CN109279046B - Cabin filling method and cart for cabin filling device - Google Patents
Cabin filling method and cart for cabin filling device Download PDFInfo
- Publication number
- CN109279046B CN109279046B CN201811039111.8A CN201811039111A CN109279046B CN 109279046 B CN109279046 B CN 109279046B CN 201811039111 A CN201811039111 A CN 201811039111A CN 109279046 B CN109279046 B CN 109279046B
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- cabin
- filling
- layer bracket
- lower layer
- sliding rail
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- 238000000034 method Methods 0.000 title claims abstract description 32
- 239000006260 foam Substances 0.000 claims abstract description 20
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 9
- 239000010959 steel Substances 0.000 claims abstract description 9
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 239000000945 filler Substances 0.000 abstract description 9
- 238000009661 fatigue test Methods 0.000 description 9
- 238000007689 inspection Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000003203 everyday effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B62—LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS
- B62B—HAND-PROPELLED VEHICLES, e.g. HAND CARTS OR PERAMBULATORS; SLEDGES
- B62B3/00—Hand carts having more than one axis carrying transport wheels; Steering devices therefor; Equipment therefor
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- Engineering & Computer Science (AREA)
- Transportation (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The application provides a cabin filling method and a cart for a cabin filling device. The cabin filling method comprises the following steps: step 1: mounting the sliding rail cart group on the I-shaped sliding rail; step 2: placing the lower layer bracket on the floor of the engine room, and suspending the lower layer bracket; and step 3: placing the filling foam on the lower layer bracket, and placing the upper layer bracket on the placed filling foam; and 4, step 4: connecting the upper layer bracket and the lower layer bracket through a binding band; and 5: connecting a steel cable with a suspender of the sliding rail trolley group and a hanging ring of the upper layer bracket, and contracting a brake screw rod of the lower layer bracket to ensure that the filled foam is hung on the sliding rail trolley to form a filling device; step 6: the filling device is pushed to a predetermined position in the aircraft cabin. The cabin filling method utilizes the cabin sliding rail, so that fillers can be moved into the cabin from the cabin door along the sliding rail, manual carrying is avoided, and the cabin filling method is rapid and convenient.
Description
Technical Field
The application belongs to the technical field of airplane structure fatigue tests, and particularly relates to a cabin filling method and a cart for a cabin filling device.
Background
In the fatigue test of the airplane structure, the cabin pressurization test is an important test item of the airplane structure test. From the aspects of the pressurizing load characteristics and safety of test projects, the pressurizing equipment is required to rapidly inflate the cabin to reach the pressurizing load required by the test in the cabin pressurizing test, and the cabin is rapidly deflated to complete a rise and fall cycle, so that the test risk is reduced, and the test speed is accelerated. Currently, the method used is to fill the cabin with filler to reduce the required inflation space and the amount of inflation to achieve the above objectives. The method is applied to the static test of the airplane structure, but the following problems exist in the practical application of the fatigue test of the airplane structure: fatigue tests require that the aircraft structure be inspected every day, and that it is necessary to remove all the filler from the cabin for comprehensive inspection and maintenance when a certain number of landing gear is reached. This requires that the tester will carry the filler out of the cabin by hand during the inspection, which is laborious and time-consuming, and seriously affects the fatigue test progress of the aircraft, resulting in an increase in test cost.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a cabin filling method that solves at least one of the above-mentioned drawbacks of the prior art.
The technical scheme of the application is as follows:
the application provides a cabin filling method, which is used for filling a filling device into an aircraft cabin, and the cabin filling method comprises the following steps:
step 1: mounting the sliding rail cart group on an I-shaped sliding rail at the upper part of an aircraft cabin;
step 2: placing a lower layer bracket with a brake screw on the floor of the engine room, and controlling the brake screw to extend out, so that the lower layer bracket is suspended;
and step 3: placing the filling foam on the lower layer bracket, and placing the upper layer bracket on the placed filling foam;
and 4, step 4: the upper layer bracket and the lower layer bracket are connected through the binding belt, and the binding belt is tightened through adjusting a ratchet type tightener on the binding belt, so that the upper layer bracket and the lower layer bracket are enabled to clamp the filling foam in the middle to form a whole;
and 5: connecting a steel cable with an anti-falling hook with a suspender of the sliding rail cart group and a hanging ring of an upper layer bracket, and contracting a brake screw of a lower layer bracket to enable filling foam to be hung on the sliding rail cart, thereby forming a filling device;
step 6: and pushing the filling device to reach a preset position in the aircraft cabin, extending out the brake screw rod 5, and transferring the weight load of the filling device to the floor of the aircraft body through the slide rail.
Preferably, the nacelle filling method further comprises:
step 6: and repeatedly manufacturing the filling devices, so that the cabin of the airplane is filled with a preset number of filling devices.
Preferably, the step 6 further comprises:
there is a space between any two filling devices.
Preferably, each of the trolley sets comprises two trolley trolleys.
The application also provides a cart for the cabin filling device, which comprises an upper layer bracket, a lower layer bracket, a connecting device and a brake screw rod; wherein,
the upper layer bracket is connected with the lower layer bracket through a connecting device;
the brake screw is installed on the lower layer bracket.
Preferably, the brake screw comprises a brake cylinder and a screw mounted within the brake cylinder, the screw being movable relative to the brake cylinder.
Preferably, the brake screw further comprises a brake pin, the brake cylinder is provided with a first hole, the screw is provided with a plurality of second holes, and the brake pin is adapted to be inserted into the first hole and the second hole simultaneously.
Preferably, the connecting means is a strap.
Preferably, the strap is provided with a ratchet type tightener.
Preferably, the cart for the cabin filling device further comprises a steel cable, wherein the steel cable is arranged on the upper layer bracket and is used for being connected with the sliding rail cart group.
The cabin filling method has the following advantages:
1. the cabin sliding rail is utilized, so that the filler can be moved into the cabin from the cabin door along the sliding rail, manual carrying is avoided, and the cabin is rapid and convenient;
2. the filling devices can slide in the engine room, and the inspection space can be replaced to each space in the engine room through replacement among the filling devices, so that the tester can quickly inspect the structure of the engine room without moving fillers out of the engine room, and the test period is shortened;
3. the filling device and the loading equipment in the cabin are strictly independent in space, so that the normal operation of the loading equipment in the cabin is prevented from being influenced, and potential safety hazards are eliminated;
4. the filling device has the advantages of simple structure, simplicity and convenience in operation, strong practical reliability and suitability for airplane structure fatigue tests.
Drawings
Fig. 1 is a schematic flow diagram of a nacelle filling method according to a first embodiment of the invention.
Fig. 2 is a schematic structural view of a filling device of the cabin filling method of the present invention.
FIG. 3 is a schematic illustration of the cabin filling apparatus of the present application being placed within an aircraft cabin.
Wherein:
the device comprises a sliding rail cart 1, an upper layer bracket 2, a filling foam 3, a binding band with a ratchet wheel type tightener 4, a brake screw rod 5, a lower layer bracket 6 and a steel cable 7.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
Fig. 1 is a schematic flow diagram of a nacelle filling method according to a first embodiment of the invention. Fig. 2 is a schematic structural view of a filling device of the cabin filling method of the present invention. FIG. 3 is a schematic illustration of the cabin filling apparatus of the present application being placed within an aircraft cabin.
A cabin filling method as shown in fig. 1 for filling a filling device into an aircraft cabin, the cabin filling method comprising the steps of:
step 1: mounting the sliding rail cart group 1 on an I-shaped sliding rail at the upper part of an aircraft cabin;
step 2: placing the lower layer bracket 6 with the brake screw 5 on the floor of the engine room, and controlling the brake screw to extend out, so that the lower layer bracket 6 is suspended;
and step 3: placing the filling foam 3 on the lower layer bracket 6, and placing the upper layer bracket 2 on the placed filling foam 3;
and 4, step 4: the upper layer bracket 2 and the lower layer bracket 6 are connected through the binding belt 4, and the binding belt is tightened through adjusting a ratchet type tightener on the binding belt 4, so that the upper layer bracket and the lower layer bracket are enabled to clamp the filling foam in the middle to form a whole;
and 5: connecting a steel cable 7 with an anti-falling hook with a suspender of the sliding rail cart group 1 and a hanging ring of the upper layer bracket 2, and contracting a brake screw 5 of the lower layer bracket 6 to make the filling foam 3 hung on the sliding rail cart 1, thereby forming a filling device;
step 6: and pushing the filling device to reach a preset position in the aircraft cabin, extending out the brake screw rod 5, and transferring the weight load of the filling device to the floor of the aircraft body through the slide rail.
The cabin filling method has the following advantages:
1. the cabin sliding rail is utilized, so that the filler can be moved into the cabin from the cabin door along the sliding rail, manual carrying is avoided, and the cabin is rapid and convenient;
2. the filling devices can slide in the engine room, and the inspection space can be replaced to each space in the engine room through replacement among the filling devices, so that the tester can quickly inspect the structure of the engine room without moving fillers out of the engine room, and the test period is shortened;
3. the filling device and the loading equipment in the cabin are strictly independent in space, so that the normal operation of the loading equipment in the cabin is prevented from being influenced, and potential safety hazards are eliminated;
4. the filling device has the advantages of simple structure, simplicity and convenience in operation, strong practical reliability and suitability for airplane structure fatigue tests.
In this embodiment, the nacelle filling method further comprises:
step 6: and repeatedly manufacturing the filling devices, so that the cabin of the airplane is filled with a preset number of filling devices.
In this embodiment, the step 6 further includes: there is a space between any two filling devices.
In the present embodiment, each trolley group 1 comprises two trolleys.
The present application is described in further detail below by way of examples, it being understood that the examples do not constitute any limitation to the present application.
Referring to fig. 2 and 3, in the present embodiment, in a first step, two slide rail carts are respectively mounted on two i-shaped slide rails at the upper part of a cabin, each slide rail cart is a cart with four pulleys and capable of sliding on the slide rails of the cabin, and has a boom mechanism capable of suspending a heavy object;
secondly, placing the lower-layer support with the brake screw on the floor of the engine room, and enabling the brake screw to extend out completely to enable the lower-layer support to be suspended in the air to avoid floor loading equipment;
and thirdly, placing the selected filling foam on a lower layer bracket, and placing an upper layer bracket on the placed filling foam. Then, the upper layer bracket and the lower layer bracket are connected through the binding band, and the binding band is tightened through adjusting a ratchet type tightener on the binding band, so that the upper layer bracket and the lower layer bracket are enabled to clamp the filling foam in the middle to form a whole;
fourthly, connecting a steel cable with an anti-drop hook with a suspender of the sliding rail cart and a hanging ring of the upper layer bracket, and contracting a brake screw of the lower layer bracket to hang the filling foam on the sliding rail cart;
fifthly, pushing the filling device to reach a preset position, extending out the brake screw rod, and transferring the weight load of the filling device to the floor of the machine body through the slide rail to realize the protection of the slide rail;
and a sixth step of repeating the first to fifth steps and moving the filling device into the cabin in sequence without filling the cabin. A plurality of spaces are reserved between the filling devices to be used as inspection spaces (as shown in fig. 3), and channels are reserved on two sides of the filling devices to facilitate the testers to go in and out of the filling devices. Through the replacement between the filling device, the inspection space can be replaced to each space in the aircraft cabin, so that the tester can quickly and comprehensively inspect the aircraft body structure, and the technical requirements of the aircraft structure fatigue test are met.
Preferably, the upper layer bracket and the lower layer bracket are provided with hanging ring structures, so that the connection of the steel cable and the binding belt is convenient.
Preferably, the four corners of the lower support are provided with brake screws which are extended and retracted by rotating the screws, and the structure is convenient for the filling device to be placed on the floor of the cabin when the filling device is in place and keeps a certain distance with the floor (as shown in fig. 3), so that the sliding rails can be protected and the interference with floor loading equipment can be avoided.
In this embodiment, the upper bracket 2 and the lower bracket 6 preferably have a ring structure to facilitate the connection between the cable 7 and the strap 4.
Preferably, the lower support 6 is provided with brake screws 5 at four corners thereof, and is extended and contracted by rotating the screws. The structure is convenient for the filling device to be placed on the floor of the cabin when the filling device is in place, and keeps a certain distance with the floor (as shown in figure 2), thereby not only protecting the sliding rail, but also avoiding the interference with floor loading equipment.
In the fatigue test of the whole airplane, the method is applied, the key problem is solved, and the obvious effect is achieved. Practice proves that the method can reduce the inflation space of the engine room, reduce the inflation quantity, meet the test requirement of quick inflation and deflation, and can improve the test progress and reduce the test cost without moving the filler out of the engine room during inspection and maintenance.
The application also provides a cart for the cabin filling device, which comprises an upper layer bracket, a lower layer bracket, a connecting device and a brake screw rod; wherein, the upper layer bracket is connected with the lower layer bracket through a connecting device; the brake screw is arranged on the lower layer bracket.
In this embodiment, the brake screw includes a brake cylinder and a screw mounted within the brake cylinder, the screw being movable relative to the brake cylinder.
In this embodiment, the brake screw further comprises a brake pin, the brake cylinder is provided with a first hole, the screw is provided with a plurality of second holes, and the brake pin is adapted to be inserted into the first hole and the second hole simultaneously. By adopting the structure, when the screw of the screw rod needs to be braked and fixed, the brake pin can penetrate into the first hole and the second hole.
Referring to fig. 2, in the present embodiment, the attachment means is a strap.
Referring to fig. 2, in the present embodiment, a ratchet-type tightener is provided on the binding band.
Referring to fig. 2, in the present embodiment, the cart for a cabin filling apparatus further includes a wire rope disposed on the upper bracket, and the wire rope 7 is used for connecting with the trolley assembly 1.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A cabin filling method is used for filling a filling device into an airplane cabin, and is characterized in that the filling device comprises a cart for the cabin filling device, and the cart for the cabin filling device comprises an upper layer bracket (2), a lower layer bracket (6), a connecting device and a brake screw rod (5); wherein,
the upper layer bracket (2) is connected with the lower layer bracket (6) through a connecting device;
the brake screw (5) is arranged on the lower layer bracket (6);
the connecting device is a binding band (4);
the binding band (4) is provided with a ratchet wheel type tightener;
the cabin filling method comprises the following steps:
step 1: mounting a sliding rail cart group (1) on an I-shaped sliding rail at the upper part of an aircraft cabin;
step 2: placing a lower layer bracket (6) with a brake screw rod (5) on the floor of the engine room, and controlling the brake screw rod to extend out, so that the lower layer bracket (6) is suspended;
and step 3: placing the filling foam (3) on the lower layer bracket (6), and placing the upper layer bracket (2) on the placed filling foam (3);
and 4, step 4: the upper layer bracket (2) and the lower layer bracket (6) are connected through the binding belt (4), and the binding belt is tightened through adjusting a ratchet type tightener on the binding belt (4), so that the upper layer bracket and the lower layer bracket are enabled to clamp the filling foam in the middle to form a whole;
and 5: connecting a steel cable (7) with an anti-falling hook with a suspender of the sliding rail cart group (1) and a hanging ring of the upper layer bracket (2), and contracting a brake screw (5) on the lower layer bracket (6) to make the filling foam (3) hung on the sliding rail cart group (1) so as to form a filling device;
step 6: and after the filling device is pushed to reach a preset position in the aircraft cabin, the braking screw rod (5) is extended out, and the weight load of the filling device is transferred to the cabin floor through the sliding rail.
2. The cabin filling method according to claim 1, further comprising:
and 7: and repeatedly manufacturing the filling devices, so that the cabin of the airplane is filled with a preset number of filling devices.
3. The cabin filling method according to claim 2, wherein the step 7 further comprises:
there is a space between any two filling devices.
4. The nacelle filling method as claimed in claim 1, wherein each skid cart group (1) comprises two skid carts.
5. Nacelle filling method according to claim 1, wherein the brake screw (5) comprises a brake cylinder and a screw mounted in the brake cylinder, the screw being movable relative to the brake cylinder.
6. Nacelle filling method according to claim 5, wherein the brake screw (5) further comprises a brake pin, the brake cylinder being provided with a first hole and the screw being provided with a plurality of second holes, the brake pin being adapted to be inserted simultaneously into the first and second holes.
7. Cabin filling method according to claim 6, wherein said cart for a cabin filling apparatus further comprises a wire rope (7), said wire rope (7) being arranged on said upper bracket (2), said wire rope (7) being intended to be connected to a trolley cart set (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811039111.8A CN109279046B (en) | 2018-09-06 | 2018-09-06 | Cabin filling method and cart for cabin filling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811039111.8A CN109279046B (en) | 2018-09-06 | 2018-09-06 | Cabin filling method and cart for cabin filling device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109279046A CN109279046A (en) | 2019-01-29 |
| CN109279046B true CN109279046B (en) | 2021-07-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811039111.8A Active CN109279046B (en) | 2018-09-06 | 2018-09-06 | Cabin filling method and cart for cabin filling device |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102680181A (en) * | 2011-03-14 | 2012-09-19 | 铁道部运输局 | Method and device for testing vehicle body airtightness and fatigue of railway vehicle |
| CN102935896A (en) * | 2011-08-15 | 2013-02-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for adjusting and controlling cabin pressure |
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN107687921A (en) * | 2017-07-07 | 2018-02-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airtight inspection method of aircraft air-tight cabin |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170149257A1 (en) * | 2015-10-30 | 2017-05-25 | Engineering Design, Inc. | Field charging unit for various batteries in multiple deployable devices |
-
2018
- 2018-09-06 CN CN201811039111.8A patent/CN109279046B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102680181A (en) * | 2011-03-14 | 2012-09-19 | 铁道部运输局 | Method and device for testing vehicle body airtightness and fatigue of railway vehicle |
| CN102935896A (en) * | 2011-08-15 | 2013-02-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for adjusting and controlling cabin pressure |
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN107687921A (en) * | 2017-07-07 | 2018-02-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airtight inspection method of aircraft air-tight cabin |
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| Publication number | Publication date |
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| CN109279046A (en) | 2019-01-29 |
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