High-temperature-resistant steering engine controller

Abstract

The invention relates to a high-temperature-resistant steering engine controller, belongs to the technical field of steering engine controllers, and solves the problem that a steering engine controller in the prior art is difficult to run for a long time in a high-temperature environment without a heat dissipation path. The steering engine controller comprises an upper shell assembly, a lower shell assembly, a control printed board, a power supply printed board, a flight control computer communication electric connector and an execution mechanism communication electric connector. The control printed board and the power supply printed board are fixedly installed in the upper shell assembly and the lower shell assembly respectively. The flight control computer communication electric connector and the execution mechanism communication electric connector are fixedly installed on the side wall of the lower shell assembly. And the interiors of bottom plates and four side plates of the upper shell assembly and the lower shell assembly are filled with phase change media. The bottom plate and the four side plates of the controller shell are filled with the phase change media, so that a good cooling effect on the controller is achieved, and it can be guaranteed that an electric device works within an expected temperature range.

Description

Technical Field

[0001] The present invention relates to the technical field of steering gear controllers, and in particular to a high temperature resistant steering gear controller. Background Art

[0002] The servo is an important part of the aircraft attitude control system, used to control the deflection of the control surface. During the flight of the aircraft, the servo needs to overcome harsh working environments such as impact, vibration, and high temperature. In particular, as the flight distance and flight time of the aircraft increase, the external radiation, heat conduction and internal heating of the servo will increase significantly. Under the simultaneous action of internal and external heat loads, ensuring the reliable operation of the servo is an urgent problem to be solved.

[0003] The servo controller is connected to the flight control computer and the servo actuator to realize functions such as power filtering and isolation conversion, rudder command signal collection, feedback of servo actuator position, and sending of servo actuator action signals. Conventional controllers generally include signal processing chips, position acquisition chips, temperature acquisition chips, isolation chips, power chips and other devices. The above devices are sensitive to high temperature environments and need to be protected by thermal design measures when working for long flight times in high temperature environments.

[0004] The servo faces the following thermal environment when working: the outer surface of the servo installation cabin generates heat due to friction when the aircraft is flying, the servo installation cabin is a small and closed space, and the servo battery generates heat. In addition, the power components on the circuit board inside the servo controller will also generate heat when working. Moreover, the temperature caused by the self-heating of the servo controller is generally much lower than the external ambient temperature. Therefore, the controller is in a closed and small space and cannot reduce its own temperature by transferring heat to the external environment. For this reason, the servo controller needs to adopt appropriate thermal design measures to ensure that its internal components work within the normal temperature range. Summary of the invention

[0005] In view of the above analysis, the present invention aims to provide a high temperature resistant steering gear controller to solve the problem that the existing machine controller operates for a long time in a high temperature environment without a heat dissipation path.

[0006] The purpose of the present invention is mainly achieved through the following technical solutions:

[0007] A high temperature resistant steering gear controller comprises: an upper housing assembly, a lower housing assembly, a control printed board, a power printed board, a flight control computer communication electrical connector and an actuator communication electrical connector; the control printed board and the power printed board are fixedly mounted inside the upper housing assembly and the lower housing assembly respectively; the flight control computer communication electrical connector and the actuator communication electrical connector are both fixedly mounted on the side wall of the lower housing assembly; the bottom plate and four side plates of the upper housing assembly and the lower housing assembly are filled with phase change medium.

[0008] Furthermore, the upper shell assembly includes: an upper shell and four upper shell side covers with the same structure; the four upper shell side covers are respectively fixedly mounted on four side surfaces of the upper shell and are arranged perpendicular to the upper shell.

[0009] Furthermore, the upper shell assembly also includes: an upper shell top cover and an upper shell inner cover; an upper shell inner cavity is provided on the inner side of the upper shell, and an upper shell outer cavity is provided on the outer side of the upper shell; the upper shell inner cover is fixedly installed on the inner side of the upper shell and can close the upper shell inner cavity to form an upper shell heat absorption chamber; the upper shell top cover is fixedly installed on the outer side of the upper shell and can close the upper shell outer cavity to form an upper shell insulation chamber.

[0010] Furthermore, the lower shell assembly includes: a lower shell, left and right side covers of the lower shell, and front and rear side covers of the lower shell.

[0011] Furthermore, the lower shell assembly also includes: a lower shell top cover and a lower shell inner cover; a lower shell inner cavity is provided on the inner side of the lower shell, and a lower shell outer cavity is provided on the outer side of the lower shell; the lower shell top cover is fixedly mounted on the outer side of the lower shell and can close the lower shell outer cavity to form a lower shell heat insulation chamber; the lower shell inner cover is fixedly mounted on the inner side of the lower shell and can close the lower shell inner cavity to form a lower shell heat absorption chamber.

[0012] Furthermore, the upper shell side cover is a hollow structure, and the outer end surface thereof is provided with a first upper shell injection hole for filling the phase change medium into the upper shell side cover.

[0013] Furthermore, a second upper shell injection hole and a third upper shell injection hole for injecting phase change medium into the upper shell heat absorption chamber and the upper shell heat insulation chamber of the upper shell assembly are also provided on the side surface of the upper shell.

[0014] Furthermore, the left and right side covers of the lower shell and the front and rear side covers of the lower shell are all hollow structures, and the outer end surfaces of the two are provided with a first lower shell injection hole for filling the phase change medium.

[0015] Furthermore, the side surface of the lower shell is also provided with a second lower shell injection hole and a third lower shell injection hole for injecting phase change medium into the lower shell heat absorption chamber and the lower shell insulation chamber of the lower shell assembly.

[0016] Furthermore, it also includes: a heat insulation ring; the lower shell assembly is fixedly installed on the inner side of the aircraft cabin by bolts, and the heat insulation ring is arranged between the lower shell assembly and the aircraft cabin.

[0017] The technical solution of the present invention can achieve at least one of the following effects:

[0018] 1. The high temperature resistant steering gear controller of the present invention has an integrated design with three functions including heat insulation, heat absorption and load bearing. The paraffin phase change medium filled on the outer side of the bottom plate of the upper shell component and the lower shell component has a low thermal conductivity and can isolate the external high temperature airflow from being conducted to the inside of the controller, mainly playing a heat insulation role.

[0019] 2. The high temperature resistant steering gear controller of the present invention has a paraffin phase change medium filled inside the bottom plate of the upper shell assembly and the lower shell assembly, and a small amount of expanded graphite is added to greatly improve the thermal conductivity. After reaching the phase change energy storage working temperature range, the internal phase change medium melts from solid phase to liquid phase and absorbs a large amount of heat, playing an active heat absorption role.

[0020] 3. The high temperature resistant servo controller of the present invention adopts a double-layer phase change medium filling design in the upper shell component and the bottom plate of the lower shell component, and adopts a design combining external heat insulation and internal heat absorption to protect the control printed circuit board and the power printed circuit board within the normal operating temperature range. It has a simple structure and compact space, can adapt to high temperature environments where there is no heat dissipation path for aircraft, is easy to implement, and has high reliability.

[0021] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained through the contents particularly pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0023] Figure 1 This is a schematic structural diagram of a high temperature resistant steering gear controller according to Embodiment 1 of the present invention;

[0024] Figure 2 This is a bottom view of a high temperature resistant steering gear controller according to embodiment 1 of the present invention;

[0025] Figure 3 It is a front view of a high temperature resistant steering gear controller according to embodiment 1 of the present invention;

[0026] Figure 4 for Figure 3 Cross-sectional view in the AA direction;

[0027] Figure 5 for Figure 1One of the three-dimensional views of the upper housing assembly in FIG.

[0028] Figure 6 for Figure 1 The second stereoscopic view of the upper housing assembly;

[0029] Figure 7 for Figure 1 A cross-sectional view of an upper housing assembly in FIG.

[0030] Figure 8 for Figure 7 One of the three-dimensional views of the upper housing in FIG.

[0031] Fig. 9 for Figure 7 The second stereogram of the upper shell;

[0032] Fig.10 for Figure 7 A sectional view of the upper shell in FIG.

[0033] Fig.11 for Figure 1 One of the three-dimensional views of the lower housing assembly in FIG.

[0034] Fig.12 for Figure 1 A second perspective view of the lower housing assembly;

[0035] Fig.13 for Figure 1 A cross-sectional view of a lower housing assembly in FIG.

[0036] Fig.14 for Fig.13 One of the three-dimensional views of the lower housing in FIG.

[0037] Fig.15 for Fig.13 The second stereogram of the lower shell in FIG.

[0038] Fig.16 for Fig.13 A cross-sectional view of the lower shell in FIG.

[0039] Fig.17 for Figure 1 A schematic diagram of the structure of the heat insulation ring;

[0040] Fig.18 This is one of the three-dimensional views of a heat-insulating ring of a high-temperature-resistant steering gear controller according to Embodiment 2 of the present invention;

[0041] Fig.19 This is a second stereoscopic diagram of a heat-insulating ring of a high-temperature-resistant steering gear controller according to Embodiment 2 of the present invention;

[0042] Fig. 20A top view of a heat-absorbing network structure of a high-temperature-resistant steering gear controller according to Embodiment 3 of the present invention;

[0043] Fig.21 A side view of a heat-absorbing network structure of a high-temperature-resistant steering gear controller according to Embodiment 3 of the present invention;

[0044] Fig. 22 Schematic diagram of the structure of the heat-absorbing cell.

[0045] Reference numerals:

[0046] 1-upper housing assembly; 2-lower housing assembly; 3-control printed circuit board; 4-power printed circuit board; 5-flight control computer communication electrical connector; 6-actuator communication electrical connector; 7-insulation ring; 8-upper housing; 9-upper housing top cover; 10-upper housing inner cover; 11-upper housing side cover; 12-lower housing; 13-lower housing top cover; 14-lower housing inner cover; 15-lower housing left and right side covers; 16-lower housing front and rear side covers; 17-fixing hole; 18-mounting hole; 19-first side wall hole; 20-second side wall hole; 21-first boss; 22-first threaded hole; 23-second boss; 24-first An upper shell injection molding hole; 25-a second upper shell injection molding hole; 26-a third upper shell injection molding hole; 27-an inner cavity of the upper shell; 28-an outer cavity of the upper shell; 29-a first lower shell injection molding hole; 30-a second lower shell injection molding hole; 31-a third lower shell injection molding hole; 32-an outer cavity of the lower shell; 33-an inner cavity of the lower shell; 34-a heat-insulating ring body; 35-a heat-insulating ring cap; 36-an outer circular ring; 37-an inner hole of the heat-insulating ring; 38-a convex ridge of the inner hole; 39-a convex circular structure; 40-a heat-insulating groove; 41-a heat-absorbing network structure; 42-a center ring; 43-a connecting rod; 44-a convex ring; 45-a support rod. DETAILED DESCRIPTION

[0047] The preferred embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0048] Example 1

[0049] A specific embodiment of the present invention discloses a high temperature resistant steering gear controller, such as Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, it includes: an upper housing assembly 1, a lower housing assembly 2, a control printed board 3, a power printed board 4, a flight control computer communication electrical connector 5 and an actuator communication electrical connector 6; the control printed board 3 and the power printed board 4 are fixedly installed inside the upper housing assembly 1 and the lower housing assembly 2 respectively; the flight control computer communication electrical connector 5 and the actuator communication electrical connector 6 are both fixedly installed on the side wall of the lower housing assembly 2; the bottom plate and four side plates of the upper housing assembly 1 and the lower housing assembly 2 are filled with phase change medium. Specifically, the upper housing assembly 1 and the lower housing assembly 2 can be processed with aluminum alloy or magnesium aluminum alloy according to weight requirements.

[0050] In a specific embodiment of the present invention, Figure 5 , Figure 6 , Figure 7 As shown, the upper housing assembly 1 includes: an upper housing 8 and four upper housing side covers 11 with the same structure; the four upper housing side covers 11 are respectively fixedly mounted on the four sides of the upper housing 8 and are arranged perpendicular to the upper housing 8. Figure 5 , Figure 6 As shown, there are four upper shell side covers 11, namely the upper shell left cover, the upper shell right cover, the upper shell front cover, and the upper shell rear cover; the four upper shell side covers 11 are fixedly connected to the upper shell 8 by welding to form a rectangular cylindrical structure.

[0051] Specifically, the upper shell 8 and the upper shell top cover 9, the upper shell inner cover 10, and the upper shell side cover 11 (the upper shell left side cover, the upper shell right side cover, the upper shell front side cover, and the upper shell rear side cover) are all fixed by laser welding, and the weld quality and airtightness are tested.

[0052] In a specific embodiment of the present invention, Fig.11 , Fig.12 , Fig.13 As shown, the lower housing assembly 2 includes: a lower housing 12, left and right side covers 15 of the lower housing, and front and rear side covers 16 of the lower housing. Specifically, the left and right side covers 15 of the lower housing include two pieces with the same structure, namely, a left side cover of the lower housing and a right side cover of the lower housing, and the front and rear side covers 16 of the lower housing include two pieces with the same structure, namely, a front side cover of the lower housing and a rear side cover of the lower housing; the left and right side covers 15 of the lower housing and the front and rear side covers 16 of the lower housing are fixed to the lower housing 12 as a whole by welding.

[0053] like Figure 5 As shown, four second bosses 23 are arranged inside the upper shell assembly 1; the second bosses 23 are arranged on the inner side of the upper shell 8 and are located at the corners of the rectangular frame surrounded by the four upper shell side covers 11; Fig.11As shown, four first bosses 21 are arranged inside the lower housing assembly 2; the first bosses 21 are arranged inside the lower housing 12 and located at the four corners of the rectangular frame formed by the front and rear side covers 16 of the lower housing and the left and right side covers 15 of the lower housing. Figure 4 As shown, the control printed circuit board 3 is fixedly mounted on the first boss 21 inside the lower housing assembly 2 by four screws, and the power printed circuit board 4 is fixedly mounted on the second boss 23 inside the upper housing assembly 1 by four screws.

[0054] Furthermore, if Figure 2 , Fig.11 As shown, the two lower shell front and rear side covers 16 of the lower shell assembly 2 are respectively provided with a first side wall hole 19 and a second side wall hole 20; the flight control computer communication electrical connector 5 and the actuator communication electrical connector 6 are respectively fixedly installed in the first side wall hole 19 and the second side wall hole 20 of the lower shell assembly 2 by screws.

[0055] Furthermore, the upper shell component 1 and the lower shell component 2 are filled with PCM phase change material. The working range of the phase change energy storage type thermal control device generally starts from the phase change point until the internal material completes the phase change. The duration of the entire process of phase change heat absorption and energy storage is related to the working time of the steering gear controller, which can be achieved by designing the volume and thermal conductivity of the internally filled phase change medium.

[0056] In a specific embodiment of the present invention, Figure 5 , Figure 6 , Figure 7 As shown, the upper shell assembly 1 also includes: an upper shell top cover 9 and an upper shell inner cover 10; the upper shell top cover 9 and the upper shell inner cover 10 are respectively fixedly mounted on the outer side and the inner side of the upper shell 8, and are arranged parallel to the upper shell 8 to form a three-layer structure, as shown in FIG. Figure 7 Further, Figure 8 , Fig. 9 , Fig.10 As shown, an upper shell inner cavity 27 is provided on the inner side of the upper shell 8, and an upper shell outer cavity 28 is provided on the outer side of the upper shell 8; the upper shell inner cover 10 is fixedly installed on the inner side of the upper shell 8 and can close the upper shell inner cavity 27 to form an upper shell heat absorption chamber; the upper shell top cover 9 is fixedly installed on the outer side of the upper shell 8 and can close the upper shell outer cavity 28 to form an upper shell insulation chamber.

[0057] In a specific embodiment of the present invention, the lower shell assembly 2 further includes: a lower shell top cover 13 and a lower shell inner cover 14; the lower shell top cover 13 and the lower shell inner cover 14 are respectively fixedly mounted on the inner and outer sides of the lower shell 12 and arranged parallel to the lower shell 12, and the three constitute a three-layer structure, such as Fig.13 Further, Fig.14 , Fig.15 , Fig.16 As shown, a lower shell inner cavity 33 is provided on the inner side of the lower shell 12, and a lower shell outer cavity 32 is provided on the outer side of the lower shell 12; the lower shell top cover 13 is fixedly mounted on the outer side of the lower shell 12 and can close the lower shell outer cavity 32 to form a lower shell heat-insulating chamber; the lower shell inner cover 14 is fixedly mounted on the inner side of the lower shell 12 and can close the lower shell inner cavity 33 to form a lower shell heat-absorbing chamber.

[0058] Furthermore, the upper shell side cover 11 is a hollow structure, and the outer end surface thereof is provided with a first upper shell injection hole 24 for filling the phase change medium into the upper shell side cover 11. Specifically, the first upper shell injection hole 24 is provided on the outer end surface of the upper shell side cover 11 and is connected to the internal cavity thereof, and the paraffin phase change medium is filled into the upper shell side cover 11 through the first upper shell injection hole 24.

[0059] Furthermore, if Fig. 9 As shown, the side of the upper shell 8 is also provided with a second upper shell injection hole 25 and a third upper shell injection hole 26 for injecting phase change medium into the upper shell heat absorption chamber and the upper shell insulation chamber of the upper shell assembly 1. Specifically, the third upper shell injection hole 26 is connected from the outer wall of the upper shell 8 to the inner wall of the upper shell outer cavity 28, and the paraffin phase change medium is filled into the upper shell insulation chamber composed of the upper shell top cover 9 and the upper shell outer cavity 28 through the third upper shell injection hole 26. Specifically, the second upper shell injection hole 25 is connected from the outer wall of the upper shell 8 to the inner wall of the upper shell inner cavity 27; the phase change medium composed of paraffin phase change medium and expanded graphite mixed material is filled into the upper shell heat absorption chamber composed of the upper shell inner cover 10 and the upper shell inner cavity 27 through the second upper shell injection hole 25. During implementation, after the upper shell component 1 is filled with the phase change medium, the first upper shell injection hole 24 , the second upper shell injection hole 25 and the third upper shell injection hole 26 are all sealed.

[0060] In this embodiment, the lower shell 12 and the lower shell top cover 13, the lower shell inner cover 14, the lower shell left and right side covers 15 (the upper shell left cover, the upper shell right cover), and the lower shell front and rear side covers 16 (the upper shell front cover, the upper shell rear cover) are all fixed by laser welding, and then the weld quality and air tightness inspection are carried out.

[0061] Furthermore, the left and right side covers 15 of the lower shell and the front and rear side covers 16 of the lower shell are both hollow structures, and the outer end surfaces of the two are both provided with first lower shell injection holes 29 for filling the phase change medium.

[0062] Furthermore, the side of the lower shell 12 is also provided with a second lower shell injection hole 30 and a third lower shell injection hole 31 for injecting phase change medium into the lower shell heat absorption chamber and the lower shell insulation chamber of the lower shell assembly 2. Specifically, the paraffin phase change medium is filled into the inner cavities of the left and right side covers 15 and the front and rear side covers 16 of the lower shell through the first lower shell injection hole 29; the paraffin phase change medium is filled into the lower shell insulation chamber composed of the lower shell top cover 13 and the lower shell inner cavity 32 through the second lower shell injection hole 30; the paraffin phase change medium and expanded graphite mixed material are filled into the lower shell heat absorption chamber composed of the lower shell inner cover 14 and the lower shell inner cavity 33 through the third injection hole 31, and the injection holes are sealed after filling.

[0063] like Figure 5 As shown, four threaded holes 22 are provided at the four corners of the upper housing 8; Fig.12 As shown, four fixing holes 17 are provided at the four corners of the lower shell 12; further, the lower shell assembly 2 is connected to the threaded hole 22 of the upper shell assembly 1 by four countersunk screws passing through the fixing holes 17, thereby achieving a fixed connection between the lower shell assembly 2 and the upper shell assembly 1.

[0064] In this embodiment, the inner cavities of the bottom plates of the upper shell component 1 and the lower shell component 2 are both porous cavity structures; Figure 8 , Fig.10 , Fig.13 , Fig.14 As shown, the surface of the upper shell inner cavity 27 and the lower shell inner cavity 33 is a multi-blade structure composed of a plurality of parallel rectangular thin plates; or, the upper shell inner cavity 27 and the lower shell inner cavity 33 are in a honeycomb form, which increases the contact area between the phase change medium and the shell body, thereby improving the heat exchange efficiency between the phase change medium and the upper shell 8 or the lower shell 12.

[0065] In this embodiment, the heat absorption chamber on the inner side of the bottom plate of the upper shell component 1 and the lower shell component 2 is filled with paraffin phase change medium, and a small amount of expanded graphite is added, which greatly improves the thermal conductivity and can quickly conduct the heat generated by the internal electrical components of the controller to the phase change medium. After reaching the phase change energy storage operating temperature range, the internal phase change medium melts from solid phase to liquid phase and absorbs a large amount of heat, playing an active heat absorption role.

[0066] In this embodiment, the upper shell outer cavity 28 and the lower shell outer cavity 32 of the upper shell assembly 1 and the lower shell assembly 2 are both rectangular cavities, and are filled with paraffin phase change medium; paraffin has a wide phase change temperature range, is non-toxic and non-corrosive, has good chemical stability, negligible supercooling, and a small volume change during phase change, but has a low thermal conductivity, which can isolate the external high-temperature airflow from conducting to the inside of the controller, and mainly plays a heat insulation role.

[0067] Furthermore, the control printed board 3 and the power printed board 4 are in contact with the upper housing 8 or the lower housing 12 using heat-conducting materials such as heat-conducting grease and heat-conducting pads, thereby increasing the heat exchange efficiency between the upper housing assembly 1 and the lower housing assembly 2 and the power device. The printed board design considers ensuring the current carrying capacity of the printed conductors, and a metal heat-conducting mesh strip can be laid on the printed board or a printed board with good thermal conductivity, such as a metal base printed board, can be used.

[0068] The present invention fills the inside of the insulation chamber outside the controller housing with paraffin phase change medium, which can isolate the aerodynamic heat of the cabin wall through radiation heat transfer, and block the external high-temperature air from transferring heat to the inside of the controller through convection heat transfer, absorb the heat transferred to the controller from the outside, and further reduce the temperature inside the controller cavity. It can adapt to a long flight time of 1000s and a high temperature environment of 150°C (induced high temperature test conditions).

[0069] Further, in order to reduce the temperature of the aircraft cabin being transmitted to the controller, in a specific embodiment of the present invention, Figure 1 , Figure 2 , Figure 3 As shown, the high temperature resistant steering gear controller further includes: a heat insulation ring 7; the lower shell assembly 2 is fixedly mounted on the inner side of the aircraft cabin by bolts, and the heat insulation ring 7 is arranged between the lower shell assembly 2 and the aircraft cabin.

[0070] Specifically, the lower housing front and rear side covers 16 of the lower housing assembly 2 are provided with protruding mounting portions, and the mounting portions are provided with mounting holes 18; Fig.12 After the heat insulating ring 7 is installed in the mounting hole 18 of the lower shell assembly 2, the lower shell assembly 2 is fixed to the inner side of the bulkhead by screws; the heat insulating ring 7 has the characteristics of strong bearing capacity and low thermal conductivity.

[0071] Preferably, the heat insulating ring 7 is processed into a ring shape using a composite material with low thermal conductivity. The material of the heat insulating ring 7 can be selected according to the temperature and mechanical environment conditions. Common low thermal conductivity materials for the steering gear controller include ceramic-based composite materials, bismaleimide resin system materials, carbon fiber reinforced carbon composite materials, etc. Using low thermal conductivity materials to make the heat insulating ring 7 can reduce the heat generated by the aerodynamic friction of the cabin wall from being transferred to the controller housing, and prevent the external heat from being transferred to the electrical components inside the controller.

[0072] In a specific implementation of the present invention, the heat-insulating ring 7 is composed of a heat-insulating ring body 34 and a heat-insulating ring cap 35, and the heat-insulating ring body 34 and the heat-insulating ring cap 35 are separate structures.

[0073] Specifically, Fig.17As shown, the middle parts of the heat-insulating ring body 34 and the heat-insulating ring cap 35 are both provided with heat-insulating ring inner holes 37 penetrating the upper and lower end surfaces thereof; the upper end of the heat-insulating ring body 34 is provided with an outer ring 36, the diameter of the outer ring 36 is smaller than the diameter of the heat-insulating ring body 34 and can be inserted into the mounting hole 18 of the lower shell assembly 2. Specifically, bolts are installed in the heat-insulating ring inner holes 37 to connect and fix the lower shell assembly 2, the heat-insulating ring 7 and the aircraft cabin.

[0074] That is to say, the outer diameter of the outer ring 36 of the insulation ring body 34 is less than or equal to the diameter of the mounting hole 18; the inner diameter of the outer ring 36 of the insulation ring body 34 is greater than or equal to the outer diameter of the bolt stud, that is, the diameter of the insulation ring inner hole 37 is greater than or equal to the diameter of the bolt stud.

[0075] Specifically, Fig.17 As shown, the heat insulation ring cap 35 is a circular ring structure.

[0076] When in use, the insulation ring cap 35 and the insulation ring body 34 are respectively arranged on the upper and lower sides of the mounting part of the lower shell assembly 2, and the outer ring 36 is inserted into the mounting hole 18 on the lower shell assembly 2 of the controller, and then the screws are successively passed through the insulation ring cap 35 and the insulation ring inner hole 37 of the insulation ring body 34 and screwed together with the aircraft cabin through threads, so as to fix the controller and the insulation ring together on the inner wall of the aircraft cabin.

[0077] Furthermore, after the controller housing is designed and produced, the thermal protection performance can be verified through an induced high temperature test. The induced high temperature test conditions can generally be determined through the following process: first, the aerodynamic thermal conditions of the bulkhead during flight are obtained through thermal simulation calculations, and secondly, the equivalent induced high temperature test conditions are obtained through temperature control tests that comprehensively consider the aerodynamic heat of the flight bulkhead and the working conditions of the servo battery. The induced high temperature test can be carried out directly in an incubator, and the thermal protection performance can be verified by collecting the temperature inside the controller in real time through a temperature chip pre-set inside the controller. The controller of this embodiment has been verified by an induced high temperature test with a long flight time of 1500s and a high temperature environment of 150°C. The internal temperature of the controller can be controlled within 85°C throughout the entire process, meeting the operating temperature range of all internal electronic components.

[0078] In this embodiment, the components of the high-temperature resistant servo controller for the aircraft generally have a maximum operating temperature of 120°C. It has been verified that after comprehensively considering the time of the phase change process and the heat transfer process, the initial operating temperature zone of the PCM material on the outside of the upper shell component 1 and the lower shell component 2 is designed to be 110°C; the components generally require a long-term operating temperature below 85°C. It has been verified that the initial operating temperature zone of the PCM material on the inside of the upper shell component 1 and the lower shell component 2 is designed to be 80°C.

[0079] Compared with the prior art, the technical solution provided by this embodiment has at least one of the following beneficial effects:

[0080] 1. The high temperature resistant steering gear controller proposed in the present invention has an integrated design with three characteristics of heat insulation, heat absorption and load bearing. The traditional controller housing is changed into a thermal protection and structural integration, realizing the two functions of structural load bearing and thermal protection in a limited space, which can solve the problem of the existing steering gear controller working for a long time in a high temperature environment without a heat dissipation path. The present invention has a compact structure, optimized process, and can realize the internal circuit of the steering gear controller to work for a long time in a high temperature environment without a heat dissipation path.

[0081] 2. The present invention proposes a high temperature resistant steering gear controller, the outer side of the upper shell component 1 and the lower shell component 2 are designed with a heat insulation chamber, and the inside of the heat insulation chamber is filled with paraffin phase change medium, the phase change medium has a low thermal conductivity and can absorb heat and store energy through phase change to reduce the heating effect of the upper shell 8 and the lower shell 12, and can isolate the external high temperature air flow from conducting to the inside of the controller, mainly playing a heat insulation role. In this embodiment, by setting a double-layer shell integrated design with an outer layer of phase change medium for heat insulation and an inner layer of phase change medium for heat absorption, the control printed board 3 and the power printed board 4 can be protected within the normal operating temperature range.

[0082] 3. In this embodiment, a mixed phase change medium composed of paraffin and expanded graphite is filled in the heat absorption chamber inside the upper shell component 1 and the lower shell component 2 to absorb heat, and the phase change medium absorbs the heat generated by the internal components of the controller; at the same time, in order to improve the heat exchange efficiency between the phase change medium inside the upper shell component 1 and the lower shell component 2 and the shell, a small amount of expanded graphite is added to the paraffin phase change medium to improve the thermal conductivity; at the same time, the cavity inside the upper shell component 1 and the lower shell component 2 is processed into a multi-blade or honeycomb form to increase the contact area between the phase change medium and the controller shell, so as to absorb the heat generated by the internal components of the controller; the above two measures are adopted to improve the heat exchange efficiency between the internal heating components of the controller and the controller shell, and reduce the working temperature of the electrical components.

[0083] 4. In this embodiment, the heat insulation ring 7 installed between the lower shell assembly 2 and the main structure of the cabin can reduce the heat of the aerodynamic friction of the cabin wall from being transferred to the controller housing. The heat insulation ring 7 is made of a composite material with low thermal conductivity and processed into a ring shape, and has the characteristics of strong bearing capacity and low thermal conductivity.

[0084] Example 2

[0085] In a specific embodiment of the present invention, in order to further reduce the heat transfer from the aircraft cabin to the controller housing, the thermal insulation ring 7 in Example 1 is further improved.

[0086] In this embodiment, Fig.18 , Fig.19As shown, a plurality of convex structures 39 in an annular array are arranged on the upper end surface of the insulation ring body 34, and a plurality of insulation grooves 40 are arranged on the lower surface of the insulation ring body 34; the convex structure 39 on the upper end surface of the insulation ring body 34 is in direct contact with the lower surface of the mounting portion of the lower shell assembly 2.

[0087] Preferably, a convex structure 39 is also provided on the lower end surface of the heat-insulating ring cap 35 , and the convex structure 39 contacts the upper surface of the mounting portion of the lower housing assembly 2 (not shown in the figure).

[0088] Preferably, if Fig.18 As shown, the convex structure 39 is a hemispherical protrusion. In this embodiment, by setting the convex structure 39 to contact the lower surface of the mounting portion, the annular surface contact between the lower shell component 2 and the insulation ring body 34 is replaced by point contact with multiple contact points, which can greatly reduce the heat transferred from the aircraft cabin to the controller housing; at the same time, when the aircraft cabin structure is subjected to external impact, the impact load can be buffered by the deformation of the convex structure 39 during the transmission of the lower shell component 2, which is conducive to maintaining the performance stability of the controller.

[0089] Furthermore, if Fig.19 As shown, the lower surface of the heat-insulating ring body 34 is provided with heat-insulating grooves 40 which are evenly spaced along the circumferential direction of the heat-insulating ring inner hole 37; preferably, the heat-insulating grooves 40 are semicircular grooves, and the heat-insulating grooves 40 extend along the radial direction of the heat-insulating ring body 34 to communicate with the heat-insulating ring inner hole 37. When in use, the setting of the heat-insulating grooves 40 divides the lower surface of the heat-insulating ring body 34 into a plurality of small-area fan-shaped planes, and the fan-shaped plane at the lower end of the heat-insulating ring body 34 contacts the aircraft cabin, thereby reducing the heat transfer from the aircraft cabin to the heat-insulating ring 7.

[0090] Furthermore, if Fig.18 , Fig.19 As shown, a plurality of inner hole ridges 38 are provided on the inner wall surface of the inner hole 37 of the thermal insulation ring; preferably, the inner hole ridges 38 are semi-cylindrical ridges. The plurality of inner hole ridges 18 are distributed at equal intervals in the circumferential direction of the inner hole 37 of the thermal insulation ring. In this embodiment, by providing the inner hole ridges 38 on the inner wall surface of the inner hole 37 of the thermal insulation ring, the plurality of inner hole ridges 38 are in contact with the bolts connecting the controller housing and the aircraft cabin, and the cylindrical surface contact between the inner hole 37 of the thermal insulation ring and the bolts is replaced by a plurality of spaced line contacts, thereby reducing the heat exchange between the inner hole 37 of the thermal insulation ring and the bolts and studs.

[0091] Example 3

[0092] In order to improve the absorption efficiency and heat absorption capacity of the phase change medium filled inside the controller housing to the heat generated by the heating device; in this embodiment, the inner cavity 27 of the upper housing and the inner cavity 33 of the lower housing in Embodiment 1 are improved and designed:

[0093] In this embodiment, a heat absorbing network structure 41 is provided in the inner cavity 27 of the upper shell and the inner cavity 33 of the lower shell; Fig. 20 , Fig.21 As shown, in this embodiment, the heat absorption network structure 41 is composed of a plurality of heat absorption cells distributed in an array; a plurality of heat absorption cells are arranged in both the lateral and longitudinal directions and are connected in sequence, and the heat absorption network structure 41 as a whole is a metal structure with a plurality of branched support rods, and the heat absorption network structure 41 is filled in the upper shell heat absorption chamber composed of the inner cavity 27 of the upper shell and the inner cover 10 of the upper shell, and the lower shell heat absorption chamber composed of the inner cavity 33 of the lower shell and the inner cover 14 of the lower shell, so as to realize uniform and equivalent transfer to the phase change medium of the upper shell heat absorption chamber and the lower shell heat absorption chamber, so that the phase change medium in the heat absorption chamber can fully participate in heat exchange and absorb heat, thereby avoiding the rapid temperature rise caused by the short-time power heating of the internal components of the controller.

[0094] Preferably, the heat absorption network structure 41 is bonded to the inner wall surfaces of the upper shell inner cover 10 and the lower shell inner cover 14 by means of heat conductive adhesive.

[0095] Preferably, the heat-absorbing network structure 41 is made of metal aluminum or aluminum alloy with high thermal conductivity and high specific heat capacity.

[0096] Furthermore, if Fig. 22 As shown, the heat absorption cell includes: a center ring 42, connecting rods 43 and support rods 45; a plurality of connecting rods 43 integrally formed with the center ring 42 are evenly spaced on the outer circumferential arc surface of the center ring 42; a plurality of inclined support rods 45 are arranged on the upper and lower sides of the center ring 42, and a plurality of support rods 54 are evenly spaced along the circumferential direction of the center hole of the center ring 42.

[0097] Preferably, the center ring 42 is a drum-shaped structure with chamfered or rounded edges, such as Fig. 22 shown.

[0098] Preferably, the angle between the axis of the support rod 45 and the axis of the center ring 42 is 45° to 60°.

[0099] Preferably, one or more layers of heat absorption network structure 41 are arranged according to the internal space height of the upper shell heat absorption chamber and the lower shell heat absorption chamber. During implementation, by adjusting the inclination angle and length of the support rods 45, the support rods 45 on both sides of the center ring 42 can contact the wall surface of the upper shell assembly 1 or the lower shell assembly 2.

[0100] Preferably, the number of the support rods 45 on one side of the central ring 42 of a heat absorbing cell is three, four or five.

[0101] Preferably, four connecting rods 43 are arranged outside the center ring 42, and the four connecting rods 43 are arranged at intervals of 90 degrees. Fig. 20 , Fig. 22 shown.

[0102] Preferably, the outer diameter of the center ring 42 is not greater than 3 mm; the diameters of the support rods 45 and the connecting rods 43 are not greater than 1 mm.

[0103] Furthermore, in this embodiment, the connecting rods 43 of two adjacent heat absorbing cells are connected.

[0104] Preferably, two heat absorbing cells adjacent to each other front to back or left to right share a connecting rod 43, such as Fig. 20 , Fig.21 During implementation, by adjusting the spacing between adjacent heat absorbing cells and adjusting the arrangement density of the heat absorbing cells, the heat inside the controller is efficiently transferred to the phase change medium, thereby ensuring the storage capacity of the phase change medium in the heat absorbing chamber, and thus ensuring the heat storage capacity of the heat absorbing chamber of the controller housing.

[0105] Furthermore, a convex ring 44 having a diameter greater than that of the connecting rod 43 is provided on the outside of the connecting rod 43. Preferably, one or more convex rings 44 are provided on the connecting rod 43; and the diameter of the convex ring 44 is not greater than 2 mm. In this embodiment, by adjusting the length, diameter and number of the convex rings 44, the space occupied by the heat absorption network structure 41 in the heat absorption chamber is adjusted to achieve a reasonable ratio of the volume of the heat absorption network structure 41 and the phase change medium. Under the premise of achieving good heat conduction efficiency, as much phase change medium as possible is filled to improve the heat storage performance of the heat absorption chamber.

[0106] In this embodiment, by providing a heat absorption network structure 41 composed of a plurality of heat absorption cells, the contact area between the phase change medium and the metal shell can be increased, and the heat absorption network structure 41 can divide the heat absorption chamber into a plurality of tiny porous cavities to form a honeycomb-like structure, thereby improving the rapid transfer of heat from the heating device to the heat absorption phase change medium. At the same time, since the plurality of cavities are interconnected, the entire heat absorption cavity can be filled from one injection hole when the phase change medium is injected.

[0107] In this embodiment, the heat absorption network structure 41 is integrally formed by 3D printing technology. The arrangement density of the heat absorption cells in the heat absorption network structure 41 and the specific structural dimensions of each part of the heat absorption cells can be simulated by finite element simulation analysis software to obtain the optimal solution. 3D printing technology and finite element simulation analysis are mature auxiliary molding tools and analysis tools, and do not belong to the improved design of this embodiment, and will not be described in detail in this embodiment.

[0108] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A high temperature resistant steering gear controller, characterized in that: include: An upper housing component (1), a lower housing component (2), a control printed circuit board (3), a power printed circuit board (4), a flight control computer communication electrical connector (5) and an actuator communication electrical connector (6); the control printed circuit board (3) and the power printed circuit board (4) are respectively fixedly mounted inside the upper housing component (1) and the lower housing component (2); the flight control computer communication electrical connector (5) and the actuator communication electrical connector (6) are both fixedly mounted on the side wall of the lower housing component (2); the bottom plate and four side plates of the upper housing component (1) and the lower housing component (2) are filled with phase change medium.

2. The high temperature resistant steering gear controller according to claim 1, characterized in that: The upper shell assembly (1) comprises: an upper shell (8) and four upper shell side covers (11) of the same structure; the four upper shell side covers (11) are respectively fixedly mounted on four side surfaces of the upper shell (8) and are arranged perpendicular to the upper shell (8).

3. The high temperature resistant steering gear controller according to claim 2, characterized in that: The upper shell assembly (1) further comprises: an upper shell top cover (9) and an upper shell inner cover (10); an upper shell inner cavity (27) is arranged on the inner side of the upper shell (8), and an upper shell outer cavity (28) is arranged on the outer side of the upper shell (8); the upper shell inner cover (10) is fixedly mounted on the inner side of the upper shell (8) and is capable of closing the upper shell inner cavity (27) to form an upper shell heat absorption chamber; the upper shell top cover (9) is fixedly mounted on the outer side of the upper shell (8) and is capable of closing the upper shell outer cavity (28) to form an upper shell heat insulation chamber.

4. The high temperature resistant steering gear controller according to any one of claims 1 to 3, characterized in that: The lower housing assembly (2) comprises: a lower housing (12), left and right side covers (15) of the lower housing, and front and rear side covers (16) of the lower housing.

5. The high temperature resistant steering gear controller according to claim 4, characterized in that: The lower shell assembly (2) further comprises: a lower shell top cover (13) and a lower shell inner cover (14); a lower shell inner cavity (33) is arranged on the inner side of the lower shell (12), and a lower shell outer cavity (32) is arranged on the outer side of the lower shell (12); the lower shell top cover (13) is fixedly mounted on the outer side of the lower shell (12) and is capable of closing the lower shell outer cavity (32) to form a lower shell heat insulation chamber; the lower shell inner cover (14) is fixedly mounted on the inner side of the lower shell (12) and is capable of closing the lower shell inner cavity (33) to form a lower shell heat absorption chamber.

6. The high temperature resistant steering gear controller according to claim 2 or 3, characterized in that: The upper shell side cover (11) is a hollow structure, and its outer end surface is provided with a first upper shell injection hole (24) for filling the interior of the upper shell side cover (11) with a phase change medium.

7. The high temperature resistant steering gear controller according to claim 6, characterized in that: The side surface of the upper shell (8) is also provided with a second upper shell injection hole (25) and a third upper shell injection hole (26) for injecting phase change medium into the upper shell heat absorption chamber and the upper shell insulation chamber of the upper shell assembly (1).

8. The high temperature resistant steering gear controller according to claim 5, characterized in that: The left and right side covers (15) of the lower shell and the front and rear side covers (16) of the lower shell are both hollow structures, and the outer end surfaces of both are provided with a first lower shell injection hole (29) for filling the phase change medium.

9. The high temperature resistant steering gear controller according to claim 8, characterized in that: The side surface of the lower shell (12) is also provided with a second lower shell injection hole (30) and a third lower shell injection hole (31) for injecting phase change medium into the lower shell heat absorption chamber and the lower shell heat insulation chamber of the lower shell assembly (2).

10. The high temperature resistant steering gear controller according to any one of claims 1-3, 5, 7-9, characterized in that: Also includes: The heat insulation ring (7) is fixedly mounted on the inner side of the aircraft cabin by means of bolts, and the heat insulation ring (7) is arranged between the lower shell component (2) and the aircraft cabin.

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