CN217730797U - Energy-absorbing structural unit for resisting falling and collision of airplane - Google Patents
Energy-absorbing structural unit for resisting falling and collision of airplane Download PDFInfo
- Publication number
- CN217730797U CN217730797U CN202222054685.0U CN202222054685U CN217730797U CN 217730797 U CN217730797 U CN 217730797U CN 202222054685 U CN202222054685 U CN 202222054685U CN 217730797 U CN217730797 U CN 217730797U
- Authority
- CN
- China
- Prior art keywords
- energy
- absorbing
- aircraft
- fixedly connected
- installation piece
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The utility model relates to the technical field of aircraft manufacturing, and discloses an energy-absorbing structural unit for resisting falling and collision of an aircraft, which comprises a cargo compartment floor beam and a lower body frame, wherein a first pin hole is formed in the side surface of the cargo compartment floor beam, a third mounting block is formed in the side surface of the body frame, the bottom end of the cargo compartment floor beam is movably connected with five second mounting blocks through connecting pins passing through the first pin holes, the bottom end of each second mounting block is fixedly connected with an energy-absorbing upright post, and the bottom end of each energy-absorbing upright post is fixedly connected with a first mounting block; the utility model discloses a many combined material energy-absorbing cylinder pipe bilateral symmetry arrange, and the top is passed through attach fitting and is connected with cargo hold floor crossbeam, and the bottom is passed through attach fitting and is connected with fuselage frame lower part and covering, weighs down the in-process at the aircraft, and the combined material cylinder pipe only bears the axial force, has effectively prolonged the conquassation distance, is favorable to the energy-absorbing destruction that advances gradually of combined material cylinder pipe, and the weight cost of paying out is less.
Description
Technical Field
The utility model relates to an aircraft manufacturing technical field, more specifically relate to an anti energy-absorbing constitutional unit who hits of aircraft.
Background
The flight accident of the airplane is difficult to avoid, and the life safety of the personnel on the airplane is seriously threatened. Therefore, in the event of a crash accident, the aircraft must be designed in a rational manner so that the lower structure of the cargo compartment floor of the aircraft absorbs as much impact energy as possible and reduces the impact overload transmitted to the passengers to within the tolerance limits of the human body.
In the process of the falling and collision of the airplane, the vertical impact kinetic energy is mainly dissipated through the compression, deformation, fracture and other forms of the lower structure of the floor, and the buffering and energy absorbing capacity of the lower structure of the cargo compartment floor can obviously influence the falling and collision resisting effect of the whole structure of the airplane. Considering that a larger use space exists in the lower structure of the cargo compartment floor of the transport aircraft, the energy absorption structure can be arranged, and the structure is a key focus of improving the dropping adaptability of the fuselage structure.
The prior art has the following defects: the lower part structure of the existing airplane fuselage floor is mostly a metal C-shaped opening upright post with an open section, and compared with a closed pipe fitting, the C-shaped post has low axial rigidity and is easier to buckle in the falling and collision process; compared with a novel light material, the aluminum alloy C-shaped column is poor in lightweight effect, and economy of aviation operation is reduced. With the application of a large number of composite materials in an airplane structure, a compression test of the composite material C-shaped stand column with an open section shows that the failure mode of the composite material C-shaped stand column is more complex, and particularly in the actual falling, collision and impact process, the composite material C-shaped stand column can be suddenly broken and cannot play a good buffering and energy absorbing effect.
SUMMERY OF THE UTILITY MODEL
In order to overcome the above-mentioned defect that exists among the prior art, the utility model provides an anti energy-absorbing structure unit that hits that weighs down of aircraft to solve the problem in the above-mentioned technical background.
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an anti energy-absorbing constitutional unit that hits that weighs down of aircraft, includes cargo hold floor crossbeam and fuselage frame, first pinhole has been seted up to the side of cargo hold floor crossbeam, third installation piece has been seted up to the side of fuselage frame, the bottom of cargo hold floor crossbeam passes five second installation pieces of first pinhole swing joint through the connecting pin, the bottom fixedly connected with energy-absorbing stand of second installation piece, the first installation piece of bottom fixedly connected with of energy-absorbing stand, the top swing joint that the connecting pin passed third installation piece and fuselage frame is passed to the bottom of first installation piece, the bottom fixedly connected with covering of fuselage frame, the long purlin of top fixedly connected with of covering, five the energy-absorbing stand is at the both ends of floor cargo hold crossbeam with the even distribution of certain angle.
Furthermore, the energy-absorbing upright column is designed into a composite energy-absorbing cylindrical tube, and the energy-absorbing upright column adopts a layer-losing design and weak link design method.
Furthermore, the five energy-absorbing upright columns are perpendicular to the tangential direction of the surface of the skin, and the five second mounting blocks are located at the same height.
Furthermore, the cargo compartment floor beam is made of a composite material E-shaped structure.
The utility model discloses a technological effect and advantage:
1. the utility model discloses a many combined material energy-absorbing cylinder pipe bilateral symmetry arrange, and the top is passed through attach fitting and is connected with cargo hold floor crossbeam, and the bottom is passed through attach fitting and is connected with fuselage frame lower part and covering, weighs down the in-process at the aircraft, and the combined material cylinder pipe only bears the axial force, has effectively prolonged the conquassation distance, is favorable to the energy-absorbing destruction that advances gradually of combined material cylinder pipe, and the weight cost of paying out is less.
2. The utility model discloses an use combined material cylinder pipe as fuselage substructure's energy-absorbing stand to adopt and lose layer design and weak link design method, guarantee that the energy-absorbing stand takes place to destroy progressively and can not snap under the axial force effect, absorb through the stable gradual failure mode and weigh down and hit the energy, reduce the overload that transmits the passenger cabin passenger.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of a cargo compartment floor beam of the present invention;
fig. 3 is a schematic structural view of the body frame of the present invention.
The reference signs are: 1. a cargo compartment floor beam; 2. an energy absorbing upright post; 3. a stringer; 4. a body frame; 5. covering a skin; 6. a first mounting block; 7. a first pin hole; 8. a second mounting block; 9. and a third mounting block.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the drawings of the present invention, and in addition, the forms of the structures described in the following embodiments are only examples, and the energy-absorbing structure unit for preventing the aircraft from falling and colliding related to the present invention is not limited to the structures described in the following embodiments, and all other embodiments obtained by a person skilled in the art without creative labor belong to the scope of protection of the present invention.
Referring to fig. 1 to 3, the utility model provides an anti energy-absorbing structure unit that hits that weighs down of aircraft, including cargo hold floor crossbeam 1 and fuselage frame 4, first pinhole 7 has been seted up to cargo hold floor crossbeam 1's side, third installation piece 9 has been seted up to fuselage frame 4's side, cargo hold floor crossbeam 1's bottom passes first pinhole 7 swing joint through the connecting pin has five second installation pieces 8, the bottom fixedly connected with energy-absorbing stand 2 of second installation piece 8, the first installation piece 6 of bottom fixedly connected with of energy-absorbing stand 2, the top swing joint that the connecting pin passed third installation piece 9 and fuselage frame 4 is passed to the bottom of first installation piece 6, the bottom fixedly connected with covering 5 of fuselage frame 4, the top fixedly connected with long purlin 3 of covering 5, the even both ends at cargo hold floor crossbeam 1 of distribution of energy-absorbing stand 2.
The energy-absorbing upright column 2 is designed into a composite energy-absorbing cylindrical tube, the energy-absorbing upright column 2 adopts a lost layer design and weak link design method, progressive damage of the energy-absorbing upright column under the action of axial force is guaranteed, the energy-absorbing upright column cannot be suddenly broken, the energy-absorbing process is stable, and energy is absorbed more.
The five energy-absorbing upright columns 2 are vertical to the surface of the skin 5, and the five second mounting blocks 8 are at the same height, so that the energy-absorbing upright columns 2 are ensured to be only subjected to axial force.
The cargo compartment floor cross beam 1 is of a composite material E-shaped structure, the structural strength of the cargo compartment floor cross beam 1 is improved, and the self weight of the structure is reduced.
The utility model discloses a theory of operation: the bottom of the skin 5 collides, five energy-absorbing columns 2 which are uniformly distributed on two sides of the cargo compartment floor beam 1 receive axial force to absorb impact force, so that the impact force received by the cargo compartment floor beam 1 is reduced, the energy-absorbing columns 2 adopt a layer-losing design and a weak link design by using composite material cylindrical pipes, the condition that the energy-absorbing columns are progressively destroyed under the action of the axial force and cannot be suddenly broken is ensured, and the energy-absorbing process is stable and the energy-absorbing quantity is large.
The points to be explained are: first, in the description of the present application, unless otherwise specified and limited, the terms "mounted," "connected," "connecting," and "connecting" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, and "upper," "lower," "left," "right," and the like are used only to indicate a relative positional relationship, and when an absolute position of an object to be described is changed, the relative positional relationship may be changed;
secondly, the method comprises the following steps: in the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are related, and other structures can refer to the conventional design, and under the condition of no conflict, the same embodiment and different embodiments of the present invention can be combined with each other;
and finally: the above description is only for the preferred embodiment of the present invention and should not be construed as limiting the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The utility model provides an anti energy-absorbing constitutional unit that hits of aircraft, includes cargo hold floor crossbeam (1) and lower part fuselage frame (4), its characterized in that, first pinhole (7) have been seted up to the side of cargo hold floor crossbeam (1), third installation piece (9) have been seted up to the side of fuselage frame (4), the bottom of cargo hold floor crossbeam (1) passes first pinhole (7) swing joint through the connecting pin has five second installation pieces (8), the bottom fixedly connected with energy-absorbing stand (2) of second installation piece (8), the first installation piece (6) of bottom fixedly connected with of energy-absorbing stand (2), the bottom of first installation piece (6) passes the top swing joint of third installation piece (9) and fuselage frame (4) through the connecting pin, the bottom fixedly connected with covering (5) of fuselage frame (4), the top fixedly connected with stringer (3) of covering (5), five energy-absorbing stand (2) are with the even distribution of certain angle at the both ends of cargo hold crossbeam (1).
2. An aircraft crash-resistant energy-absorbing structural unit as defined in claim 1, wherein: the energy-absorbing upright column (2) is made of a composite material cylindrical pipe, and the energy-absorbing upright column (2) is designed by a lost layer and a weak link.
3. An aircraft crash-resistant energy-absorbing structural unit as defined in claim 1, wherein: the five energy-absorbing upright columns (2) are vertical to the surface of the skin (5), and the five second mounting blocks (8) are at the same height.
4. An energy absorbing structural unit for resisting crash of an aircraft according to claim 1, wherein: the cargo compartment floor beam (1) is of a composite material E-shaped structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222054685.0U CN217730797U (en) | 2022-08-05 | 2022-08-05 | Energy-absorbing structural unit for resisting falling and collision of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222054685.0U CN217730797U (en) | 2022-08-05 | 2022-08-05 | Energy-absorbing structural unit for resisting falling and collision of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217730797U true CN217730797U (en) | 2022-11-04 |
Family
ID=83813060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222054685.0U Active CN217730797U (en) | 2022-08-05 | 2022-08-05 | Energy-absorbing structural unit for resisting falling and collision of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217730797U (en) |
-
2022
- 2022-08-05 CN CN202222054685.0U patent/CN217730797U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2735093C (en) | Vehicle front-end for mounting to the front face of a track-bound vehicle, in particular a rail vehicle | |
| DK2694347T3 (en) | A rail vehicle fitted with a crumple zone | |
| US8740150B2 (en) | Connection of a wing to a fuselage of an airplane | |
| US8142873B2 (en) | Rod for supporting components in a fuselage cell structure of an aircraft | |
| CN108032912B (en) | Automobile engine hood with special microcell filling layer | |
| CN107416042B (en) | A kind of endian format framework beam of front of car floor | |
| CN111002934A (en) | Retractable layering buffering car bumper step by step | |
| WO2020047924A1 (en) | Collision energy absorption structure and rail vehicle having same | |
| US20160214719A1 (en) | Floor Attachment Assembly and Aircraft Seat | |
| CN217730797U (en) | Energy-absorbing structural unit for resisting falling and collision of airplane | |
| CN112027060A (en) | Energy-absorbing upright column for lower part of cargo compartment floor of airplane | |
| CN209080000U (en) | A kind of automobile-used anti-collision structure | |
| CN108674635A (en) | A kind of undercarriage pendant hits energy absorption device | |
| CN209833781U (en) | Connecting assembly and vehicle | |
| US9493134B2 (en) | Motor vehicle rollover protection device and method | |
| US6886779B2 (en) | Impact-absorbing, load-limiting connection device and rotary wing aircraft having such a connection device | |
| CN208868033U (en) | Vehicle end skeleton structure and rail vehicle with it | |
| CN102582821A (en) | Energy absorption scheme and layout mode of lower square tube supporting rod structure of passenger cabin floor of civil aircraft | |
| CN109455290A (en) | A kind of cargo deck lower part endergonic structure unit for fitting pendant property for improving aircraft | |
| CN112373672A (en) | Energy absorption structure of lower structure of cargo compartment floor of airplane | |
| CN201367050Y (en) | Passenger car frame carling structure | |
| CN220332927U (en) | Anti-falling collision machine body structure | |
| Ubels et al. | Increasing the survivability of helicopter accidents over water | |
| CN201172402Y (en) | Safety screen for automobile | |
| CN219573503U (en) | Test barrier for automobile crash test |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |