CN113895633B - Safety belt device of civil aircraft - Google Patents
Safety belt device of civil aircraft Download PDFInfo
- Publication number
- CN113895633B CN113895633B CN202111502603.8A CN202111502603A CN113895633B CN 113895633 B CN113895633 B CN 113895633B CN 202111502603 A CN202111502603 A CN 202111502603A CN 113895633 B CN113895633 B CN 113895633B
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- aircraft
- seat
- safety belt
- mounting seat
- elastic
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/062—Belts or other passenger restraint means for passenger seats
Abstract
The invention provides a civil aircraft safety belt device, which belongs to the technical field of aircraft accessories and comprises an aircraft body, a buffering limiting part, a mounting seat, an elastic jacking part, a winding part and a safety belt, wherein a clamping groove is formed in one side of the aircraft body, the mounting seat is movably arranged in the clamping groove, the mounting seat can slide along the inside of the clamping groove under the action of inertia in the process of emergency stop or braking of an aircraft, the safety belt is wound on the winding part, one end of the safety belt extends to the outside of the aircraft body, the winding part is rotatably arranged on one side of the mounting seat, one end of the elastic jacking part is connected with the aircraft body, and the other end of the elastic jacking part is connected with the mounting seat. Compared with the prior art, the embodiment of the invention can limit the driver on the driving seat when the aircraft is in an emergency, and has the advantages of simple structure, low cost, convenient maintenance and good protection effect.
Description
Technical Field
The invention belongs to the technical field of aircraft accessories, and particularly relates to a safety belt device of a civil aircraft.
Background
Aircraft safety belts are protective devices used to restrain a pilot in an emergency situation on a seat to protect the pilot from striking the aircraft's nose gear.
In the prior art, most of the safety belts of the aircraft detect collision information of the aircraft by using a collision sensor, the collision information is transmitted to a control unit, the control unit is used for controlling a motor to be coupled with a safety belt winding device, and further limitation of installation of the safety belt winding device is realized, and locking of the safety belts is realized.
Disclosure of Invention
In view of the above-mentioned deficiencies of the prior art, an embodiment of the present invention provides a seatbelt device for a civil aircraft.
In order to solve the technical problems, the invention provides the following technical scheme:
a safety belt device of a civil aircraft comprises an aircraft body, a buffering limiting part, a mounting seat, an elastic jacking part, a rolling part and a safety belt,
a clamping groove is formed in one side of the aircraft body, the mounting seat is movably arranged in the clamping groove, the mounting seat can slide along the inside of the clamping groove under the action of inertia in the process of sudden stop or braking of the aircraft,
the safety belt is wound on the winding part, one end of the safety belt extends to the outside of the aircraft body,
the winding part is rotatably arranged on one side of the mounting seat, one end of the elastic jacking piece is connected with the aircraft body, the other end of the elastic jacking piece is connected with the mounting seat and used for providing elastic support for the mounting seat,
the buffer limiting part is arranged inside the clamping groove, and when the mounting seat moves along the inside of the clamping groove, the buffer limiting part is used for limiting the rotation of the winding part.
As a further improvement of the invention: the winding part comprises a reel and a post rod fixedly arranged at the end part of the reel,
one end of the post rod, which is far away from the reel, is rotationally connected with the mounting seat, and the safety belt is wound on the outer side of the reel.
As a further improvement of the invention: the buffer limiting part comprises a supporting seat, an elastic part, a flexible connecting piece, a pull ring and a sliding seat,
the supporting seat is fixedly arranged inside the clamping groove, a channel is arranged inside the supporting seat, the sliding seat is arranged inside the channel in a sliding way,
one end of the elastic part is connected with the sliding seat, the other end of the elastic part is connected with the inner wall of the channel, one end of the flexible connecting part is connected with the sliding seat, the other end of the flexible connecting part extends to the outside of the supporting seat and is connected with the pull ring, and the side wall of the post rod is fixedly provided with a protruding part which can be inserted into the pull ring.
As a further improvement of the invention: the channels are provided with a plurality of groups in the supporting seat, the channels are distributed at intervals, the slide seat is arranged in each group of channels in a sliding manner, one side of each slide seat is connected with the inner wall of the channel through the elastic piece, one side of each slide seat is connected with the flexible connecting piece,
one end of each group of the flexible connecting pieces far away from the corresponding sliding seat extends to the outside of the supporting seat and is connected with a group of pull rings, the pull rings are linearly distributed at intervals outside the supporting seat,
the protruding pieces are arranged on the outer side of the post rod at intervals and are in one-to-one correspondence with the pull rings.
As a still further improvement of the invention: the plurality of protruding pieces are spirally distributed along the outer side of the pole.
As a still further improvement of the invention: the protruding piece is of a hook-shaped structure or a straight rod-shaped structure.
As a still further improvement of the invention: the utility model discloses a post rod installation structure, including mount pad, post rod, installation hole, the mount pad is seted up on one side and is supplied post rod male mounting hole, the post rod with it links to each other to reset through elasticity between the mounting hole inner wall, elasticity resets and is used for driving post rod antiport.
Compared with the prior art, the invention has the beneficial effects that:
in the embodiment of the invention, when the safety belt retractor is used, the safety belt can be pulled, the safety belt drives the winding part to adaptively rotate so as to realize unwinding of the safety belt, one end of the safety belt is connected with the buckle on the driver seat so as to limit a flight crew on the driver seat, and in the process, the movement of the mounting seat can be limited by utilizing the elastic supporting function of the elastic supporting piece on the mounting seat, namely, the movement of the winding part is limited; when the aircraft takes off, runs into emergency and needs braking or scram in the flight and landing process, the mounting seat slides along the inside of the clamping groove under the action of inertia to drive the rolling part to move synchronously, when the rolling part moves to a certain position, the buffering limiting part can limit the rotation of the rolling part, so that the safety belt is limited to be continuously unreeled, a pilot is limited on a seat, the pilot is prevented from striking the front gear of the aircraft and even throwing the aircraft under the action of inertia, the protection of the pilot is realized, compared with the prior art, when the aircraft is in an emergency, the pilot can be limited on the pilot seat, and the aircraft safety belt has the advantages of simple structure, low cost, convenience in maintenance and good protection effect.
Drawings
FIG. 1 is a schematic structural view of a civilian aircraft seatbelt apparatus;
FIG. 2 is a schematic structural view of a buffering and limiting part in a safety belt device of a civil aircraft;
FIG. 3 is a schematic view of the structure of a retractor of a civilian aircraft seatbelt apparatus;
FIG. 4 is an enlarged view of area A of FIG. 1;
FIG. 5 is an enlarged view of the area B in FIG. 1;
in the figure: 10-aircraft body, 101-top support seat, 102-through hole, 103-guide rail, 104-clamping groove, 20-buffer limiting part, 201-supporting seat, 202-channel, 203-flexible connecting piece, 204-elastic piece, 205-pull ring, 206-sliding seat, 30-mounting seat, 301-mounting hole, 40-elastic top support piece, 50-elastic reset piece, 60-rolling part, 601-protruding piece, 602-pole, 603-rolling shaft and 70-safety belt.
Detailed Description
The technical solution of the present patent will be described in further detail with reference to the following embodiments.
Reference will now be made in detail to embodiments of the present patent, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present patent and are not to be construed as limiting the present patent.
Referring to fig. 1, the embodiment provides a civil aircraft safety belt device, which includes an aircraft body 10, a buffering limiting portion 20, a mounting seat 30, an elastic propping member 40, a winding portion 60, and a safety belt 70, wherein a slot 104 is formed on one side of the aircraft body 10, the mounting seat 30 is movably disposed inside the slot 104, the mounting seat 30 can slide along the inside of the slot 104 under the inertia effect during an emergency stop or braking process of an aircraft, the safety belt 70 is wound around the winding portion 60, one end of the safety belt 70 extends to the outside of the aircraft body 10, the winding portion 60 is rotatably disposed on one side of the mounting seat 30, one end of the elastic propping member 40 is connected to the aircraft body 10, the other end of the elastic propping member is connected to the mounting seat 30 for providing elastic support for the mounting seat 30, the buffering limiting portion 20 is disposed inside the slot 104, when the mounting seat 30 moves along the inside of the engaging groove 104, the buffer position-limiting portion 20 is used to limit the rotation of the winding portion 60.
When the seat belt retractor is used, the safety belt 70 can be pulled, the safety belt 70 drives the winding portion 60 to rotate adaptively, so that the safety belt 70 is unwound, one end of the safety belt 70 is connected with a buckle on a driver seat, so that a flight crew is limited on the driver seat, and in the process, the elastic supporting function of the elastic supporting piece 40 on the installation seat 30 is utilized, so that the movement of the installation seat 30 can be limited, namely the movement of the winding portion 60 is limited; when the aircraft needs braking or sudden stop in emergency situations during takeoff, flight and landing of the aircraft, the mounting seat 30 slides along the inside of the clamping groove 104 under the action of inertia to drive the winding part 60 to move synchronously, and when the winding part 60 moves to a certain position, the buffering limiting part 20 can limit the rotation of the winding part 60, so that the safety belt 70 is limited to be continuously unwound, a pilot is limited on the seat, the pilot is prevented from impacting the front gear of the aircraft and even throwing out of the aircraft under the action of inertia, and the protection of the pilot is realized.
Referring to fig. 1 and 3, in an embodiment, the winding portion 60 includes a winding shaft 603 and a post 602 fixedly disposed at an end of the winding shaft 603, an end of the post 602 away from the winding shaft 603 is rotatably connected to the mounting seat 30, and the safety belt 70 is wound around an outer side of the winding shaft 603.
By pulling the safety belt 70, the safety belt 70 can drive the reel 603 and the pole 602 to rotate along one side of the mounting seat 30, so that the safety belt 70 can be unreeled, and the safety belt 70 can be smoothly stretched to be connected with the driving seat.
Referring to fig. 1, 2, 3, 4 and 5, in an embodiment, the buffer position-limiting portion 20 includes a supporting seat 201, an elastic member 204, a flexible connecting member 203, a pull ring 205 and a sliding seat 206, the supporting seat 201 is fixedly installed inside the clamping groove 104, a channel 202 is formed inside the supporting seat 201, the sliding seat 206 is slidably installed inside the channel 202, one end of the elastic member 204 is connected to the sliding seat 206, the other end of the elastic member is connected to an inner wall of the channel 202, one end of the flexible connecting member 203 is connected to the sliding seat 206, the other end of the flexible connecting member extends to the outside of the supporting seat 201 and is connected to the pull ring 205, and a protruding member 601 capable of being inserted into the pull ring 205 is fixedly disposed on a side wall of the post 602.
When the mounting seat 30 slides along the inside of the slot 104 under the inertia effect, the post 602 and the reel 603 can be driven to move synchronously, when the post 602 drives the protrusion 601 to move to a certain position, because a driver has a pulling effect on the safety belt 70 under the inertia effect, the reel 603 and the post 602 are driven to rotate along one side of the mounting seat 30, and further the protrusion 601 is driven to rotate, at this time, the protrusion 601 can be inserted into the pull ring 205 in a rotating manner and drives the pull ring 205 to move in a direction away from the supporting seat 201, so that the sliding seat 206 is pulled to move along the inside of the channel 202 through the flexible connecting member 203 to extrude the elastic member 204, at this time, the support effect of the elastic member 204 is utilized to further limit the continuous movement of the pull ring 205, thereby limiting the continuous rotation of the protrusion 601, the post 602 and the reel 603, and further unwinding of the safety belt 70, and further pulling the driver, and preventing the driver from impacting the front gear under the inertia effect of the aircraft, the protection of the driver is realized, and under the supporting action of the elastic piece 204, the reel 603 does not stop rotating immediately, but along with the increase of the compression degree of the elastic piece 204, the reel 603 stops rotating slowly, so that the situation that the force of the safety belt 70 acting on the driver is too large is avoided, the reinjuring of the driver is prevented, and the further protection of the driver is realized.
Referring to fig. 2 and 3, in an embodiment, the channel 202 is provided with a plurality of groups inside the support seat 201, the plurality of channels 202 are distributed at intervals, the slide base 206 is slidably disposed inside each group of channels 202, one side of each group of slide base 206 is connected to the inner wall of the channel 202 through the elastic member 204, one side of each group of slide base 206 is connected to the flexible connecting member 203, one end of each group of flexible connecting member 203, which is far away from the corresponding slide base 206, extends to the outside of the support seat 201 and is connected to one group of pull rings 205, the plurality of pull rings 205 are linearly distributed at intervals outside the support seat 201, the plurality of groups of protruding members 601 are arranged at intervals outside the post 602, and the plurality of protruding members 601 are in one-to-one correspondence with the plurality of pull rings 205.
Through the one-to-one correspondence of the plurality of protruding parts 601 and the plurality of pull rings 205, the plurality of protruding parts 601 can enter the corresponding pull rings 205 in a rotating mode respectively, and the pressing of the plurality of groups of elastic parts 204 is matched to limit the rotation of the reel 603 together, so that the limiting effect of the reel 603 is improved, and the limiting effect of the safety belt 70 is improved.
Referring to fig. 3, in one embodiment, a plurality of the protrusions 601 are spirally distributed along the outer side of the mast 602, so that a plurality of the protrusions 601 can sequentially enter the corresponding pull rings 205, when the braking force of the aircraft is small, the restraint of the safety belt 70 can be realized by the cooperation between one or more groups of the protrusions 601 and the pull rings 205, and the rest groups of the protrusions 601 and the corresponding pull rings 205 do not need to enter the cooperation state.
Referring to fig. 1 and 3, in an embodiment, the protruding member 601 may be a hook-shaped structure, but the protruding member 601 may also be a straight rod-shaped structure or other shapes, which is not limited herein, and only needs to ensure that the protruding member 601 can enter the interior of the tab 205 when rotating with the post 602.
In one embodiment, the flexible connecting element 203 may be a rope or a flexible wire, which is not limited herein.
In one embodiment, the elastic top supporting member 40 and the elastic member 204 may be a spring or a metal spring, which is not limited herein.
Referring to fig. 1, in an embodiment, a mounting hole 301 for inserting the post 602 is formed in one side of the mounting base 30, the post 602 is connected to an inner wall of the mounting hole 301 through an elastic restoring member 50, and the elastic restoring member 50 is used for driving the post 602 to rotate reversely.
After the flight mission is finished, the connection between the safety belt 70 and the driving seat can be released, and at this time, the elastic restoring piece 50 can drive the post 602 to rotate reversely so as to wind up the safety belt 70, so that the safety belt 70 is wound up to a certain length into the clamping groove 104, and the length of the safety belt 70 exposed outside is prevented from being too long.
In one embodiment, the elastic restoring member 50 may be a coil spring or a torsion spring, which is not limited herein.
Referring to fig. 1, in an embodiment, a supporting seat 101 is further fixedly disposed on an inner wall of the slot 104, and when the mounting seat 30 slides along the inside of the slot 104 against the elastic supporting member 40 under the action of inertia, the mounting seat may act on the supporting seat 101 to further limit the position of the mounting seat 30, at this time, the protruding member 601 just enters the inside of the pull ring 205 along with the rotation of the post 602, so as to achieve the matching between the protruding member 601 and the pull ring 205.
Referring to fig. 1, in one embodiment, the aircraft body 10 is further provided with a through hole 102 for the safety belt 70 to extend from the inside to the outside of the slot 104.
Referring to fig. 1, in an embodiment, a guide rail 103 is fixedly installed on an inner wall of the slot 104, and a limit groove (not shown) adapted to the guide rail 103 is formed on a side wall of the mounting base 30, so that the mounting base 30 can slide stably inside the slot 104 under an inertia effect through cooperation between the slide groove and the guide rail 103.
In another embodiment, the winding portion 60 may further include a winding rod and a gear fixedly disposed on the winding rod, an end of the winding rod is rotatably connected to the mounting seat 30, the safety belt 70 is wound on an outer side of the winding rod, the buffering limiting portion 20 may further include a limiting inserted link, when the mounting seat 30 moves along the inside of the slot 104, the winding rod and the gear may be driven to move synchronously, and one end of the limiting inserted link may be inserted between teeth of the gear, so as to limit rotation of the winding rod, so as to limit continuous unwinding of the safety belt 70, and further limit a driver on the driving seat, thereby protecting the driver.
In the embodiment of the invention, when the seat belt retractor is used, the safety belt 70 can be pulled, the safety belt 70 drives the winding part 60 to adaptively rotate so as to unwind the safety belt 70, one end of the safety belt 70 is connected with a buckle on a driver seat so as to limit a flight crew on the driver seat, and in the process, the elastic supporting function provided by the elastic supporting piece 40 on the mounting seat 30 can limit the movement of the mounting seat 30, namely the movement of the winding part 60; when the aircraft needs braking or emergency stop when meeting emergency in the processes of takeoff, flight and landing, the mounting seat 30 slides along the inside of the clamping groove 104 under the action of inertia to drive the winding part 60 to move synchronously, when the winding part 60 moves to a certain position, the buffering limiting part 20 can limit the rotation of the winding part 60, so that the safety belt 70 is limited to be continuously unwound, a pilot is limited on the seat, the pilot is prevented from impacting the front gear of the aircraft and even throwing out the aircraft under the action of inertia, and the protection of the pilot is realized.
Although the preferred embodiments of the present patent have been described in detail, the present patent is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present patent within the knowledge of those skilled in the art.
Claims (7)
1. A safety belt device of a civil aircraft is characterized by comprising an aircraft body, a buffering limiting part, a mounting seat, an elastic top supporting part, a winding part and a safety belt,
a clamping groove is formed in one side of the aircraft body, the mounting seat is movably arranged in the clamping groove, the mounting seat can slide along the inside of the clamping groove under the action of inertia in the process of sudden stop or braking of the aircraft,
the safety belt is wound on the winding part, one end of the safety belt extends to the outside of the aircraft body,
the winding part is rotatably arranged on one side of the mounting seat, one end of the elastic jacking piece is connected with the aircraft body, the other end of the elastic jacking piece is connected with the mounting seat and used for providing elastic support for the mounting seat,
the buffer limiting part is arranged inside the clamping groove, and when the mounting seat moves along the inside of the clamping groove, the buffer limiting part is used for limiting the rotation of the winding part.
2. The civilian aircraft seatbelt apparatus of claim 1, wherein the take-up includes a spool and a post fixedly disposed at an end of the spool,
one end of the post rod, which is far away from the reel, is rotationally connected with the mounting seat, and the safety belt is wound on the outer side of the reel.
3. The civilian aircraft seatbelt apparatus of claim 2, wherein the bump stopper comprises a support seat, an elastic member, a flexible connecting member, a pull ring, and a slider,
the supporting seat is fixedly arranged inside the clamping groove, a channel is arranged inside the supporting seat, the sliding seat is arranged inside the channel in a sliding way,
one end of the elastic part is connected with the sliding seat, the other end of the elastic part is connected with the inner wall of the channel, one end of the flexible connecting part is connected with the sliding seat, the other end of the flexible connecting part extends to the outside of the supporting seat and is connected with the pull ring, and the side wall of the post rod is fixedly provided with a protruding part which can be inserted into the pull ring.
4. The civilian aircraft seatbelt apparatus according to claim 3, wherein the channel has a plurality of sets of channels formed therein, the plurality of channels are spaced apart from each other, the slide is slidably disposed in each set of channels, one side of each set of slide is connected to the inner wall of the channel via the elastic member, and one side of each set of slide is connected to the flexible connecting member,
one end of each group of the flexible connecting pieces far away from the corresponding sliding seat extends to the outside of the supporting seat and is connected with a group of pull rings, the pull rings are linearly distributed at intervals outside the supporting seat,
the protruding pieces are arranged on the outer side of the post rod at intervals and are in one-to-one correspondence with the pull rings.
5. The civilian aircraft seatbelt apparatus of claim 4, wherein a plurality of the projections are helically disposed along an outer side of the post.
6. A civilian aircraft seatbelt apparatus according to any one of claims 3 to 5, wherein the projection is of hook or straight rod configuration.
7. The civilian aircraft seatbelt apparatus as claimed in claim 2, wherein a mounting hole is formed at one side of the mounting seat for the insertion of the post, and the post is connected to an inner wall of the mounting hole by an elastic return member for driving the post to rotate in a reverse direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111502603.8A CN113895633B (en) | 2021-12-10 | 2021-12-10 | Safety belt device of civil aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111502603.8A CN113895633B (en) | 2021-12-10 | 2021-12-10 | Safety belt device of civil aircraft |
Publications (2)
| Publication Number | Publication Date |
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| CN113895633A CN113895633A (en) | 2022-01-07 |
| CN113895633B true CN113895633B (en) | 2022-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111502603.8A Active CN113895633B (en) | 2021-12-10 | 2021-12-10 | Safety belt device of civil aircraft |
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|---|---|
| CN113895633A (en) | 2022-01-07 |
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