the tail section. The large-head end of the tail section is connected to the other axial end of the middle connecting section, and the tail hole is communicated with the middle cylindrical hole; the small-head end of the tail section is closed.

[0019] Optionally, a threaded hole is opened on the side wall of the head mounting section and / or the middle connecting section, and a screw for fastening the probe is installed in the threaded hole.

[0020] Optionally, the materials of the head mounting section, the middle connecting section, and the tail section are aluminum alloy or nickel.

[0021] Optionally, the transmission device is a crank transmission mechanism, which includes a long crank rod and a short crank rod. The length of the long crank rod is greater than the length of the short crank rod, where:

[0022] The first end of the long crank rod is hinged to the external force application point;

[0023] The first end of the short crank rod is hinged to the second end of the long crank rod, and the second end of the short crank rod is connected to the driving device. The driving device is used to drive the short crank rod to rotate, thereby driving the long crank rod to perform a linear reciprocating motion along the angular connection line of a set of diagonals.

[0024] Optionally, two crank long rods are provided. The two crank long rods are symmetrically distributed on both sides of the multi-stable parallelogram frame, and the first ends of the two crank long rods are both hinged to the external force application point. The second ends of the two crank long rods are hinged to the first end of the same crank short rod.

[0025] Optionally, the driving device includes:

[0026] A steering gear, the output end of the steering gear is connected to the second end of the crank short rod;

[0027] A chassis, the top of the chassis is connected to the support member. The steering gear is arranged in the chassis, and crank short rod rotation avoidance notches are formed in both the bottom plate of the chassis and the support member.

[0028] In addition, the present invention provides an air data detection system, including an air data probe, a computer, and the air data probe arm as described above. The air data probe is installed at the installation interface of the air data probe arm, and both the air data probe and the steady-state transition driving mechanism are communicatively connected to the computer.

[0029] The present invention has achieved the following technical effects compared with the prior art:

[0030] The air data probe arm proposed by the present invention installs the air data probe through the installation interface, so that the probe arm and the air data probe form an integral body. By means of the mutual cooperation of the bistable structure and the steady-state transition driving mechanism, the conversion between various steady-state structures of the bistable structure is realized, thereby driving the installation interface together with the air data probe to move reciprocally, and the attitude of the integral structure formed by the probe arm and the air data probe is continuously converted, so as to achieve the effect of breaking and removing ice on the outer surface of the integral structure, and further realize the effect of de-icing the air data probe. The structure of the air data probe arm is novel and reasonable. Compared with the traditional method of preventing and removing ice by welding heating wires inside the air data probe, the arm supports the air data probe externally and will not affect the structure and performance of the air data probe itself. It has the advantages of simple processing and manufacturing, convenient use, strong ice-breaking ability of the arm, and good insulation.

[0031] The air data detection system proposed by the present invention includes the above-mentioned air data probe arm and has the ice-breaking and anti-icing effects of the above-mentioned air data probe arm, which will not be elaborated here. In this detection system, the ice prevention and removal ability of the air data probe arm is reflected by the reciprocating transformation of the steady state of the bistable structure, which can be adjusted by the pilot or the air data computer according to the actual situation, avoiding the bistable structure still being in the working state when there is no ice formation obstruction, ensuring the service life of the air data probe, and at the same time reducing the energy consumption of the bistable structure. Description of the Drawings

[0032] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0033] Figure 1 It is a schematic diagram of the overall structure of the air data probe arm disclosed in the embodiments of the present invention;

[0034] Figure 2 It is a schematic diagram of the structure of the mounting interface in the air data probe arm disclosed in the embodiments of the present invention;

[0035] Figure 3 It is a schematic diagram of the structure of the multi-stable structure in the air data probe arm disclosed in the embodiments of the present invention;

[0036] Figure 4 It is an assembly schematic diagram of the multi-stable structure and the transmission device in the air data probe arm disclosed in the embodiments of the present invention;

[0037] Figure 5 It is a schematic diagram of the structure of the transmission device in the stable state transition drive mechanism disclosed in the embodiments of the present invention;

[0038] Figure 6 It is an assembly schematic diagram of the multi-stable structure, the mounting interface, and the support member disclosed in the embodiments of the present invention;

[0039] Figure 7 It is an assembly schematic diagram of the support member and the chassis in the drive device disclosed in the embodiments of the present invention;

[0040] Figure 8 It is a schematic diagram of the internal structure of the drive device in the stable state transition drive mechanism disclosed in the embodiments of the present invention.

[0041] Among them, the reference numerals are:

[0042] 100, air data probe arm;

[0043] 1, mounting interface; 2, multi-stable structure; 3, transmission device; 4, drive device; 5, cable; 6, head mounting section; 7, middle connection section; 8, tail section; 9, threaded hole; 10, "Y"-shaped bracket; 11, pin shaft; 12, long crank rod; 13, pin shaft; 14, short crank rod; 15, support member; 16, chassis; 17, screw; 18, parallelogram frame; 19, servo; 20, rotation avoidance notch of the short crank rod; 21, mounting space. Specific embodiments

[0044] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0045] One of the objectives of the present invention is to provide an air data probe arm to solve the problems that the existing anti-icing method for the probe requires installing heating wires inside the probe, resulting in poor insulation of the probe, low qualification rate, short service life, and high energy consumption for anti-icing.

[0046] Another objective of the present invention is to provide an air data detection system with the above air data probe arm to solve the problems that the existing anti-icing method for the probe requires installing heating wires inside the probe, resulting in poor insulation of the probe, low qualification rate, short service life, and high energy consumption for anti-icing.

[0047] To make the above objectives, features, and advantages of the present invention more obvious and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0048] Embodiment 1

[0049] As Figures 1 - 8 shown, this embodiment provides an air data probe arm 100, which is specifically an air data probe arm based on bistable intelligent structure technology and can achieve the effects of probe anti-icing and de-icing (breaking ice). The air data probe arm 100 mainly includes a support member 15, a multi-stable structure 2, a mounting interface 1, and a stable state transition driving mechanism. Among them, the multi-stable structure 2 includes a plurality of bistable unit models. Any bistable unit model includes a parallelogram frame 18 and a "Y"-shaped bracket 10 arranged inside the parallelogram frame 18. The "Y"-shaped bracket 10 has three rods distributed radially, one long rod and two short rods, and the two short rods are simultaneously connected to one end of the long rod, thus forming a "Y" shape. As Figure 1 、 3As shown in Fig. 4, the other end of the long rod in the "Y" - shaped bracket 10 serves as the first end of the "Y" - shaped bracket 10 and is connected to the vertex angle of a set of opposite angles of the parallelogram frame 18, that is, the upper - corner angle. The other ends of the two short rods respectively serve as the second end and the third end of the "Y" - shaped bracket 10 and are respectively connected to the two sides of the bottom - corner angle of the above - mentioned set of opposite angles, that is, the lower - corner angle. The aforementioned vertex angle of the parallelogram frame 18 can approach or move away from the aforementioned bottom - corner angle under the action of an external force, so as to realize the conversion of the bistable unit cell model between the first stable structure and the second stable structure. The first stable structure is the initial state of the bistable unit cell model. At this time, the bistable unit cell model is not affected by an external force, and the distance between the top side and the bottom side of its parallelogram frame 18 is the largest. After an external force acts on the vertex angle of the bistable unit cell model, this vertex angle will approach the bottom - corner angle along the angular connection line of the above - mentioned opposite angle. During this process, the bottom side of the parallelogram frame 18 remains relatively stationary, and the top side of the parallelogram frame 18 approaches the bottom side under the traction of the external force, so that the distance between the top side and the bottom side of the parallelogram frame 18 decreases non - linearly until, due to the support of the "Y" - shaped bracket 10, the distance between the top side and the bottom side of the parallelogram frame 18 cannot continue to decrease, reaching the second stable structure of the bistable unit cell model. The bistable unit cell model is a highly geometrically non - linear intelligent deformation structure, having the above - mentioned two stable configurations, capable of remaining in their respective equilibrium positions without continuously applying an external force, and being able to reciprocally convert between its first stable structure and the second stable structure under the action of an external - force drive. In the multi - stable structure 2 of this embodiment, all the bistable unit cell models are stacked from top to bottom and connected end - to - end in sequence, that is, in adjacent two bistable unit cell models, the bottom side of the upper bistable unit cell model is connected to the top side of the lower bistable unit cell model, or shares one side, thus forming a large multi - stable parallelogram frame. This multi - stable parallelogram frame is the overall frame of the multi - stable structure 2 and has a similar - parallelogram relationship with the parallelogram frame 18 in each bistable unit cell model. The vertex angle of the bistable unit cell model located at the top of the multi - stable parallelogram frame is the external - force application point of the entire multi - stable parallelogram frame, and the bottom side of the bistable unit cell model located at the bottom of the multi - stable parallelogram frame is connected to the above - mentioned support member 15. The support member 15 can be a support - plate structure to install and support the above - mentioned multi - stable structure 2. The aforementioned installation interface 1 is connected to the top side of the bistable unit cell model located at the top of the multi - stable parallelogram frame, and the installation interface 1 is used to install an air - data probe.The steady-state transition driving mechanism includes a transmission device 3 and a driving device 4 connected to the transmission device 3. The transmission device 3 is connected to the aforementioned external force application point. The transmission device 3 is configured to apply an external force to the external force application point under the drive of the driving device 4, so that the bistable unit cell models in the multi-stable parallelogram frame are sequentially converted between the first steady-state structure and the second steady-state structure from top to bottom. For example, if the transmission device 3 applies a tensile force to the external force application point, the first bistable unit cell model at the top first undergoes a transition from the first steady-state structure to the second steady-state structure, followed by the second bistable unit cell model at the top undergoing a transition from the first steady-state structure to the second steady-state structure, the third bistable unit cell model at the top undergoing a transition from the first steady-state structure to the second steady-state structure... and so on.

[0050] In this embodiment, the bistable unit cell model can be composed of a composite material, generally having a certain viscoelasticity, and can be formed by three-dimensional weaving technology.

[0051] In this embodiment, as Figure 3 shown, preferably, the multi-stable structure 2 is a rectangular intelligent structure formed by stacking two bistable unit cell models up and down. Among them, the parallelogram frame 18 of any bistable unit cell model is a rhombus frame, that is, the four side lengths of the parallelogram frame 18 are the same. This rhombus frame is more preferably a square frame. When no external force acts, that is, when the parallelogram frame 18 is in the first steady-state structure, the parallelogram frame 18 is a square, and its second stable structure is a rhombus. Correspondingly, as Figure 3 shown, the multi-stable parallelogram frame of the multi-stable structure 2 is a rectangular frame formed by stacking two square frames. In this rectangular frame, the external force application point is located at its upper right corner. This rectangular frame has a total of three steady-state structures. When no external force acts, it is the first steady-state structure of the multi-stable parallelogram frame. At this time, both parallelogram frames 18 are squares, and the multi-stable parallelogram frame is rectangular. When an external force acts, first, the upper parallelogram frame 18 is converted to the second steady-state structure. At this time, the upper parallelogram frame 18 is a rhombus, while the lower parallelogram frame 18 still remains in its own first steady-state structure (square), that is, when the upper parallelogram frame 18 is in the second steady-state structure and the lower parallelogram frame 18 is in the first steady-state structure, it is in the second steady-state structure of the entire multi-stable parallelogram frame. After that, when the external force continues to be applied in the same direction, the lower parallelogram frame 18 also begins to transition from its own first steady-state structure to the second steady-state structure until the lower parallelogram frame 18 is also in its own second steady-state structure, and the entire multi-stable parallelogram frame reaches the third steady-state structure.

[0052] In this embodiment, on the basis that the parallelogram frames 18 of the aforementioned bistable unit cell model are all diamond frames, the "Y"-shaped bracket 10 is also set as a symmetric structure, that is, the two short rods of the "Y"-shaped bracket 10 are symmetrically distributed with the long rod as the center. After the two short rods are connected to the two sides of the bottom angle of the diamond frame, the figure enclosed by the two short rods and the diamond frame has a similar diamond relationship with the diamond frame. In this embodiment, the "Y"-shaped bracket 10 is used for three-point support of the parallelogram frame 18, which can effectively ensure the structural stability of the bistable unit cell model.

[0053] Further, in this embodiment, the top side of the upper diamond frame can be connected to the bottom of the mounting interface 1 by welding, 3D printing or bonding. The bottom side of the upper diamond frame is connected to or shares one side with the top side of the lower diamond frame. The bottom side of the lower diamond frame can be connected to the upper part of the support 15 by welding, 3D printing or bonding.

[0054] In this embodiment, as Figure 1 、 Figure 2 and Figure 6 shown, the mounting interface 1 is a columnar structure with a mounting space 21 opened inside. The mounting space 21 is used to mount an air data probe. Specifically, the columnar structure includes a head mounting section 6, a middle connecting section 7 and a tail section 8 arranged in sequence along its axis. Among them, the head mounting section 6 is set as a conical section. A head cylindrical hole penetrating through both axial ends of the head mounting section 6 is opened inside the head mounting section 6. The middle connecting section 7 is a cylindrical section. A middle cylindrical hole penetrating through both axial ends of the middle connecting section 7 is opened inside the middle connecting section 7. One axial end of the middle connecting section 7 is connected to the large end of the head mounting section 6, and the middle cylindrical hole is communicated with the head cylindrical hole. The tail section 8 is bullet-shaped. A tail hole is opened inside the tail section 8. One end of the tail hole penetrates through the large end of the tail section 8. The large end of the tail section 8 is connected to the other axial end of the middle connecting section 7, and the tail hole is communicated with the middle cylindrical hole. The small end of the tail section 8 is closed. Thus, the above-mentioned head cylindrical hole, middle cylindrical hole and tail hole are sequentially communicated to form the aforementioned mounting space 21, and the air data probe is loaded into the mounting space 21 from the head cylindrical hole. The head mounting section 6 is the head of the mounting interface 1. The outer wall surface of the head mounting section 6 is set as a conical surface. This conical surface is used as the windward surface and gradually expands from the head to the tail, which can effectively reduce the influence of wind resistance on the aerodynamics of the front straight pipe. The tail section 8 is bullet-shaped, which also makes the whole mounting interface 1 bullet-shaped.

[0055] In this embodiment, threaded holes 9 can be formed in the side walls of the head mounting section 6 and / or the middle connecting section 7, and screws for fastening the probe are installed in the threaded holes 9. As a preferred solution, the threaded holes 9 can be formed only in the middle connecting section 7 or the head mounting section 6. More preferably, in order to ensure the overall structural strength of the mounting interface 1, the threaded holes 9 are formed only in the side wall of the middle connecting section 7. A plurality of threaded holes 9 can be evenly formed along the circumferential direction of the middle connecting section 7. The threaded holes 9 penetrate through the outer wall and the inner wall of the middle connecting section 7, and screws are installed therein. The internal probe can be tightened and reinforced by tightening the screws. Generally, when installing the straight pipe of the air data probe, the straight pipe step is first fixedly installed in the installation space 21 by welding or bonding, etc., and then further fastened by installing screws in the threaded holes 9.

[0056] In this embodiment, the aforementioned head mounting section 6, middle connecting section 7, and tail section 8 are preferably integrally formed structures, and different sections can also be assembled by means of threaded connection. In order to reduce weight and ensure a certain strength, the materials of the head mounting section 6, middle connecting section 7, and tail section 8 are all preferably made of aluminum alloy or nickel. Taking the head mounting section 6, middle connecting section 7, and tail section 8 all being preferably made of nickel as an example, the inner diameter of the head mounting section 6, that is, the diameter of the head cylindrical hole is 14 mm, the outer diameter of the small head end is 15 mm, and the outer diameter of the large head end is 18 mm; the inner diameter of the middle connecting section 7, that is, the diameter of the middle cylindrical hole is 14 mm, and the outer diameter is 18 mm; the axial length of the tail section 8 is 20 mm, and the sizes of the tail hole and the outer wall of the tail section 8 gradually converge from the head to the tail, and the whole is in a bullet shape.

[0057] In this embodiment, the transmission device 3 is preferably a crank transmission mechanism, which includes a long crank rod 12 and a short crank rod 14. As the name implies, the length of the long crank rod 12 is greater than that of the short crank rod 14. Among them, the first end (top end) of the long crank rod 12 can be hinged to the aforementioned external force application point through a pin shaft 11. The first end (top end) of the short crank rod 14 is hinged to the second end (bottom end) of the long crank rod 12 through a pin shaft 13, and the pin shaft 11 is arranged parallel to the pin shaft 13. The second end (bottom end) of the short crank rod 14 is connected to the driving device 4. The driving device 4 is used to drive the short crank rod 14 to rotate, thereby driving the long crank rod 12 to perform a linear reciprocating motion along the angular connection line of the aforementioned set of diagonals, so as to realize the reciprocating conversion of any bistable single-cell model between the first stable structure and the second stable structure. Driven by the driving device 4, the short crank rod 14 rotates around its rotation center. Generally, when the short crank rod 14 rotates one week, it will drive the long crank rod 12 to reciprocate once, that is, the rotational motion of the short crank rod 14 drives the long crank rod 12 to perform a periodic reciprocating motion. The motion of the long crank rod 12 will apply a driving load to the external force application point at the upper right corner of the multi-stable structure 2, thereby driving the multi-stable structure 2 to perform reciprocating deformation and motion. By combining the crank transmission mechanism with the multi-stable structure 2, it is possible to ensure that the air data probe arm performs reciprocating deformation and motion, thereby achieving the effects of ice breaking and ice prevention.

[0058] In this embodiment, two long crank rods 12 are preferably provided. The two long crank rods 12 are symmetrically distributed on both sides of the multi-stable parallelogram frame, and the first ends (top ends) of the two long crank rods 12 are both hinged to the external force application point through the pin shaft 11. The second ends (bottom ends) of the two long crank rods 12 are hinged to the first end (top end) of the same short crank rod 14 through the same pin shaft 13, as Figure 5 shown. The long crank rods 12 are symmetrically arranged on both sides of the multi-stable parallelogram frame, which ensures the symmetry of the later external load drive and eliminates the influence of uneven load application on the deformation of the multi-stable parallelogram frame.

[0059] In this embodiment, the aforementioned driving device 4 includes a chassis 16, a servo motor 19, a cable 5, etc. The chassis 16 is a bottomed box body, and the support member 15 is a support plate member and is installed at the top opening of the chassis 16 through screws 17, thereby realizing the enclosure of the chassis 16. The servo motor 19 is arranged inside the chassis 16. The output end of the servo motor 19 is connected to the second end (bottom end) of the short crank rod 14 to drive the short crank rod 14 to rotate. Since the servo motor 19 is arranged inside the chassis 16, in order to avoid interfering with the operation of the crank transmission mechanism, crank short rod rotation avoidance notches 20 can be opened on both the bottom plate of the chassis 16 and the support member 15 for the short crank rod 14 to rotate smoothly and the long crank rod 12 to move linearly smoothly. As a preferred solution, the aforementioned chassis 16 is preferably a cylindrical chassis, and the support member 15 is correspondingly set as a circular support plate member adapted to it, asFigure 7 as shown

[0060] In actual operation, the servo 19 can be connected to the short crank rod 14 through a shaft or the like, and assembled on the lower surface of the support member 15 or the upper surface of the bottom plate of the chassis 16 by screws 17. At the same time, the servo 19 can be connected to the air data computer through the cable 5. The pilot or the air data computer can adjust parameters such as the driving speed and driving frequency of the servo 19 for driving the short crank rod 14 according to the actual situation, thereby adjusting the anti-icing level, and the air data computer generates a PWM control signal. The built-in circuit board of the servo 19 receives the PWM control signal and judges the rotation angle and direction of the short crank rod 14, so as to drive the short crank rod 14 to perform a rotational motion. The frequency of this rotational motion will change according to the frequency of the PWM signal.

[0061] In this embodiment, the air data probe arm 100 is both an installation and support component for the air data probe, and can also prevent the probe from icing at high altitudes or in cold weather, and can also break and remove ice after the probe is iced. The air data probe installed on the air data probe arm 100 can be an air data probe that senses pressure data such as the total pressure, static pressure, dynamic pressure, pressure on the upper surface of the probe, and pressure on the lower surface of the probe of the aircraft. Among them, the parallelogram frames 18 of the upper and lower bistable unit models and the "Y"-shaped bracket 10 are an integrally formed structure, and are preferably 3D printed using a TPU-95A material (such as thermoplastic polyurethane elastomer rubber).

[0062] The working principle of the above air data probe arm 100 in this embodiment will be described below:

[0063] In the air data probe arm 100, when there is no external force driving the upper and lower bistable unit models, it is in the initial steady state, that is, the first steady-state structure. In the initial steady state, the parallelogram frames 18 of the upper and lower bistable unit models are both squares. When an external force drives the upper right corner of the upper bistable unit model, it squeezes from the upper right corner to the lower left corner along its diagonal. First, the parallelogram frame 18 of the upper bistable unit model deforms, and the parallelogram frame 18 of the lower bistable unit model remains in the initial steady state. At this time, it is the second steady state of the air data probe arm 100. In the second steady state, the parallelogram frame 18 of the upper bistable unit model is in its own second steady-state structure, and the parallelogram frame 18 of the lower bistable unit model is in its own first steady-state structure. When the external load continues to press down, the parallelogram frame 18 of the lower bistable unit model also deforms until the parallelogram frames 18 of the upper and lower bistable unit models are both in the second steady-state structure, reaching the third steady state of the air data probe arm 100. In this embodiment, the above external load is applied by the driving device 4. Specifically, the servo motor 19 drives the short crank rod 14 to rotate, thereby driving the long crank rod 12 to perform a linear reciprocating motion, providing a driving force for the multi-stable structure 2. This driving force generates a pushing or pulling external load on the multi-stable structure 2. For example, when the driving force generates a pulling external load on the multi-stable structure 2, it drives the multi-stable structure 2 to change from the initial steady state to the second steady state. Continuing to increase this pulling load causes the multi-stable structure 2 to continue to change from the second steady state to the third steady state. When the driving force generates a pushing external load on the multi-stable structure 2, it can drive the multi-stable structure 2 to change from the third steady state to the second steady state. Continuing to increase the pushing load can cause the multi-stable structure 2 to change from the second steady state to the initial steady state. By driving the multi-stable structure 2 to transform between multiple steady states, the deformation and movement of the overall structure of the air data probe arm 100 are realized. In actual operation, the pilot or the air data computer modulates the PWM signal of the driving device according to the actual icing situation or the external climate conditions of the aircraft, thereby changing the frequency of the reciprocating deformation and movement of the overall structure of the air data probe arm 100, and finally achieving the effect of probe ice breaking and anti-icing. Taking the multi-stable structure 2 in the initial steady state as an example, with an overall height of 87 mm, an overall width of 46 mm, and an overall thickness of 6 mm, compared with the initial steady state, the second and third steady states of the multi-stable structure 2 are reduced by about 8 mm and about 16 mm in height respectively, and can maintain stability in each state.

[0064] The air data probe arm based on the bistable intelligent structure technology proposed in this embodiment has been verified by a large number of engineering tests and has the following advantages:

[0065] 1. The air data probe arm 100 achieves anti-icing based on a bistable intelligent structure. Compared with the traditional anti-icing method of heating wires for air data probes, in this technical solution, the air data probe arm 100 is used to install and support the air data probe. The air data probe and the air data probe arm 100 form an integral structure, which will continuously change its attitude during the detection process based on the bistable intelligent structure. Even if the external of this integral structure freezes, the ice layer formed outside can be broken due to its attitude change, achieving the effect of ice breaking and de-icing. At the same time, since the structure formed by the air data probe and the air data probe arm 100 continuously performs telescopic motion through the bistable intelligent structure, the relative position of the air data probe to the aircraft is continuously converted, which can effectively prevent the outside of the air data probe from icing, thus achieving the anti-icing effect. The air data probe arm 100 has the advantages of simple manufacturing, strong ice-breaking ability of the arm, and good insulation.

[0066] 2. The anti-icing ability of the air data probe arm 100 can be adjusted by the pilot or the air data computer according to the actual situation, which ensures the service life of the air data probe and reduces the energy consumption.

[0067] 3. The air data probe arm 100 is a general-purpose probe arm, which can realize the installation of various forms of straight pipes of air data probes (such as total pressure straight pipes, total static pressure straight pipes, total static pressure and upper and lower surface pressure straight pipes, etc.), and can be used as an independent in-field replaceable unit, which is convenient for maintenance.

[0068] It should be noted that in actual operation, the number of bistable unit models set in the multi-stable structure 2 can also be three, four or even more, and the stable forms of the formed multi-stable structure 2 will also increase. In addition to setting multiple ones, the multi-stable structure 2 can also be configured by only one bistable unit model, and the size of the bistable unit model can be adjusted accordingly. Thus, it can be seen that the multi-stable structure 2 proposed in this technical solution is not limited to being composed of the superposition of two bistable unit models as described above, and the number of set bistable unit models and the structural size of the bistable unit model can both be adaptively adjusted according to actual needs.

[0069] Embodiment 2

[0070] This embodiment proposes an air data detection system, which includes an air data probe, a computer and the air data probe arm 100 disclosed in Embodiment 1. The air data probe is installed in the installation space 21 of the installation interface 1 of the air data probe arm 100, and both the air data probe and the steady-state transformation driving mechanism are communicatively connected to the computer. In actual operation, the pilot or the air data computer modulates the PWM signal of the driving device according to the actual icing situation or the external climate conditions of the aircraft, etc., so as to change the frequency of the reciprocating deformation and movement of the overall structure of the air data probe arm 100, and finally achieve the effects of ice breaking and anti-icing of the probe.

[0071] It should be noted that it is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims are included in the present invention, and any figure mark in the claims should not be regarded as limiting the claims involved.

[0072] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An air data probe arm, characterized in that, Comprising: A support member; A multi-stable structure, the multi-stable structure comprising a plurality of bistable unit cell models, any one of the bistable unit cell models comprising a parallelogram frame and a "Y"-shaped bracket disposed within the parallelogram frame, a first end of the "Y"-shaped bracket being connected to a vertex angle of a pair of opposite angles in the parallelogram frame, and a second end and a third end of the "Y"-shaped bracket being respectively connected to two sides of the base angles of the pair of opposite angles, the vertex angle of the parallelogram frame being capable of approaching or moving away from the base angle under the action of an external force so as to effect a conversion of the bistable unit cell model between a first stable structure and a second stable structure; All of the bistable unit cell models are stacked from top to bottom and connected end to end in sequence to form a multi-stable parallelogram frame, the vertex angle of the bistable unit cell model located at the topmost of the multi-stable parallelogram frame being the external force application point, and the base of the bistable unit cell model located at the bottommost of the multi-stable parallelogram frame being connected to the support member; An installation interface, the installation interface being connected to the top edge of the bistable unit cell model located at the topmost of the multi-stable parallelogram frame, the installation interface being for installing an air data probe; A stable state conversion drive mechanism, the stable state conversion drive mechanism comprising a transmission device and a drive device connected to the transmission device, the transmission device being connected to the external force application point, the transmission device being for applying an external force to the external force application point under the drive of the drive device so as to effect a conversion of the bistable unit cell models in the multi-stable parallelogram frame from top to bottom in sequence between a first stable structure and a second stable structure.

2. The air data probe arm according to claim 1, characterized in that, The multi-stable structure comprises two bistable unit cell models stacked up and down, the parallelogram frame of any one of the bistable unit cell models being a rhombus frame, wherein the top edge of the rhombus frame located above is connected to the installation interface, the bottom edge of the rhombus frame located above is connected to the top edge of the rhombus frame located below, and the bottom edge of the rhombus frame located below is connected to the support member.

3. The air data probe boom according to claim 1 or 2, characterized in that, The installation interface is a columnar structure with an installation space opened inside, and the air data probe is installed in the installation space.

4. The air data probe boom according to claim 3, characterized in that, The columnar structure comprises a head installation section, a middle connection section and a tail section arranged in sequence along its axis, wherein: The head installation section is a conical section, and a head cylindrical hole penetrating through both axial ends of the head installation section is opened inside the head installation section; The middle connection section is a cylindrical section, a middle cylindrical hole penetrating through both axial ends of the middle connection section is opened inside the middle connection section, one axial end of the middle connection section is connected to the large end of the head installation section, and the middle cylindrical hole is communicated with the head cylindrical hole; The tail section is bullet-shaped, a tail hole is opened inside the tail section, one end of the tail hole penetrates through the large end of the tail section, the large end of the tail section is connected to the other axial end of the middle connection section, and the tail hole is communicated with the middle cylindrical hole; the small end of the tail section is closed.

5. The air data probe boom according to claim 4, characterized in that, Threaded holes are provided in the side walls of the head mounting section and / or the middle connecting section, and screws for installing and fastening the probe are arranged in the threaded holes.

6. The air data probe boom according to claim 4, characterized in that, The head mounting section, the middle connecting section, and the tail section are made of aluminum alloy or nickel.

7. The air data probe boom according to claim 1 or 2, characterized in that, The transmission device is a crank transmission mechanism, which includes a long crank rod and a short crank rod, and the length of the long crank rod is greater than that of the short crank rod, where: The first end of the long crank rod is hinged to the external force application point; The first end of the short crank rod is hinged to the second end of the long crank rod, and the second end of the short crank rod is connected to the driving device. The driving device is used to drive the short crank rod to rotate, thereby driving the long crank rod to perform a linear reciprocating motion along the angular connection line of the set of diagonals.

8. The air data probe boom according to claim 7, characterized in that, Two long crank rods are provided, and the two long crank rods are symmetrically distributed on both sides of the multi-stable parallelogram frame. The first ends of the two long crank rods are both hinged to the external force application point, and the second ends of the two long crank rods are hinged to the first end of the same short crank rod.

9. The air data probe boom according to claim 7, characterized in that, The driving device includes: A servo motor, the output end of which is connected to the second end of the short crank rod; A chassis, the top of which is connected to the support member. The servo motor is arranged in the chassis, and crank short rod rotation avoidance notches are provided on both the bottom plate of the chassis and the support member.

10. An air data detection system, characterized in that, It includes an air data probe, a computer, and an air data probe arm according to any one of claims 1 to 9. The air data probe is installed at the installation interface of the air data probe arm, and both the air data probe and the steady-state transition driving mechanism are in communication connection with the computer.

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