CN114212268B - Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft - Google Patents
Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft Download PDFInfo
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- CN114212268B CN114212268B CN202111615253.6A CN202111615253A CN114212268B CN 114212268 B CN114212268 B CN 114212268B CN 202111615253 A CN202111615253 A CN 202111615253A CN 114212268 B CN114212268 B CN 114212268B
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- cylinder
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- 238000009434 installation Methods 0.000 claims abstract description 23
- 238000005381 potential energy Methods 0.000 claims description 2
- 238000002955 isolation Methods 0.000 abstract description 9
- 230000003044 adaptive effect Effects 0.000 abstract description 2
- 230000009466 transformation Effects 0.000 abstract description 2
- 239000002360 explosive Substances 0.000 description 5
- 230000000977 initiatory effect Effects 0.000 description 5
- 230000005611 electricity Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000011179 visual inspection Methods 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Rotary Switch, Piano Key Switch, And Lever Switch (AREA)
Abstract
The invention relates to a rotary eccentric wheel type electric safety switch mechanism of an in-cylinder launching aircraft, which comprises a switch mounting body, a torsion spring, an eccentric wheel, a rotating shaft, a torsion arm disc, a switch rotating body and an electric switch, wherein the switch mounting body is provided with a torsion arm disc; the switch installation body is arranged in the aircraft, one end of the switch installation body is fixedly connected with the inner wall of the aircraft, and two sides of the other end of the switch installation body are respectively fixed with an electric switch; the invention not only can meet the requirement of quick switching of the state of electrical isolation/conduction in/out of the cylinder of the aircraft, but also can be widely applicable to different in-cylinder launching aircrafts through adaptive transformation as an independent mechanism design, has good universality and can effectively accumulate reliability samples. The device has the advantages of simple structure, stable and reliable operation, modularized universality, suitability for in-cylinder launching aircrafts and good application prospect.
Description
Technical Field
The invention belongs to the field of aircrafts, and particularly relates to a rotary eccentric wheel type electric safety switch mechanism of an in-cylinder launching aircraft, which mainly relates to an electric isolation safety of an on-board initiating explosive device before the in-cylinder launching aircraft is launched from a cylinder and a safety protection mechanism for switching the electric quick release isolation safety to a communication state after the on-board initiating explosive device is launched from 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, the electric micro switch is arranged at the folding machine and the rudder wing, and is switched to be isolated/conducted when the folding and unfolding are switched. 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 rotary eccentric wheel type electric safety switch mechanism of an in-cylinder launching aircraft, which aims to solve the technical problems that: the electric physical isolation device can be used for completely isolating electricity and physical and separating the electric physical isolation device from an on-board actuating mechanism without affecting each other.
In order to solve the technical problems, the invention provides a rotary eccentric wheel type electric safety switch mechanism of an in-cylinder launching aircraft, which is characterized in that: the electric switch comprises a switch mounting body 1, a torsion spring 2, an eccentric wheel 5, a rotating shaft 7, a torsion arm disc 8, a switch rotating body 9 and an electric switch 11; the switch installation body 1 is arranged in the aircraft, one end of the switch installation body 1 is fixedly connected with the inner wall of the aircraft, and two sides of the other end are respectively fixed with an electric switch; the connection end of the switch mounting body 1 and the aircraft is provided with a U-shaped groove, and the inner wall of the aircraft corresponding to the U-shaped groove is provided with a long groove; the rotating shaft is arranged on the switch installation body and is bilaterally symmetrical relative to the center line of the switch installation body; the eccentric wheel 5, the torsion spring 2 and the torsion arm disc 8 are symmetrically arranged on the rotating shafts on the left side and the right side of the switch mounting body; the two eccentric wheels correspond to the positions of the electric switches respectively; the switch rotator 9 is fixed on the rotating shaft and is positioned in the U-shaped groove of the switch installation body 1, and the end part of the switch rotator 9 passes through the side wall of the aircraft to be in contact fit with the inner wall of the launching tube.
The beneficial effects are that: the invention not only can meet the requirement of quick switching of the state of electrical isolation/conduction in/out of the cylinder of the aircraft, but also can be widely applicable to different in-cylinder launching aircrafts through adaptive transformation as an independent mechanism design, has good universality and can effectively accumulate reliability samples. The device has the advantages of simple structure, stable and reliable operation, modularized universality, suitability for in-cylinder launching aircrafts and good application prospect.
Drawings
Fig. 1 (a) and (b) are front and left views, respectively, of the present invention in its configuration within a cartridge.
Fig. 2 is a schematic structural view of the present invention after leaving the launch canister.
FIG. 3 is a schematic diagram of the structural composition of the present invention
Fig. 4 is a left side view of fig. 3.
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 rotary eccentric wheel type electric safety switch mechanism of an in-cylinder launching aircraft, which comprises a switch mounting body 1, a torsion spring 2, a torsion arm fixing bracket 3, a switch rotating body locking pin 4, an eccentric wheel 5, an eccentric wheel locking pin 6, a rotating shaft 7, a torsion arm disc 8, a switch rotating body 9, a stop pin 10, an electric switch 11 and a screw 12;
the switch installation body 1 is arranged in the aircraft, one end of the switch installation body 1 is fixedly connected with the inner wall of the aircraft, and two sides of the other end are respectively fixed with an electric switch; the connection end of the switch mounting body 1 and the aircraft is provided with a U-shaped groove, and the inner wall of the aircraft corresponding to the U-shaped groove is provided with a long groove;
the rotating shaft is arranged on the switch installation body and is bilaterally symmetrical relative to the center line of the switch installation body; the eccentric wheel 5, the torsion spring 2 and the torsion arm disc 8 are symmetrically arranged on the rotating shafts on the left side and the right side of the switch mounting body; the left side and the right side of the switch installation body are provided with torsion arm fixing brackets 3 corresponding to the eccentric wheels; one end of the torsion spring is fixed on the torsion arm disc 8, and the other end is fixed on the torsion arm fixing bracket; the two eccentric wheels correspond to the positions of the electric switches respectively; the switch rotator 9 is fixed on the rotating shaft through the switch rotator locking pin 4 and is positioned in the U-shaped groove of the switch installation body 1, and the end part of the switch rotator 9 penetrates through the side wall of the aircraft to be in contact fit with the inner wall of the launching tube.
The switch rotator can also be provided with an eccentric wheel, and an electric switch can also be arranged at the corresponding position of the eccentric wheel.
The torsion spring is pre-twisted for storing energy, and the electric micro switch is in a 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 eccentric wheel (the switch rotating body can also be characterized by the eccentric wheel) to trigger the electric switch, so that the electric 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, and the rotation of the eccentric wheel changes the contact distance between the eccentric wheel and the electric micro-switch. The device can drive 1 or a plurality of electric micro switches which are arranged according to the requirement, and realizes redundant design.
The electric 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 rotator 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, after the aircraft leaves the cylinder, the torsion spring drives the switch rotating body to rotate and be in place, the electric safety mechanism does not protrude the surface of the aircraft, and no separation object is separated from the machine body.
The swing length X of the switch rotating body 9 is adjusted, so that the in-barrel launching aircraft with different barrel machine gaps L can be adapted.
The switch installation body can be transplanted to different aircrafts by changing the adaptability, and the aircrafts with different barrel machine gaps L can be adapted by changing the swing length X of the switch rotating body, so that the switch installation body has universal applicability.
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 symmetrical structure scheme of the double (arm) torsion spring energy storage in the cylinder and the off-cylinder torsion spring to release the limit eccentric wheel rotation to trigger the independent multi-channel electric micro switch, has the advantages of strong mechanism independence, convenient on-board layout, convenient and clear visual inspection of the mechanical state of the general assembly in the cylinder, redundant backup of electric insurance and good platform transplanting universality, and is suitable for various in-cylinder launching aircrafts such as vehicle-mounted launching, airborne launching, portable launching and the like.
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 (8)
1. An in-cylinder launching aircraft rotating eccentric wheel type electric safety switch mechanism is characterized in that: the electric switch comprises a switch mounting body (1), a torsion spring (2), an eccentric wheel (5), a rotating shaft (7), a torsion arm disc (8), a switch rotating body (9) and an electric switch (11); the switch installation body (1) is arranged in the aircraft, one end of the switch installation body (1) is fixedly connected with the inner wall of the aircraft, and two sides of the other end of the switch installation body are respectively fixed with an electric switch; a U-shaped groove is formed at the connecting end of the switch mounting body (1) and the aircraft, and a long groove is formed on the inner wall of the aircraft corresponding to the U-shaped groove; the rotating shaft is arranged on the switch installation body and is bilaterally symmetrical relative to the center line of the switch installation body; the rotating shafts on the left side and the right side of the switch mounting body are symmetrically provided with eccentric wheels (5), torsion springs (2) and torsion arm discs (8); the two eccentric wheels correspond to the positions of the electric switches respectively; the switch rotator (9) is fixed on the rotating shaft and is positioned in the U-shaped groove of the switch installation body (1), and the end part of the switch rotator (9) penetrates through the side wall of the aircraft to be in contact fit with the inner wall of the launching cylinder.
2. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the left side and the right side of the switch installation body are provided with torsion arm fixing brackets (3) corresponding to the eccentric wheels, one end of the torsion spring is fixed on the torsion arm disc (8), and the other end is fixed on the torsion arm fixing brackets.
3. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the switch rotator is provided with an eccentric wheel, and an electric switch is arranged at the corresponding position of the eccentric wheel.
4. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the torsion spring is pre-twisted for storing energy, and the electric micro switch is in a safety state; and the rotation limit of the torsion spring is released, and the potential energy of the torsion spring releases the driving switch rotating body to drive the eccentric wheel to trigger the electric switch.
5. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the plane of rotational movement of the switching rotator is parallel to and intersects the aircraft axis.
6. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: 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, after the aircraft leaves the cylinder, the torsion spring drives the switch rotating body to rotate and be in place, and the electric safety mechanism does not protrude out of the surface of the aircraft.
7. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the swing length of the switch rotating body (9) is adjusted, so that the device can be suitable for the in-barrel launching aircrafts with different barrel machine gaps L.
8. An in-barrel launching vehicle rotary eccentric electric safety switch mechanism as in claim 1, wherein: the launching tube of the launching aircraft in the tube is 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 |
|---|---|---|---|
| CN202111615253.6A CN114212268B (en) | 2021-12-27 | 2021-12-27 | Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111615253.6A CN114212268B (en) | 2021-12-27 | 2021-12-27 | Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114212268A CN114212268A (en) | 2022-03-22 |
| CN114212268B true CN114212268B (en) | 2023-10-31 |
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| CN202111615253.6A Active CN114212268B (en) | 2021-12-27 | 2021-12-27 | Rotary eccentric wheel type electric safety switch mechanism of in-cylinder launching aircraft |
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| CN114212268A (en) | 2022-03-22 |
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