CN106644466B - A kind of simulating test device for aircraft rudder transmission mechanism - Google Patents
A kind of simulating test device for aircraft rudder transmission mechanism Download PDFInfo
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- CN106644466B CN106644466B CN201611136019.4A CN201611136019A CN106644466B CN 106644466 B CN106644466 B CN 106644466B CN 201611136019 A CN201611136019 A CN 201611136019A CN 106644466 B CN106644466 B CN 106644466B
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- pressure chamber
- static pressure
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- transmission mechanism
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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
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- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a kind of simulating test devices for aircraft rudder transmission mechanism, for carrying out simulation test to the performance of rudder transmission mechanism in high and low temperature environment；Flexible heat insultating cavity is made using antivacuum heat-insulating material and internal support in simulating test device；Static pressure chamber is set at the entrance and exit of flexible non-vacuum environment test cavity, high temperature nitrogen and low temperature nitrogen is set uniformly to flow into flexible non-vacuum environment test cavity, inside flexible non-vacuum environment test cavity, uniform High Temperature Simulation environment or low temperature simulated environment are realized.Load test equipment is installed outside flexible non-vacuum environment test cavity, and it is installed on the sealing bellows structure of flexible non-vacuum environment test cavity, hydraulic motor drive load connecting rod cooperates the movement of tested rudder face transmission, it is sealed processing between connecting rod and flexible non-vacuum environment test cavity simultaneously, enhances the thermal insulation property of cavity.Simulating test device structure is simple, reduces experimentation cost, and space utilization rate is high.
Description
Technical field
The invention belongs to aircraft ground test and testing field, specifically, being related to a kind of for aerospace craft
The ground simulation test device that rudder transmission mechanism is tested for the property in high and low temperature environment.
Background technique
Aerospace craft is that one kind can fly in endoatmosphere, also can be in the aircraft of extra-atmospheric flight.In addition to
It during being reentered across atmosphere and return, even more to be undergone by except severe temperature environment in space environment
The high temperature of thousands of degree and temperature change rapidly, highest can be to 1800 DEG C.So in aerospace craft research and design process,
Reliably and effectively ground simulation humid test is very important.Thermal insulation tile made of external application composite material is generallyd use to guarantee
Airborne equipment works in suitable temperature, nevertheless, 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
It is required that generally 25~32 DEG C, and the requirement of external airborne equipment and other equipment is relatively low, generally are as follows: -50~50 DEG C.
But for the reliability of test, need temperature range to be tested are as follows: -100~100 DEG C.
(Chinese vacuum association 2012 is academic for existing disclosed technical literature " KM7 large space environment simulator development [C] "
Annual meeting, 2012) a kind of simulator is described in, which is mainly realized high temperature mould by thermal infrared radiation mode
Quasi-, cold nitrogen system realizes low temperature simulation；But cost and experimentation cost are very high, meet the test need of Large Spacecraft or whole star
It asks.It is disclosed in patent CN104670523 " a kind of high/low temperature environmental simulation testing equipment ", which is tried using box type
Environment is tested, for the static test of product, does not adapt to the testing experiment under product moving situation, and big to the size of product
It is small restricted, poor universality.A kind of " large size high-low temperature environment simulation test box inside cabin is proposed in patent CN104588135
Body structure " the structure realizes a kind of large-scale simulation in order to solve the test to large scale equipment, using square steel, corrugated sheet, glass reinforced plastic
Chamber；Cost is higher, and space utilization rate is low, is also limited when carrying out the measurement of telecontrol equipment.
Summary of the invention
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of simulation for aircraft rudder transmission mechanism is surveyed
Trial assembly is set；The simulating test device is using flexible antivacuum heat-insulating material composition, and volume, which is adjusted, can be changed, and space utilization rate is high, right
Plant bulk it is adaptable, suitable under vehicle rudder machine transmission mechanism motion state high temperature performance test.
The technical solution adopted by the present invention to solve the technical problems is: quiet including test cavity, input static pressure chamber, outlet
Press chamber, pedestal, tested steering engine, rudder transmission mechanism, tested rudder face, sealing bellows, load connecting rod, hydraulic motor, supporting mechanism, solid
Fixed circle, static pressure chamber enclosure, orifice plate, sealing plate, zone circle, insulation sealant tape, the test cavity both ends pass through supporting mechanism and
Input static pressure chamber is connected with exit static pressure chamber, and tested steering engine is connect with tested rudder face by rudder transmission mechanism, and is mounted on test
On intracavitary pedestal, the test cavity bottom positioned at the lower section of tested rudder face is provided with circular hole, for sealing bellows, liquid to be fixedly mounted
Pressure motor, which is located at below test cavity, to be fixed in mounting base, and load connecting rod one end passes through the round tube hole of sealing bellows, passes through ear
Fork is connected on the loaded ring of tested rudder face bottom, and the load connecting rod other end is connect with hydraulic motor by shaft coupling；
The input static pressure chamber and the exit static pressure chamber use stainless steel cylindrical shell, and inside is equipped with glass reinforced plastic drilling
Plate, uniformly distributed several apertures, input static pressure chamber and exit static pressure chamber outer end are equipped with stainless steel sealing plate and retainer plate on orifice plate,
Input static pressure chamber outer end is connected with test pipeline and admission line, exit static pressure chamber outer end have outlet conduit, exhaust pipe,
Outlet test pipeline is connect with micro-pressure sensor, drain tap, gas recovery conduit respectively；
The sealing bellows is that the zone circle that diameter gradient increases forms tower structure, and zone circle uses double-layer polyester fiber package
It wraps up in, centre is equipped with round tube hole, loads with sealant tape sealing is insulated between connecting rod and round tube hole, sealing bellows is fixed on test cavity
Bottom.
The test cavity is combined using multilayer heat insulation paper and aluminized mylar, 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 insulation by with
Flexible thermal insulative test cavity made of the support of inside can sufficiently cooperate with certain deformability while keeping shape
The motion requirement of rudder face transmission；Static pressure chamber is set at the entrance and exit of flexible non-vacuum environment test cavity, makes high temperature nitrogen
Or low temperature nitrogen uniformly flows 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；Load test equipment, Yi Jian are installed for compatibility test chamber simulated environment
Sealing bellows loaded on flexible non-vacuum environment test cavity, while meeting loading equipemtn motion requirement, to connecting rod and flexibility
Processing, the thermal insulation property of enhancing test cavity are sealed between non-vacuum environment 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 utilization rate is high.
Detailed description of the invention
With reference to the accompanying drawing 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 the simulating test device bottom view that the present invention is used for aircraft rudder transmission mechanism.
Fig. 2 is the simulating test device schematic diagram that the present invention is used 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 cross-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 cross-sectional view of simulating test device of the present invention.
Fig. 7 is the sealing bellows bottom 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. test 2. input static pressure chamber of cavity, 3. exit static pressure chamber, 4. pedestal 5. is tested 6. rudder transmission mechanism of steering engine
7. tested rudder face 8. seals bellows 9. and loads the test of 10. hydraulic motor of connecting rod, 11. supporting mechanism, 12. admission line 13.
18. outlet conduit of pipeline 14. retainer plate, 15. static pressure chamber enclosure, 16. orifice plate, 17. sealing plate, 19. exhaust pipe 20. goes out
21. round tube hole of mouth test pipeline, 22. zone circle 23. is insulated sealant tape
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, the simulation being tested for the property to rudder transmission mechanism
Test.Flexible heat insultating cavity is made using antivacuum heat-insulating material and internal support in simulating test device；In flexible non-real idle loop
Static pressure chamber is set at the entrance and exit of border test cavity, high temperature nitrogen or low temperature nitrogen is made uniformly to flow into flexible non-vacuum environment
Test cavity realizes uniform High Temperature Simulation environment or low temperature simulated environment inside flexible non-vacuum environment test cavity；Simulation
Test device structure is simple, reduces experimentation cost, and space utilization rate is high.
Refering to fig. 1~Fig. 8, the present embodiment be used for aircraft rudder transmission mechanism simulating test device, by test cavity 1,
Input static pressure chamber 2, exit static pressure chamber 3, pedestal 4, tested steering engine 5, rudder transmission mechanism 6, tested rudder face 7, sealing bellows 8, load
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, insulation
Sealant tape 23 and admission line 12, test pipeline 13, outlet conduit 18, exhaust pipe 19, outlet test pipeline 20, round tube hole
21 compositions；Wherein, test 1 both ends of cavity are connect by supporting mechanism 11 with input static pressure chamber 2 and exit static pressure chamber 3, are tested rudder
Machine 5 passes through with tested rudder face 7 on the pedestal 4 that rudder transmission mechanism 6 connect, and is mounted in test cavity 1；Positioned at tested rudder face 7
1 bottom of test cavity of lower section is machined with circular hole, for sealing bellows 8 to be fixedly mounted.Hydraulic motor 10 is located under test cavity 1
Side is fixed in mounting base；Load 9 one end of connecting rod passes through the load that sealing bellows 8 is connected to tested 7 bottom of rudder face by ear fork
On ring, load 9 other end of connecting rod is connect with hydraulic motor 10 by shaft coupling.
In the present embodiment, test cavity 1 is combined using multilayer heat insulation paper and multilayer aluminized mylar, central filler
Aeroge, thermal conductivity is extremely low, realizes antivacuum insulation effect.It is good using stainless steel stent and elasticity to test support inside cavity 1
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 for testing 1 both ends of cavity use stainless steel cylindrical shell, and inside is equipped with
Glass reinforced plastic drilling plate 16, uniformly distributed several apertures on orifice plate 16, input static pressure chamber 2 and 3 outer end of exit static pressure chamber are equipped with stainless
Steel sealing plate 17,2 outer end of input static pressure chamber are connected with test pipeline 13 and admission line 12；3 outer end of exit static pressure chamber has
Outlet conduit 18, exhaust pipe 19, outlet test pipeline 20 respectively with micro-pressure sensor, drain tap, gas recovery conduit
Connection.Retainer plate 14 and static pressure chamber enclosure 15 are used cooperatively.The circular orifice 16 set in input static pressure chamber 2 is with a thickness of 10cm, hole
Uniformly distributed circular aperture diameter is 4mm~8mm on plate 16, and aperture working (finishing) area accounts for the 30~50% of main valve cross-sectional area.It is close
The distance between sealing plate 17 and orifice plate 16 are 10cm~20cm.Static pressure chamber enclosure 15 and 17 outside cladding thickness of sealing plate are 15mm
Superfine glass silk floss heat preservation.
Sealing bellows 8 is that the zone circle 22 that diameter gradient increases forms tower structure, zone circle 22 using multi-layered polyester fiber and
Package after sheathing paper is compound, and be combined with the antivacuum insulation of test cavity 1 by note.It seals and is equipped with round lead among bellows 8
Hole 21, load connecting rod 9 are passed through from round tube hole 21, are loaded and are sealed between connecting rod 9 and round tube hole 21 with insulation sealant tape 23, and can
It realizes and stretches, Bending Deformation state.Sealing bellows 8 is fixed on 1 bottom of test cavity.
In the present embodiment, test cavity 1 volume and shape can according to pedestal 4, tested steering engine 5, rudder transmission mechanism 6 and by
The physical model for surveying rudder face 7 is adjusted flexibly.Support construction 11 is made of stainless steel stent and Elastic Carbon fiber, can kept
Under the premise of cavity shape, flexibility characteristics are kept, the motion state of tested device is cooperated.By being passed through height to input static pressure chamber 2
The high pure nitrogen of temperature or low temperature, and optimize the flow and temperature for being passed through gas, uniform simulated normal pressure height in cavity 1 can tested
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 recycles, and is passed through experimental rig again after heat temperature raising or heat exchange refrigeration.Improve gas and energy
Utilization rate is measured, experimentation cost is reduced.When testing tested device, then simulated implementation high and low temperature environment first controls quilt
Surveying steering engine 5 moves rudder transmission mechanism 6 and tested rudder face 7 according to instruction, and control hydraulic motor 10 applies negative on tested rudder face 7
Simulation is carried, the performance test of entire 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 testing cavity, input static pressure
Chamber, exit static pressure chamber, pedestal, tested steering engine, rudder transmission mechanism, tested rudder face, sealing bellows, load connecting rod, hydraulic motor, branch
Support mechanism, retainer plate, static pressure chamber enclosure, orifice plate, sealing plate, zone circle, insulation sealant tape, the test cavity both ends pass through branch
Support mechanism is connect with input static pressure chamber and exit static pressure chamber, and tested steering engine is connect with tested rudder face by rudder transmission mechanism, and is pacified
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 being fixedly mounted
Sealer box, hydraulic motor, which is located at below test cavity, to be fixed in mounting base, and the circle that load connecting rod one end passes through sealing bellows is logical
Hole is connected on the loaded ring of tested rudder face bottom by ear fork, and the load connecting rod other end and hydraulic motor are connected by shaft coupling
It connects；
The input static pressure chamber and the exit static pressure chamber use stainless steel cylindrical shell, and inside is equipped with glass reinforced plastic drilling plate,
Uniformly distributed several apertures, input static pressure chamber and exit static pressure chamber outer end are equipped with stainless steel sealing plate and retainer plate, enter on orifice plate
Mouth static pressure chamber outer end is connected with test pipeline and admission line, and there is outlet conduit in exit static pressure chamber outer end, exhaust pipe, goes out
Mouth test pipeline is connect with micro-pressure sensor, drain tap, gas recovery conduit respectively；
The sealing bellows is that the zone circle that diameter gradient increases forms tower structure, and zone circle is wrapped up using double-layer polyester fiber, in
Between be equipped with round tube hole, load between connecting rod and round tube hole with insulation sealant tape sealing, sealing bellows is fixed on test cavity bottom.
2. the simulating test device according to claim 1 for aircraft rudder transmission mechanism, it is characterised in that: the examination
It tests cavity to be combined using multilayer heat insulation paper and aluminized mylar, 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 |
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| CN106644466A CN106644466A (en) | 2017-05-10 |
| CN106644466B true CN106644466B (en) | 2019-02-01 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111397830B (en) * | 2020-03-02 | 2022-08-09 | 北京空天技术研究所 | Wind tunnel examination device of sealed heat-proof structure |
| 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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2016
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