CN214566238U - Functional reliability testing device for PSU oxygen system of airplane - Google Patents
Functional reliability testing device for PSU oxygen system of airplane Download PDFInfo
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- CN214566238U CN214566238U CN202120560656.4U CN202120560656U CN214566238U CN 214566238 U CN214566238 U CN 214566238U CN 202120560656 U CN202120560656 U CN 202120560656U CN 214566238 U CN214566238 U CN 214566238U
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- psu
- panel
- piston rod
- electric putter
- photoelectric sensor
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Abstract
The utility model provides an aircraft PSU oxygen system functional reliability testing arrangement, the piston rod of electric putter II stretches out the back, it passes through unblock subassembly unblock PSU panel, later the piston rod of electric putter II inwards retracts, PSU panel downwardly rotating this moment, the realization is dropped and is opened, later the piston rod of electric putter I outwards stretches out, it promotes the PSU panel and upwards rotates, until its locking, the piston rod of electric putter I inwards retracts behind the PSU panel locking, get back to the initial position, accomplish the test that drops of PSU panel once, action step more than the repetition, can realize the reliability test to the PSU panel, the efficiency of software testing is improved, and the cost is reduced.
Description
Technical Field
The utility model relates to an aircraft spare part testing arrangement field, concretely relates to aircraft PSU oxygen system functional reliability testing arrangement.
Background
The reliability test of the automatic falling function of the PSU oxygen system of the airplane generally requires high reliability, the failure rate is required to be lower than 10-7, and the reliability test is to carry out failure rate test on the PSU panel by carrying out multiple times of electric falling and resetting actions. The method for testing the reliability of the automatic falling function of the PSU oxygen system comprises the following steps: (1) powering on the PSU; (2) the panel falls off; (3) restoring the panel to the original position; (4) using a tool to pass through the reset hole to unlock the PSU assembly electromagnetic lock mechanism; (5) the panel is locked in place; (6) repeated energization makes a drop test. The test requires too many times, the time is very long, the counting is difficult, and manual operation can not be adopted to meet the requirements. Therefore, an automated handling and counting test system is required to complete the task.
Disclosure of Invention
The utility model discloses an overcome not enough of above technique, provide one kind and realize the automatic test that drops of aircraft PSU panel, the aircraft PSU oxygen system functional reliability testing arrangement of raising efficiency.
The utility model overcomes the technical scheme that its technical problem adopted is:
an aircraft PSU oxygen system functional reliability testing arrangement includes:
the upper end of the frame is provided with an airplane PSU assembly, and a PSU panel of the PSU assembly rotates downwards after being unlocked;
the electric push rod II is vertically fixed in the rack through a threaded fastener, an unlocking assembly is mounted on the PSU panel, and when a piston rod of the electric push rod II extends out completely, the electric push rod II drives the unlocking assembly to unlock the PSU panel; and
electric putter I is through the vertical frame that is fixed in of threaded fastener, and when electric putter I's piston rod was all stretched out, it promoted the PSU panel and upwards overturn to the locking state.
Furthermore, the unlocking assembly comprises a circular ring-shaped connecting ring which is stuck at the lock hole of the PSU panel, the through hole in the connecting ring is coaxial with the lock hole, the outer side of the connecting ring is provided with an external thread, the upper end of the cylindrical sleeve is provided with a screw hole, the sleeve is screwed on the external thread of the connecting ring through the screw hole, the driving column is slidably arranged in the sleeve, the upper end of the driving column is coaxially provided with a thimble, the thimble penetrates through the through hole and then is inserted into the lock hole in a sliding way, the thimble is sleeved with a spring, one end of the spring is connected with the driving column, the other end of the electric push rod II is connected with the connecting ring, when the spring is in a free state, the head end of the drive column extends out of the sleeve, the head end of the piston rod of the electric push rod II is provided with an actuating panel, when the piston rod of the electric push rod II extends out completely, the actuating panel pushes the driving column to move upwards until the ejector pin is inserted into the lock hole to unlock the PSU panel.
In order to prevent to damage the PSU panel, still include and rotate the returning face plate of installing in I piston rod head end of electric putter through the round pin axle, one side end of piston rod head end is provided with magnet, its opposite side is provided with the gag lever post, magnet is fixed with the returning face plate actuation under the initial condition and is the state that is acute angle contained angle setting with the horizontal plane, when I piston rod of electric putter stretches out the returning face plate and is the face contact with the PSU panel and drive the PSU panel locking under the state, the lower terminal surface of returning face plate contacts with the up end of gag lever post.
In order to realize counting, the device also comprises a photoelectric sensor transmitting end and a photoelectric sensor receiving end, wherein the photoelectric sensor transmitting end is horizontally arranged at the left side end of the top of the rack, the photoelectric sensor receiving end is horizontally arranged at the right side end of the top of the rack, the photoelectric sensor transmitting end and the photoelectric sensor receiving end are coaxially arranged, and after the PSU panel is unlocked and rotates downwards, the PSU panel shields light emitted by the photoelectric sensor transmitting end to the photoelectric sensor receiving end.
In order to further prevent the PSU panel from being damaged, the upper surface of the turnover plate is provided with a rubber pad.
The utility model has the advantages that: after the piston rod of electric putter II stretches out, it is through unblock subassembly unblock PSU panel, later the piston rod of electric putter II inwards retracts, PSU panel downwardly rotating this moment, the realization is dropped and is opened, later the piston rod of electric putter I outwards stretches out, it promotes the PSU panel and upwards rotates, until its locking, the piston rod of electric putter I inwards retracts behind the PSU panel locking, get back to initial position, accomplish the test that drops of a PSU panel, action step more than the repetition, can realize the reliability test to the PSU panel, the efficiency of testing is improved, the cost is reduced.
Drawings
Fig. 1 is a schematic perspective view of the present invention;
fig. 2 is a schematic perspective view of the PSU panel of the present invention;
FIG. 3 is a schematic perspective view of the turnover plate of the present invention;
in the figure, 1, a rack 2, an electric push rod I3, an electric push rod II 4, a photoelectric sensor transmitting end 5, a photoelectric sensor receiving end 6, an actuating panel 7, a turnover plate 8, a PSU panel 9, a connecting ring 10, a lock hole 11, a through hole 12, a driving column 13, a sleeve 14, a thimble 15, a spring 16, a pin shaft 17, a magnet 18 and a limiting rod are arranged.
Detailed Description
The present invention will be further explained with reference to fig. 1, fig. 2 and fig. 3.
An aircraft PSU oxygen system functional reliability testing arrangement includes: an airplane PSU assembly is installed at the upper end of the frame 1, and a PSU panel 8 of the PSU assembly rotates downwards after being unlocked; the electric push rod II 3 is vertically fixed in the rack 1 through a threaded fastener, an unlocking assembly is mounted on the PSU panel 8, and when a piston rod of the electric push rod II 3 extends out completely, the unlocking assembly is driven to unlock the PSU panel 8; and electric putter I2, through the vertical frame 1 that is fixed in of threaded fastener, when electric putter I2's piston rod was all stretched out, it promoted PSU panel 8 upwards to overturn to the locking state. After electric putter II 3's piston rod stretches out, it is through unblock subassembly unblock PSU panel 8, later the piston rod of electric putter II 3 inwards withdraws, PSU panel 8 rotates downwards this moment, the realization is dropped and is opened, later the piston rod of electric putter I2 outwards stretches out, it promotes PSU panel 8 upwards to rotate, until its locking, PSU panel 8 locking back electric putter I2's piston rod inwards withdraws, get back to the initial position, accomplish the test that drops of PSU panel 8 once, action step more than the repetition, can realize the reliability test to PSU panel 8, the efficiency of software testing is improved, and the cost is reduced.
The unlocking component can be a structure which comprises a circular connecting ring 9 adhered to a lock hole 10 of the PSU panel 8, a through hole 11 in the connecting ring 9 is coaxially arranged with the lock hole 10, an external thread is arranged on the outer side of the connecting ring 9, a screw hole is arranged at the upper end of a cylindrical sleeve 13, the sleeve 13 is screwed on the external thread of the connecting ring 9 through the screw hole, a driving column 12 is slidably arranged in the sleeve 13, an ejector pin 14 is coaxially arranged at the upper end of the driving column 12, the ejector pin 14 penetrates through the through hole 11 and then is slidably inserted into the lock hole 10, a spring 15 is sleeved on the ejector pin 14, one end of the spring 15 is connected with the driving column 12, the other end of the spring is connected with the connecting ring 9, when the spring 15 is in a free state, the head end of the driving column 12 extends out of the sleeve 13, the actuating panel 6 is arranged at the head end of a piston rod of the electric push rod II 3, when the piston rod of the electric push rod II 3 extends out completely, the actuating panel 6 pushes the driving rod 12 to move upward until the thimble 14 is inserted into the locking hole 10 to unlock the PSU panel 8. After the PSU panel 8 is unlocked, the electric push rod ii 3 drives the actuating panel 6 to move downwards, and then under the elastic force of the spring 15, the driving column 12 is driven to move downwards and drives the thimble 14 to move downwards, and the head end of the driving column 12 extends out of the sleeve 13 again and returns to the initial state.
Further, still include to rotate through round pin axle 16 and install in the returning face plate 7 of electric putter I2 piston rod head end, one side end of piston rod head end is provided with magnet 17, its opposite side is provided with gag lever post 18, magnet 17 is fixed with returning face plate 7 actuation under the initial condition and is the state that is the acute angle contained angle setting with the horizontal plane, when electric putter I2 piston rod stretches out that returning face plate 7 is the locking of driving PSU panel 8 under the state that the face contacted with PSU panel 8, the lower terminal surface of returning face plate 7 contacts with the up end of gag lever post 18. When electric putter I2 promoted the upshifting of returning face plate 7, when returning face plate 7 began to contact with PSU panel 8, the back of returning face plate 7 atress was thrown away with magnet 17, and gradual returning face plate 7 can rotate to the mutual face contact with PSU panel 8, later when promoting PSU panel 8 upwards pivoted, returning face plate 7 all the time with 8 face contacts of PSU panel through real-time angle regulation to prevent the damage to PSU panel 8. After the PSU panel 8 is locked and fixed, the electric push rod I2 drives the turnover plate 7 to move downwards, and the turnover plate 7 is separated from the PSU panel 8, so that the turnover plate returns to the initial position under the action of the magnet 17, and the turnover plate is convenient to use next time. The limiting rod 18 can prevent the overturning plate 7 from excessively rotating, and the use reliability is improved.
Further, still include horizontal installation in the photoelectric sensor transmitting terminal 4 of frame 1 top left side end and horizontal installation in the photoelectric sensor receiving terminal 5 of frame 1 top right side end, photoelectric sensor transmitting terminal 4 sets up with photoelectric sensor receiving terminal 5 coaxial, after PSU panel 8 unblock and down rotate, it shelters from the light that photoelectric sensor transmitting terminal 4 launches to photoelectric sensor receiving terminal 5. At this moment, the photoelectric sensor is triggered once, the PSU panel 8 is recorded to fall once, and the counting effect is achieved.
Preferably, the upper surface of the turnover plate 7 is provided with a rubber pad. Because the rubber pad has soft characteristic, so when returning the board 7 and the surface contact of PSU panel 8, through rubber pad and the contact of PSU panel 8, can further prevent to damage PSU panel 8, improved the reliability of using.
Claims (5)
1. The utility model provides an aircraft PSU oxygen system functional reliability testing arrangement which characterized in that includes:
the upper end of the frame (1) is provided with an airplane PSU assembly, and a PSU panel (8) of the PSU assembly rotates downwards after being unlocked;
the electric push rod II (3) is vertically fixed in the rack (1) through a threaded fastener, an unlocking assembly is mounted on the PSU panel (8), and when a piston rod of the electric push rod II (3) extends out completely, the electric push rod II drives the unlocking assembly to unlock the PSU panel (8); and
electric putter I (2), through the vertical frame (1) of being fixed in of threaded fastener, when the piston rod of electric putter I (2) was all stretched out, it promoted PSU panel (8) and upwards overturns to the locking state.
2. The aircraft PSU oxygen system functional reliability testing apparatus of claim 1, further comprising: the unlocking assembly comprises a circular connecting ring (9) adhered to a lock hole (10) of a PSU panel (8), a through hole (11) in the connecting ring (9) and the lock hole (10) are coaxially arranged, an external thread is arranged on the outer side of the connecting ring (9), a screw hole is formed in the upper end of a cylindrical sleeve (13), the sleeve (13) is screwed on the external thread of the connecting ring (9) through the screw hole, a driving column (12) is slidably installed in the sleeve (13), an ejector pin (14) is coaxially arranged at the upper end of the driving column (12), the ejector pin (14) penetrates through the through hole (11) and then is slidably inserted into the lock hole (10), a spring (15) is sleeved on the ejector pin (14), one end of the spring (15) is connected with the driving column (12), the other end of the spring is connected with the connecting ring (9), and when the spring (15) is in a free state, the head end of the driving column (12) extends out of the sleeve (13), and an actuating panel (6) is installed at the head end of the piston rod of the electric push rod II (3), and when the piston rod of the electric push rod II (3) is completely extended out, the actuating panel (6) pushes the driving column (12) to move upwards until the ejector pin (14) is inserted into the lock hole (10) to unlock the PSU panel (8).
3. The aircraft PSU oxygen system functional reliability testing apparatus of claim 1, further comprising: still include through round pin axle (16) rotate install in returning face plate (7) of electric putter I (2) piston rod head end, one side end of piston rod head end is provided with magnet (17), its opposite side is provided with gag lever post (18), magnet (17) are fixed returning face plate (7) actuation under the initial condition be with the horizontal plane for the state that the acute angle contained angle set up, when electric putter I (2) piston rod stretches out returning face plate (7) and PSU panel (8) are when driving PSU panel (8) locking under the state that the face contact was, the lower terminal surface of returning face plate (7) contacts with the up end of gag lever post (18).
4. The aircraft PSU oxygen system functional reliability testing apparatus of claim 1, further comprising: still include horizontal installation in the photoelectric sensor transmitting terminal (4) of frame (1) top left side end and horizontal installation in the photoelectric sensor receiving terminal (5) of frame (1) top right side end, photoelectric sensor transmitting terminal (4) and photoelectric sensor receiving terminal (5) same axle set up, after PSU panel (8) unblock and down rotated, it sheltered from the light of photoelectric sensor transmitting terminal (4) transmission to photoelectric sensor receiving terminal (5).
5. The aircraft PSU oxygen system functional reliability testing device of claim 3, wherein: the upper surface of the turnover plate (7) is provided with a rubber pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120560656.4U CN214566238U (en) | 2021-03-19 | 2021-03-19 | Functional reliability testing device for PSU oxygen system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120560656.4U CN214566238U (en) | 2021-03-19 | 2021-03-19 | Functional reliability testing device for PSU oxygen system of airplane |
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| CN214566238U true CN214566238U (en) | 2021-11-02 |
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| CN202120560656.4U Active CN214566238U (en) | 2021-03-19 | 2021-03-19 | Functional reliability testing device for PSU oxygen system of airplane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115228857A (en) * | 2022-06-14 | 2022-10-25 | 湖南开放大学(湖南网络工程职业学院、湖南省干部教育培训网络学院) | Robot for cleaning interior of pipeline |
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2021
- 2021-03-19 CN CN202120560656.4U patent/CN214566238U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115228857A (en) * | 2022-06-14 | 2022-10-25 | 湖南开放大学(湖南网络工程职业学院、湖南省干部教育培训网络学院) | Robot for cleaning interior of pipeline |
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