CN114212267A - Single torsional spring energy storage rotating cam type safety switch mechanism of aircraft - Google Patents
Single torsional spring energy storage rotating cam type safety switch mechanism of aircraft Download PDFInfo
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- CN114212267A CN114212267A CN202111613241.XA CN202111613241A CN114212267A CN 114212267 A CN114212267 A CN 114212267A CN 202111613241 A CN202111613241 A CN 202111613241A CN 114212267 A CN114212267 A CN 114212267A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 55
- 238000004146 energy storage Methods 0.000 title claims abstract description 21
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 238000002054 transplantation Methods 0.000 abstract description 3
- 238000011179 visual inspection Methods 0.000 abstract description 3
- 238000002955 isolation Methods 0.000 description 9
- 239000002360 explosive Substances 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanisms For Operating Contacts (AREA)
- Rotary Switch, Piano Key Switch, And Lever Switch (AREA)
Abstract
The invention relates to an energy-storage rotating cam type safety switch mechanism of a single torsion spring of an aircraft, which comprises a rotating shaft, a torsion spring, a cam, an electric microswitch, a mechanism body and a switch rotating body, wherein the rotating shaft is connected with the torsion spring; the torsion spring, the cam and the switch rotating body are sequentially arranged on the rotating shaft in series and are connected with the mechanism body through the rotating shaft; one end of the mechanism body is fixed on the side wall in the aircraft, two sides of the other end of the mechanism body are respectively fixed with an electrical microswitch, and the two electrical microswitches respectively correspond to the positions of the cam and the switch rotating body; the switch rotating body is arranged in a cavity of the mechanism body, and the end part of the switch rotating body is contacted with the inner wall of the launching tube after penetrating through one end of the mechanism body and the long groove of the side wall of the aircraft. The invention has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the final assembly cylinder, redundant backup of the electrical insurance and good platform transplantation universality, and is suitable for various in-cylinder launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like.
Description
Technical Field
The invention belongs to the field of aircrafts, and particularly relates to an aircraft single-torsion spring energy-storage rotating cam type safety switch mechanism, which mainly relates to a safety protection mechanism for converting an aircraft storage and transportation state, an electrical isolation safety of an on-machine initiating explosive device before an aircraft is fired to leave a cylinder, and an electrical quick isolation safety after the aircraft leaves the cylinder into a communication state.
Background
The number of initiating explosive devices on the launching aircraft in the cylinder is large, and meanwhile, the onboard battery is used as a power supply part of the aircraft. Under various environments of aircraft storage, transportation, launching and the like, the requirements that an initiating explosive device and a power supply in a barrel are physically isolated before launching and that the on-board electricity is quickly conducted after the initiating explosive device and the power supply are launched from the barrel are simultaneously met.
Common isolation schemes: the first is an isolating switch which switches isolation/conduction by actuating the electric firer; and secondly, the electric micro switch is arranged at the folding wing and the rudder wing and is switched to be isolated/conducted when the folding wing and the rudder wing are folded and unfolded. The limitations and the disadvantages of the isolation schemes are obvious, and the firer isolation switch for isolating the electricity is in a closed state, so that the firer isolation switch has no isolation and subsequent hidden dangers, has obvious impact vibration and the like; the assembly precision of the aircraft rudder wing is strict, the action of the aircraft rudder wing is affected, the position of the aircraft rudder wing on an aircraft is limited, a safety switch cannot be arranged close to the tail of the aircraft frequently, and the safety switch is inconsistent with the situation that the aircraft is far away from a cylinder as far as possible to relieve the safety.
Disclosure of Invention
The invention provides an energy-storage rotating cam type safety switch mechanism of a single torsion spring of an aircraft, which aims to solve the technical problems that: the quick switching of the state of the electrical isolation/conduction of the inner/outer cylinder of the aircraft can be met, and the quick switching mechanism can be widely applied to launching aircrafts in different cylinders through adaptive transformation as an independent mechanism design, has good universality and can effectively accumulate reliability samples.
In order to solve the technical problems, the invention provides an aircraft single torsion spring energy storage rotating cam type safety switch mechanism, which is characterized in that: comprises a rotating shaft 1, a torsion spring 2, a cam 3, an electric microswitch 6, a mechanism body 7 and a switch rotating body 8; the torsion spring, the cam and the switch rotating body are sequentially arranged on the rotating shaft in series and are connected with the mechanism body 7 through the rotating shaft; one end of the mechanism body 7 is fixed on the side wall in the aircraft, two sides of the other end are respectively fixed with an electric microswitch 6, and the two electric microswitches respectively correspond to the cam 3 and the switch rotating body; the switch rotating body is arranged in a cavity of the mechanism body, and the end part of the switch rotating body is contacted with the inner wall of the launching tube after penetrating through one end of the mechanism body and the long groove of the side wall of the aircraft.
Has the advantages that: the invention adopts torsion springs in the cylinder to pre-twist and store energy, and the electric microswitch is in a free safety state; the rotation limit of the torsion spring is released, the potential energy of the torsion spring releases and drives the switch rotating body to drive the cam to trigger the electric microswitch, so that the electric microswitch is converted into a working state from a safety state, and the on/off conversion of a circuit is realized. The invention has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the final assembly cylinder, redundant backup of the electrical insurance and good platform transplantation universality, and is suitable for various in-cylinder launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like.
Drawings
Fig. 1 is a schematic diagram of the structural form of a single torsion spring energy storage rotating cam type safety switch mechanism in a launching tube.
Fig. 2 is a schematic structural form diagram of the single torsion spring energy storage rotating cam type safety switch mechanism after leaving the launching tube.
Fig. 3 is a schematic structural composition diagram of a single torsion spring energy storage rotating cam type safety switch mechanism.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention is provided.
The invention provides an energy-storage rotating cam type safety switch mechanism of a single torsion spring of an aircraft, which comprises a rotating shaft 1, a torsion spring 2, a cam 3, a key groove locking block 4, a screw 5, an electric microswitch 6, a mechanism body 7, a switch rotating body 8 and a mechanical retainer ring 9; the cam is an eccentric circular wheel; the switch rotating body is also provided with a cam structure;
the torsion spring, the cam and the switch rotating body are sequentially arranged on the rotating shaft in series according to requirements and are connected with the mechanism body 7 through the rotating shaft; one end of the mechanism body 7 is fixed on the side wall in the aircraft, two sides of the other end of the mechanism body are respectively fixed with an electric microswitch 6, and the two electric microswitches respectively correspond to the cam 3 and the switch rotating body.
The end part of the rotating shaft is provided with an organic retainer ring 9. The cam is connected with the rotating shaft through a key slot locking block 4.
The switch rotating body is arranged in a cavity of the mechanism body, and the end part of the switch rotating body is contacted with the inner wall of the launching tube after penetrating through one end of the mechanism body and the long groove of the side wall of the aircraft.
According to the invention, a single torsion spring is designed on one side of the switch revolving body, and the design is asymmetric.
The safety switch mechanism is arranged in the aircraft, and the reliability of the mechanism can be improved when the rotary motion plane of the switch rotating body is parallel to and intersected with the axis of the aircraft (namely the direction of the aircraft moving along the launching tube); when the switch rotating body is in the launching tube, the surface of the protruding machine body contacts the inner wall of the launching tube and is in a torsional spring pre-twisting limit state, the switch rotating body is driven by the torsional spring to rotate and reach the position after the aircraft leaves the launching tube, the switch safety mechanism does not protrude the surface of the aircraft, and no separator is separated from the machine body.
The torsion spring in the cylinder is used for pre-twisting energy storage, and the electric microswitch is in a free safety state; the rotation limit of the torsion spring is released, the potential energy of the torsion spring is released to drive the switch rotating body to drive the cam (the switch rotating body can also contain the cam characteristic) to trigger the electric microswitch, so that the electric microswitch is converted into a working state from a safety state, and the on/off conversion of a circuit is realized.
The torsional spring provides the actuating energy of mechanism, and the rotation of cam changes the contact distance with electric micro-gap switch, can drive 1 or several electric micro-gap switch that sets up as required, realizes the redundant design.
The installation body of the adaptability change mechanism can be transplanted to different aircrafts, and the swing length X of the switch rotating body 8 is adjusted, so that the adaptability change mechanism can adapt to launching aircrafts in cylinders with different cylinder gaps L.
The launching aircraft launching canister in the invention can be a guide rail launched by a guide rail or a launching box launched by a box.
The invention adopts the asymmetrical structure scheme that a single torsion spring in a cylinder stores energy, the off-cylinder torsion spring relieves the rotation of the limit cam to trigger the independent multi-path electric microswitch, has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the assembled cylinder, redundant backup of the electric insurance and good platform transplantation universality, is suitable for various in-cylinder launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like, and has good application prospect.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. The utility model provides an aircraft single torsional spring energy storage rotary cam formula safety switch mechanism which characterized in that: comprises a rotating shaft 1, a torsion spring 2, a cam 3, an electric microswitch 6, a mechanism body 7 and a switch rotating body 8; the torsion spring, the cam and the switch rotating body are sequentially arranged on the rotating shaft in series and are connected with the mechanism body 7 through the rotating shaft; one end of the mechanism body 7 is fixed on the side wall in the aircraft, two sides of the other end are respectively fixed with an electric microswitch 6, and the two electric microswitches respectively correspond to the cam 3 and the switch rotating body; the switch rotating body is arranged in a cavity of the mechanism body, and the end part of the switch rotating body is contacted with the inner wall of the launching tube after penetrating through one end of the mechanism body and the long groove of the side wall of the aircraft.
2. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the cam is an eccentric circular wheel.
3. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the switch rotating body is also provided with a cam structure.
4. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the end part of the rotating shaft is provided with an organic retainer ring 9.
5. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the cam is connected with the rotating shaft through a key slot locking block 4.
6. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the plane of the rotary motion of the switch rotary body is parallel to and intersects the aircraft axis.
7. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: when the switch rotating body is in the launching tube, the surface of the protruding machine body is in contact with the inner wall of the launching tube and is in a torsional spring pre-twisting limit state, the switch rotating body is driven by the torsional spring to rotate and be in place after the aircraft leaves the launching tube, and the switch safety mechanism does not protrude out of the surface of the aircraft.
8. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the rotation of the cam changes the contact distance with the electric micro-switches, and 1 or a plurality of electric micro-switches arranged as required can be driven.
9. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the length of the switch rotating body 8 is adjusted, so that the launching aircraft can be suitable for launching aircrafts in barrels with different barrel machine gaps.
10. The aircraft single torsion spring energy storage rotating cam type safety switch mechanism according to claim 1, characterized in that: the launching tube can be replaced by a guide rail for guide rail launching or a launching box for box launching.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111613241.XA CN114212267B (en) | 2021-12-27 | 2021-12-27 | Single torsion spring energy storage rotary cam type safety switch mechanism of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111613241.XA CN114212267B (en) | 2021-12-27 | 2021-12-27 | Single torsion spring energy storage rotary cam type safety switch mechanism of aircraft |
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| CN114212267A true CN114212267A (en) | 2022-03-22 |
| CN114212267B CN114212267B (en) | 2023-10-31 |
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Citations (13)
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|---|---|---|---|---|
| GB583122A (en) * | 1943-03-09 | 1946-12-10 | All American Aviat Inc | Improvements in method and apparatus for launching aircraft |
| US4392411A (en) * | 1980-05-02 | 1983-07-12 | Dornier Gmbh | Launch for carrying and launching flying bodies, in particular for aircraft |
| US4410151A (en) * | 1979-08-30 | 1983-10-18 | Vereinigte Flugtechnische Werke-Fokker Gmbh | Unmanned craft |
| US20100282230A1 (en) * | 2009-05-11 | 2010-11-11 | Donmark Holdings Inc. | Apparatus and method for launching incendiary projectiles |
| KR20120009020A (en) * | 2010-07-21 | 2012-02-01 | 국방과학연구소 | Rotary safety switch and missile system having the same |
| KR101343246B1 (en) * | 2013-09-24 | 2013-12-18 | (주)한국유에이브이 | Launchign apparatus for samll unmanned aerial vehicle |
| BR102016000552A2 (en) * | 2016-01-11 | 2017-07-18 | Embraer S.A. | LONGITUDINAL LOAD DEVICE FOR LOADING IN AIRCRAFT, SAFETY SWITCH FOR LONGITUDINAL LATCH DEVICE |
| CN109229412A (en) * | 2018-03-22 | 2019-01-18 | 吉少波 | A kind of ejector |
| CN111077018A (en) * | 2019-12-30 | 2020-04-28 | 华中科技大学 | Light unidirectional loading test device and application thereof |
| RU2725013C1 (en) * | 2019-04-04 | 2020-06-29 | Федеральное государственное унитарное предприятие "Российский федеральный ядерный центр - Всероссийский научно-исследовательский институт технической физики имени академика Е.И. Забабахина" | Catapult for launching of unmanned aerial vehicles |
| CN111572798A (en) * | 2020-05-15 | 2020-08-25 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle emitter and unmanned aerial vehicle cluster transmitter thereof |
| CN112407286A (en) * | 2020-11-12 | 2021-02-26 | 西安工业大学 | Method and device for casting airborne cartridge-mounted unmanned aerial vehicle spreader |
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2021
- 2021-12-27 CN CN202111613241.XA patent/CN114212267B/en active Active
Patent Citations (13)
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|---|---|---|---|---|
| GB583122A (en) * | 1943-03-09 | 1946-12-10 | All American Aviat Inc | Improvements in method and apparatus for launching aircraft |
| US4410151A (en) * | 1979-08-30 | 1983-10-18 | Vereinigte Flugtechnische Werke-Fokker Gmbh | Unmanned craft |
| US4392411A (en) * | 1980-05-02 | 1983-07-12 | Dornier Gmbh | Launch for carrying and launching flying bodies, in particular for aircraft |
| US20100282230A1 (en) * | 2009-05-11 | 2010-11-11 | Donmark Holdings Inc. | Apparatus and method for launching incendiary projectiles |
| KR20120009020A (en) * | 2010-07-21 | 2012-02-01 | 국방과학연구소 | Rotary safety switch and missile system having the same |
| KR101343246B1 (en) * | 2013-09-24 | 2013-12-18 | (주)한국유에이브이 | Launchign apparatus for samll unmanned aerial vehicle |
| BR102016000552A2 (en) * | 2016-01-11 | 2017-07-18 | Embraer S.A. | LONGITUDINAL LOAD DEVICE FOR LOADING IN AIRCRAFT, SAFETY SWITCH FOR LONGITUDINAL LATCH DEVICE |
| CN109229412A (en) * | 2018-03-22 | 2019-01-18 | 吉少波 | A kind of ejector |
| RU2725013C1 (en) * | 2019-04-04 | 2020-06-29 | Федеральное государственное унитарное предприятие "Российский федеральный ядерный центр - Всероссийский научно-исследовательский институт технической физики имени академика Е.И. Забабахина" | Catapult for launching of unmanned aerial vehicles |
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| CN111572798A (en) * | 2020-05-15 | 2020-08-25 | 珠海天晴航空航天科技有限公司 | Unmanned aerial vehicle emitter and unmanned aerial vehicle cluster transmitter thereof |
| CN112407286A (en) * | 2020-11-12 | 2021-02-26 | 西安工业大学 | Method and device for casting airborne cartridge-mounted unmanned aerial vehicle spreader |
| CN113044233A (en) * | 2021-04-30 | 2021-06-29 | 河南华讯方舟航空科技有限公司 | Unmanned aerial vehicle emitter |
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| CN114212267B (en) | 2023-10-31 |
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