阅读说明：本技术 飞机气候环境实验室用宽温域大截面直通式通风装置 (Wide-temperature-range large-section straight-through type ventilation device for airplane climate environment laboratory ) 是由 王彬文 成竹 吴敬涛 马建军 刘海燕 于 2021-11-18 设计创作，主要内容包括：本发明公开了飞机气候环境实验室用宽温域大截面直通式通风装置,包括：用于搭载各个构件的壳体、用于配合动叶片进行风口大小调节的静叶片、用于转动调节与静叶片相对夹角的动叶片、用于吊装动叶片的吊杆组件、用于承载吊杆组件以及动叶片的承载横梁以及用于操控动叶片转动的气动执行机构。本发明通风装置采用动叶片悬浮式设计,可降低动叶片与静叶片的摩擦,防止在模拟飞机低温气候时,动叶片出现冻结的情况,在极端气候条件下可正常工作,可以满足不同温度下飞机气候环境模拟的需要。(The invention discloses a wide-temperature-range large-section straight-through type ventilation device for an aircraft climate environment laboratory, which comprises: the air inlet adjusting device comprises a shell for carrying various components, a fixed blade for matching with the moving blade to adjust the size of an air inlet, a moving blade for rotating and adjusting an included angle relative to the fixed blade, a suspender component for hoisting the moving blade, a bearing cross beam for bearing the suspender component and the moving blade and a pneumatic actuating mechanism for controlling the moving blade to rotate. The ventilation device adopts a moving blade suspension design, can reduce the friction between the moving blades and the static blades, prevents the moving blades from being frozen when the low-temperature climate of the airplane is simulated, can normally work under extreme climate conditions, and can meet the requirement of the climate environment simulation of the airplane at different temperatures.)

1. Aircraft climate environment laboratory is with wide temperature range big cross-section through formula ventilation unit, its characterized in that includes: the air inlet adjusting device comprises a shell (1) for carrying various components, stationary blades (2) and moving blades (3) which are used for being matched with each other to adjust the size of an air inlet, a suspender assembly (4) for hoisting the moving blades (3), a bearing cross beam (5) for bearing the suspender assembly (4) and the moving blades (3), and a pneumatic actuator (6) for controlling the moving blades (3) to rotate;

the suspender component (4) comprises a suspender (41), a suspender top limiting pin (42) and a carrying ring for reducing the friction coefficient of the suspender (41) and the carrying beam (5), wherein the suspender top limiting pin (42) is arranged at the top of the suspender (41) and is used for enabling the suspender (41) to be suspended and supported on the carrying beam (5), and the carrying ring is sleeved on the suspender (41) between the carrying beam (5) and the suspender top limiting pin (42);

the bearing cross beam (5) is fixedly connected to the upper top of the shell (1), and a through hole (51) for the suspension rod (41) to pass through is formed in the center of the bearing cross beam (5);

the stator blade (2) comprises a stator blade main body (21), a hanger rod bottom limiting pin (22), a stator blade reinforcing support (23) and bolt holes (24), a sunk groove (25) is formed in the center of the stator blade main body (21), a limiting hole used for limiting a hanger rod (41) is formed in the center of the hanger rod bottom limiting pin (22), the hanger rod bottom limiting pin (22) is fixed to the inner bottom surface of the sunk groove (25), a plurality of groups of bolt holes (24) are formed in the bolt holes and distributed on the periphery of the stator blade main body (21) at equal intervals, the stator blade main body (21) is fixedly connected with the shell (1) through the bolt holes (24) and fixing bolts (15), and each blade of the stator blade main body (21) is connected with the shell (1) through a group of stator blade reinforcing supports (23);

the moving blade (3) comprises a moving blade body (31), a moving blade bottom fixing pin (32), a moving blade upper fixing pin (33) and a moving blade reinforcing support (34), wherein the moving blade bottom fixing pin (32) is fixedly connected with the moving blade body (31), the moving blade upper fixing pin (33) is connected with each blade of the moving blade body (31) through a group of moving blade reinforcing supports (34), and the moving blade body (31) is fixedly connected with a suspender (41) through the moving blade bottom fixing pin (32) and the moving blade upper fixing pin (33);

the pneumatic actuator (6) comprises a pneumatic actuator (61) and a push rod (62), wherein the pneumatic actuator (61) is fixed on the outer wall surface of the shell (1) and is connected with the lug of the moving blade upper fixing pin (33) through the push rod (62).

2. The aircraft climate environment laboratory wide temperature range large cross-section straight-through ventilation device according to claim 1, it is characterized in that the shell (1) is formed by splicing a straight cylinder (11) and a bell mouth (12) up and down through a transition flange, the transition flange comprises a straight cylinder flange (13) arranged at the joint of the straight cylinder (11) and a bell mouth flange (14) arranged at the joint of the bell mouth (12), holes for fixing bolts (15) to penetrate are arranged at the positions corresponding to the bolt holes (24) of the straight cylinder flange (13) and the bell mouth flange (14) and the stationary blade (2), a polytetrafluoroethylene cushion block (16) for expanding the distance between the straight cylinder flange (13) and the bell mouth flange (14) is arranged at each fixing bolt (15) between the straight cylinder flange (13) and the bell mouth flange (14), and a polytetrafluoroethylene gasket (17) is arranged at the lower part of the polytetrafluoroethylene cushion block (16).

3. The wide-temperature-range large-section straight-through ventilation device for the aircraft climate environment laboratory according to claim 2, characterized in that the bell mouth (12) is manufactured by means of segmented stamping and welding, the bell mouth (12) is equally divided into a plurality of segments of arc-shaped pieces for stamping and manufacturing, and then the plurality of segments of arc-shaped pieces are welded to form the bell mouth (12).

4. The wide-temperature-range large-section straight-through ventilation device for the aircraft climate environment laboratory according to claim 1, wherein the stationary blades (2) and the moving blades (3) are formed by cutting and folding round stainless steel plates and integrally, and the included angles between the blades of the stationary blades (2) and the moving blades (3) and the horizontal plane are both 60 °.

5. The wide-temperature-range large-section straight-through type ventilation device for the aircraft climate environment laboratory according to claim 1, wherein the stationary blade reinforcing support (23) and the moving blade reinforcing support (34) are both a plurality of groups of thin rods corresponding to the number and positions of the stationary blades (2) and the moving blades (3); the bearing cross beam (5) is a structure formed by two groups of stainless steel plate pieces in a cross mode.

6. A wide temperature range large cross-section straight-through ventilation device for an aircraft climate environment laboratory according to claim 1, characterized in that the carrier ring is a teflon ring (7).

7. A wide temperature range large cross-section straight-through ventilation device for an aircraft climate environment laboratory according to claim 1, characterized in that the carrying ring is an annular carrying piece (8) of an adjustable worn teflon strip (87) and the boom (41) is a hollow cylinder;

the annular carrier (8) comprises: a guide disc (81) used for guiding and moving each polytetrafluoroethylene strip (87), a truncated cone-shaped push head (82) used for upwards moving and pushing each polytetrafluoroethylene strip (87) to move outwards along the guide disc (81), an extension rod (83) used for extending the contact of the truncated cone-shaped push head (82) and a trigger (84), a distance measuring sensor (85) used for monitoring the state position of each polytetrafluoroethylene strip (87) and a prompter (86) used for prompting the state position of the polytetrafluoroethylene strip (87),

the guide disc (81) is sleeved on the suspender (41) below the suspender top limit pin (42) and is fixedly connected with the suspender top limit pin (42), a plurality of groups of chutes (811) for guiding and moving the polytetrafluoroethylene strips (87) are circumferentially arranged on the lower bottom surface of the guide disc (81) at equal angles,

the polytetrafluoroethylene strips (87) correspond to the sliding grooves (811) in number one by one, the corresponding positions of the outer wall surface of the suspender (41) and each polytetrafluoroethylene strip (87) are respectively provided with a guide hole (411) for the polytetrafluoroethylene strip (87) to extend into the suspender (41),

the extension rod (83) is arranged in the suspender (41) in a sliding way, a baffle ring (412) used for limiting the movement of the extension rod (83) is arranged at the inner lower part of the suspender (41), the baffle ring (412) is fixedly connected with the inner wall surface of the suspender (41),

the distance measuring sensors (85) correspond to the polytetrafluoroethylene strips (87) in quantity one to one, and are connected with the outer wall surface of the guide disc (81) through fixing rings (88), the fixing rings (88) are detachably connected with the guide disc (81) through bolts,

the prompter (86) is arranged on the upper surface of the guide disc (81), the prompter (86) comprises a buzzer and an indicator light, and the prompter (86) is connected with each ranging sensor (85) through a single chip microcomputer and a data line;

and an annular bulge (52) used for locally contacting the bearing beam (5) with a polytetrafluoroethylene strip (87) is arranged on the periphery of the bearing beam (5) at the position corresponding to the through hole (51).

8. The wide-temperature-range large-section straight-through ventilation device for the aircraft climate environment laboratory according to claim 7, characterized in that the trigger (84) is a mandril (841), the mandril (841) is arranged right below the extension rod (83) and is fixedly connected with the sink (25), the top of the mandril (841) is conical, and the lower bottom surface of the extension rod (83) is provided with a groove (831) which is matched with the top of the mandril (841).

9. The wide-temperature-range large-section through ventilation device for the aircraft climate environment laboratory according to claim 7, wherein the trigger (84) is a trigger rod (842), the trigger rod (842) is arranged right below the extension rod (83) and penetrates through a through hole of the sinking groove (25), the trigger rod (842) is connected with the through hole in a sliding manner, a circular push plate (843) facilitating the push-up of the trigger rod (842) is arranged at the lower end of the trigger rod (842), and a limit ring (844) for limiting the sliding stroke of the trigger rod (842) is sleeved on the upper portion of the trigger rod (842).

10. The wide-temperature-range large-section straight-through ventilation device for the aircraft climate environment laboratory according to claim 7, characterized in that the trigger (84) is a magnetic pillar (845), the magnetic pillar (845) is arranged right below the extension rod (83) and fixedly connected with the sinking groove (25), and a position of the lower bottom surface of the extension rod (83) corresponding to the position of the magnetic pillar (845) is provided with a repulsive magnetic sheet (832).

Technical Field

The invention relates to the technical field of ventilation devices, in particular to a wide-temperature-range large-section straight-through type ventilation device for an aircraft climate environment laboratory.

Background

The airplane refers to an airplane which has one or more engines, a power device generates forward thrust or pull force, a fixed wing of a fuselage generates lift force, and heavier than air flies in the atmosphere, although the structural form of the airplane is continuously improved, the types of the airplane are continuously increased, so far, most airplanes except for few airplanes in special forms are composed of the following six main parts, namely: wings, fuselage, empennage, landing gear, operating systems, and power plants.

In order to enable the airplane to adapt to the extreme climate environment on the earth surface, the structural design of the airplane should ensure that the airplane has the predetermined good stability and maneuverability in aerodynamic aspects, and the wings, the empennage and the airplane body all need to have enough strength and rigidity and light weight, so that the wings, the empennage, the airplane body or the whole airplane need to be subjected to simulation environment tests through a large-scale comprehensive climate laboratory in the design process of the airplane to verify the strength of each part or the whole airplane.

The large-scale comprehensive climate laboratory can simulate the climate environments on the earth surface such as extremely low temperature, high temperature, damp and hot, snowfall, solar irradiation, ice and freezing rain, rain and freezing fog, the size of the large-scale comprehensive climate laboratory can meet the climate test requirements of an airplane, the height of the large-scale comprehensive climate laboratory exceeds 20 m, the large-scale comprehensive climate laboratory belongs to a large space, all complex climate environments are realized in the same area, the temperature and humidity environments are the most basic factors, and the climate environments are realized by feeding air subjected to temperature and humidity treatment from the upper part of the laboratory.

The ventilation device must satisfy the following points: a) large air output more than 30000 m³H; b) the direction of the air supply flow can be adjusted, the mixing effect is good, so that different airplane climate environment simulation requirements can be met, for example, for an airplane temperature test with higher requirement on the uniformity of a temperature field, the buoyancy effect is considered, the air supply flow in the low-temperature test is prevented from directly falling to cause too low local temperature, and the air supply flow in the high-temperature test is prevented from falling as far as possible to overcome the buoyancy to reach the position near the ground; c) the environment-friendly energy-saving device is resistant to extreme climatic environments and can work normally in the extreme environments.

Ventilation unit is diversified on the market, but can satisfy the not of extra-large-scale climate laboratory demand, current circular ventilation unit throat diameter is only about 0.8 m at most, and the amount of wind is little, if adopt conventional ventilation unit on the market, not only required in large quantity, moreover because ventilation unit is little, air supply jet attenuation distance is short, can't satisfy the aircraft environmental simulation demand of high accuracy, current ventilation unit all belongs to civilian field simultaneously, can't tolerate extreme climate environment.

Disclosure of Invention

In order to solve the technical problem, the invention provides a wide-temperature-range large-section straight-through type ventilation device for an aircraft climate environment laboratory.

The technical scheme of the invention is as follows: aircraft climate environment laboratory is with wide temperature range big cross-section through ventilation unit includes: the air inlet device comprises a shell for carrying various components, stationary blades and moving blades which are used for being matched with each other to adjust the size of an air inlet, a suspender component for hoisting the moving blades, a bearing cross beam for bearing the suspender component and the moving blades and a pneumatic actuating mechanism for controlling the moving blades to rotate;

the suspender component comprises a suspender, a suspender top limiting pin and a carrying ring for reducing the friction coefficient of the suspender and the carrying beam, wherein the suspender top limiting pin is arranged at the top of the suspender and is used for enabling the suspender to be suspended and supported on the carrying beam, and the carrying ring is sleeved on the suspender between the carrying beam and the suspender top limiting pin;

the bearing cross beam is fixedly connected to the upper top of the shell, and a through hole for the suspension rod to pass through is formed in the center of the bearing cross beam;

the static blade comprises a static blade body, a suspender bottom limiting pin, a static blade reinforcing support and bolt holes, wherein a sunken groove is formed in the center of the static blade body, a limiting hole used for limiting the suspender is formed in the center of the suspender bottom limiting pin, the suspender bottom limiting pin is fixed with the inner bottom surface of the sunken groove, a plurality of groups of bolt holes are formed in the bolt holes and distributed on the periphery of the static blade body at equal intervals, the static blade body is fixedly connected with the shell through the bolt holes and fixing bolts, and each blade of the static blade body is connected with the shell through a group of static blade reinforcing supports;

the moving blade comprises a moving blade body, a moving blade bottom fixing pin, a moving blade upper fixing pin and a moving blade reinforcing support, wherein the moving blade bottom fixing pin is fixedly connected with the moving blade body;

the pneumatic actuator comprises a pneumatic actuator and a push rod, the pneumatic actuator is fixed on the outer wall surface of the shell and is connected with the lug of the fixed pin on the upper part of the moving blade through the push rod;

the ventilating device adopts a floating design of the moving blades, the angle of the air flow can be continuously adjusted between 0 degree and 90 degrees so as to meet the requirements of different airplane climate environment simulation, the moving blades are arranged in a floating manner, the friction between the moving blades and the static blades can be reduced, the situation that the moving blades are frozen and the angle cannot be adjusted when the low-temperature climate of an airplane is simulated is prevented, and the ventilating device can normally work under extreme climate conditions by adopting a pneumatic actuating mechanism so as to meet the requirements of airplane climate environment simulation at different temperatures.

Furthermore, the shell is formed by splicing a straight cylinder and a bell mouth up and down through a transition flange, the transition flange comprises a straight cylinder flange arranged at the joint of the straight cylinder and a bell mouth flange arranged at the joint of the bell mouth, holes for fixing bolts to pass through are arranged at the positions corresponding to bolt holes of the straight cylinder flange, the bell mouth flange and the stationary blade, a polytetrafluoroethylene cushion block for enlarging the distance between the straight cylinder flange and the bell mouth flange is arranged at each fixing bolt between the straight cylinder flange and the bell mouth flange, a polytetrafluoroethylene gasket is arranged at the lower part of the polytetrafluoroethylene cushion block, a space can be reserved for the periphery of the moving blade through the arrangement of components such as the transition flange, the periphery of the moving blade is not contacted with other components, the moving blade can be prevented from descending under unexpected conditions through the arrangement of the polytetrafluoroethylene gasket, and the periphery of the moving blade is contacted with the polytetrafluoroethylene gasket, the friction of its rotation is relatively small.

Furthermore, the horn mouth is manufactured in a segmented stamping and welding mode, the horn mouth is equally divided into a plurality of segments of arc-shaped pieces for stamping and manufacturing, and then the plurality of segments of arc-shaped pieces are welded to form the horn mouth.

Furthermore, the static blades and the moving blades are formed by cutting and folding round stainless steel plates in an integrated mode, and included angles between the blades of the static blades and the moving blades and a horizontal plane are both 60 degrees.

Furthermore, the fixed blade reinforcing support and the moving blade reinforcing support are both provided with a plurality of groups of thin rods corresponding to the number and the positions of the fixed blades and the moving blades; the bearing cross beam is a structure formed by two groups of stainless steel plate pieces in a cross mode, the fixed effect of the static blades can be enhanced through the arrangement of the static blade reinforcing support, and the rotation stability of the moving blades can be enhanced through the arrangement of the moving blade reinforcing support.

As an alternative of the invention, the carrying ring is a polytetrafluoroethylene ring, is made of polytetrafluoroethylene material, is corrosion-resistant and has long service life.

As another alternative of the invention, the carrying ring is an annular carrying piece capable of adjusting the abraded polytetrafluoroethylene strip, and the suspender is a hollow cylinder;

the annular carrier comprises: a guide disc used for guiding and moving each polytetrafluoroethylene strip, a truncated cone-shaped push head used for upwards moving and pushing each polytetrafluoroethylene strip to move outwards along the guide disc, an extension rod used for extending the contact of the truncated cone-shaped push head and a trigger, a distance measuring sensor used for monitoring the state position of each polytetrafluoroethylene strip and a prompter used for prompting the state position of the polytetrafluoroethylene strip,

the guide disc is sleeved on the suspender below the limiting pin at the top of the suspender and is fixedly connected with the limiting pin at the top of the suspender, a plurality of groups of chutes for guiding and moving the polytetrafluoroethylene strips are circumferentially arranged on the lower bottom surface of the guide disc at equal angles,

the polytetrafluoroethylene strips correspond to the sliding grooves in quantity one by one, and the outer wall surface of the suspender is respectively provided with a guide hole for the polytetrafluoroethylene strip to extend into the suspender at the position corresponding to each polytetrafluoroethylene strip,

the extension rod is arranged in the suspender in a sliding way, the lower part in the suspender is provided with a baffle ring for limiting the movement of the extension rod, the baffle ring is fixedly connected with the inner wall surface of the suspender,

the distance measuring sensors correspond to the polytetrafluoroethylene strips in number one to one and are connected with the outer wall surface of the guide disc through fixing rings, the fixing rings are detachably connected with the guide disc through bolts,

the prompter is arranged on the upper surface of the guide disc and comprises a buzzer and an indicator light, and the prompter is connected with each ranging sensor through a single chip microcomputer and a data line;

the periphery of the bearing beam corresponding to the through hole is provided with an annular bulge used for the local contact of the bearing beam and the polytetrafluoroethylene strip;

the annular carrier is designed based on the polytetrafluoroethylene strips, and when the hanger rods and the moving blades move downwards after the polytetrafluoroethylene strips are worn, the annular carrier adjusts the positions of the polytetrafluoroethylene strips, so that the polytetrafluoroethylene strips at the parts which are not worn move to the annular bulges, the using effect of the polytetrafluoroethylene strips is kept, and the working stability of the carrier is improved.

As an alternative scheme of the invention, the trigger is a mandril which is arranged right below the extension rod and fixedly connected with the sinking groove, the top of the mandril is conical, and the lower bottom surface of the extension rod is provided with a groove matched with the top of the mandril.

As another alternative of the invention, the trigger is a trigger rod, the trigger rod is arranged right below the extension rod and penetrates through a through hole of the sinking groove, the trigger rod is connected with the through hole in a sliding manner, a round push plate convenient for pushing the trigger rod upwards is arranged at the lower end of the trigger rod, and a limit ring used for limiting the sliding stroke of the trigger rod is sleeved at the upper part of the trigger rod.

As a third alternative of the present invention, the trigger is a magnetic column, the magnetic column is disposed right below the extension rod and fixedly connected to the sinking groove, and a repelling magnetic sheet is disposed at a position corresponding to the magnetic column on the lower bottom surface of the extension rod.

The invention has the beneficial effects that:

(1) according to the inventionVentilating devices with air delivery of more than 30000 m³The air volume requirement of a large-scale climatic environment laboratory of the airplane can be met.

(2) The ventilation device provided by the invention has the advantages that the air supply angle is adjustable, and the requirements of different airplane climate environment simulation on air supply can be met.

(3) The ventilation device adopts the floating design of the moving blades, so that the friction between the moving blades and the static blades can be reduced, and the conditions that the moving blades are frozen and the like when the low-temperature climate of an airplane is simulated are prevented; and a pneumatic actuating mechanism is adopted, so that the aircraft can normally work under extreme climatic conditions, and the requirements of aircraft climate environment simulation at different temperatures can be met.

(4) The ventilating device is convenient to overhaul and maintain, the main structure is made of stainless steel, the components such as the carrying ring and the like are made of polytetrafluoroethylene, the ventilating device is corrosion-resistant and long in service life, and the ventilating device is convenient to overhaul by adopting an external pneumatic actuating mechanism.

(5) The ventilating device disclosed by the invention has the advantages that the annular carrier designed based on the polytetrafluoroethylene material can be subjected to position adjustment along with the abrasion of the polytetrafluoroethylene strip, so that the using effect of the polytetrafluoroethylene strip is kept, and the working stability of the carrier ring is improved.

Drawings

Fig. 1 is a schematic view showing the overall structure of the ventilation apparatus of the present invention.

Fig. 2 is an overall top view schematic diagram of the ventilation device of the present invention.

FIG. 3 is a schematic view showing the relationship of the stationary blades and the moving blades of the ventilator according to the present invention.

FIG. 4 is a schematic view of a stationary blade structure of the ventilating device of the present invention.

FIG. 5 is a schematic view showing the structure of a moving blade of the ventilating device of the present invention.

FIG. 6 is a cross-sectional view A-A of FIG. 2 in example 1 of the present invention.

Fig. 7 is a partial view of ZA of fig. 6 in accordance with the present invention.

FIG. 8 is a partial view of ZB of FIG. 6 according to the present invention.

FIG. 9 is a ZC partial diagram of FIG. 6 of the present invention.

FIG. 10 is a cross-sectional view A-A of FIG. 2 in example 2 of the present invention.

Fig. 11 is a partial view of ZA of fig. 10 in accordance with the present invention.

FIG. 12 is a partial view of ZB of FIG. 10 according to the present invention.

Fig. 13 is a schematic view showing the installation position of the ring carrier in embodiment 2 of the present invention.

FIG. 14 is a cross-sectional view A-A of FIG. 2 in example 3 of the present invention.

Fig. 15 is a partial view of ZA of fig. 14 in accordance with the present invention.

Fig. 16 is a schematic view showing the installation position of the ring carrier in embodiment 3 of the present invention.

FIG. 17 is a cross-sectional view A-A of FIG. 2 in example 4 of the present invention.

Fig. 18 is a partial view of ZA of fig. 17 in accordance with the present invention.

Fig. 19 is a schematic view showing the installation position of the ring carrier in embodiment 4 of the present invention.

Fig. 20 is a schematic bottom view of the structure of the embodiment 1-3 of the present invention.

Fig. 21 is a schematic bottom view of the whole structure in embodiment 4 of the present invention.

Fig. 22 is a schematic top view of the toroidal support according to embodiments 2-4 of the present invention.

Fig. 23 is a bottom view of the ring carrier in embodiments 2-4 of the present invention.

Fig. 24 is a schematic view showing the construction of a suspension bar according to embodiment 2 to 4 of the present invention.

Fig. 25 is a schematic structural view of an extension pole in embodiment 2 of the present invention.

Fig. 26 is a schematic view of the structure of the annular projection of the load beam in embodiments 2 to 4 of the present invention.

Fig. 27 is a schematic view of the overall structure of mode one in embodiment 1 of the present invention.

Fig. 28 is an overall structural schematic diagram of mode two in embodiment 1 of the present invention.

Wherein the content of the first and second substances,

1-shell, 11-straight cylinder, 12-bell mouth, 13-straight cylinder flange, 14-bell mouth flange, 15-fixing bolt, 16-polytetrafluoroethylene cushion block, 17-polytetrafluoroethylene gasket,

2-stationary blades, 21-stationary blade bodies, 22-hanger rod bottom limiting pins, 23-stationary blade reinforcing brackets, 24-bolt holes and 25-sink grooves,

3-moving blade, 31-moving blade body, 32-moving blade bottom fixing pin, 33-moving blade upper fixing pin, 34-moving blade reinforcing bracket,

4-a suspender component, 41-a suspender, 411-a guide hole, 412-a retaining ring and 42-a suspender top limit pin,

5-bearing beam, 51-through hole, 52-annular projection,

6-a pneumatic actuating mechanism, 61-a pneumatic actuator and 62-a push rod,

7-a polytetrafluoroethylene ring, wherein the polytetrafluoroethylene ring is a polytetrafluoroethylene ring,

8-annular carrier, 81-guide disc, 811-sliding chute, 82-truncated cone-shaped pushing head, 83-extension rod, 831-groove, 832-magnetic sheet, 84-trigger, 841-ejector rod, 842-trigger rod, 843-circular push plate, 844-limiting ring, 845-magnetic column, 85-distance measuring sensor, 86-prompter, 87-polytetrafluoroethylene strip and 88-fixing ring.

Detailed Description

The present invention will be described in further detail with reference to specific embodiments thereof for better understanding the advantages of the invention.

Example 1

The aircraft climate environment laboratory wide temperature range large cross-section straight-through ventilation device as shown in fig. 1, 2, 20 comprises: a housing 1 for carrying various components, a stationary blade 2 and a moving blade 3 for adjusting the size of a tuyere by matching with each other, a boom assembly 4 for hoisting the moving blade 3, a bearing beam 5 for bearing the boom assembly 4 and the moving blade 3, and a pneumatic actuator 6 for controlling the rotating of the moving blade 3;

as shown in fig. 6 and 9, the casing 1 is formed by vertically splicing a straight cylinder 11 and a bell mouth 12 through transition flanges, the transition flanges include a straight cylinder flange 13 arranged at the joint of the straight cylinder 11 and a bell mouth flange 14 arranged at the joint of the bell mouth 12, holes for passing fixing bolts 15 are arranged at the positions corresponding to bolt holes 24 of the straight cylinder flange 13 and the bell mouth flange 14 and the stationary blade 2, a polytetrafluoroethylene cushion block 16 for enlarging the distance between the straight cylinder flange 13 and the bell mouth flange 14 is arranged at each fixing bolt 15 between the straight cylinder flange 13 and the bell mouth flange 14, a polytetrafluoroethylene gasket 17 is arranged at the lower part of the polytetrafluoroethylene cushion block 16, the thickness of the polytetrafluoroethylene cushion block 16 is 10 mm, the thickness of the polytetrafluoroethylene gasket 17 is 1 mm, a space can be left for the periphery of the moving blade 3 by arranging the transition flanges and other members, and the periphery of the moving blade 3 is not contacted with other members, the polytetrafluoroethylene gasket 17 can prevent the moving blade 3 from falling down in an unexpected situation, the periphery of the moving blade 3 is contacted with the polytetrafluoroethylene gasket, and the rotating friction force is relatively small;

wherein, the straight cylinder 11 is a cylinder and is made of stainless steel material with the thickness of 1.8 mm, and the effective diameter is 1.5 m; the bell mouth 12 is made of stainless steel with the thickness of 1.8 mm by adopting a sectional stamping welding mode, the diameter of the bottom is 1.9 m, the diameter of the upper part is the same as that of the straight cylinder 11 and is 1.5 m, and the flanging radius of the bell mouth 12 is 0.16 m; the horn mouth 12 is equally divided into 4 sections of arc-shaped pieces for punching manufacture, and then the multiple sections of arc-shaped pieces are welded by laser welding to form the horn mouth 12, because the air quantity required by the simulation of the aircraft climate environment is larger, the diameter of the ventilation device is larger, the cost is overlarge by adopting a conventional spinning forming method, the ventilation device is manufactured by adopting a sectional punching welding mode, and the large-caliber horn mouth 12 can be effectively obtained;

as shown in fig. 6, 7 and 8, the suspension rod assembly 4 includes a suspension rod 41, a suspension rod top limit pin 42 and a carrying ring for reducing a friction coefficient between the suspension rod 41 and the carrying beam 5, the suspension rod top limit pin 42 is disposed at the top of the suspension rod 41 and is used for suspending and supporting the suspension rod 41 on the carrying beam 5, the carrying ring is sleeved on the suspension rod 41 between the carrying beam 5 and the suspension rod top limit pin 42, the carrying ring is specifically a teflon ring 7 with a thickness of 5 mm, the carrying ring is made of teflon, and is corrosion-resistant and long in service life;

as shown in fig. 2, the bearing beam 5 is fixedly connected to the upper top of the housing 1, a through hole 51 for the hanger rod 41 to pass through is formed in the center of the bearing beam 5, the bearing beam 5 is a structure formed by two groups of stainless steel plate pieces in a cross manner, the bearing beam 5 is formed by bending the stainless steel plate pieces with the thickness of 1.8 mm, and is fixed on the straight cylinder 11 by welding;

as shown in fig. 3 and 4, the stationary blade 2 includes a stationary blade body 21, a boom bottom stopper pin 22, a stationary blade reinforcing bracket 23, and bolt holes 24, a sunken groove 25 is provided at the center of the stationary blade body 21, a stopper hole for limiting the boom 41 is provided at the center of the boom bottom stopper pin 22, the boom bottom stopper pin 22 is fixed to the inner bottom surface of the sunken groove 25, the bolt holes 24 are provided with a plurality of groups and are distributed at equal intervals on the periphery of the stationary blade body 21, the stationary blade body 21 is fixedly connected to the casing 1 through the bolt holes 24 and the fixing bolts 15, and each blade of the stationary blade body 21 is connected to the casing 1 through the stationary blade reinforcing bracket 23; the hanger rod bottom limiting pin 22 is made of a stainless steel plate with the thickness of 1.8 mm, and the center of the hanger rod bottom limiting pin is a limiting hole with the diameter of 16 mm;

as shown in fig. 3 and 5, the rotor blade 3 includes a rotor blade body 31, a rotor blade bottom fixing pin 32, a rotor blade upper fixing pin 33, and a rotor blade reinforcing bracket 34, the rotor blade bottom fixing pin 32 is fixedly connected to the rotor blade body 31, the rotor blade upper fixing pin 33 is connected to each blade of the rotor blade body 31 by a set of rotor blade reinforcing brackets 34, and the rotor blade body 31 is fixedly connected to the hanger 41 by the rotor blade bottom fixing pin 32 and the rotor blade upper fixing pin 33;

as shown in fig. 3, the stationary blade 2 and the moving blade 3 are formed by cutting and folding a circular stainless steel plate into a whole, the diameter of the circular stainless steel plate is 1.58 m, the thickness of the circular stainless steel plate is 1.8 mm, the stationary blade 2 and the moving blade 3 are equally divided into 6 blades, and the included angles between the blades and the horizontal plane are both 60 degrees; the stationary blade reinforcing bracket 23 and the moving blade reinforcing bracket 34 are 6 sets of thin rods corresponding to the number and positions of the stationary blades 2 and the moving blades 3; the stationary blade 2 fixing effect can be enhanced by the stationary blade reinforcing bracket 23, and the rotational stability of the moving blade 2 can be enhanced by the moving blade reinforcing bracket 34;

as shown in fig. 6, the pneumatic actuator 6 includes a pneumatic actuator 61 and a push rod 62, the pneumatic actuator 61 is fixed on the outer wall surface of the casing 1, and is connected to the tab of the moving blade upper portion fixing pin 33 through the push rod 62;

the ventilating device adopts a suspended design of the moving blades 3, the angle of the supplied air flow can be continuously adjusted between 0 degree and 90 degrees so as to meet the requirements of different airplane climate environment simulation, the moving blades 3 are suspended, the friction between the moving blades 3 and the static blades 2 can be reduced, the situation that the moving blades 3 are frozen and the angle cannot be adjusted when the low-temperature climate of an airplane is simulated is prevented, and the ventilating device can normally work under extreme climate conditions by adopting the pneumatic actuating mechanism 6 so as to meet the requirements of airplane climate environment simulation at different temperatures.

The working method of the ventilation device of the embodiment comprises the following steps:

a boom 41 is inserted into the moving blade bottom fixing pin 32 and fixed by a bolt, a moving blade upper fixing pin 33 is inserted into the boom 41 and fixed by a bolt, and then the moving blade reinforcing bracket 34 is welded so that the boom 41 and the moving blade 3 are integrated, and then placed above the stationary blade 2 with the lower end of the boom 41 inserted into the boom bottom stopper pin 22;

placing a polytetrafluoroethylene gasket 17 above the periphery of the static blade 2, placing a polytetrafluoroethylene cushion block 16 above the polytetrafluoroethylene gasket 17, then placing the straight cylinder 11, and fixing the bell mouth 2, the static blade 2, the polytetrafluoroethylene gasket 17, the polytetrafluoroethylene cushion block 16 and the placing straight cylinder 11 together through a fixing bolt 15;

welding the stationary blade reinforcing bracket 23 to ensure the structural strength and rigidity of the stationary blade 2;

fixing a bearing beam 5 on a straight cylinder 11 in a welding mode, enabling a through hole of the bearing beam 5 to penetrate through a suspender 41, then sequentially inserting a polytetrafluoroethylene ring 7 and a suspender top limiting pin 42 into the suspender 41, pulling up the moving blade 3 and the suspender 41, and inserting a bolt into the suspender top limiting pin 42 and fixing, so that the moving blade 3 is suspended on the bearing beam 5, and the bottom surface of the moving blade 3 is not contacted with the static blade 2 or the straight cylinder 11 and the like;

the pneumatic actuator 61 of the pneumatic actuator 6 is fixedly arranged on the straight cylinder 11, then the push rod 62 is arranged, and the pneumatic actuator 61 can be a commercially available linear or rotary pneumatic actuator, but is finally converted into the linear motion of the push rod 62;

after the installation, the initial position of the pneumatic actuator 61 is adjusted to make the relative included angle between the moving blade 3 and the stationary blade 2 be 30 °, as shown in fig. 28, so that the pneumatic actuator 61 will push the change of the position of the moving blade 3 through the push rod 62, and the tuyere is changed between the two positions of the high-temperature air supply state shown in fig. 27 and the low-temperature air supply state shown in fig. 28, so as to meet different environment simulation requirements.

Example 2

This embodiment is substantially the same as embodiment 1, except that, as shown in fig. 10 and 13, the carrier ring is embodied as an annular carrier member 8 capable of adjusting a worn teflon strip 87, and the suspension rod 41 is a hollow cylinder;

as shown in fig. 11, 22, and 23, the annular carrier 8 includes: a guide disc 81 used for guiding and moving 12 polytetrafluoroethylene strips 87, a truncated cone-shaped push head 82 used for upwards moving and pushing the 12 polytetrafluoroethylene strips 87 to move outwards along the guide disc 81, an extension rod 83 used for extending the contact of the truncated cone-shaped push head 82 and a trigger 84, a distance measuring sensor 85 used for monitoring the state position of the 12 polytetrafluoroethylene strips 87 and a prompter 86 used for prompting the state position of the polytetrafluoroethylene strips 87,

as shown in fig. 23 and 24, the guide disc 81 is sleeved on the suspension rod 41 below the suspension rod top limit pin 42 and is fixedly connected with the suspension rod top limit pin 42, 12 sets of sliding grooves 811 for guiding and moving the polytetrafluoroethylene strips 87 are circumferentially arranged on the lower bottom surface of the guide disc 81 at equal angles, the polytetrafluoroethylene strips 87 correspond to the sliding grooves 811 in number one by one, the outer wall surface of the suspension rod 41 is provided with a guide hole 411 for the polytetrafluoroethylene strip 87 to extend into the suspension rod 41 at a position corresponding to the 12 polytetrafluoroethylene strips 87, the side of the polytetrafluoroethylene strip 87, which is in contact with the sliding groove 811, is provided with an anti-falling flange, and a groove body matched with the flange is arranged in the sliding groove 811;

as shown in fig. 10 and 25, the extension rod 83 is slidably disposed in the suspension rod 41, a stop ring 412 for limiting the movement of the extension rod 83 is disposed at the lower portion of the suspension rod 41, the stop ring 412 is fixedly connected to the inner wall surface of the suspension rod 41,

as shown in fig. 23, the distance measuring sensors 85 correspond to the teflon strips 87 in number one by one and are connected with the outer wall surface of the guide disc 81 through the fixing ring 88, the fixing ring 88 is detachably connected with the guide disc 81 through bolts, the distance measuring sensors 85 adopt commercially available miniature laser radar distance measuring modules, such as TFmini Plus miniaturized laser radar module short-distance sensors, or are adjusted in shape according to the commercially available laser radar distance measuring modules so as to be fittingly installed on the device,

as shown in fig. 22, the prompter 86 is arranged on the upper surface of the guide plate 81, the prompter 86 comprises a buzzer and an indicator light, the prompter 86 is connected with each distance measuring sensor 85 through a single chip microcomputer and a data line, the single chip microcomputer is an AT91SAM9263B-CU-100 microprocessor,

wherein, the shell of the prompter 86, the shell of the distance measuring sensor 85 and the outer wall of the fixing ring 88 are made of heat-insulating materials, such as commercial rubber-plastic heat-insulating materials; the fixing ring 88 is hollow and internally provided with an electric heating wire for heating the fixing ring, the electric heating wire is electrically connected with a built-in battery of the prompter 86, and the electric heating wire is started to electrically heat the fixing ring 88 in a low-temperature environment, and each distance measuring sensor 85 is kept at a normal working temperature through the heat conduction action of the heat conduction metal (copper) on the inner wall of the fixing ring 88 and the heat conduction metal (copper) on the inner wall of the shell of each distance measuring sensor 85, so that the situation that the distance measuring sensors 85 cannot work in an extreme environment and the like is avoided,

as shown in fig. 26, the outer periphery of the bearing beam 5 at the position corresponding to the through hole 51 is provided with an annular protrusion 52 for partially contacting the bearing beam 5 with the teflon strip 87;

as shown in fig. 12 and 13, the trigger 84 is a post 841, the post 841 is disposed right below the extension rod 83 and is fixedly connected to the sink 25, the top of the post 841 is tapered, and the lower bottom surface of the extension rod 83 is provided with a recess 831 to match with the top of the post 841;

in the embodiment, the carrier ring is designed based on the polytetrafluoroethylene strip 87, when the hanger rod 41 and the moving blade 3 move downwards after the polytetrafluoroethylene strip is worn, the position of the annular carrier 8 is adjusted, so that the polytetrafluoroethylene strip 87 at the non-worn part moves to the annular bulge 52, the use effect of the polytetrafluoroethylene strip 87 is maintained, and the working stability of the carrier ring is improved;

the working method of the annular carrier 8 comprises the following steps:

the annular protrusion 52 is disposed at one end of the outer side of the teflon strip 87, when the teflon strip 87 is worn out greatly, the thickness of the teflon strip 87 is reduced, and the related components such as the suspension rod 41 and the moving blade 3 fall down to the worn thickness, so that the extension rod 83 and the truncated cone-shaped pushing head 82 move upward relatively under the action of the push rod 841, and each teflon strip 87 moves outward along the sliding groove 811 of the guide disc 81 under the action of the truncated cone-shaped pushing head 82, so that the worn part of the teflon strip 87 is switched to the unworn part,

when the teflon strip 87 moves to the outside along the sliding groove 811 completely, the distance measuring sensor 85 is triggered to trigger the buzzer and the indicator light of the prompter 86, so as to remind the operator to replace the annular carrier 8 in time, thereby avoiding the abrasion of the components such as the suspender assembly 4, the moving blade 3 and the like.

Example 3

The embodiment is substantially the same as embodiment 2, and is different from embodiment 2 in that, as shown in fig. 14, 15, 16, and 21, the trigger 84 is a trigger rod 842, the trigger rod 842 is disposed right below the extension rod 83 and passes through a through hole of the sinking groove 25, the trigger rod 842 is slidably connected with the through hole, a circular push plate 843 facilitating pushing up of the trigger rod 842 is disposed at the lower end of the trigger rod 842, and a limiting ring 844 for limiting the sliding stroke of the trigger rod 842 is sleeved on the upper portion of the trigger rod 842; the method of operation of the annular carrier 8 is the same as in example 2.

Example 4

This embodiment is substantially the same as embodiment 2, and is different therefrom in that, as shown in fig. 17, 18 and 19, the trigger 84 is a magnetic pillar 845, the magnetic pillar 845 is disposed right below the extension rod 83 and fixedly connected to the sinking groove 25, a repulsive magnetic sheet 832 is disposed at a position of the lower bottom surface of the extension rod 83 corresponding to the position of the magnetic pillar 845, and when the trigger 84 is the magnetic pillar 845, the working environment temperature thereof needs to be determined according to the adaptive temperature range of the magnetic pillar 845; the method of operation of the annular carrier 8 is the same as in example 2.

Examples of the experiments

To illustrate that the air blowing effect is better when the inclination angles (included angles with the horizontal plane) of the blades of the stationary blade 2 and the moving blade 3 are 60 °, the following calculation is made:

the ultra-large ventilation device is used for simulating airplanes in various complex climates to provide uniform air supply flow meeting requirements and adjust the temperature field in the airplane environment simulation room, in addition, the air port is also used as an air supply port when extra-large air supply is carried out, the air supply flow is 1.5 times of that in a normal state,

the conventional air port has large resistance at the edge folding angle, and large vibration and noise caused by high-speed airflow, and the resistance characteristic of the air port can adopt a pressure loss coefficientTo characterize:

（1）

in the formula (I), the compound is shown in the specification,

is the pressure loss through the tuyere in Pa;

is the air density in kg/m³；

The unit is the wind speed of the throat part of the tuyere and is m/s;

taking the example that the angle between the movable and stationary blades and the horizontal plane is 30 degrees (i.e. 12 blades can be seen as shown in fig. 28), when the folding angle (the angle between the folding angle and the horizontal plane) is 30 degrees,up to 18.5, and the folding angle (included angle with the horizontal plane) is 60 degrees,only 4.5; that is, under the same air quantity, the air inlet resistance with the edge folding angle (the included angle with the horizontal plane) of 60 degrees is only 1/4 which is not met when the edge folding angle (the included angle with the horizontal plane) is 30 degrees; when the folding angle (included angle with the horizontal plane) is 60 degrees, the change of the angle from the horizontal direction to the vertical direction can be realized by the air supply flow;

the primary function of the tuyere is to meet the requirement of indoor air flow structure adjustment, and in this respect, the folding angle (included angle with the horizontal plane) of the conventional swirl tuyere can also meet the requirement of 30 degrees or 45 degrees, but the resistance is slightly large, so that the inclination angles (included angle with the horizontal plane) of the blades of the stationary blade 2 and the moving blade 3 are relatively more preferable to be 60 degrees.