CN202529150U - Landing stopper for airplane - Google Patents
Landing stopper for airplane Download PDFInfo
- Publication number
- CN202529150U CN202529150U CN 201220020519 CN201220020519U CN202529150U CN 202529150 U CN202529150 U CN 202529150U CN 201220020519 CN201220020519 CN 201220020519 CN 201220020519 U CN201220020519 U CN 201220020519U CN 202529150 U CN202529150 U CN 202529150U
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- warship
- cable wire
- cylinder
- main frame
- mouth
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Abstract
The utility model discloses a landing stopper for an airplane. The landing stopper comprises a host engine and an auxiliary engine, wherein the host engine and the auxiliary engine are separately arranged on the left side and the right side of a carrier deck; a steel cable is connected between the host engine and the auxiliary engine; an elastic buffer mechanism and/or a hydraulic buffer mechanism are/is arranged on a connection part of the host engine, the auxiliary engine and the steel cable; and the host engine and the auxiliary engine can rotate on the carrier deck. The elastic buffer mechanism and/or a hydraulic buffer mechanism are/is arranged on the host engine and the auxiliary engine, so that the motion of the steel cable can be effectively decelerated and stopped after a landing hook of the airplane and the cable are hooked to consume the kinetic energy of the airplane; and therefore, the high-efficiency and safe deceleration operation of the airplane is realized. The landing stopper has a simple and reliable structure, and can be used as a deceleration device for various ships when the airplane is landed.
Description
Technical field
The utility model relates to a kind of warship and uses equipment, the obstruction device that slows down when warship for aircraft.
Background technology
On the capital ship, particularly aircraft carrier, but polygamy has the aircraft that at high speed takes off.Generally speaking; The deck length of warship body is limited; Can not provide a very long runway to come out to supply the aircraft speedup to take off and fall-retarding; So on warship, often with supporting from warship ejector and warship obstruction device, the warship obstruction device and be the kinetic energy that will make every effort in limited distance as soon as possible aircraft and be reduced to zero.Nowadays, mostly common warship obstruction device is to adopt large-scale wirerope to add the structure of netting, during the airplane nose down landing, with wirerope catch on aircraft forward the warship hook, cooperate netting, aircraft is stopped, be allowed to condition on the runway at last and slide until stop motion slowly.But, the rigidity that traditional aircraft the warship obstruction device is too big, easily aircraft warship moment and impacts, and is damaging the warship hook, and serious also possibly cause aircraft unstability, upset.Therefore, need the safe and aircraft that buffer deceleration is effective of a kind of safety of design the warship obstruction device.
The utility model content
The purpose of the utility model is to provide the safe and aircraft that buffer deceleration is effective of a kind of safety the warship obstruction device.
The solution that the utility model solves its technical matters is:
Aircraft the warship obstruction device; Comprise about separation, be arranged on main frame and secondary machine on the warship body deck; Be connected with cable wire between said main frame and the secondary machine; On main frame, secondary machine and position that cable wire connects, be provided with elastic buffering mechanism and/or hydraulic cushion mechanism, main frame and secondary machine all can rotate on warship body deck.
As the further improvement of technique scheme, said hydraulic cushion mechanism is arranged in the main frame, and elastic buffering mechanism is arranged in the secondary machine.
Further improvement as technique scheme; Said hydraulic cushion mechanism is such: it comprises a drop-gear box with input end and mouth; The input end of drop-gear box is provided with the cable wire capstan winch, and the cable wire dish is located on the cable wire capstan winch, by the folding and unfolding of its control cable wire; The mouth of drop-gear box connects with the piston rod that is located at hydraulic actuating cylinder on one side, the motion of mouth this piston rod of control in hydraulic actuating cylinder of drop-gear box.
As the further improvement of technique scheme, said drop-gear box is a gear reduction box, and its mouth is provided with a gear, and the piston rod of hydraulic actuating cylinder is provided with tooth bar, and said wheel and rack connects the formation pinion and rack.
As the further improvement of technique scheme, the cylinder body of said hydraulic actuating cylinder is drawn pressurize oil circuit and oil feeding line, and said pressurize oil circuit is provided with limiting valve and flow regulating valve, is back to then in the oil cylinder; Said oil feeding line also connects with oil cylinder, is provided with check valve and oil pump, and the water inlet of check valve points to the mouth of oil pump.
Further improvement as technique scheme; Said elastic buffering mechanism is such: it comprises the deceleration cylinder that is provided with platen in; Said platen connects with cable wire, and between the end of platen and deceleration cylinder, is provided with preloading spring; Preloading spring withstands platen, stops its direction motion toward cable wire.
The beneficial effect of the utility model is: elastic buffering mechanism and/or hydraulic cushion mechanism are housed on main frame in the utility model and the secondary machine; When aircraft after warship hook and cable wire be affiliated to; Can be effectively the motion of cable wire be stopped at a slow speed; Thereby consume the kinetic energy of aircraft, realize efficient, safe aircraft deceleration operation.
In addition, the utility model adopts main frame that the frame mode of hydraulic cushion mechanism, secondary machine installation elastic buffering mechanism is installed, and complements each other, and when having guaranteed that aircraft safety warship, is protecting warship hook and cable wire again, increases the service life.
The utility model is simple and reliable for structure, can install with various ships on deceleration instrumentation during as aircraft landing.
Description of drawings
In order to be illustrated more clearly in the technical scheme among the utility model embodiment, the accompanying drawing of required use is done simple declaration in will describing embodiment below.Obviously, described accompanying drawing is a part of embodiment of the utility model, rather than whole embodiment, and those skilled in the art can also obtain other design plans and accompanying drawing according to these accompanying drawings under the prerequisite of not paying creative work.
Fig. 1 is the plan structure scheme drawing of the utility model, the content that wherein solid line identified, the state that the expression aircraft just has been affiliated to cable wire, the content that long and short dash line identified, the state that the expression aircraft stops fully;
Fig. 2 is the structural representation of main frame;
Fig. 3 is the structural representation of secondary machine.
The specific embodiment
Below will combine embodiment and accompanying drawing that the technique effect of design, concrete structure and the generation of the utility model is carried out clear, complete description, with purpose, characteristic and the effect of understanding the utility model fully.Obviously; Described embodiment is a part of embodiment of the utility model, rather than whole embodiment, based on the embodiment of the utility model; Other embodiment that those skilled in the art is obtained under the prerequisite of not paying creative work all belong to the scope that the utility model is protected.In addition, all connection/annexations of being mentioned in the literary composition are not to refer to that singly member directly joins, and are meant and can connect auxiliary through adding or reducing according to the practical implementation situation, form more excellent draw bail.
With reference to Fig. 1～Fig. 3; Aircraft the warship obstruction device; Comprise about separation, be arranged on main frame 1 and secondary machine 2 on the warship body deck 5, be connected with cable wire 3 between said main frame 1 and the secondary machine 2, on main frame 1, secondary machine 2 and position that cable wire 3 connects; Be provided with elastic buffering mechanism and/or hydraulic cushion mechanism, main frame 1 all can rotate on warship body deck 5 with secondary machine 2.Particularly, said rotating manner is through on warship body deck 5, vertical blind hole being set, and in this hole, inserts the rotating shaft that connects with main frame 1/ secondary machine 2 then, and is certain, should be provided with the accessory of auxiliary rotation such as bearing in the cooperation of hole axle.
Further as preferred embodiment, said hydraulic cushion mechanism is arranged in the main frame 1, and elastic buffering mechanism is arranged in the secondary machine 2.
Further as preferred embodiment; Said hydraulic cushion mechanism is such: it comprises a drop-gear box 13 with input end and mouth; The input end of drop-gear box 13 is provided with cable wire capstan winch 12, and cable wire 3 dishes are located on the cable wire capstan winch 12, by the folding and unfolding of its control cable wire 3; The mouth of drop-gear box 13 connects with the piston rod that is located at hydraulic actuating cylinder 9 on one side, the motion of mouth this piston rod of control in hydraulic actuating cylinder 9 of drop-gear box 13.
Further as preferred embodiment, said drop-gear box 13 is a gear reduction box, and its mouth is provided with a gear, and the piston rod of hydraulic actuating cylinder 9 is provided with tooth bar, and said wheel and rack connects formation pinion and rack 11.
Further as preferred embodiment, the cylinder body of said hydraulic actuating cylinder 9 is drawn pressurize oil circuit and oil feeding line, and said pressurize oil circuit is provided with limiting valve 15 and flow regulating valve 14, is back in the oil cylinder then; Said oil feeding line also connects with oil cylinder, is provided with check valve 10 and oil pump, and the water inlet of check valve 10 points to the mouth of oil pump.Oil pump can be given hydraulic actuating cylinder 9 fuel feeding, and check valve 10 guarantees that oil can not flow backwards, and limiting valve 15 can guarantee that with flow regulating valve 14 oil pressure is in running order in the cylinder, in time gives the release of cylinder inner fluid.
Further as preferred embodiment; Said elastic buffering mechanism is such: it comprises the deceleration cylinder 7 that is provided with platen 8 in; Said platen 8 connects with cable wire 3, and between the end of platen 8 and deceleration cylinder 7, is provided with preloading spring 6; Preloading spring 6 withstands platen 8, stops its direction motion toward cable wire 3.
During work, the aircraft hook is lived cable wire 3 middle parts, and pull line 3 marches forward; Main frame 1, secondary machine 2 about cable wire 3 drives are at the beginning followed rotation, in case turn to this angle when being not enough to bear the length deformation quantity of cable wire 3, cable wire capstan winch 12 beginning trace are put rope and rotated; But the moment of torsion of this rotation is through being delivered to the gear of mouth behind the drop-gear box 13; Pinion and rack 11 turns to translation with rotation, the traction piston rod movement, and this motion outbound flows hydraulic oil in the squeeze cylinder; Set valve, the pump housing then hinder this trend, thereby play the effect of buffering; Simultaneously, the platen 8 on the secondary machine 2 also is pulled to such an extent that outwards move, compressing preloading spring 6, and deformation take place in preloading spring 6, hinder platen 8 motions, also play buffer action.
More than be that preferred embodiments to the utility model specifies; But the invention is not limited to said embodiment; Those of ordinary skill in the art also can make all equivalent modifications or replacement under the prerequisite of the utility model spirit, modification that these are equal to or replacement all are included in the application's claim institute restricted portion.
Claims (6)
1. aircraft the warship obstruction device; It is characterized in that: comprise about separation, be arranged on main frame (1) and secondary machine (2) on the warship body deck (5); Be connected with cable wire (3) between said main frame (1) and the secondary machine (2); On main frame (1), secondary machine (2) and position that cable wire (3) connects, be provided with elastic buffering mechanism and/or hydraulic cushion mechanism, main frame (1) and secondary machine (2) all can be gone up on warship body deck (5) and rotate.
2. aircraft according to claim 1 the warship obstruction device, it is characterized in that: said hydraulic cushion mechanism is arranged in the main frame (1), and elastic buffering mechanism is arranged in the secondary machine (2).
3. aircraft according to claim 2 the warship obstruction device; It is characterized in that: said hydraulic cushion mechanism is such: it comprises a drop-gear box (13) with input end and mouth; The input end of drop-gear box (13) is provided with cable wire capstan winch (12); Cable wire (3) dish is located on the cable wire capstan winch (12); By the folding and unfolding of its control cable wire (3), the mouth of drop-gear box (13) connects with the piston rod that is located at hydraulic actuating cylinder (9) on one side, the motion of mouth this piston rod of control in hydraulic actuating cylinder (9) of drop-gear box (13).
4. aircraft according to claim 3 the warship obstruction device; It is characterized in that: said drop-gear box (13) is a gear reduction box; Its mouth is provided with a gear, and the piston rod of hydraulic actuating cylinder (9) is provided with tooth bar, and said wheel and rack connects formation pinion and rack (11).
5. the warship obstruction device according to claim 3 or 4 described aircrafts; It is characterized in that: the cylinder body of said hydraulic actuating cylinder (9) is drawn pressurize oil circuit and oil feeding line; Said pressurize oil circuit is provided with limiting valve (15) and flow regulating valve (14), is back in the oil cylinder then; Said oil feeding line also connects with oil cylinder, is provided with check valve (10) and oil pump, and the water inlet of check valve (10) points to the mouth of oil pump.
6. aircraft according to claim 2 the warship obstruction device; It is characterized in that: said elastic buffering mechanism is such: it comprises the deceleration cylinder (7) that is provided with platen (8) in; Said platen (8) connects with cable wire (3), and between the end of platen (8) and deceleration cylinder (7), is provided with preloading spring (6); Preloading spring (6) withstands platen (8), stops its direction motion toward cable wire (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220020519 CN202529150U (en) | 2012-01-17 | 2012-01-17 | Landing stopper for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220020519 CN202529150U (en) | 2012-01-17 | 2012-01-17 | Landing stopper for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202529150U true CN202529150U (en) | 2012-11-14 |
Family
ID=47130349
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220020519 Expired - Fee Related CN202529150U (en) | 2012-01-17 | 2012-01-17 | Landing stopper for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202529150U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN107472550A (en) * | 2017-09-19 | 2017-12-15 | 方立波 | Arresting gear and its system energetically |
| CN117048844A (en) * | 2023-10-09 | 2023-11-14 | 中国飞机强度研究所 | Aeroplane tire running rolling blocking steel cable impact test system and method |
-
2012
- 2012-01-17 CN CN 201220020519 patent/CN202529150U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105691631A (en) * | 2014-11-28 | 2016-06-22 | 四川航空工业川西机器有限责任公司 | Hydraulic ejection high-speed damping buffer system |
| CN107472550A (en) * | 2017-09-19 | 2017-12-15 | 方立波 | Arresting gear and its system energetically |
| CN117048844A (en) * | 2023-10-09 | 2023-11-14 | 中国飞机强度研究所 | Aeroplane tire running rolling blocking steel cable impact test system and method |
| CN117048844B (en) * | 2023-10-09 | 2024-01-05 | 中国飞机强度研究所 | Aeroplane tire running rolling blocking steel cable impact test system and method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121114 Termination date: 20140117 |