CN115477020A - Aircraft slide release testing arrangement - Google Patents
Aircraft slide release testing arrangement Download PDFInfo
- Publication number
- CN115477020A CN115477020A CN202211204013.1A CN202211204013A CN115477020A CN 115477020 A CN115477020 A CN 115477020A CN 202211204013 A CN202211204013 A CN 202211204013A CN 115477020 A CN115477020 A CN 115477020A
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- China
- Prior art keywords
- pipe
- slide release
- fixedly mounted
- aircraft slide
- velocity sensor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to the technical field of civil aviation equipment, and discloses an aircraft slide release testing device which comprises an inflation tank, wherein an air injection pipe is fixedly installed on one side of the inflation tank, a detection pipe is fixedly installed on one side of the air injection pipe, a flow velocity sensor is fixedly installed in one side of the detection pipe, one side of the flow velocity sensor extends into the detection pipe, and a speed measurement fan blade is movably installed on one side of the flow velocity sensor.
Description
Technical Field
The invention relates to the technical field of civil aviation equipment, in particular to an aircraft slide release testing device.
Background
The slide of civil aviation passenger plane is the special equipment of installation in passenger plane emergency escape hatch door department, can not use usually, but in case the aircraft meets the air accident and need promptly compel when landing to the sea, then need use the slide to flee, the working method of slide is inflatable, need carry out quick instantaneous inflation to compressed slide, make the slide expand rapidly in the short time and supply passengers to flee for use, consequently the most important component structure on the aircraft slide is the module of aerifing, in case the module of aerifing breaks down can't inflate fast, or the inflation flow rate is not enough, then can cause bigger injures and deaths.
Traditional slide release function detects and needs to transport the module of aerifing to the factory of reprocessing and carry out the performance detection, and this kind of detection mode is comparatively delayed time, can not carry out quick detection on the spot to the module of aerifing.
Based on the above situation, it is necessary to design an airplane slide release testing device to quickly detect the inflation device of the slide in the airport.
Disclosure of Invention
In order to overcome the above-mentioned drawbacks of the prior art, the present invention provides an aircraft slide release testing device to solve the above-mentioned problems in the background art.
The invention provides the following technical scheme: an aircraft slide release testing device comprising: the device comprises a device bottom plate and an external connecting pipe, wherein an inflatable tank is movably arranged at the top end of the device bottom plate; the utility model discloses an air inflation pump, including the outside connecting pipe, one side fixed mounting has jet-propelled pipe, one side fixed mounting of jet-propelled pipe has the detecting tube, the inside fixed mounting in one side of detecting tube has velocity of flow sensor, one side of velocity of flow sensor extends to the inside of detecting tube, one side movable mounting of velocity of flow sensor has the flabellum that tests the speed, through the setting of above-mentioned structure, again by the detecting tube blowout after leading-in air inflation pump of outside connecting pipe with the air in the in-service use, the air current is through velocity of flow sensor this moment to blow velocity of flow sensor's fan, velocity of flow sensor can carry out the velocity of flow to detecting tube department spun air current fast, has effectively accelerated the performance detection efficiency of air inflation pump, has solved traditional slide release function and has detected and need transport the module of inflating to the return repair factory and carry out the performance detection, and this kind of detection mode is comparatively delayed time, can not carry out quick detection's problem in the field to the module of inflating.
Further, the jet-propelled pipe and the one side that the test tube is close to each other all fixed mounting have sealed the pad, two sealed pad all closely laminates, through the setting of above-mentioned structure, can effectively seal jet-propelled pipe and test tube in the in-service use, avoids the air to leak from the junction of jet-propelled pipe and test tube.
Further, jet-propelled pipe runs through with test tube interconnect department and installs two threaded rods, the installation direction of threaded rod is all opposite, through the setting of above-mentioned structure, can effectively strengthen being connected of jet-propelled pipe and test tube in the in-service use, makes the connection of the two more firm.
Further, there are two spring buffer poles bottom one side movable mounting of gas tank, one side of spring buffer pole all with device bottom plate fixed connection, spring buffer pole's inside all is provided with the spring, and through the setting of above-mentioned structure, can appear backward recoil power when gas injection detection is carried out to the gas tank in the in-service use, and spring buffer pole can effectively avoid gas tank and device bottom plate to collide each other, provides better buffering protection for the gas tank.
Furthermore, four pulleys are rotatably mounted at the bottom end of the inflation tank, and through the arrangement of the structure, when the inflation tank moves in the device bottom plate due to the actual recoil force, the sliding friction between the inflation tank and the device bottom plate can be changed into rolling friction, so that the abrasion of the contact surfaces of the inflation tank and the device bottom plate is effectively reduced.
Further, place ahead and the rear of device bottom plate all are provided with two pivots, all fixed mounting has two support frames in the pivot, the bottom of support frame all fixed mounting have fixed awl, the shape of fixed awl all is the awl thorn shape, through the setting of above-mentioned structure, can carry out spacingly and fixed with the device bottom plate in the soil in the fixed awl insertion airport in the in-service use, improve the spacing efficiency of device bottom plate, avoid the device bottom plate to take place to empty when detecting simultaneously.
Compared with the prior art, the invention has the following technical effects and advantages:
1. according to the invention, through the arrangement of the device bottom plate, the detection pipe and the flow velocity sensor, air can be introduced into the inflation tank from the external connecting pipe and then is ejected from the detection pipe in practical use, at the moment, the fan of the flow velocity sensor is blown, and the flow velocity sensor can quickly detect the flow velocity of the air flow ejected from the detection pipe, so that the performance detection efficiency of the inflation tank is effectively accelerated, and the problems that the conventional slide release function detection needs to convey the inflation module to a repair factory for performance detection, the detection mode delays time and cannot quickly detect the inflation module in the field are solved.
2. According to the invention, through the arrangement of the rotating shaft, the support frame and the fixing cone, the fixing cone can be inserted into soil in a airport to limit and fix the device bottom plate in practical use, so that the limiting efficiency of the device bottom plate is improved, and the device bottom plate is prevented from toppling during detection.
Drawings
FIG. 1 is a perspective view of the overall structure of the present invention;
FIG. 2 is a schematic side view of the overall structure of the present invention;
FIG. 3 is an enlarged perspective view of a portion of the present invention;
fig. 4 is a front view schematically illustrating the overall structure of the present invention.
The reference signs are: 100-device backplane; 110-an aeration tank; 111-external connection pipe; 112-gas lances; 113-a detection tube; 114-a flow rate sensor; 115-a gasket; 116-a threaded rod; 117-spring buffer rod; 118-a pulley; 119-a rotating shaft; 120-a support frame; 121-fixed cone.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings of the present invention, and the forms of the structures described in the following embodiments are merely examples, and the aircraft slide release testing apparatus according to the present invention is not limited to the structures described in the following embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative efforts fall within the scope of the present invention.
The first embodiment is as follows:
referring to fig. 1 and 2, the present invention provides an aircraft slide release testing apparatus comprising: the device comprises a device bottom plate 100 and an external connecting pipe 111, wherein the top end of the device bottom plate 100 is movably provided with an inflatable tank 110;
outside connecting pipe 111 fixed mounting on aeration tank 110, one side fixed mounting of aeration tank 110 has jet-propelled pipe 112, one side fixed mounting of jet-propelled pipe 112 has detecting tube 113, the inside fixed mounting in one side of detecting tube 113 has velocity sensor 114, one side of velocity sensor 114 extends to the inside of detecting tube 113, one side movable mounting of velocity sensor 114 has the flabellum that tests the speed.
The working principle is as follows: firstly, fix device bottom plate 100 on the land at the airport with fixed awl 121, then insert outside connecting pipe 111 with the air hose, make outside connecting pipe 111 with the air leading-in to gas tank 110 in, gas tank 110 can spout the air to detecting tube 113 from jet-propelled pipe 112, from detecting tube 113 department high-speed blowout, the spun air can drive the rotation of speed measuring fan on velocity sensor 114, velocity sensor 114 then can measure whether up to standard the velocity of flow in detecting tube 113 exit fast this moment.
The second embodiment:
referring to fig. 1, the difference between the second embodiment and the first embodiment is: two spring buffering rods 117 are movably mounted on one side of the bottom end of the inflation tank 110, one sides of the spring buffering rods 117 are fixedly connected with the device bottom plate 100, and springs are arranged inside the spring buffering rods 117.
The working principle is as follows: when the flow rate of the inflator 110 is tested, the high-speed ejected air flow can cause the inflator 110 to generate a recoil force, at the moment, the inflator 110 can move backwards under the action of the recoil force, but because the device base plate 100 is limited in position, the inflator 110 can only be allowed to move in the device base plate 100, the spring buffer rods 117 are compressed, the spring buffer rods 117 try to rebound after being compressed to the limit, direct collision between the inflator 110 and the device base plate 100 is avoided, and effective buffer protection effect is achieved on the inflator 110.
The present invention is not limited to the above preferred embodiments, but rather, any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. An aircraft slide release testing device, comprising: a device chassis (100) and an external connection pipe (111); the device is characterized in that an inflation tank (110) is movably mounted at the top end of the device base plate (100), an external connecting pipe (111) is fixedly mounted on the inflation tank (110), an air injection pipe (112) is fixedly mounted on one side of the inflation tank (110), a detection pipe (113) is fixedly mounted on one side of the air injection pipe (112), a flow velocity sensor (114) is fixedly mounted inside one side of the detection pipe (113), one side of the flow velocity sensor (114) extends into the detection pipe (113), and a speed measuring fan blade is movably mounted on one side of the flow velocity sensor (114); the device is characterized in that two rotating shafts (119) are arranged in front of and behind the device bottom plate (100), two supporting frames (120) are fixedly mounted on the rotating shafts (119), fixed cones (121) are fixedly mounted at the bottom ends of the supporting frames (120), and the fixed cones (121) are in cone thorn shapes.
2. An aircraft slide release test apparatus according to claim 1, wherein: the jet pipe (112) and the detection tube (113) are both fixedly provided with a sealing gasket (115) at one side close to each other, and the sealing gaskets (115) are both tightly attached.
3. An aircraft slide release testing device according to claim 1, wherein: the mutually connected parts of the air injection pipe (112) and the detection pipe (113) are provided with two threaded rods (116) in a penetrating way, and the installation directions of the threaded rods (116) are opposite.
4. An aircraft slide release test apparatus according to claim 1, wherein: bottom one side movable mounting of aeration tank (110) has two spring buffering poles (117), one side of spring buffering pole (117) all with device bottom plate (100) fixed connection, the inside of spring buffering pole (117) all is provided with the spring.
5. An aircraft slide release test apparatus according to claim 1, wherein: four pulleys (118) are rotatably arranged at the bottom end of the aeration tank (110).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211204013.1A CN115477020A (en) | 2022-09-29 | 2022-09-29 | Aircraft slide release testing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211204013.1A CN115477020A (en) | 2022-09-29 | 2022-09-29 | Aircraft slide release testing arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115477020A true CN115477020A (en) | 2022-12-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211204013.1A Pending CN115477020A (en) | 2022-09-29 | 2022-09-29 | Aircraft slide release testing arrangement |
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| CN (1) | CN115477020A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117068388A (en) * | 2023-10-17 | 2023-11-17 | 中国飞机强度研究所 | Free flight hooking simulation test system and method for airplane based on crushing device |
-
2022
- 2022-09-29 CN CN202211204013.1A patent/CN115477020A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117068388A (en) * | 2023-10-17 | 2023-11-17 | 中国飞机强度研究所 | Free flight hooking simulation test system and method for airplane based on crushing device |
| CN117068388B (en) * | 2023-10-17 | 2024-01-09 | 中国飞机强度研究所 | Free flight hooking simulation test system and method for airplane based on crushing device |
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