CN106628196B - Aircraft drag parachute cabin with combined rear cover - Google Patents
Aircraft drag parachute cabin with combined rear cover Download PDFInfo
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- CN106628196B CN106628196B CN201710079229.2A CN201710079229A CN106628196B CN 106628196 B CN106628196 B CN 106628196B CN 201710079229 A CN201710079229 A CN 201710079229A CN 106628196 B CN106628196 B CN 106628196B
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- cover shell
- parachute cabin
- inner cylinder
- drag parachute
- torsion spring
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- 230000002411 adverse Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 230000009471 action Effects 0.000 description 6
- 239000003638 chemical reducing agent Substances 0.000 description 4
- 238000004880 explosion Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 4
- 230000000903 blocking effect Effects 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Emergency Lowering Means (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model discloses an aircraft drag parachute cabin with a combined rear cover, which relates to the field of aircraft deceleration assistance and comprises an outer cylinder, an inner cylinder, a small cover shell and a large cover shell, wherein the outer cylinder and the inner cylinder are connected through Z-shaped ribs arranged on the inner cylinder, the large cover shell is hinged on the inner cylinder through a second support, the small cover shell is hinged on the inner cylinder through a first support, an electromagnetic unlocking device with a locking hook is arranged on the large cover shell, a shaft pin is arranged on the small cover shell and is suitable for the locking hook on the electromagnetic unlocking device, and the electromagnetic unlocking device is communicated with a cable arranged between the outer cylinder and the inner cylinder. The aircraft drag parachute cabin with the combined rear cover has a simple structure, does not increase excessive weight, fuses the opening and closing device and the uncovering rotating shaft into the parachute cabin by arranging the inner layer and the outer layer of the parachute cabin, has no excessive structure on the surface of the closed parachute cabin, and solves the adverse effect of the excessive structure on the surface of the parachute cabin on the aerodynamic performance of the aircraft in the prior art.
Description
Technical Field
The utility model relates to the field of airplane deceleration assistance, in particular to the field of airplane drag parachutes, and specifically relates to an airplane drag parachute cabin with a combined rear cover.
Background
Modern aircraft generally remain at a high speed while landing, and therefore require assistance to shorten the landing distance of the aircraft. The united states aircraft adopts a mode that a speed reducer or each airfoil speed reducer deflects simultaneously to serve as the speed reducer to realize the speed reduction of the aircraft, and China Russian and European aircraft adopt a mode that a drag parachute is matched with a fuselage speed reducer to realize the speed reduction of the aircraft.
Currently, drag parachute cabin arrangements are divided into backpack and buried type. The back pack type drag parachute cabin is arranged on the back of the back fuselage, after receiving an instruction, the back pack type drag parachute cabin is opened and thrown, the embedded type drag parachute cabin is arranged inside the fuselage, and when the drag parachute cabin is thrown, the drag parachute cabin is pushed out of the fuselage through an actuator, and then the back pack type drag parachute cabin is opened and thrown. The embedded type parachute cabin has a complex structure and mechanism and causes weight increase, so that the backpack type parachute cabin is adopted.
In the prior art, the backpack drag parachute cabin has a plurality of defects: considering pneumatic requirements, the existing knapsack drag parachute cabin opening and closing modes mainly comprise an electric cold air type, a mechanical type, an explosion cover opening type and an electromagnetic type, wherein the electric cold air type or the mechanical type needs manual unlocking by a pilot, and a transmission mechanism is arranged outside the parachute cabin; the explosion cover opening type is unlocked by igniting gunpowder in the explosion device, the explosion device is arranged at one side of the parachute cabin, and a fairing is required to be added on the surface of the parachute cabin; electromagnetic unlocking is performed through the electromagnetic unlocking device, the electromagnetic unlocking device is exposed outside, and a fairing is required to be added on the surface of the parachute cabin.
Chinese patent CN205837216U discloses a light stealth electromagnetic unlocking drag parachute cabin structure, which comprises a saw tooth cover, a torsion bracket and a first electromagnetic unlocking device, wherein the saw tooth cover, the torsion bracket and the first electromagnetic unlocking device are arranged on the machine body, an umbrella barrel is fixedly connected below the saw tooth cover, an opening at the front end of the umbrella barrel is provided with an umbrella barrel cover, the lower part of the umbrella barrel cover is connected with the umbrella barrel through a torsion hinge, the upper part of the umbrella barrel cover is provided with a second locking hook, and the lower part of the saw tooth cover is also provided with a second electromagnetic unlocking device matched with the first locking hook; the bottom of the umbrella barrel at the rear end is fixedly connected with a torsion bracket, and a first lock hook matched with the first electromagnetic unlocking device is arranged at the joint of the torsion bracket and the umbrella barrel. The whole set of structure of the assembly in the stealth flap is hidden in the surface of the machine body, and the saw-tooth flap is matched to meet the stealth requirement. However, the outside of the umbrella cylinder cover is also required to be provided with the saw tooth port cover, the outside is additionally provided with the structural component, the aerodynamic performance of the aircraft is affected to a certain extent, and as the umbrella cabin is provided with the two layers of port covers, two sets of port locks are required to be matched for use, the structure is complex, the maintenance is not facilitated, the two sets of port locks are required to be in a normal state at the same time during use, any port lock cannot normally start the drag parachute when in a problem, and the fault probability is greatly increased.
Chinese patent CN205168929U discloses an electromagnetic unlocking cover-opening type drag parachute cabin, which comprises a parachute cabin, a cabin door locking mechanism, a drag parachute locking hook and an electromagnetic unlocking device, wherein the cabin door is connected with the parachute cabin through a bolt, the electromagnetic unlocking device is connected on a support of the parachute cabin through a bolt, and the electromagnetic unlocking device is connected with the cabin door through the locking hook. According to the utility model, the drag parachute cabin door is opened under the action of the internal electromagnetic force of the cabin door lock, and the drag parachute cabin door is opened to guide the parachute to pop out and bring out the main parachute; the utility model does not need to connect an electric cooling system and a mechanical system, and simultaneously omits complex mechanical structures such as a mechanical unlocking mechanism, a true lock, a false lock system and the like, but the resistance umbrella cabin door lock can only be opened under the action of electromagnetic force, can not be opened manually under the condition of power failure, and brings inconvenience to maintenance and repair, and the electromagnetic unlocking device is exposed outside, so that a fairing is required to be added on the surface of the umbrella cabin.
In the prior art, a plurality of unlocking forms are all required to be additionally provided with structures on the outer surface of the parachute cabin, so that the aerodynamic performance of the aircraft is adversely affected.
Disclosure of Invention
The utility model aims to provide an aircraft drag parachute cabin with a combined rear cover, which is used for solving the problems that the outside of the drag parachute cabin needs to be additionally provided with a structure and has adverse effect on the aerodynamic performance of an aircraft in the prior art.
The utility model is realized by the following technical scheme: the utility model provides an aircraft drag parachute cabin with combined type rear cover, includes urceolus, inner tube, little lid casing, big lid casing, urceolus and inner tube are connected through the Z shape rib that sets up on the inner tube, big lid casing passes through the second support and articulates on the inner tube, little lid casing passes through first support and articulates on the inner tube, be provided with the electromagnetic unlocking ware of taking the latch hook on the big lid casing, be provided with the pivot on the little lid casing, the latch hook that sets up on the electromagnetic unlocking ware suits with the pivot, electromagnetic unlocking ware and cable intercommunication, the cable sets up between urceolus and inner tube.
Preferably, in order to be convenient for maintain, be provided with first quick-release flap on the little lid casing, be provided with the quick-release flap of second on the big lid casing, under the outage condition, the technician can open first quick-release flap, second quick-release flap, inspect big lid casing, little lid casing inside or manual latch hook of opening electromagnetic unlocking ware through quick-release opening.
Preferably, the first support comprises a first support frame and a first rotating shaft, the second support comprises a second support frame and a second rotating shaft, the fatigue resistance of the joint of the support and the shell is improved, the durability and the reliability of the component are enhanced, the first support frame is connected with the small cover shell through a high-locking bolt, the first rotating shaft is fixedly connected with the outer surface of the inner cylinder, the second support frame is connected with the large cover shell through a high-locking bolt, and the second rotating shaft is fixedly connected with the outer surface of the inner cylinder.
Preferably, in order to make the ejecting effect of the drag parachute better, a first torsion spring is arranged on the first rotating shaft, one end of the first torsion spring is clamped on the small cover shell, and the other end of the first torsion spring is clamped on the outer surface of the inner cylinder; the second rotating shaft is provided with a second torsion spring, one end of the second torsion spring is clamped on the large cover shell, and the other end of the second torsion spring is clamped on the outer surface of the inner cylinder. When the latch hook and the shaft pin of the electromagnetic unlocking device are separated, the large cover shell and the small cover shell respectively and rapidly spring and separate under the action of the first torsion spring and the second torsion spring, so that the possibility of blocking when the drag parachute pops out is reduced.
Compared with the prior art, the utility model has the following advantages:
(1) The aircraft drag parachute cabin with the combined rear cover has a simple structure, does not increase excessive weight, fuses the opening and closing device and the uncovering rotating shaft into the parachute cabin by arranging the inner layer and the outer layer of the parachute cabin, has no excessive structure on the surface of the closed parachute cabin, eliminates the influence of the excessive structure on the surface of the parachute cabin on the aerodynamic performance of the aircraft, and can effectively reduce the flight drag.
(2) Compared with the prior art, after unlocking, the electromagnetic unlocking device and the shaft pin leave the hatch of the umbrella along with the large cover shell and the small cover shell, and the electromagnetic unlocking device and the shaft pin are not in the umbrella cabin and cannot adversely affect the ejection of the drag umbrella while the rapid unlocking and the uncovering are ensured.
(3) According to the utility model, the first quick-release cover is arranged on the surface of the small cover shell, the second quick-release cover is arranged on the surface of the large cover shell, and under the condition of power failure, a technician can open the first quick-release cover and the second quick-release cover to inspect the inside of the large cover shell and the small cover shell or manually open the lock hook of the electromagnetic unlocking device, so that the maintenance is more convenient.
(4) Compared with the traditional two electromagnetic unlocking devices for jointly controlling the loading and the releasing of the drag parachute, the utility model has simpler structure and simpler mode, and reduces the probability of faults.
(5) The first support frame is connected with the small cover shell, the second support frame is connected with the large cover shell through the high-locking bolt, so that the fatigue resistance of the joint of the support and the shell is effectively improved, and the durability and the reliability of the component are enhanced.
(6) The first rotating shaft is provided with a first torsion spring, the second rotating shaft is provided with a second torsion spring, one end of the first torsion spring is clamped on the small cover shell, the other end of the first torsion spring is clamped on the outer surface of the inner cylinder, one end of the second torsion spring is clamped on the large cover shell, and the other end of the second torsion spring is clamped on the outer surface of the inner cylinder. When the latch hook and the shaft pin of the electromagnetic unlocking device are separated, the large cover shell and the small cover shell respectively and rapidly spring and separate under the action of the first torsion spring and the second torsion spring, so that the possibility of blocking when the drag parachute pops out is reduced.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic view of a first support structure;
FIG. 3 is a schematic view of a second support structure;
FIG. 4 is a schematic side elevational view;
the electromagnetic unlocking device comprises a 1-outer cylinder, a 2-first quick-release cover, a 3-small cover shell, a 4-shaft pin, a 5-inner cylinder, a 6-large cover shell, a 7-electromagnetic unlocking device, an 8-second quick-release cover, a 9-cable, a 10-first support, an 11-first torsion spring, a 12-second support, a 13-second torsion spring, a 14-first support frame, a 15-first rotating shaft, a 16-second support frame and a 17-second rotating shaft.
Detailed Description
The present utility model will be described in further detail with reference to examples, but embodiments of the present utility model are not limited thereto.
Example 1:
referring to fig. 1-4, an aircraft drag parachute cabin with combined rear cover comprises an outer cylinder 1, an inner cylinder 5, a small cover shell 3 and a large cover shell 6, wherein an electromagnetic unlocking device 7 with a locking hook is arranged on the large cover shell 6, a shaft pin 4 is arranged on the small cover shell 3, the locking hook on the electromagnetic unlocking device 7 is matched with the shaft pin 4, the electromagnetic unlocking device 7 is communicated with a cable 9, the cable 9 is arranged between the outer cylinder 1 and the inner cylinder 5, the outer cylinder 1 and the inner cylinder 5 are connected through Z-shaped ribs arranged on the inner cylinder, the small cover shell 3 is hinged on the inner cylinder 5 through a first support 10, and the large cover shell 6 is hinged on the inner cylinder 5 through a second support 12.
The technician installs drag parachute inside the utility model, manually closes the big cover shell 6 and the small cover shell 3, and the lock hook on the electromagnetic unlocking device 7 is inserted into the shaft pin 4 and automatically falls down. After the aircraft lands, the cable 9 is used for powering on the electromagnetic unlocking device 7, the locking hook on the electromagnetic unlocking device 7 rotates and is separated from the shaft pin 4, the large cover shell 6 and the small cover shell 3 can be separated, and the drag parachute can be ejected.
Example 2:
on the basis of embodiment 1 and with reference to fig. 1-4, the first support 10 comprises a first support frame 14 and a first rotating shaft 15, the second support 12 comprises a second support frame 16 and a second rotating shaft 17, the first rotating shaft 15 and the second rotating shaft 17 are respectively and fixedly connected to the outer surface of the inner cylinder 5, the first support frame 14 is respectively connected with the small cover shell 3 and the second support frame 16 is respectively connected with the large cover shell 6 through high-locking bolts with good shearing resistance, the fatigue resistance of joints of the support frame and the shells is improved, and the durability and the reliability of components are enhanced.
Further, a first torsion spring 11 is arranged on the first rotating shaft 15, one end of the first torsion spring 11 is clamped on the small cover shell 3, and the other end of the first torsion spring is clamped on the outer surface of the inner cylinder 5; the second rotating shaft 17 is provided with a second torsion spring 13, one end of the second torsion spring 13 is clamped on the large cover shell 6, and the other end of the second torsion spring is clamped on the outer surface of the inner cylinder 5. When the latch hook of the electromagnetic unlocking device 7 is disengaged from the shaft pin 4, the large cover shell 6 rapidly and downwards pops open under the action of the second torsion spring 13, and the small cover shell 3 rapidly and upwards pops open under the action of the first torsion spring 11, so that the possibility of blocking when the drag parachute pops up is reduced.
Example 3:
on the basis of the embodiment 1 or 2, as shown in fig. 1-4, a first quick-release cover 2 is arranged on the small cover shell 3, and a second quick-release cover 8 is arranged on the large cover shell 6. When the electromagnetic unlocking device is maintained and maintained under the condition of power failure, the first quick-release cover 2 on the small cover shell 3 and the second quick-release cover 8 on the large cover shell 6 are dismounted, the large cover shell 6 and the small cover shell 3 are manually closed, the lock hook on the electromagnetic unlocking device 7 is inserted into the shaft pin 4 and automatically locked, a technician can check the locking condition from the first quick-release opening, and if the locking condition is not automatically locked, the lock hook of the electromagnetic unlocking device 7 can be pulled to manually lock; when the electromagnetic unlocking device is opened, a person skilled in the art stretches hands into the large cover shell 6 through the second quick-release opening, and the electromagnetic unlocking device 7 is manually operated to unlock, so that the locking hook of the electromagnetic unlocking device 7 is separated from the shaft pin 4.
The foregoing description is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present utility model fall within the scope of the present utility model.
Claims (7)
1. The utility model provides an aircraft drag parachute cabin with combined rear cover, includes urceolus (1), inner tube (5), little lid casing (3), big lid casing (6), its characterized in that, be provided with electromagnetic unlocking ware (7) of taking the latch hook on big lid casing (6), be provided with pivot (4) on little lid casing (3), the latch hook that sets up on electromagnetic unlocking ware (7) suits with pivot (4), electromagnetic unlocking ware (7) and cable (9) intercommunication, cable (9) set up between urceolus (1) and inner tube (5), urceolus (1) and inner tube (5) are connected through the Z-shaped rib that sets up on the inner tube, little lid casing (3) are articulated on inner tube (5) through first support (10), big lid casing (6) are articulated on inner tube (5) through second support (12); an electromagnetic unlocking device (7) is arranged on one side, close to the small cover shell (3), of the large cover shell (6), and the electromagnetic unlocking device (7) is arranged in a space where the small cover shell (3) and the large cover shell (6) are closed.
2. Aircraft drag parachute cabin with combined rear cover according to claim 1, characterized in that the small cover housing (3) is provided with a first quick release flap (2).
3. Aircraft drag parachute cabin with combined rear cover according to claim 2, characterized in that the big cover housing (6) is provided with a second quick release flap (8).
4. An aircraft drag parachute kit with a combined rear cover according to any one of claims 1-3, characterized in that the first support (10) comprises a first support frame (14) and a first rotating shaft (15), the first support frame (14) is connected with the small cover shell (3) through a high locking bolt, and the first rotating shaft (15) is fixedly connected to the outer surface of the inner cylinder (5).
5. The aircraft drag parachute cabin with the combined rear cover according to claim 4, wherein a first torsion spring (11) is arranged on the first rotating shaft (15), one end of the first torsion spring (11) is clamped on the small cover shell (3), and the other end of the first torsion spring is clamped on the outer surface of the inner cylinder (5).
6. An aircraft drag parachute kit with a combined rear cover according to any one of claims 1-3 or 5, wherein said second support (12) comprises a second support frame (16) and a second rotating shaft (17), said second support frame (16) is connected with the large cover housing (6) by a high lock bolt, and said second rotating shaft (17) is fixedly connected to the outer surface of the inner cylinder (5).
7. The aircraft drag parachute cabin with the combined rear cover according to claim 6, wherein a second torsion spring (13) is arranged on the second rotating shaft (17), one end of the second torsion spring (13) is clamped on the large cover shell (6), and the other end of the second torsion spring is clamped on the outer surface of the inner cylinder (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710079229.2A CN106628196B (en) | 2017-02-14 | 2017-02-14 | Aircraft drag parachute cabin with combined rear cover |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710079229.2A CN106628196B (en) | 2017-02-14 | 2017-02-14 | Aircraft drag parachute cabin with combined rear cover |
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| Publication Number | Publication Date |
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| CN106628196A CN106628196A (en) | 2017-05-10 |
| CN106628196B true CN106628196B (en) | 2023-05-09 |
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| CN201710079229.2A Active CN106628196B (en) | 2017-02-14 | 2017-02-14 | Aircraft drag parachute cabin with combined rear cover |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774955B (en) * | 2019-03-06 | 2022-01-25 | 成都飞机工业（集团）有限责任公司 | Double-door embedded resistance umbrella cabin structure |
| CN114933008A (en) * | 2022-05-23 | 2022-08-23 | 成都飞机工业（集团）有限责任公司 | Embedded drag parachute cabin lifting structure and resetting method thereof |
| CN118047043A (en) * | 2024-04-15 | 2024-05-17 | 四川凌空天行科技有限公司 | Modularized parachute cabin system |
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| Publication number | Publication date |
|---|---|
| CN106628196A (en) | 2017-05-10 |
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