Low-temperature heating device for aviation electromechanical instrument

Abstract

The utility model discloses an aviation electromechanical instrument low-temperature heating device which comprises an installation seat, the two ends of the top of the installation seat are fixedly connected with fixing blocks, pin grooves are formed in the surfaces of the fixing blocks, L-shaped clamping grooves are formed in the periphery of the installation seat, and an aviation electromechanical instrument body is fixedly installed at the bottom of an inner cavity of the installation seat. A temperature relay is fixedly installed at the upper end of the left side of an inner cavity of the aviation electromechanical instrument body, and an armored heating wire is fixedly installed at the middle end of the outer surface of the aviation electromechanical instrument body. According to the utility model, through the arrangement of the armored heating wire and the temperature relay, when the temperature in the aviation electromechanical instrument main body is lower than the lower limit temperature threshold of the temperature relay, the temperature relay switches on the circuit of the armored heating wire, so that the periphery of the aviation electromechanical instrument main body can be effectively heated; and the influence of the low-temperature environment on the normal work of the aviation electromechanical instrument main body is effectively avoided.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation electromechanical instrument technical field, concretely to a kind of aviation electromechanical instrument low temperature heating device. BACKGROUND

[0002] The existing aviation machinery or electromechanical instrument generally adopts diaphragm, corrugated pipe, bag end pipe as sensitive element output displacement, and utilizes gear set or connecting rod, sector gear mechanism to transmit and amplify displacement, finally displays through pointer, dial or outputs electric signal through component, and the low temperature working and storage temperature of aviation instrument is generally-55 degrees Celsius, compared with normal temperature (15-35 degrees Celsius) environment, low temperature can cause a series of adverse effects.

[0003] For example, Chinese utility model provides "a kind of aviation machinery or electromechanical instrument low temperature heating device", announcement number: CN221652792U, the application includes: shell, heater, fixed layer and lower limit temperature relay;Shell is cylindrical, and is connected with aviation machinery or electromechanical instrument, and recess is milled on circumferential side for fixing heater, lower limit temperature relay is fixed at inside position, and external potting fixed layer;Lower limit temperature relay is always open, and is connected in series with heater, lower limit temperature relay is used to automatically close when detecting that the temperature in shell is lower than lower limit temperature threshold, starts heater to heat, utilizes low temperature heating device, installation in aviation machinery or electromechanical instrument inside, simple structure, compact size, reliable work, convenient maintenance.

[0004] Although the aviation machinery or electromechanical instrument low temperature heating device in the above-mentioned technology can heat the aviation electromechanical instrument through the heater, but when the heater is damaged during long-term use, the worker cannot replace it individually, and the whole device and the aviation electromechanical instrument need to be disassembled, which increases the maintenance cost and difficulty. UTILITY MODEL CONTENTS

[0005] The utility model aims at providing an aviation electromechanical instrument low temperature heating device, which can heat the aviation electromechanical instrument, and the heater can be replaced individually when it is damaged, which is convenient and fast to operate, and reduces the cost and difficulty of maintenance.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a low-temperature heating device for aviation electromechanical instruments, comprising a mounting base, with fixing blocks fixedly connected to both ends of the top of the mounting base, pin grooves formed on the surface of the fixing blocks, and L-shaped slots formed around the perimeter of the mounting base. An aviation electromechanical instrument body is fixedly mounted at the bottom of the inner cavity of the mounting base. A temperature relay is fixedly mounted at the upper left end of the inner cavity of the aviation electromechanical instrument body. An armored heating wire is fixedly mounted at the middle of the outer surface of the aviation electromechanical instrument body. An external protective cylinder is movably connected between the outer surface of the aviation electromechanical instrument body and the inner cavity of the mounting base. Locking blocks are fixedly connected around the lower perimeter of the outer surface of the external protective cylinder, and the surfaces of the locking blocks are movably connected to the surfaces of the L-shaped slots. Receiving holes are formed at the lower ends of both sides of the outer surface of the external protective cylinder. Pin blocks are movably connected between the surfaces of the receiving holes and the pin grooves, and support springs are fixedly connected between the surfaces of the pin blocks and the receiving holes.

[0007] As a preferred embodiment, the outer protective cylinder has a receiving cavity at its middle end, and an insulating cotton sleeve is fixedly connected to the surface of the receiving cavity.

[0008] As a preferred embodiment, both ends of the receiving hole are fixedly connected to guide slide rods, and both ends of the pin block are provided with guide holes, the surface of the guide holes being movably connected to the surface of the guide slide rods.

[0009] As a preferred embodiment, mounting holes are provided around the mounting base, and mounting bolts are movably connected to the surface of the mounting holes.

[0010] As a preferred embodiment, a rubber pad is fixedly connected to the bottom of the inner cavity of the mounting base, and the bottom of the outer protective cylinder is movably connected to the top of the rubber pad.

[0011] As a preferred embodiment, a rubber ring is fixedly connected to the upper end of the inner cavity of the outer protective cylinder, and the surface of the rubber ring is movably connected to the upper end of the outer surface of the aircraft electromechanical instrument body.

[0012] As a preferred embodiment, a pressure rod is fixedly connected to the surface of the pin block and the side away from the support spring.

[0013] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0014] 1. The utility model discloses a heating wire and temperature relay's setting, when the temperature of the aviation electromechanical instrument main part inside is lower than the lower limit temperature threshold of temperature relay, temperature relay will connect the circuit of the armored heating wire, and can effectively heat the surrounding of the aviation electromechanical instrument main part, effectively avoid the influence of low temperature environment on the normal work of the aviation electromechanical instrument main part, and through the setting of the external protection cylinder, the effective safety protection can be carried out around the armored heating wire, avoid the armored heating wire from being damaged by the direct collision of object in the process of using, and through the setting of L-shaped clamping groove, clamping block, fixed block, pin slot, pin block, accommodating hole and supporting spring, the effective limiting fixing between the external protection cylinder and mounting seat can be carried out, the external protection cylinder is prevented from loosening in the process of using, and personnel can carry out separate replacement operation when the armored heating wire is damaged, the overall operation is convenient and fast, and the cost and difficulty of later replacement maintenance operation are effectively reduced.

[0015] 2. The utility model discloses the setting of accommodating cavity and heat preservation cotton cover forms good heat preservation protection in the inside of external protection cylinder, effectively reduces the influence of external low temperature on the aviation electromechanical instrument main part, and the probability of temperature loss to the outside environment in the working process of armored heating wire is reduced, through the setting of guide slide rod and guide hole, the purpose of guiding pin block is reached, avoids the pin block from separating from the inside of accommodating hole, through the setting of mounting hole and mounting bolt, personnel can install and fix mounting seat, through the setting of rubber pad, the sealing property of the contact between the bottom of external protection cylinder and mounting seat is effectively improved, through the setting of rubber ring, the sealing property of the contact between external protection cylinder and aviation electromechanical instrument main part is effectively improved, through the setting of pressure rod, personnel can press and push pin block in the process of maintenance. ACCURACY OF DRAWINGS

[0016] Figure 1 It is the perspective view of the utility model;

[0017] Figure 2 It is the utility model Figure 1 A place partial close -up in;

[0018] Figure 3 It is the front cross section structure schematic diagram of the utility model;

[0019] Figure 4 It is the fixed block side cross section structure schematic diagram of the utility model.

[0020] In the figure: 1, the main body of the aviation electromechanical instrument; 2, the outer protective cylinder; 3, the mounting hole; 4, the mounting seat; 5, the L-shaped clamping groove; 6, the clamping block; 7, the pin groove; 8, the pressing rod; 9, the fixed block; 10, the pin block; 11, the rubber ring; 12, the containing cavity; 13, the temperature relay; 14, the thermal insulation cotton sleeve; 15, the armored heating wire; 16, the rubber pad; 17, the supporting spring; 18, the containing hole; 19, the guide slide rod; 20, the guide hole. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0022] Secondly, the "one embodiment" or "embodiment" referred to herein means that the specific features, structures or characteristics can be included in at least one implementation of the utility model. The "in one embodiment" appearing in different places in the specification does not mean the same embodiment, nor is it an embodiment that is independent of or selected from other embodiments.

[0023] Embodiment one:

[0024] Please refer to Figures 1-4 As shown in the figure, the utility model provides a kind of aviation electromechanical instrument low temperature heating device, including mounting seat 4, the top of mounting seat 4 Both ends are fixedly connected with fixed block 9, pin groove 7 is established on the surface of fixed block 9, L-shaped clamping groove 5 is established in the periphery of mounting seat 4, aviation electromechanical instrument main body 1 is fixedly installed in the bottom of the inner chamber of mounting seat 4, temperature relay 13 is fixedly installed in the upper end of left side in the inner chamber of aviation electromechanical instrument main body 1, armored heating wire 15 is fixedly installed in the middle end of outer surface of aviation electromechanical instrument main body 1, outer protective cylinder 2 is movably connected between the outer surface of aviation electromechanical instrument main body 1 and the inner chamber of mounting seat 4, clamping block 6 is fixedly connected in the periphery of the lower end of outer surface of outer protective cylinder 2, the surface of clamping block 6 is movably connected to the surface of L-shaped clamping groove 5, containing hole 18 is established in the lower end of both sides of outer surface of outer protective cylinder 2, pin block 10 is movably connected between the surface of containing hole 18 and the surface of pin groove 7, supporting spring 17 is fixedly connected between the surface of pin block 10 and the surface of containing hole 18.

[0025] The temperature relay 13 is connected to the circuit of the armored heating wire 15 when the temperature inside the main body 1 of the aeronautical electromechanical instrument is lower than the lower limit temperature threshold of the temperature relay 13, so that the surrounding of the main body 1 of the aeronautical electromechanical instrument can be effectively heated, and the influence of the low temperature environment on the normal work of the main body 1 of the aeronautical electromechanical instrument is effectively avoided. Meanwhile, the external protection cylinder 2 is arranged around the armored heating wire 15 to effectively protect the armored heating wire 15 from being damaged by direct collision with objects during use. The L-shaped clamping groove 5, the clamping block 6, the fixed block 9, the pin slot 7, the pin block 10, the accommodating hole 18 and the supporting spring 17 are arranged to effectively limit and fix the external protection cylinder 2 and the mounting seat 4, so that the external protection cylinder 2 is not loosened during use, and the damaged armored heating wire 15 can be replaced individually, which is convenient and fast and effectively reduces the cost and difficulty of the later replacement and maintenance work.

[0026] Embodiment two:

[0027] On the basis of the embodiment one, the utility model discloses as shown in Figures 1-4 the middle end of the external protection cylinder 2 is provided with a containing cavity 12, the surface of the containing cavity 12 is fixedly connected with a heat preservation cotton cover 14, the two ends of the accommodating hole 18 are fixedly connected with a guide sliding rod 19, the two ends of the pin block 10 are provided with a guide hole 20, the surface of the guide hole 20 is movably connected to the surface of the guide sliding rod 19, the periphery of the mounting seat 4 is provided with a mounting hole 3, the surface of the mounting hole 3 is movably connected with a mounting bolt, the bottom of the inner cavity of the mounting seat 4 is fixedly connected with a rubber pad 16, the bottom of the external protection cylinder 2 is movably connected to the top of the rubber pad 16, the upper end of the inner cavity of the external protection cylinder 2 is fixedly connected with a rubber ring 11, the surface of the rubber ring 11 is movably connected to the upper end of the outer surface of the aeronautical electromechanical instrument main body 1, and the surface of the pin block 10 and the side away from the supporting spring 17 are fixedly connected with a pressing rod 8.

[0028] The application has the advantages that the accommodation cavity 12 and the heat preservation cotton sleeve 14 are arranged, good heat preservation is formed in the inside of the external protection cylinder 2, the influence of the low temperature outside on the aviation electromechanical instrument body 1 is reduced, the temperature loss of the armored heating wire 15 to the outside environment in the working process is reduced, the guiding slide rod 19 and the guiding hole 20 are arranged, the guiding purpose of the pin block 10 is achieved, the pin block 10 is prevented from being separated from the inside of the accommodation hole 18, the mounting hole 3 and the mounting bolt are arranged, the mounting seat 4 is conveniently installed and fixed, the rubber pad 16 is arranged, the sealing property of the contact between the bottom of the external protection cylinder 2 and the mounting seat 4 is effectively improved, the rubber ring 11 is arranged, the sealing property of the contact between the external protection cylinder 2 and the aviation electromechanical instrument body 1 is effectively improved, and the pressure rod 8 is arranged, so that the pin block 10 is conveniently pressed and pushed in the maintenance process.

[0029] The working principle of the utility model discloses is: through the arrangement of armored heating wire 15 and temperature relay 13, when the temperature inside aviation electromechanical instrument body 1 is lower than the lower limit temperature threshold (0 degrees Celsius) of temperature relay 13, temperature relay 13 will connect the circuit of armored heating wire 15, and the surrounding of aviation electromechanical instrument body 1 can be effectively heated and warmed, effectively avoiding the influence of low temperature environment on the normal work of aviation electromechanical instrument body 1, and through the arrangement of external protection cylinder 2, the surrounding of armored heating wire 15 can be effectively protected, armored heating wire 15 is prevented from being damaged due to direct collision with objects in the use process, and through the arrangement of L-shaped clamping groove 5, clamping block 6, fixed block 9, pin slot 7 and pin block 10, external protection cylinder 2 and mounting seat 4 can be effectively limited and fixed, external protection cylinder 2 is prevented from being loosened in the use process, and when armored heating wire 15 needs to be replaced due to damage in the long-term use process, pin block 10 is pressed and moved to compress support spring 17 in accommodation hole 18, until pin block 10 is separated from the surface of pin slot 7, then external protection cylinder 2 and clamping block 6 are pulled and moved upwards to be separated from the surface of L-shaped clamping groove 5, mounting seat 4 and aviation electromechanical instrument body 1, so that armored heating wire 15 can be exposed in the environment, armored heating wire 15 is conveniently replaced, the whole operation is convenient and fast, and the cost and difficulty of the later replacement and maintenance operation are effectively reduced.

[0030] It should be explained finally that the above embodiment is only used to illustrate the technical scheme of the utility model, and is not the limit of the protection scope of the utility model, although the utility model is explained in detail with reference to the preferred embodiment, the ordinary skilled in the art should understand that the technical scheme of the utility model can be modified or replaced equivalently, and does not deviate from the essence and scope of the technical scheme of the utility model.

Claims

1. An aircraft electromechanical instrument low temperature heating device comprising a mounting base (4), characterised in that: The both ends of top of mounting seat (4) are fixedly connected with fixed block (9), the surface of fixed block (9) is equipped with pin slot (7), the periphery of mounting seat (4) is equipped with L-shaped clamping slot (5), the bottom of inner chamber of mounting seat (4) is fixedly installed with aeronautical electromechanical instrument body (1), the upper end of left side in inner chamber of aeronautical electromechanical instrument body (1) is fixedly installed with temperature relay (13), the middle end of outer surface of aeronautical electromechanical instrument body (1) is fixedly installed with armored heating wire (15), the outer surface of aeronautical electromechanical instrument body (1) and the inner chamber of mounting seat (4) are movably connected with external protection cylinder (2), the periphery of lower end of outer surface of external protection cylinder (2) is fixedly connected with clamping block (6), the surface of clamping block (6) is movably connected to the surface of L-shaped clamping slot (5), the lower end of both sides of outer surface of external protection cylinder (2) is equipped with accommodating hole (18), the surface of accommodating hole (18) and the surface of pin slot (7) are movably connected with pin block (10), the surface of pin block (10) and the surface of accommodating hole (18) are fixedly connected with supporting spring (17).

2. An aircraft electromechanical instrument low temperature heating device according to claim 1, characterized in that: The middle end of external protection cylinder (2) is equipped with accommodating cavity (12), the surface of accommodating cavity (12) is fixedly connected with thermal insulation cotton cover (14).

3. An aircraft electromechanical instrument low temperature heating device according to claim 1, characterized in that: The both ends of accommodating hole (18) are fixedly connected with guide sliding rod (19), the both ends of pin block (10) are equipped with guide hole (20), the surface of guide hole (20) is movably connected to the surface of guide sliding rod (19).

4. An aircraft electromechanical instrument low temperature heating device according to claim 1, characterized in that: The periphery of mounting seat (4) is equipped with mounting hole (3), the surface of mounting hole (3) is movably connected with mounting bolt.

5. An aircraft electromechanical instrument low temperature heating device as claimed in claim 1, characterized in that: The bottom of mounting seat (4) is fixedly connected with rubber pad (16), the bottom of external protection cylinder (2) is movably connected to the top of rubber pad (16).

6. An aircraft electromechanical instrument low temperature heating device according to claim 1, characterized in that: The upper end of inner chamber of external protection cylinder (2) is fixedly connected with rubber ring (11), the surface of rubber ring (11) is movably connected to the upper end of outer surface of aeronautical electromechanical instrument body (1).

7. An aircraft electromechanical instrument low temperature heating device as claimed in claim 1, characterized in that: The surface of pin block (10) and the side away from supporting spring (17) are fixedly connected with pressing rod (8). The both ends of top of mounting seat (4) are fixedly connected with fixed block (9), the surface of fixed block (9) is equipped with pin slot (7), the periphery of mounting seat (4) is equipped with L-shaped clamping slot (5), the bottom of inner chamber of mounting seat (4) is fixedly installed with aeronautical electromechanical instrument body (1), the upper end of left side in inner chamber of aeronautical electromechanical instrument body (1) is fixedly installed with temperature relay (13), the middle end of outer surface of aeronautical electromechanical instrument body (1) is fixedly installed with armored heating wire (15), the outer surface of aeronautical electromechanical instrument body (1) and the inner chamber of mounting seat (4) are movably connected with external protection cylinder (2), the periphery of lower end of outer surface of external protection cylinder (2) is fixedly connected with clamping block (6), the surface of clamping block (6) is movably connected to the surface of L-shaped clamping slot (5), the lower end of both sides of outer surface of external protection cylinder (2) is equipped with accommodating hole (18), the surface of accommodating hole (18) and the surface of pin slot (7) are movably connected with pin block (10), the surface of pin block (10) and the surface of accommodating hole (18) are fixedly connected with supporting spring (17).

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