CN106644466A - Simulation testing device used for air vehicle rudder transmission mechanism - Google Patents
Simulation testing device used for air vehicle rudder transmission mechanism Download PDFInfo
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- CN106644466A CN106644466A CN201611136019.4A CN201611136019A CN106644466A CN 106644466 A CN106644466 A CN 106644466A CN 201611136019 A CN201611136019 A CN 201611136019A CN 106644466 A CN106644466 A CN 106644466A
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- static pressure
- pressure chamber
- test cavity
- transmission mechanism
- test
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
Abstract
The invention discloses a simulation testing device used for an air vehicle rudder transmission mechanism. The simulation testing device provided by the invention is used for simulation testing on performance of the rudder transmission mechanism in a high and low temperature environment. According to the invention, non-vacuum heat insulation material and an inner support are adopted for making a flexible heat insulation cavity. Static pressure cavities are arranged at an inlet and an outlet of a flexible non-vacuum environment test cavity, so that high temperature nitrogen and low temperature nitrogen flow into the flexible non-vacuum environment test cavity uniformly. In the flexible non-vacuum environment test cavity, uniform high temperature simulation environment or low temperature simulation environment are realized. A loading test device is mounted outside the flexible non-vacuum environment test cavity and a sealing film box structure is mounted in the flexible non-vacuum environment test cavity. A hydraulic pressure motor drives a loading connection rod to cooperate with movement of a control surface to be detected. At the same time, sealing treatment is performed between the connection rod and the flexible non-vacuum environment test cavity, so that heat insulation performance of the cavity is improved. The simulation testing device is simple in structure, and reduces testing cost and improves space utilization rate.
Description
Technical field
The invention belongs to aircraft ground test and field tests, specifically, it is related to a kind of for aerospace craft
The ground simulation test device of performance test is carried out to rudder transmission mechanism in high and low temperature environment.
Background technology
Aerospace craft is that one kind can fly in endoatmosphere, also can be in the aircraft of extra-atmospheric flight.Except
To be subjected in space environment outside severe temperature environment, during reentering across atmosphere and return, even more to experience
The high temperature of thousands of degree and temperature change rapidly, highest can be to 1800 DEG C.So in aerospace craft research with design process,
Reliably and effectively ground simulation humid test is very important.Generally ensured using thermal insulation tile made by external application composite
Airborne equipment is operated in suitable temperature, even so, airborne equipment is still in a higher operating temperature.System testing pair
As being mainly rudder face steerable system, under the protection of aerospace craft outer heat shield system, temperature control in internal personnel transport capsule
Generally 25～32 DEG C are required, and the requirement of the airborne equipment of outside and miscellaneous equipment is relatively low, generally:- 50～50 DEG C.
But for the reliability of test, the temperature range for needing test is:- 100～100 DEG C.
(Chinese vacuum association 2012 is academic for existing disclosed technical literature " KM7 large spaces environment simulator develops [C] "
Annual meeting, 2012) in describe a kind of simulator, the simulator is mainly realized high temperature mould by thermal infrared radiation mode
Intend, cold nitrogen system realizes that low temperature is simulated；But cost and experimentation cost are very high, the test need of Large Spacecraft or whole star are met
Ask.Disclose in patent CN104670523 " a kind of high/low temperature environmental simulation testing equipment ", the testing equipment is tried using box type
Environment is tested, for the static test of product, it is impossible to adapt to the testing experiment under product moving situation, and it is big to the size of product
It is little restricted, poor universality.A kind of " cabin in large-scale high-low temperature environment simulation test box is proposed in patent CN104588135
Body structure " the structure realizes a kind of large-scale simulation to solve the test to main equipment using square steel, corrugated sheet, fiberglass
Chamber；Cost is higher, low space utilization, is also limited when the measurement of telecontrol equipment is carried out.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes that a kind of simulation for aircraft rudder transmission mechanism is surveyed
Trial assembly is put；The simulating test device adjusts variable using flexible antivacuum heat-insulating material composition, volume, and space availability ratio is high, right
The strong adaptability of plant bulk, it is adaptable to the high temperature performance test under vehicle rudder machine transmission mechanism motion state.
The technical solution adopted for the present invention to solve the technical problems is:Including test cavity, input static pressure chamber, export quiet
It is pressure chamber, pedestal, tested steering wheel, rudder transmission mechanism, tested rudder face, sealing bellows, loading connecting rod, hydraulic motor, supporting mechanism, solid
Fixed circle, static pressure chamber enclosure, orifice plate, sealing plate, zone circle, adiabatic sealant tape, the test cavity two ends by supporting mechanism and
Input static pressure chamber and exit static pressure chamber connect, and tested steering wheel is connected with tested rudder face by rudder transmission mechanism, and installed in test
On pedestal in chamber, the test cavity bottom positioned at the lower section of tested rudder face is provided with circular hole, for fixed installation sealing bellows, liquid
Pressure motor is located at test cavity lower section and is fixed in mounting seat, connecting rod one end is loaded through the round tube hole of sealing bellows, by ear
Fork is connected on the loaded ring of tested rudder face bottom, and the loading connecting rod other end is connected with hydraulic motor by shaft coupling；
The input static pressure chamber adopts stainless steel cylinder blanket with the exit static pressure chamber, and inside is provided with fiberglass drilling
Plate, uniform some apertures on orifice plate, input static pressure chamber is provided with stainless steel sealing plate and retainer plate with exit static pressure chamber outer end,
Input static pressure chamber outer end is connected with test pipeline and admission line, exit static pressure chamber outer end have outlet conduit, discharge duct,
Outlet test pipeline is connected respectively with micro-pressure sensor, drain tap, gas recovery conduit；
The sealing bellows is the zone circle composition tower structure of diameter gradient increase, and zone circle adopts double-layer polyester fiber bag
Wrap up in, centre is provided with round tube hole, with adiabatic sealant tape sealing between loading connecting rod and round tube hole, sealing bellows is fixed on test cavity
Bottom.
The test cavity is made using multilayer heat insulation paper and aluminized mylar are compound, central filler aeroge.
Beneficial effect
A kind of simulating test device for aircraft rudder transmission mechanism proposed by the present invention.Using it is antivacuum it is adiabatic by with
Flexible thermal insulative test cavity, with certain deformability while profile is kept, can fully coordinate made by the support of inside
The motion requirement of rudder face transmission；Static pressure chamber is set at the entrance and exit of flexible non-vacuum environment test cavity, high temperature nitrogen is made
Or low temperature nitrogen uniformly flows into flexible non-vacuum environment test cavity, inside flexible non-vacuum environment test cavity, realize uniform
High Temperature Simulation environment or low temperature simulated environment；Loading test equipment, Yi Jian are installed for compatibility test chamber simulated environment
Sealing bellows loaded on flexible non-vacuum environment test cavity, while loading equipemtn motion requirement is met, to connecting rod and flexibility
Encapsulation process is carried out between non-vacuum environment test cavity, strengthens the heat-insulating property of test cavity.
The present invention is used for the simulating test device of aircraft rudder transmission mechanism compared with existing large-scale experiment case, adaptability
By force, experimentation cost is reduced, space availability ratio is high.
Description of the drawings
Below in conjunction with the accompanying drawings with embodiment to a kind of simulating test device for aircraft rudder transmission mechanism of the present invention
It is described in further detail.
Fig. 1 is simulating test device upward view of the present invention for aircraft rudder transmission mechanism.
Fig. 2 is simulating test device schematic diagram of the present invention for aircraft rudder transmission mechanism.
Fig. 3 is the input static pressure chamber schematic diagram of simulating test device of the present invention.
Fig. 4 is the input static pressure chamber sectional view of simulating test device of the present invention.
Fig. 5 is the exit static pressure chamber schematic diagram of simulating test device of the present invention.
Fig. 6 is the exit static pressure chamber sectional view of simulating test device of the present invention.
Fig. 7 is the sealing bellows upward view of simulating test device of the present invention.
Fig. 8 is the sealing bellows schematic diagram of simulating test device of the present invention.
In figure:
1. the rudder transmission mechanism of 2. input static pressure chamber of cavity, 3. exit static pressure chamber, 4. 5. tested steering wheel of pedestal 6. is tested
7. the admission line 13. of 11. supporting mechanism of the sealing of tested rudder face 8. bellows 9. loading 10. hydraulic motor of connecting rod 12. is tested
The discharge duct 20. of 18. outlet conduit of pipeline 14. retainer plate, 15. static pressure chamber enclosure, 16. orifice plate, 17. sealing plate 19. goes out
The adiabatic sealant tape of 22. zone circle of mouth test 21. round tube hole of pipeline 23.
Specific embodiment
The present embodiment is a kind of simulating test device for aircraft rudder transmission mechanism.
Simulating test device is used in hot environment or low temperature environment, and to rudder transmission mechanism the simulation of performance test is carried out
Test.Simulating test device makes flexible heat insultating cavity using antivacuum heat-insulating material with internal support；In flexible non-real idle loop
Static pressure chamber is set at the entrance and exit of border test cavity, makes high temperature nitrogen or low temperature nitrogen uniformly flow into flexible non-vacuum environment
Test cavity, inside flexible non-vacuum environment test cavity, realizes uniform High Temperature Simulation environment or low temperature simulated environment；Simulation
Test device simple structure, reduces experimentation cost, and space availability ratio is high.
Refering to Fig. 1～Fig. 8, the present embodiment is used for the simulating test device of aircraft rudder transmission mechanism, by test cavity 1,
Input static pressure chamber 2, exit static pressure chamber 3, pedestal 4, tested steering wheel 5, rudder transmission mechanism 6, tested rudder face 7, sealing bellows 8, loading
Connecting rod 9, hydraulic motor 10, supporting mechanism 11, retainer plate 14, static pressure chamber enclosure 15, orifice plate 16, sealing plate 17, zone circle 22, thermal insulation
Sealant tape 23 and admission line 12, test pipeline 13, outlet conduit 18, discharge duct 19, outlet test pipeline 20, round tube hole
21 compositions；Wherein, test the two ends of cavity 1 to be connected with input static pressure chamber 2 and exit static pressure chamber 3 by supporting mechanism 11, tested rudder
Machine 5 is connected with tested rudder face 7 by rudder transmission mechanism 6, and on the pedestal 4 in test cavity 1；Positioned at tested rudder face 7
The bottom of test cavity 1 of lower section is machined with circular hole, for fixed installation sealing bellows 8.Hydraulic motor 10 is located under test cavity 1
Side is fixed in mounting seat；Loading connecting rod 9 one end is connected to the loading of the bottom of tested rudder face 7 through sealing bellows 8 by ear fork
On ring, the loading other end of connecting rod 9 is connected with hydraulic motor 10 by shaft coupling.
In the present embodiment, test cavity 1 is made using multilayer heat insulation paper and multilayer aluminized mylar are compound, central filler
Aeroge, thermal conductivity is extremely low, realizes antivacuum insulation effect.The inside of test cavity 1 supports good using stainless steel stent and elasticity
Good carbon fiber support composition, keeps the shape of antivacuum flexibility test cavity 1, while adapting to certain deformation demand.
The input static pressure chamber 2 and exit static pressure chamber 3 at test cavity 1 two ends adopts stainless steel cylinder blanket, and inside is provided with
Fiberglass drilling plate 16, uniform some apertures on orifice plate 16 and are provided with not input static pressure chamber 2 with the outer end of exit static pressure chamber 3
Rust steel sealing plate 17, the outer end of input static pressure chamber 2 is connected with test pipeline 13 and admission line 12；The outer end of exit static pressure chamber 3
Have outlet conduit 18, discharge duct 19, outlet test pipeline 20 respectively with micro-pressure sensor, drain tap, gas recovery pipe
Road connects.Retainer plate 14 and static pressure chamber enclosure 15 are used cooperatively.The thickness of circular orifice 16 set in input static pressure chamber 2 as 10cm,
A diameter of 4mm～the 8mm of uniform circular aperture on orifice plate 16, aperture working (finishing) area accounts for the 30～50% of main valve cross-sectional area.
The distance between sealing plate 17 and orifice plate 16 are 10cm～20cm.Static pressure chamber enclosure 15 and the outside cladding thickness of sealing plate 17 are
The superfine glass silk floss insulation of 15mm.
Sealing bellows 8 is the composition tower structure of zone circle 22 of diameter gradient increase, zone circle 22 using multi-layered polyester fiber and
Wrap up after sheathing paper is compound, and be combined by note with the antivacuum thermal insulation of test cavity 1.It is logical circle to be provided with the middle of sealing bellows 8
Hole 21, loading connecting rod 9 is passed through from round tube hole 21, is sealed with adiabatic sealant tape 24 between loading connecting rod 9 and round tube hole 21, and can
Realize stretching, Bending Deformation state.Sealing bellows 8 is fixed on the bottom of test cavity 1.
In the present embodiment, the volume and profile for testing cavity 1 can be according to pedestal 4, tested steering wheel 5, rudder transmission mechanism 6 and quilt
The physical model for surveying rudder face 7 is adjusted flexibly.Supporting construction 11 is made up of stainless steel stent and Elastic Carbon fiber, can kept
On the premise of cavity profile, flexibility characteristics are kept, coordinate the motion state of tested device.By being passed through height to input static pressure chamber 2
The high pure nitrogen of temperature or low temperature, and optimization is passed through the flow and temperature of gas, can test uniform simulated normal pressure height in cavity 1
Warm environment or low temperature environment, temperature range is -100～100 DEG C, to meet the environmental simulation demand of tested mechanism.Gas via
Exit static pressure chamber 2 is discharged and is reclaimed, and after heat temperature raising or heat exchange refrigeration experimental rig is passed through again.Improve gas and energy
Amount utilization rate, reduces experimentation cost.When testing tested device, then simulated implementation high and low temperature environment first controls quilt
Surveying steering wheel 5 makes rudder transmission mechanism 6 and tested rudder face 7 according to instruction motion, and control hydraulic motor 10 applies negative on tested rudder face 7
Simulation is carried, the performance test of whole rudder transmission mechanism is completed.
Claims (2)
1. a kind of simulating test device for aircraft rudder transmission mechanism, it is characterised in that:Including test cavity, input static pressure
Chamber, exit static pressure chamber, pedestal, tested steering wheel, rudder transmission mechanism, tested rudder face, sealing bellows, loading connecting rod, hydraulic motor,
Support mechanism, retainer plate, static pressure chamber enclosure, orifice plate, sealing plate, zone circle, adiabatic sealant tape, the test cavity two ends are by propping up
Support mechanism is connected with input static pressure chamber and exit static pressure chamber, and tested steering wheel is connected with tested rudder face by rudder transmission mechanism, and is pacified
It is mounted on the pedestal in test cavity, the test cavity bottom positioned at the lower section of tested rudder face is provided with circular hole, close for fixedly mounting
Sealer box, hydraulic motor is located at test cavity lower section and is fixed in mounting seat, loads connecting rod one end and leads to through the circle of sealing bellows
Hole, is connected on the loaded ring of tested rudder face bottom by ear fork, and the loading connecting rod other end is connected with hydraulic motor by shaft coupling
Connect；
The input static pressure chamber adopts stainless steel cylinder blanket, inside to be provided with fiberglass drilling plate with the exit static pressure chamber,
Uniform some apertures on orifice plate, input static pressure chamber is provided with stainless steel sealing plate and retainer plate with exit static pressure chamber outer end, enters
Mouth static pressure chamber outer end is connected with test pipeline and admission line, and there are outlet conduit, discharge duct in exit static pressure chamber outer end, go out
Mouth test pipeline is connected respectively with micro-pressure sensor, drain tap, gas recovery conduit；
The sealing bellows is the zone circle composition tower structure of diameter gradient increase, and zone circle adopts double-layer polyester fibers encapsulation, in
Between be provided with round tube hole, with adiabatic sealant tape sealing between loading connecting rod and round tube hole, sealing bellows is fixed on test cavity bottom.
2. the simulating test device for aircraft rudder transmission mechanism according to claim 1, it is characterised in that:The examination
Test cavity to make using multilayer heat insulation paper and aluminized mylar are compound, central filler aeroge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611136019.4A CN106644466B (en) | 2016-12-12 | 2016-12-12 | A kind of simulating test device for aircraft rudder transmission mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611136019.4A CN106644466B (en) | 2016-12-12 | 2016-12-12 | A kind of simulating test device for aircraft rudder transmission mechanism |
Publications (2)
| Publication Number | Publication Date |
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| CN106644466A true CN106644466A (en) | 2017-05-10 |
| CN106644466B CN106644466B (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611136019.4A Expired - Fee Related CN106644466B (en) | 2016-12-12 | 2016-12-12 | A kind of simulating test device for aircraft rudder transmission mechanism |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111397830A (en) * | 2020-03-02 | 2020-07-10 | 北京空天技术研究所 | Wind tunnel examination device of sealed heat-proof structure |
| CN113607403A (en) * | 2021-09-06 | 2021-11-05 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4419730A (en) * | 1980-02-18 | 1983-12-06 | Nippondenso Co., Ltd. | Method and system for controlling the setting temperature of a vehicle air conditioner |
| CN201126403Y (en) * | 2007-12-12 | 2008-10-01 | 沙市久隆汽车动力转向器有限公司 | High and low temperature test apparatus for power steering gear |
| CN103341375A (en) * | 2013-06-18 | 2013-10-09 | 上海宇航系统工程研究所 | High and low temperature environment simulation experiment system |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN103691500A (en) * | 2013-12-25 | 2014-04-02 | 上海交通大学 | Simulation system for high-low-temperature environment of controlled flexible cavity body |
| CN203616154U (en) * | 2013-12-04 | 2014-05-28 | 中国航空工业第六一八研究所 | Aircraft steering engine temperature testing device |
| CN104588135A (en) * | 2013-10-30 | 2015-05-06 | 上海交通大学 | An inner cabin structure of a large-scale high- and low-temperature environment simulation test chamber |
| CN204439326U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | A kind of test rudder face actuator simulator |
-
2016
- 2016-12-12 CN CN201611136019.4A patent/CN106644466B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4419730A (en) * | 1980-02-18 | 1983-12-06 | Nippondenso Co., Ltd. | Method and system for controlling the setting temperature of a vehicle air conditioner |
| CN201126403Y (en) * | 2007-12-12 | 2008-10-01 | 沙市久隆汽车动力转向器有限公司 | High and low temperature test apparatus for power steering gear |
| CN103341375A (en) * | 2013-06-18 | 2013-10-09 | 上海宇航系统工程研究所 | High and low temperature environment simulation experiment system |
| CN103542997A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment |
| CN104588135A (en) * | 2013-10-30 | 2015-05-06 | 上海交通大学 | An inner cabin structure of a large-scale high- and low-temperature environment simulation test chamber |
| CN203616154U (en) * | 2013-12-04 | 2014-05-28 | 中国航空工业第六一八研究所 | Aircraft steering engine temperature testing device |
| CN103691500A (en) * | 2013-12-25 | 2014-04-02 | 上海交通大学 | Simulation system for high-low-temperature environment of controlled flexible cavity body |
| CN204439326U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | A kind of test rudder face actuator simulator |
Non-Patent Citations (2)
| Title |
|---|
| 孙培杰等: "空间对接综合试验台温度环境模拟系统及其温场特性", 《上海交通大学学报》 * |
| 杨偲婵等: "非真空条件下柔性多层材料高低温绝热性能实验测量", 《低温工程》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111397830A (en) * | 2020-03-02 | 2020-07-10 | 北京空天技术研究所 | Wind tunnel examination device of sealed heat-proof structure |
| CN113607403A (en) * | 2021-09-06 | 2021-11-05 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
| CN113607403B (en) * | 2021-09-06 | 2022-04-29 | 北京空间机电研究所 | Height-adjustable spacecraft storage box simulation loading static test device and method |
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