CN209037879U - One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig - Google Patents
One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig Download PDFInfo
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- CN209037879U CN209037879U CN201821589591.0U CN201821589591U CN209037879U CN 209037879 U CN209037879 U CN 209037879U CN 201821589591 U CN201821589591 U CN 201821589591U CN 209037879 U CN209037879 U CN 209037879U
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Abstract
The present apparatus belongs to Aviation Test device field, is related to one kind for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig, for realizing auxiliary tank of aircraft flight environment of vehicle and attitude-simulating.The application passes through the combination of air pump, air accumulator, vacuum tank and auxiliary fuel tank, and the pressure of servo valve regulation auxiliary fuel tank is adjusted by TT&C system, to simulate auxiliary fuel tank flight pressure environment；Auxiliary fuel tank state is adjusted by servo motor, makes auxiliary fuel tank around drive shaft turns, and revolute is set on the driving shaft, to simulate auxiliary fuel tank flight attitude, be can be realized to auxiliary tank of aircraft environmental pressure and attitude angle simulation, had the characteristics that easily operated and use.
Description
Technical field
The application belongs to Aviation Test device field, in particular to a kind of to be used for auxiliary tank of aircraft flight environment of vehicle and posture mould
Quasi- experimental rig.
Background technique
Auxiliary tank of aircraft flight environment of vehicle and attitude-simulating are that aircraft fuel system tests important component part, and previous flies
Auxiliary tank of aircraft is mostly installed in large-scale test-bed through hydraulic cylinder or electricity by machine auxiliary fuel tank flight environment of vehicle and attitude-simulating
Dynamic cylinder driving rack realizes flight environment of vehicle and attitude-simulating, and this experiment simulator system is cumbersome, and required testing stand is built
If capital quantity is larger.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided one kind to be used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig for the purpose of the application, can
Conveniently realize auxiliary tank of aircraft flight environment of vehicle and attitude-simulating.
The technical solution of the application is:
One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig, comprising:
Auxiliary fuel tank is suspended on auxiliary fuel tank connecting plate by drive shaft, and auxiliary fuel tank can be around drive shaft turns, and auxiliary fuel tank is also
It is provided with oiling pipeline；
Revolute, setting on the driving shaft, can be provided with angular transducer in revolute with drive shaft turns；
The drive shaft of servo motor, servo motor is connect by gear and rack gear with auxiliary fuel tank；
Vacuum tank is connected to by steam hose road with auxiliary fuel tank, and vacuum tank is provided with exhaust outlet, the row of being provided on exhaust outlet
Controlled atmosphere section servo valve is additionally provided with pressure sensor on vacuum tank；
Air accumulator is connected to by the first ventilation pipe with vacuum tank, and air inflow adjusting is provided on the first ventilation pipe and is watched
Valve is taken, is additionally provided with pressure sensor on air accumulator；
Air pump is connected on air accumulator by the second ventilation pipe, and ventilation pipe is provided with check valve；
TT&C system, TT&C system are used to receive the data of processing angular transducer, pressure sensor and pressure sensor
And control exhaust adjusts servo valve, air inflow adjusts servo valve servo motor state.
Optionally, reduction gearbox band self-locking mechanism is additionally provided in the drive shaft of servo motor.
Optionally, safety valve is additionally provided on air accumulator.
Optionally, pressure sensor is additionally provided on auxiliary fuel tank, pressure sensor is connect with TT&C system.
Optionally, further includes:
Truss, including two parallel support plates and the crossbeam being horizontally set between two parallel support plates, auxiliary fuel tank connection
Plate is fixed on crossbeam.
Optionally, servo motor is fixed in the support plate of truss.
At least there are following advantageous effects in the application:
The application passes through the combination of air pump, air accumulator, vacuum tank and auxiliary fuel tank, and adjusts servo valve by TT&C system
The pressure of auxiliary fuel tank is adjusted, to simulate auxiliary fuel tank flight pressure environment；Auxiliary fuel tank state is adjusted by servo motor, makes auxiliary fuel tank
Around drive shaft turns, and revolute is set on the driving shaft, to simulate auxiliary fuel tank flight attitude, can be realized to auxiliary tank of aircraft
Environmental pressure and attitude angle simulation, have the characteristics that easily operated and use.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the application experimental rig.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without making creative work, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 couple of the application is described in further details with reference to the accompanying drawing.
The application includes auxiliary fuel tank 15, revolute 7, watches for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig
Take motor 11, vacuum tank 4, air accumulator 2, air pump 1 and TT&C system 16.
Specifically, auxiliary fuel tank 15 is suspended on auxiliary fuel tank connecting plate 14 by drive shaft, and auxiliary fuel tank 15 can be around drive shaft
Rotation, auxiliary fuel tank 15 are additionally provided with oiling pipeline, are provided with valve on oiling pipeline.
Further, pressure sensor p3 is additionally provided on auxiliary fuel tank 15, pressure sensor p3 is connect with TT&C system 16, is used
Air pressure in test auxiliary fuel tank 15.
Revolute 7 is arranged on the driving shaft, can be additionally provided with angular transducer 8 with drive shaft turns, revolute 7；
It is additionally provided with reduction gearbox band self-locking mechanism 12 in the drive shaft of servo motor 11, and passes through gear 13 and rack gear 10
It connect, is used for so that auxiliary fuel tank 15 is around drive shaft turns with auxiliary fuel tank 15.
Vacuum tank 4 is connected to by steam hose road 9 with auxiliary fuel tank 15, and vacuum tank 4 is provided with exhaust outlet, sets on exhaust outlet
It is equipped with exhaust and adjusts servo valve 5, pressure sensor p2 is additionally provided on vacuum tank 4, vacuum tank 4 is for balancing in auxiliary fuel tank 15
Air pressure；
Air accumulator 2 is connected to vacuum tank 4 by the first ventilation pipe 21, is provided with air inflow on the first ventilation pipe 21
Servo valve 3 is adjusted, pressure sensor p1 is additionally provided on air accumulator 2, also, be additionally provided with safety valve on air accumulator 2, for protecting
Card.
Air pump 1 is connected on air accumulator 2 by the second ventilation pipe 22, and ventilation pipe 22 is provided with check valve, to protect
Card airflow direction is only air pump 1 to air accumulator 2, and air pump 1 is used to inflate to air accumulator 2, so that keeping higher in air accumulator 2
Air pressure.
TT&C system 16, for issuing control command and collecting test data, TT&C system 16 is adjusted with exhaust respectively
Servo valve 5, air inflow adjust servo valve 3, angular transducer 8, servo motor 11, pressure sensor p1 and pressure sensor p2 and connect
It connects, TT&C system 16 is used to receive the data and control of processing angular transducer 8, pressure sensor p1 and pressure sensor p2
Exhaust adjusts servo valve 5, air inflow adjusts servo valve 3,11 state of servo motor.
TT&C system 16 can obtain pressure sensor p1 measurement 2 pressure of air accumulator and pressure sensor p2 measurement it is steady
4 pressure of tank is pressed, and then air pump 1 is controlled according to the pressure data of acquisition, air inflow adjusts servo valve 3 and is vented adjusting servo valve 5
Switch state, vacuum tank 4 is inflated or is vented, to adjust the air pressure in auxiliary fuel tank 15, is formed to 15 ring of auxiliary fuel tank
The simulation to auxiliary tank of aircraft flight environment of vehicle pressure is realized in the closed-loop control of border pressure；
TT&C system 16 can also obtain 15 flight attitude of auxiliary fuel tank by angular transducer 8, and be flown according to auxiliary fuel tank 15
Row gesture stability servo motor 11 acts, by reduction gearbox band self-locking mechanism 12, gear 13 and rack gear 10 so as to adjust auxiliary fuel tank
15 flight attitudes form the closed-loop control to the flight attitude of auxiliary fuel tank 15, realize and simulate to auxiliary tank of aircraft flight attitude.
Further, experimental rig further includes truss 6, and truss 6 includes two parallel support plates and is horizontally set with parallel at two
Crossbeam between support plate, auxiliary fuel tank connecting plate 14 are fixed on crossbeam, being capable of more real simulation auxiliary fuel tank installation condition；It watches
Motor 11 is taken to be fixed in the support plate of truss 6.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (6)
1. one kind is used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig characterized by comprising
Auxiliary fuel tank (15) is suspended on auxiliary fuel tank connecting plate (14) by drive shaft, and the auxiliary fuel tank (15) can be around the drive
Moving axis rotation, the auxiliary fuel tank (15) are additionally provided with oiling pipeline；
Revolute (7) is arranged in the drive shaft, can be additionally provided with angle with the drive shaft turns, the revolute (7)
It spends sensor (8)；
The drive shaft of servo motor (11), the servo motor (11) passes through gear (13) and rack gear (10) and the auxiliary fuel tank
(15) it connects；
Vacuum tank (4) is connected to by steam hose (9) with the auxiliary fuel tank (15), and the vacuum tank (4) is provided with exhaust outlet,
It is provided with exhaust on the exhaust outlet and adjusts servo valve (5), is additionally provided with pressure sensor (p2) on the vacuum tank (4)；
Air accumulator (2) is connected to, on first ventilation pipe (21) with the vacuum tank (4) by the first ventilation pipe (21)
It is provided with air inflow and adjusts servo valve (3), be additionally provided with pressure sensor (p1) on the air accumulator (2)；
Air pump (1) is connected on the air accumulator (2) by the second ventilation pipe (22), and the ventilation pipe (22) is provided with
Check valve；
TT&C system (16), the TT&C system (16) handle the angular transducer (8), pressure sensor (p1) for receiving
Servo valve (5) are adjusted with the data of pressure sensor (p2) and the control exhaust, air inflow adjusts servo valve (3) servo electricity
Machine (11) state.
2. experimental rig according to claim 1, which is characterized in that also set up in the drive shaft of the servo motor (11)
There is reduction gearbox band self-locking mechanism (12).
3. experimental rig according to claim 1, which is characterized in that be additionally provided with safety valve on the air accumulator (2).
4. experimental rig according to claim 1, which is characterized in that be additionally provided with pressure sensing on the auxiliary fuel tank (15)
Device (p3), the pressure sensor (p3) connect with the TT&C system (16).
5. experimental rig according to claim 1, which is characterized in that further include:
Truss (6), including two parallel support plates and the crossbeam being horizontally set between described two parallel support plates, the secondary oil
Case connecting plate (14) is fixed on the crossbeam.
6. experimental rig according to claim 5, which is characterized in that the servo motor (11) is fixed on the truss
(6) in support plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821589591.0U CN209037879U (en) | 2018-09-28 | 2018-09-28 | One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821589591.0U CN209037879U (en) | 2018-09-28 | 2018-09-28 | One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig |
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| Publication Number | Publication Date |
|---|---|
| CN209037879U true CN209037879U (en) | 2019-06-28 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110793744B (en) * | 2019-12-02 | 2021-04-13 | 中国空气动力研究与发展中心 | Wind tunnel test model suspension joint |
| CN113063597A (en) * | 2021-03-15 | 2021-07-02 | 中国航发沈阳发动机研究所 | System and method for testing attitude characteristic of lubricating oil tank |
| CN114084385A (en) * | 2021-12-28 | 2022-02-25 | 贵州航天乌江机电设备有限责任公司 | Detection platform for aircraft |
-
2018
- 2018-09-28 CN CN201821589591.0U patent/CN209037879U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110793744B (en) * | 2019-12-02 | 2021-04-13 | 中国空气动力研究与发展中心 | Wind tunnel test model suspension joint |
| CN113063597A (en) * | 2021-03-15 | 2021-07-02 | 中国航发沈阳发动机研究所 | System and method for testing attitude characteristic of lubricating oil tank |
| CN114084385A (en) * | 2021-12-28 | 2022-02-25 | 贵州航天乌江机电设备有限责任公司 | Detection platform for aircraft |
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