CN114212267B - Single torsion spring energy storage rotary cam type safety switch mechanism of aircraft - Google Patents
Single torsion spring energy storage rotary cam type safety switch mechanism of aircraft Download PDFInfo
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- CN114212267B CN114212267B CN202111613241.XA CN202111613241A CN114212267B CN 114212267 B CN114212267 B CN 114212267B CN 202111613241 A CN202111613241 A CN 202111613241A CN 114212267 B CN114212267 B CN 114212267B
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- switch
- torsion spring
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- cam
- energy storage
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- 230000007246 mechanism Effects 0.000 title claims abstract description 52
- 238000004146 energy storage Methods 0.000 title claims abstract description 21
- 238000011179 visual inspection Methods 0.000 abstract description 3
- 238000002955 isolation Methods 0.000 description 6
- 239000002360 explosive Substances 0.000 description 4
- 230000000977 initiatory effect Effects 0.000 description 4
- 230000003044 adaptive effect Effects 0.000 description 2
- 238000010586 diagram Methods 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
- 230000001960 triggered effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- 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
Landscapes
- 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 a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which comprises a rotating shaft, a torsion spring, a cam, an electric micro switch, a mechanism body and a switch rotating body, wherein the rotating shaft is arranged on the rotating shaft; the torsion spring, the cam and the switch rotator 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 of the interior of the aircraft, two sides of the other end of the mechanism body are respectively fixed with an electric micro switch, and the two electric micro switches respectively correspond to the positions of the cam and the switch rotating body; the switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube. The invention has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the general assembly into the barrel, redundant backup of electric insurance and good platform transplanting universality, and is suitable for various in-barrel 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 a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which mainly relates to an electrical isolation safety of an on-board initiating explosive device before the aircraft is triggered to leave a cylinder and a safety protection mechanism for switching the isolation safety into a communication state after the aircraft is triggered to leave the cylinder.
Background
The number of initiating explosive devices on the aircraft launched in the cylinder is large, and the battery is used as a power supply part of the aircraft at the same time. Under various environments such as storage, transportation, emission of an aircraft, the requirements of the initiating explosive device and a power supply in a cylinder before emission on the electricity on the aircraft to be conducted quickly after the aircraft is emitted from the cylinder are met.
Common isolation schemes: firstly, an isolating switch which is dynamically switched on/off by power supply fire work; and secondly, an electric micro switch is arranged at the position of the folding wing and the rudder wing, and when the folding wing is folded and unfolded, the electric micro switch is switched to be isolated/conducted. The limitations and the defects of the isolation schemes are obvious, and the isolation of the electrical initiating explosive device isolating switch is in a passage state, so that the isolating switch is free from subsequent hidden danger, obvious in impact vibration and the like; the assembly accuracy of the rudder wing is strictly required, the actuation of the rudder wing is influenced, and the rudder wing is limited by the position of the rudder wing on the aircraft, so that a safety switch cannot be arranged close to the tail of the aircraft, and the contradiction between the rudder wing and the aircraft is relieved as far as possible.
Disclosure of Invention
The invention provides a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which aims to solve the technical problems that: the device can meet the requirement of quick switching of the state of electrical isolation/conduction in/from the cylinder of the aircraft, is used as an independent mechanism design, can be widely suitable for different in-cylinder launching aircrafts through adaptive transformation, has good universality and can effectively accumulate reliability samples.
In order to solve the technical problems, the invention provides a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which is characterized in that: the electric micro-switch comprises a rotating shaft 1, a torsion spring 2, a cam 3, an electric micro-switch 6, a mechanism body 7 and a switch rotating body 8; the torsion spring, the cam and the switch rotator 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 inner side wall of the aircraft, two sides of the other end are respectively fixed with an electric micro switch 6, and the two electric micro switches respectively correspond to the positions of the cam 3 and the switch rotating body; the switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube.
The beneficial effects are that: the invention adopts the torsion spring in the cylinder to pretwist and store energy, and the electric micro switch is in a free safety state; the rotation limit of the torsion spring is released, the potential energy of the torsion spring releases the driving switch rotator to enable the cam to trigger the electric micro switch, so that the electric micro switch is switched from a safety state to a working state, and the on/off switching 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 general assembly into the barrel, redundant backup of electric insurance and good platform transplanting universality, and is suitable for various in-barrel launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like.
Drawings
Fig. 1 is a schematic diagram of the structure of a single torsion spring energy storage rotary cam type safety switch mechanism in a transmitting cylinder.
Fig. 2 is a schematic structural form of the single torsion spring energy storage rotary cam type safety switch mechanism after leaving the transmitting cylinder.
Fig. 3 is a schematic structural diagram of a single torsion spring energy storage rotary cam type safety switch mechanism.
Detailed Description
To make the objects, contents and advantages of the present invention more apparent, the following detailed description of the specific embodiments of the present invention will be given.
The invention provides a single torsion spring energy storage rotary cam type safety switch mechanism of an aircraft, which comprises a rotating shaft 1, a torsion spring 2, a cam 3, a key slot locking block 4, a screw 5, an electric micro switch 6, a mechanism body 7, a switch rotating body 8 and an mechanical check ring 9; the cam is an eccentric round wheel; the switch rotating body is also provided with a cam structure;
the torsion spring, the cam and the switch rotator are sequentially arranged on the rotating shaft in series according to the requirement 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 of the interior of the aircraft, two sides of the other end are respectively fixed with an electric micro switch 6, and the two electric micro switches respectively correspond to the positions of the cam 3 and the switch rotator.
An organic check ring 9 is arranged at the end part of the rotating shaft. The cam is connected with the rotating shaft through a key slot locking block 4.
The switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube.
The invention designs a single torsion spring at one side of the switch revolving body and is asymmetrically designed.
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 along the movement of the launching tube); when the switch rotating body is in the launching cylinder, the surface of the protruding machine body contacts the inner wall of the launching cylinder and is in a torsion spring pretwisting limiting state, the switch rotating body is driven to rotate and be in place by the torsion spring after the aircraft leaves the cylinder, the switch safety mechanism does not protrude the surface of the aircraft, and no separation object is separated from the machine body.
The torsion spring in the cylinder is used for pretwisting and storing energy, and the electric micro switch is in a free safety state; the rotation limit of the torsion spring is released, the potential energy of the torsion spring releases the driving switch rotating body to drive the cam (the switch rotating body can also contain cam characteristics) to trigger the electric micro switch, so that the electric micro switch is switched from a safety state to a working state, and the on/off conversion of a circuit is realized.
The torsion spring provides the actuating energy of the mechanism, the rotation of the cam changes the contact distance with the electric micro-switches, and the electric micro-switches can be driven to be arranged 1 or a plurality of electric micro-switches according to the requirement, so that the redundant design is realized.
The adaptive change mechanism installation body can be transplanted to different aircrafts, and the pendulum length X of the switch rotator 8 can be adjusted to adapt to the in-barrel launching aircrafts with different barrel machine gaps L.
The launching tube of the launching aircraft in the tube can also be a guide rail launched by a guide rail or a launching box launched in a box.
The invention adopts the asymmetric structural proposal of single torsion spring energy storage in the cylinder and release of limit cam rotation triggering of independent multi-path electric micro-switch by the off-cylinder torsion spring, has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the general assembly cylinder, redundant backup of electric insurance and good platform transplanting 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 foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and variations could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications and variations should also be regarded as being within the scope of the 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 micro switch (6), a mechanism body (7) and a switch rotating body (8); the torsion spring, the cam and the switch rotator 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 of the interior of the aircraft, two sides of the other end are respectively fixed with an electric micro switch (6), and the two electric micro switches respectively correspond to the positions of the cam (3) and the switch rotating body; the switch rotator is arranged in the cavity of the mechanism body, and the end part of the switch rotator passes through one end of the mechanism body and the long groove of the side wall of the aircraft and then contacts with the inner wall of the launching tube.
2. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the cam is an eccentric round wheel.
3. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the switch rotator is also provided with a cam structure.
4. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: an organic check ring (9) is arranged at the end part of the rotating shaft.
5. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the cam is connected with the rotating shaft through a key slot locking block (4).
6. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the plane of rotational movement of the switching rotator is parallel to and intersects the aircraft axis.
7. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: 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 torsion spring pretwisting limiting state, the torsion spring drives the switch rotating body 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. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the rotation of the cam changes the contact distance with the electric micro-switches, and can drive 1 or a plurality of electric micro-switches which are arranged according to the requirement.
9. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the swing length of the switch rotating body (8) is adjusted, so that the device can be suitable for in-cylinder launching aircrafts with different cylinder gaps.
10. An aircraft single torsion spring energy storage rotary cam safety switching mechanism according to claim 1, wherein: the launching tube can be replaced by a guide rail launched by a guide rail or a launching box launched in a box.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114212267A CN114212267A (en) | 2022-03-22 |
| CN114212267B true CN114212267B (en) | 2023-10-31 |
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| CN202111613241.XA Active 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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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8316750B2 (en) * | 2009-05-11 | 2012-11-27 | Donmark Holdings Inc. | Apparatus and method for launching incendiary projectiles |
-
2021
- 2021-12-27 CN CN202111613241.XA patent/CN114212267B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN111077018A (en) * | 2019-12-30 | 2020-04-28 | 华中科技大学 | Light unidirectional loading test device and application thereof |
| 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 |
Non-Patent Citations (3)
| Title |
|---|
| Multidisciplinary design and optimization of an innovative nano air launch vehicle with a twin-fuselage UAV as carrier aircraft;Daxi Zhang;Acta Astronautica;第170卷;第397-411页 * |
| 无人机他力发射技术综述;叶帅辰;指挥与控制学报;第4卷(第01期);第15-21页 * |
| 某新型发射系统发射动力学建模与仿真分析;李庚;兵器装备工程学报;第38卷(第12期);第1-5页 * |
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| CN114212267A (en) | 2022-03-22 |
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