CN209427053U - It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism - Google Patents
It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism Download PDFInfo
- Publication number
- CN209427053U CN209427053U CN201822060237.5U CN201822060237U CN209427053U CN 209427053 U CN209427053 U CN 209427053U CN 201822060237 U CN201822060237 U CN 201822060237U CN 209427053 U CN209427053 U CN 209427053U
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- fixed
- guide rail
- air
- air guide
- launching platform
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Abstract
The utility model discloses a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, air guide rail is provided with above lower guideway, air guide rail is fixedly arranged above launching platform, and pressurization air pump and battery are provided in launching platform, and the air pump that pressurizes is connected to air guide rail by air delivery pipe；The lower end of launching platform is fixed with linear motor core iron, and the lower end two sides of linear motor core iron are provided with linear motor coil, and linear motor coil fixes on the ground；Wherein the bottom end of air guide rail is provided with air permeable plate, pore is offered on air permeable plate, closed between air permeable plate and air guide rail to have air guide rail cavity, air guide rail cavity is connected to pressurization air pump by air delivery pipe, and air delivery pipe road is additionally provided with check valve；The front end of launching platform is provided with impact head, and the top of launching platform is fixed with positive stop and backstop, is additionally provided on lower guideway and blocks mechanism.The utility model has the beneficial effects that solving the problems, such as that aircraft can consume a large amount of oil plants when taking off.
Description
Technical field
The utility model relates to aircraft launching apparatus technical fields, more specifically, being related to a kind of with blocking mechanism
Auxiliary takeoff apparatus for airplane.
Background technique
Aircraft is a kind of essential vehicles of today's society, is needed when generally taking off enterprising in straightaway
Row slides over long distances, when the air generated in wing taxiing procedures, which lifts power, is greater than the self gravity of aircraft, while having reached
When rapidly spending, it can be completed and take off, the runway on airport is all up to several hundred rice even several kms；Therefore aircraft meeting when taking off
Consuming a large amount of oil plants influences cruising ability, and the power of cruising ability is extremely important for operational aircraft.
Therefore, a kind of auxiliary takeoff apparatus for airplane that can increase aircraft cruising ability of utility model is those skilled in the art
Problem to be solved.
Utility model content
For disadvantages described above, the utility model provide it is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, to solve
Aircraft can consume the problem of a large amount of oil plants influence cruising ability when taking off.
To achieve the above object, the utility model uses following technical scheme:
It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, including lower guideway, be provided with above the lower guideway
Air guide rail, air guide rail are fixedly arranged above launching platform, and pressurization air pump and battery are provided in launching platform, and pressurize gas
Pump is connected to air guide rail by air delivery pipe；The lower end of the launching platform is fixed with linear motor core iron, linear motor
The lower end two sides of core iron are provided with linear motor coil, and linear motor coil fixes on the ground；The rear end of the launching platform
Two sides are respectively fixed with mounting plate, and fixing axle is fixed on mounting plate, and fixing axle connects articulated shaft by lever one,
By lever two, hingedly friction turbine/lever, the one end for the turbine/lever that rubs are hinged on launching platform articulated shaft, and other end setting exists
On the axis of rolling, the both ends of the axis of rolling are provided with friction pulley, and the middle position of the axis of rolling is provided with generator motor, generator motor
It is electrically connected with battery；The articulated shaft is fixedly arranged above electric push rod, is fixed with spring below articulated shaft and fixes
Bar, spring fixed link are interspersed in fixed plate, and spring is provided between articulated shaft and fixed plate, and spring pocket is mounted in spring fixed link
On, wherein electric push rod and fixed plate are all fixed on mounting plate；The front end of the launching platform is provided with impact head,
The top of launching platform is fixed with positive stop and backstop, and backstop is detachably mounted to the top of launching platform by bolt
End；It is additionally provided on the lower guideway and blocks mechanism；
Wherein the bottom end of air guide rail is provided with air permeable plate, and pore, air permeable plate and air guide rail are offered on air permeable plate
Between it is closed have an air guide rail cavity, air guide rail cavity passes through air delivery pipe connection pressurization air pump, air delivery pipe
On be additionally provided with check valve, check valve is arranged in air guide rail；
Wherein block mechanism include left connector, right connector, overload protection safety pin, drawstring, fixed ring, anti-flying barrel,
Check cable, jackscrew, rotating cylinder, fixing barrel, compressed spring, upper cover plate, protective cover and impact block, the left connector and right connection
Body is arranged on lower guideway, and left connector and right connector are connected and fixed by overload protection safety pin, overload protection safety pin
It is fixed by jackscrew, the both ends of overload protection safety pin are provided with anti-flying barrel, and anti-flying barrel is connected and fixed ring, fixed ring by drawstring
It is fixed on right connector；It is connected separately with check cable on the right side of the left side of the left connector and right connector, check cable twines
On the rotating cylinder for being fixed on lower guideway both ends, rotating cylinder is sleeved in fixing barrel, and fixing barrel is fixed in protective cover, protective cover
Top be fixed with upper cover plate, be provided with compressed spring between upper cover plate and the roof of rotating cylinder；The left connector and right company
The front end of junctor is both provided with impact block.
Further, the top of the impact head is sphere structure.
Further, the front end of the impact block is arcuate structure.
The beneficial effects of the utility model are: the present apparatus is safe and reliable, can second-mission aircraft take off, solve aircraft and rising
The problem of a large amount of oil plants influence cruising ability can be consumed when winged.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram with the auxiliary takeoff apparatus for airplane for blocking mechanism described in the utility model；
Fig. 2 is a kind of partial structural diagram with the auxiliary takeoff apparatus for airplane for blocking mechanism described in the utility model
One；
Fig. 3 is the structural schematic diagram of air guide rail described in the utility model；
Fig. 4 is the partial enlarged view at Fig. 3 A；
Fig. 5 is a kind of partial structural diagram with the auxiliary takeoff apparatus for airplane for blocking mechanism described in the utility model
Two；
Fig. 6 is the partial enlarged view at Fig. 5 B；
Fig. 7 is the partial enlarged view at Fig. 6 C；
Fig. 8 is a kind of partial structural diagram with the auxiliary takeoff apparatus for airplane for blocking mechanism described in the utility model
Three；
Fig. 9 is the partial enlarged view at Fig. 5 D；
Figure 10 is the structural schematic diagram described in the utility model for blocking mechanism；
Figure 11 is the partial enlarged view at Figure 10 E；
Figure 12 is the schematic top plan view described in the utility model for blocking mechanism；
Figure 13 is the partial enlarged view at Figure 12 F；
In figure, 1, lower guideway；2, air guide rail；3, launching platform；4, mechanism is blocked；5, pressurize air pump；6, air delivery
Pipeline；7, linear motor core iron；8, linear motor coil；9, mounting plate；10, lever one；11, lever two；12, fixed
Axis；13, articulated shaft；14, rub turbine/lever；15, the axis of rolling；16, friction pulley；17, generator motor；18, electric push rod；
19, spring；20, spring fixed link；21, fixed plate；22, battery；23, positive stop；24, backstop；25, impact head；201,
Check valve；202, air permeable plate；203, air guide rail cavity；204, pore；4001, left connector；4002, right connector；
4003, overload protection safety pin；4004, drawstring；4005, fixed ring；4006, anti-flying barrel；4007, check cable；4008, jackscrew；
4009, rotating cylinder；4010, fixing barrel；4011, compressed spring；4012, upper cover plate；4013, protective cover；4014, impact block.
Specific embodiment
The utility model is specifically described with reference to the accompanying drawing, according to Fig. 1-13, one kind has and blocks mechanism
Auxiliary takeoff apparatus for airplane, including lower guideway 1 is provided with air guide rail 2, the top of air guide rail 2 in the top of lower guideway 1
It is fixed with launching platform 3, pressurization air pump 5 and battery 22 are provided in launching platform 3, pressurization air pump 5 passes through air delivery pipe
Road 6 is connected to air guide rail 2；Linear motor core iron 7, the lower end two sides of linear motor core iron 7 are fixed in the lower end of launching platform 3
It is provided with linear motor coil 8, linear motor coil 8 fixes on the ground；It is respectively fixed in the rear end sides of launching platform 3
Mounting plate 9 is fixed with fixing axle 12 on mounting plate 9, and fixing axle 12 connects articulated shaft 13 by lever 1, hingedly
By lever 2 11, hingedly friction turbine/lever 14, one end of friction turbine/lever 14 are hinged on launching platform 3 axis 13, and the other end is set
It sets on the axis of rolling 15, the both ends of the axis of rolling 15 are provided with friction pulley 16, and the middle position of the axis of rolling 15 is provided with electricity generation and electromotion
Machine 17, generator motor 17 and battery 22 are electrically connected；Electric push rod 18, articulated shaft are fixedly arranged above in articulated shaft 13
13 lower section is fixed with spring fixed link 20, and spring fixed link 20 is interspersed in fixed plate 21, articulated shaft 13 and fixed plate 21 it
Between be provided with spring 19, spring 19 is sleeved in spring fixed link 20, and wherein electric push rod 18 and fixed plate 21 are all fixed on
On mounting plate 9；The front end of launching platform 3 is provided with impact head 25, is fixed with positive stop 23 on the top of launching platform 3
With backstop 24, backstop 24 is detachably mounted to the top of launching platform 3 by bolt；It is additionally provided on lower guideway 1
Block mechanism 4；
Wherein the bottom end of air guide rail 2 is provided with air permeable plate 202, and pore 204, air permeable plate are offered on air permeable plate 202
Closed between 202 and air guide rail 2 to have air guide rail cavity 203, air guide rail cavity 203 is connected to by air delivery pipe 6
Pressurize air pump 5, and check valve 201 is additionally provided on air delivery pipe 6, and check valve 201 is arranged in air guide rail 2；
Wherein blocking mechanism 4 includes left connector 4001, right connector 4002, overload protection safety pin 4003, drawstring
4004, fixed ring 4005, anti-flying barrel 4006, check cable 4007, jackscrew 4008, rotating cylinder 4009, fixing barrel 4010, compressed spring
4011, upper cover plate 4012, protective cover 4013 and impact block 4014, the left connector 4001 and right connector 4002 are arranged under
On guide rail 1, left connector 4001 and right connector 4002 are connected and fixed by overload protection safety pin 4003, overload protection safety
Pin 4003 is fixed by jackscrew 4008, and the both ends of overload protection safety pin 4003 are provided with anti-flying barrel 4006, and anti-flying barrel 4006 is logical
It crosses drawstring 4004 and is connected and fixed ring 4005, fixed ring 4005 is fixed on right connector 4002；A left side for the left connector 4001
Side and the right side of right connector 4002 are connected separately with check cable 4007, and check cable 4007 is fastened at 1 both ends of lower guideway
On rotating cylinder 4009, rotating cylinder 4009 is sleeved in fixing barrel 4010, and fixing barrel 4010 is fixed in protective cover 4013, protective cover
4013 top is fixed with upper cover plate 4012, is provided with compressed spring between upper cover plate 4012 and the roof of rotating cylinder 4009
4011；The front end of the left connector 4001 and right connector 4002 is both provided with impact block 4014.
In order to preferably realize the utility model, the top of impact head 25 is sphere structure.
In order to preferably realize the utility model, the front end of the impact block 4014 is arcuate structure.
In the present embodiment, pressurization air pump 5 is powered by battery 22, when needing to carry out Assisted Take Off to aircraft,
Aircraft is drawn on launching platform 3 by pulling equipment first, so that the front end of aircraft nose wheel tire is close to positive stop 23, then uses
Backstop 24 is fixed on the rear end of aircraft nose wheel tire by bolt, and aircraft is fixed immovable at this time；At this moment by aircraft engine
Power is transferred to maximum and holds the brake of aircraft, and the air pump 5 that pressurizes at this time is connected to air guide rail 2 by air delivery pipe 6, makes
Compressed air is sprayed by pore 204, is formed air film between air guide rail 2 and lower guideway 1 at this time, is reduced air and lead
Frictional force between rail 2 and lower guideway 1 is powered at the same time with external power supply to linear motor coil 8, at this moment in aircraft thrust
Under the action of 8 thrust of linear motor coil, launching platform 3 and aircraft meeting high-speed motion, when what is generated in wing taxiing procedures
When air lifts self gravity of the power greater than aircraft, the front tyre of aircraft can be detached from positive stop 23 and the completion of backstop 24 is taken off；
At this moment under the action of electric push rod 18, friction pulley 16 is in contact with lower guideway 1, drives the axis of rolling 15 by friction pulley 16
Generator motor 17 is rotated through to 22 electric power storage of battery, the deceleration for being completed at the same time launching platform 3 stops, when launching platform 3 stops
After only moving, is powered with battery 22 to generator motor 17, so that 3 counter motion of launching platform is returned to original position, while to straight
8 reverse power supply of line electrical-coil makes linear motor coil 8 push linear motor core iron 7 that 3 counter motion of launching platform is driven to return to
Original position；After launching platform 3 returns to original position, friction pulley 16 is risen, backstop 24 is dismantled, at this moment can be waited auxiliary
The lower airplane of take-off-helping.
If aircraft breaks down when cannot smoothly take off, launching platform 3 and aircraft can be at a high speed by taking off section
With 3 deceleration area of launching platform, at this moment the impact head 25 of 3 front end of launching platform, which can hit to be arranged on lower guideway 1, blocks machine
Structure 4, impact head 25 are hit with the impact block 4014 blocked in mechanism 4, and impact block 4014 drives left connector 4001 and right connection
4002 forward slip of body, while left connector 4001 and right connector 4002 can tense check cable 4007, check cable 4007 is being drawn
Rotating cylinder 4009 and fixing barrel 4010 can be made to relatively rotate during tight, launching platform 3 can be absorbed in rotation process and flown
The kinetic energy of machine, when check cable 4007 is tightened, check cable 4007 can pull left connector 4001 and right connector 4002 respectively, when
When pulling force is more than the overload protection pulling force that overload protection safety pin 4003 is set, overload protection safety pin 4003 is cut off, this
When left connector 4001 and right connector 4002 can be separated, lower guideway 1 is left, under launching platform 3 and aircraft can be hit at this time
One group is blocked mechanism 4, until launching platform 3 and aircraft stopping.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solutions of the utility model, the technology of the art
Personnel embody the principles of the present invention to some variations that some of them part may be made, and belong to the utility model
Protection scope within.
Claims (3)
1. a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, it is characterised in that: including lower guideway (1), the lower guideway
(1) it is provided with above air guide rail (2), air guide rail (2) is fixedly arranged above launching platform (3), is set in launching platform (3)
It is equipped with pressurization air pump (5) and battery (22), pressurization air pump (5) passes through air delivery pipe (6) connection air guide rail (2)；Institute
The lower end for stating launching platform (3) is fixed with linear motor core iron (7), and the lower end two sides of linear motor core iron (7) are provided with straight line
Electrical-coil (8), linear motor coil (8) fix on the ground；The rear end sides of the launching platform (3) are respectively fixed with peace
It fills fixed plate (9), is fixed with fixing axle (12) on mounting plate (9), fixing axle (12) is hinged by lever one (10) connection
Axis (13), articulated shaft (13) are hingedly rubbed turbine/lever (14) by lever two (11), and one end of friction turbine/lever (14) is hinged on
On launching platform (3), the other end is arranged on the axis of rolling (15), and the both ends of the axis of rolling (15) are provided with friction pulley (16), rolls
The middle position of axis (15) is provided with generator motor (17), and generator motor (17) and battery (22) are electrically connected；It is described
Being fixedly arranged above electric push rod (18) for articulated shaft (13), is fixed with spring fixed link (20), bullet below articulated shaft (13)
Spring fixed link (20) is interspersed in fixed plate (21), and spring (19), spring are provided between articulated shaft (13) and fixed plate (21)
(19) it is sleeved on spring fixed link (20), wherein electric push rod (18) and fixed plate (21) are all fixed on mounting plate
(9) on；The front end of the launching platform (3) is provided with impact head (25), and the top of launching platform (3) is fixed with positive stop (23)
With backstop (24), backstop (24) is detachably mounted to the top of launching platform (3) by bolt；The lower guideway (1)
On be additionally provided with and block mechanism (4)；
Wherein the bottom end of air guide rail (2) is provided with air permeable plate (202), pore (204) is offered on air permeable plate (202), thoroughly
Closed between gas plate (202) and air guide rail (2) to have air guide rail cavity (203), air guide rail cavity (203) is defeated by air
Pipeline (6) connection pressurization air pump (5) is sent, is additionally provided with check valve (201) on air delivery pipe (6), check valve (201) setting
In air guide rail (2)；
Mechanism (4) is wherein blocked to include left connector (4001), right connector (4002), overload protection safety pin (4003), draw
It restricts (4004), fixed ring (4005), anti-flying barrel (4006), check cable (4007), jackscrew (4008), rotating cylinder (4009), fix
Bucket (4010), compressed spring (4011), upper cover plate (4012), protective cover (4013) and impact block (4014), the left connector
(4001) it is arranged on lower guideway (1) with right connector (4002), left connector (4001) and right connector (4002) passed through
It carries protection safety pin (4003) to be connected and fixed, overload protection safety pin (4003) is fixed by jackscrew (4008), overload protection peace
The both ends of full pin (4003) are provided with anti-flying barrel (4006), and anti-flying barrel (4006) is connected and fixed ring by drawstring (4004)
(4005), fixed ring (4005) is fixed on right connector (4002)；The left side of the left connector (4001) and right connector
(4002) it is connected separately on the right side of check cable (4007), check cable (4007) is fastened in the rotation at lower guideway (1) both ends
On bucket (4009), rotating cylinder (4009) is sleeved on fixing barrel (4010), and fixing barrel (4010) is fixed in protective cover (4013),
The top of protective cover (4013) is fixed with upper cover plate (4012), is arranged between upper cover plate (4012) and the roof of rotating cylinder (4009)
There are compressed spring (4011)；The front end of the left connector (4001) and right connector (4002) is both provided with impact block
(4014).
2. according to claim 1 a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, it is characterised in that: described to hit
Tap the head (25) top be sphere structure.
3. according to claim 1 a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism, it is characterised in that: described to hit
The front end for hitting block (4014) is arcuate structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822060237.5U CN209427053U (en) | 2018-12-10 | 2018-12-10 | It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822060237.5U CN209427053U (en) | 2018-12-10 | 2018-12-10 | It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209427053U true CN209427053U (en) | 2019-09-24 |
Family
ID=67971196
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822060237.5U Expired - Fee Related CN209427053U (en) | 2018-12-10 | 2018-12-10 | It is a kind of with the auxiliary takeoff apparatus for airplane for blocking mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209427053U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111284723A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with arresting mechanism for airplane |
| CN111284720A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with pneumatic control system for airplane |
| CN111284719A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Airplane auxiliary takeoff device with brake mechanism |
| CN111319784A (en) * | 2018-12-15 | 2020-06-23 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with tire positioning mechanism for airplane |
-
2018
- 2018-12-10 CN CN201822060237.5U patent/CN209427053U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111284723A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with arresting mechanism for airplane |
| CN111284720A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with pneumatic control system for airplane |
| CN111284719A (en) * | 2018-12-10 | 2020-06-16 | 邯郸市复兴区宏昌科技有限公司 | Airplane auxiliary takeoff device with brake mechanism |
| CN111284720B (en) * | 2018-12-10 | 2024-07-09 | 江苏拓维环境科技有限公司 | Aircraft auxiliary take-off device with pneumatic control system |
| CN111284723B (en) * | 2018-12-10 | 2024-07-19 | 南京星然环境科技有限公司 | Aircraft auxiliary take-off device with arresting mechanism |
| CN111284719B (en) * | 2018-12-10 | 2024-07-23 | 南京荔泰品阅科技文化有限公司 | Aircraft auxiliary take-off device with braking mechanism |
| CN111319784A (en) * | 2018-12-15 | 2020-06-23 | 邯郸市复兴区宏昌科技有限公司 | Auxiliary take-off device with tire positioning mechanism for airplane |
| CN111319784B (en) * | 2018-12-15 | 2024-07-23 | 江苏八维体育设备有限公司 | Aircraft auxiliary take-off device with tire positioning mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190924 Termination date: 20191210 |
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| CF01 | Termination of patent right due to non-payment of annual fee |