CN213277171U - Teaching simulator of airplane hydraulic retraction control system - Google Patents
Teaching simulator of airplane hydraulic retraction control system Download PDFInfo
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- CN213277171U CN213277171U CN202022045082.5U CN202022045082U CN213277171U CN 213277171 U CN213277171 U CN 213277171U CN 202022045082 U CN202022045082 U CN 202022045082U CN 213277171 U CN213277171 U CN 213277171U
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Abstract
The utility model discloses an aircraft hydraulic pressure receive and releases control system teaching simulator supplies pressure system, control actuating system, signal indication system four bibliographic categories to divide to form by bearing structure, hydraulic pressure wherein supplies pressure system, control actuating system, signal indication system respectively fixed connection to bearing structure on, hydraulic pressure supplies pressure system for control actuating system provides power, and signal indication system supplies pressure system and control actuating system for hydraulic pressure and provides indicating signal, the utility model discloses receive and release control system with the hydraulic pressure of aircraft and show on the plane of simulation aircraft organism, make the student can clearly see that the system architecture is constituteed and the control principle, make things convenient for the student to learn the operation.
Description
Technical Field
The utility model relates to aircraft system teaching field, especially aircraft hydraulic pressure receive and releases operating system teaching simulator.
Background
In order to meet the actual requirements of practical teaching and enable a student to visually know and master the composition, installation and debugging principle method of hydraulic system components, so as to achieve a better learning purpose, the student is required to have a physical object capable of being operated and exercised in person, but in the actual physical object of the airplane, all systems of the airplane are often interwoven together, the hydraulic system of the airplane is complex, the assembly of a conduit and the components is overlapped with other systems, the hydraulic system components cannot be visually displayed to the student, the physical object is large and limited by places, even if the physical object of the airplane is reached, the risk of damaging the physical object exists due to too many people, and the maintenance cost is improved.
Therefore, in order to enable students to know the structural composition and the control principle of the hydraulic retraction control system of the airplane more clearly, the teaching simulator is designed, and the teaching simulator can be operated simply, conveniently and visually display the principle of the hydraulic system to meet the actual teaching requirements.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft hydraulic pressure receive and releases operating system teaching simulator can show whole hydraulic pressure receive and releases operating system on a plane, makes the composition, installation and the debugging method that students can audio-visual understanding and grasp the hydraulic system part to reach better teaching purpose.
In order to achieve the above purpose, the following technical scheme is provided:
aircraft hydraulic pressure receive and releases control system teaching simulator supplies pressure system, control actuating system, signal indication system four bibliographic categories to constitute by bearing structure, hydraulic pressure supply pressure system, control actuating system, signal indication system respectively fixed connection on bearing structure, signal indication system supplies pressure system and control actuating system with hydraulic pressure respectively and is connected, hydraulic pressure supplies pressure system and controls actuating system and is connected, bearing structure includes support frame, panel, universal wheelset, the panel is one side of a rectangular flat board and fixed connection to support frame, the support frame is the right triangle support body, and its bottom fixedly connected with universal wheelset, universal wheelset includes four universal wheels, four universal wheels are fixed connection in the bottom four corners of support frame respectively, control actuating system is by undercarriage electromagnetic switch, flap electromagnetic switch, signal indication system four bibliographic categories, and the signal indication system is divided into, The landing gear actuator group comprises two landing gear actuator cylinders, the end parts of the two landing gear actuator cylinders are respectively and fixedly connected with one landing gear, the flap electromagnetic switch is connected with the flap actuator cylinder, the flap actuator cylinder is fixedly connected with one end of the second rocker arm, the other end of the second rocker arm is hinged with the upper part of the flap, the flap is a rectangular flat plate, and the speed reduction plate electromagnetic switch is connected with the speed reduction plate actuator cylinder, the utility model provides a novel gear train, including speed reduction board actuator cylinder, rocking arm one, the other end of rocking arm one is articulated with the upper portion of speed reduction board, the speed reduction board is a rectangular flat board, signal indication system is by signal box, undercarriage receive and release switch, speed reduction board receive and release switch, flap receive and release switch, total power receive and release switch, power indicator, voltmeter, terminal gate group, accumulator manometer, supply to press manometer, return pressure gauge to constitute, the signal box is the box of cuboid and fixed connection in the lower part of panel, undercarriage receive and release switch, speed reduction board receive and release switch, flap receive and release switch, total power receive and release switch are one row of interval fixed connection in the lower part of signal box, power indicator fixed connection in the lower part of signal box and be located flap receive and release switch's top, voltmeter, accumulator manometer, pressure gauge, supply to press manometer, The oil return manometer is one row of interval fixed connection in the upper portion of signal case, the voltmeter is connected with the main circuit, the terminal electric door group includes six terminal electric doors, the equal fixed connection of six terminal electric doors is on the plane of panel, and all connects in parallel with the main circuit, hydraulic pressure supplies the pressure system to strain one, oil by hydraulic motor, oil and strains two, hydraulic tank, check valve, hydraulic safety valve and constitute, hydraulic motor, oil strain one, hydraulic tank, oil strain two, hydraulic safety valve, check valve form one in proper order end to end and supply the pressure return circuit.
Preferably, the landing gear electromagnetic switch, the flap electromagnetic switch and the electric control connecting part of the speed reducing plate electromagnetic switch are all connected in parallel to the main circuit.
Preferably, the left side of the first rocker arm is movably connected with a terminal electric door, the left side of the second rocker arm is movably connected with a terminal electric door, the upper portion of the undercarriage on the left side is movably connected with a terminal electric door, the upper portion of the undercarriage on the right side is movably connected with a terminal electric door, and two terminal electric doors are further arranged between the two undercarriages.
Preferably, two lines of the landing gear electromagnetic switch and the landing gear actuator cylinder are respectively provided with a current-limiting valve, two lines of the flap electromagnetic switch and the flap actuator cylinder are respectively provided with a current-limiting valve, and two lines of the speed reduction plate electromagnetic switch and the speed reduction plate actuator cylinder are respectively provided with a current-limiting valve.
Preferably, the hydraulic connection parts of the landing gear electromagnetic switch, the flap electromagnetic switch and the speed reducing plate electromagnetic switch are all connected in parallel on the pressure supply circuit.
Preferably, the speed reducing plate electromagnetic switch is further connected with a pressure accumulator, one end of the pressure accumulator is divided into two branches which are respectively connected with the speed reducing plate electromagnetic switch and a hydraulic system safety valve, and the other end of the pressure accumulator is connected with a pressure accumulator pressure gauge.
Preferably, the oil return line of the pressure supply loop is divided into a branch which is connected with an oil return pressure gauge, and the pressure supply line of the pressure supply loop is divided into a branch which is sequentially connected with a current limiting valve and the pressure supply pressure gauge.
The utility model has the advantages that:
1. the utility model discloses a take out whole aircraft hydraulic pressure receive and release operating system alone, show on a plane, make the structural component and the control principle of this system of understanding that the student can surveyability, easy operation is convenient moreover.
2. The utility model discloses occupation space is little, and convenient the removal has improved the convenient degree of teaching moreover.
3. The utility model discloses low in cost practices thrift the cost.
Drawings
Fig. 1 is a front view of the present invention;
fig. 2 is a left side view of the present invention;
the reference symbols shown in the figures are: 1-a support frame, 2-a panel, 3-universal wheels, 4-a landing gear electromagnetic switch, 5-a flap electromagnetic switch, 6-a speed reducing plate electromagnetic switch, 7-a speed reducing plate actuator cylinder, 8-a flap actuator cylinder, 9-a landing gear, 10-a speed reducing plate, 11-a flap, 12-a rocker one, 13-a rocker two, 14-a landing gear actuator cylinder, 15-a signal box, 16-a landing gear retraction switch, 17-a speed reducing plate retraction switch, 18-a flap retraction switch, 19-a main power switch, 20-a power indicator lamp, 21-a voltmeter, 22-an accumulator manometer, 23-a pressure supply manometer, 24-an oil return manometer, 25-a terminal electric door, 26-a main circuit and 27-a hydraulic motor, 28-oil filter I, 29-oil filter II, 30-hydraulic oil tank, 31-check valve, 32-hydraulic safety valve, 33-check valve and 34-pressure accumulator.
Detailed Description
The following describes the present design in detail with reference to the accompanying drawings.
As shown in fig. 1-2, the teaching simulator for the hydraulic retraction control system of an airplane comprises a supporting structure, a hydraulic pressure supply system, a control action system and a signal indication system, wherein the hydraulic pressure supply system, the control action system and the signal indication system are respectively and fixedly connected to the supporting structure, the signal indication system is respectively connected with the hydraulic pressure supply system and the control action system, the hydraulic pressure supply system is connected with the control action system, the supporting structure comprises a supporting frame 1, a panel 2 and a universal wheel set, wherein the panel 2 is a rectangular flat plate and is fixedly connected to one side of the supporting frame 1, the supporting frame 1 is a right-angled triangle frame body, the bottom of the supporting frame is fixedly connected with the universal wheel set, the universal wheel set comprises four universal wheels 3, the four universal wheels 3 are respectively and fixedly connected to four corners of the bottom of the supporting frame 1, and the control action system, A flap electromagnetic switch 5, a speed reducing plate electromagnetic switch 6, a landing gear actuator group, a speed reducing plate actuator cylinder 7, a flap actuator cylinder 8, an undercarriage 9, a speed reducing plate 10, a flap 11, a rocker arm I12 and a rocker arm II 13, wherein the landing gear electromagnetic switch 4, the flap electromagnetic switch 5, the speed reducing plate electromagnetic switch 6, the landing gear actuator group, the speed reducing plate actuator cylinder 7 and the flap actuator cylinder 8 are all fixedly connected on the plane of a panel, the landing gear electromagnetic switch 4 is connected with the landing gear actuator group, the landing gear actuator group comprises two landing gear actuator cylinders 14, the end parts of the two landing gear actuator cylinders 14 are respectively and fixedly connected with one undercarriage 9, the flap electromagnetic switch 5 is connected with the flap actuator cylinder 8, the flap actuator cylinder 8 is fixedly connected with one end of the rocker arm II 13, the other end of the rocker arm II 13 is hinged with the upper part of the flap 11, and the flap 11 is, the speed reducing plate electromagnetic switch 6 is connected with the speed reducing plate actuator cylinder 7, the speed reducing plate actuator cylinder 7 is fixedly connected with one end of a rocker arm I12, the other end of the rocker arm I12 is hinged with the upper part of the speed reducing plate 10, the speed reducing plate 10 is a rectangular flat plate, a signal indicating system comprises a signal box 15, an undercarriage retracting switch 16, a speed reducing plate retracting switch 17, a flap retracting switch 18, a main power supply retracting switch 19, a power indicator lamp 20, a voltmeter 21, a terminal electric door group, an accumulator pressure gauge 22, a pressure supply pressure gauge 23 and an oil return pressure gauge 24, the signal box 15 is a cuboid box body and is fixedly connected to the lower part of the panel 2, the undercarriage retracting switch 16, the speed reducing plate retracting switch 17, the flap retracting switch 18 and the main power supply retracting switch 19 are fixedly connected to the lower part of the signal box 15 at intervals, the power indicator lamp 20 is fixedly connected to the lower part of the signal box 15 and is, voltmeter 21, accumulator manometer 22, supply pressure manometer 23, oil return manometer 24 is one row of interval fixed connection in the upper portion of signal case 15, voltmeter 21 is connected with main circuit 26, the terminal electric door group includes six terminal electric doors 25, six terminal electric doors 25 all fixed connection are on the plane of panel 2, and all connect in parallel with main circuit 26, hydraulic pressure supplies the pressure system by hydraulic motor 27, oil is strained one 28, oil is strained two 29, hydraulic tank 30, check valve 31, hydraulic safety valve 32 is constituteed, hydraulic motor 27, oil is strained one 28, hydraulic tank 30, oil is strained two 29, hydraulic safety valve 32, check valve 31 forms a pressure supply return circuit end to end in proper order.
The landing gear electromagnetic switch 4, the flap electromagnetic switch 5 and the electric control connection part of the speed reducing plate electromagnetic switch 6 are all connected in parallel on the main circuit 26.
The left side of the first rocker arm 12 is movably connected with a terminal electric door 25, the left side of the second rocker arm 13 is movably connected with a terminal electric door 25, the upper portion of the landing gear 9 on the left side is movably connected with the terminal electric door 25, the upper portion of the landing gear 9 on the right side is movably connected with the terminal electric door 25, and two terminal electric doors 25 are further arranged between the two landing gears 9.
Wherein, two lines of the landing gear electromagnetic switch 4 connected with the landing gear actuator cylinder 14 are respectively provided with a current-limiting valve 33, two lines of the flap electromagnetic switch 5 connected with the flap actuator cylinder 8 are respectively provided with a current-limiting valve 33, and two lines of the speed reduction plate electromagnetic switch 6 connected with the speed reduction plate actuator cylinder 7 are respectively provided with a current-limiting valve 33.
The hydraulic connection parts of the landing gear electromagnetic switch 4, the flap electromagnetic switch 5 and the speed reducing plate electromagnetic switch 6 are all connected in parallel on the pressure supply loop.
The speed reducing plate electromagnetic switch 6 is further connected with a pressure accumulator 34, one end of the pressure accumulator 34 is divided into two branches which are respectively connected with the speed reducing plate electromagnetic switch 6 and the hydraulic system safety valve 32, and the other end of the pressure accumulator is connected with the pressure gauge 22 of the pressure accumulator.
Wherein, the oil return line of the pressure supply loop is divided into a branch to be connected with the oil return pressure gauge 24, and the pressure supply line of the pressure supply loop is divided into a branch to be sequentially connected with a current-limiting valve 33 and the pressure supply pressure gauge 23.
The hydraulic connection among all parts is realized by adopting an airplane hydraulic conduit.
Examples
As shown in figures 1-2, before use, all parts are connected, a main power switch 19 of a signal box 15 is switched on, a power indicator lamp 20 is turned on, a hydraulic motor 27 is turned on to supply pressure to the system, hydraulic oil sequentially passes through the hydraulic motor 27, an oil filter I28, a hydraulic oil tank 30, an oil filter II 29, a hydraulic safety valve 32 and a one-way valve 31 to form a pressure supply loop, and pressure is accumulated to 100kgf/cm through an accumulator 342The undercarriage control switch 16 is operated, the undercarriage electromagnetic switch 4 is started, pressure is supplied to the undercarriage actuator cylinder 14, the undercarriage actuator cylinder 14 drives the undercarriage 9 to move, the two undercarriages 9 are retracted inwards until the undercarriage 9 abuts against the end switch 25 between the two undercarriages 9 respectively, the movement is stopped, the speed reduction plate control switch 17 is operated, the speed reduction plate electromagnetic switch 6 is started, pressure is supplied to the speed reduction plate actuator cylinder 7, the speed reduction plate actuator cylinder 7 drives the rocker arm I12 to move, the speed reduction plate 10 is opened, similarly, the flap control switch 18 is operated, the flap electromagnetic switch 5 is started, pressure is supplied to the flap actuator cylinder 8, and the flap is actuatedThe barrel 8 drives the second rocker arm 13 to move, so that the flap 11 is opened, when the undercarriage 9, the speed reduction plate 10 and the flap 11 need to return to the original positions, the corresponding switches are closed, the pressure suddenly drops, the first rocker arm 12, the second rocker arm 13 and the undercarriage 9 respectively contact the end point electric door 25 at the original positions, and the movement stops.
Claims (7)
1. Aircraft hydraulic pressure receive and releases control system teaching simulator, its characterized in that supplies pressure system, control actuating system, signal indication system four bibliographic categories to constitute by bearing structure, hydraulic pressure supplies pressure system, control actuating system, signal indication system respectively fixed connection to bearing structure on, signal indication system supplies pressure system and control actuating system with hydraulic pressure respectively to be connected, hydraulic pressure supplies pressure system and controls actuating system to be connected, bearing structure includes support frame, panel, universal wheelset, the panel is one side of a rectangular flat board and fixed connection to support frame, the support frame is the right angled triangle support body, and its bottom fixedly connected with universal wheelset, universal wheelset includes four universal wheels, four universal wheels are fixed connection in the bottom four corners of support frame respectively, it is by undercarriage electromagnetic switch, the control actuating system, The landing gear electromagnetic switch, the flap electromagnetic switch, the speed reducing plate electromagnetic switch, the landing gear actuator cylinder group, the speed reducing plate actuator cylinder, the flap actuator cylinder, the landing gear, the speed reducing plate, the flap, the first rocker arm and the second rocker arm are all fixedly connected to the plane of the panel, the landing gear electromagnetic switch is connected with the landing gear actuator cylinder group, the landing gear actuator cylinder group comprises two landing gear actuator cylinders, the end portions of the two landing gear actuator cylinders are respectively and fixedly connected with one landing gear, the flap electromagnetic switch is connected with the flap actuator cylinder, the flap actuator cylinder is fixedly connected with one end of the second rocker arm, the other end of the second rocker arm is hinged with the upper portion of the flap, the flap is a rectangular flat plate, and the speed reducing plate electromagnetic switch is connected with the speed reducing plate actuator cylinder, the utility model provides a novel gear train, including speed reduction board actuator cylinder, rocking arm one, the other end of rocking arm one is articulated with the upper portion of speed reduction board, the speed reduction board is a rectangular flat board, signal indication system is by signal box, undercarriage receive and release switch, speed reduction board receive and release switch, flap receive and release switch, total power receive and release switch, power indicator, voltmeter, terminal gate group, accumulator manometer, supply to press manometer, return pressure gauge to constitute, the signal box is the box of cuboid and fixed connection in the lower part of panel, undercarriage receive and release switch, speed reduction board receive and release switch, flap receive and release switch, total power receive and release switch are one row of interval fixed connection in the lower part of signal box, power indicator fixed connection in the lower part of signal box and be located flap receive and release switch's top, voltmeter, accumulator manometer, pressure gauge, supply to press manometer, The oil return manometer is one row of interval fixed connection in the upper portion of signal case, the voltmeter is connected with the main circuit, the terminal electric door group includes six terminal electric doors, the equal fixed connection of six terminal electric doors is on the plane of panel, and all connects in parallel with the main circuit, hydraulic pressure supplies the pressure system to strain one, oil by hydraulic motor, oil and strains two, hydraulic tank, check valve, hydraulic safety valve and constitute, hydraulic motor, oil strain one, hydraulic tank, oil strain two, hydraulic safety valve, check valve form one in proper order end to end and supply the pressure return circuit.
2. The teaching simulator of an aircraft hydraulic retraction control system according to claim 1, wherein the electrically controlled connection parts of the landing gear electromagnetic switch, the flap electromagnetic switch and the speed reduction plate electromagnetic switch are all connected in parallel to the main circuit.
3. The teaching simulator of the hydraulic retraction control system of the aircraft according to claim 1, wherein a terminal electric door is movably connected to the left side of the first rocker arm, a terminal electric door is movably connected to the left side of the second rocker arm, a terminal electric door is movably connected to the upper portion of the landing gear on the left side, a terminal electric door is movably connected to the upper portion of the landing gear on the right side, and two terminal electric doors are further arranged between the two landing gears.
4. The teaching simulator of the hydraulic retraction control system of the airplane as claimed in claim 1, wherein the landing gear electromagnetic switch is provided with a current limiting valve on each of two lines connecting the landing gear actuator, the flap electromagnetic switch is provided with a current limiting valve on each of two lines connecting the flap actuator, and the speed reduction plate electromagnetic switch is provided with a current limiting valve on each of two lines connecting the speed reduction plate actuator.
5. The teaching simulator of an aircraft hydraulic retraction control system according to claim 1, wherein the hydraulic connections of the landing gear electromagnetic switch, the flap electromagnetic switch and the speed reduction plate electromagnetic switch are all connected in parallel to the pressure supply circuit.
6. The teaching simulator of the hydraulic retraction control system of the airplane as claimed in claim 1, wherein the electromagnetic switch of the speed reduction plate is further connected with a pressure accumulator, one end of the pressure accumulator is divided into two branches which are respectively connected with the electromagnetic switch of the speed reduction plate and a safety valve of the hydraulic system, and the other end of the pressure accumulator is connected with a pressure gauge of the pressure accumulator.
7. The aircraft hydraulic retraction control system teaching simulator of claim 1,
the oil return line that supplies to press the return circuit divides a branch road to be connected with oil return manometer, the confession that supplies to press the return circuit divides a branch road to be connected with a current-limiting valve and supply to press the manometer in proper order.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022045082.5U CN213277171U (en) | 2020-09-17 | 2020-09-17 | Teaching simulator of airplane hydraulic retraction control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022045082.5U CN213277171U (en) | 2020-09-17 | 2020-09-17 | Teaching simulator of airplane hydraulic retraction control system |
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| Publication Number | Publication Date |
|---|---|
| CN213277171U true CN213277171U (en) | 2021-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022045082.5U Active CN213277171U (en) | 2020-09-17 | 2020-09-17 | Teaching simulator of airplane hydraulic retraction control system |
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|---|---|
| CN (1) | CN213277171U (en) |
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2020
- 2020-09-17 CN CN202022045082.5U patent/CN213277171U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230805 Address after: No. FFZ04, New Office of Jihang Maintenance Fleet, Shuangji Street, Changyi District, Jilin City, 132000 Jilin Province Patentee after: Jilin Hangxiu Enterprise Management Co.,Ltd. Address before: 132000 no.3-12-76 Shuangji street, Changyi District, Jilin City, Jilin Province Patentee before: Liu Zhihong |
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| TR01 | Transfer of patent right |