CN108362426A - A kind of aeroengine thrust detection device - Google Patents
A kind of aeroengine thrust detection device Download PDFInfo
- Publication number
- CN108362426A CN108362426A CN201810061045.8A CN201810061045A CN108362426A CN 108362426 A CN108362426 A CN 108362426A CN 201810061045 A CN201810061045 A CN 201810061045A CN 108362426 A CN108362426 A CN 108362426A
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- China
- Prior art keywords
- fixedly connected
- load
- centre position
- bearing
- pedestal
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- Granted
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 21
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 28
- 239000004973 liquid crystal related substance Substances 0.000 claims description 10
- 239000002828 fuel tank Substances 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 238000012360 testing method Methods 0.000 description 8
- 230000005484 gravity Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/13—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring the tractive or propulsive power of vehicles
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Abstract
The invention discloses a kind of aeroengine thrust detection devices, including pedestal, the pedestal is fixedly mounted on the ground, the base upper surface centre position is provided with instrument connection, pressure apparatus is equipped in the pedestal, the pressure apparatus is by the sliding part that is sleeved in instrument connection, the pressure plare being slidably connected in sliding part and with sliding part inner surface, it is fixedly connected with pressure plare lower surface below the pressure plare and equally distributed pressure sensor and the Signal connector that is fixedly connected on the right side of pressure sensor and with pressure sensor right lateral surface lower section centre position collectively forms, fixing device is equipped with above the pressure plare, clamp device is equipped with above the fixing device.The invention has the advantages that of simple structure and strong practicability.
Description
Technical field
The present invention relates to aero-engine performance technical field of measurement and test, especially a kind of aeroengine thrust detection is set
It is standby.
Background technology
When aero-engine dispatches from the factory or repairs failure, it is required for carrying out thrust measurement, carries out relevant experiment, generate
The dynamic change of different atmospheric pressure conditions lower thrusts determines good condition, traditional test according to the variation effect of thrust
Method can generally test on horizontal guide rail, since the gravity of aero-engine is too big, even if friction factor very little, it is also possible to
Prodigious frictional force is brought, the objectivity of detection is influenced.
Invention content
The purpose of the present invention is to solve the above problems, devise a kind of aeroengine thrust detection device.
Realize above-mentioned purpose the technical scheme is that, a kind of aeroengine thrust detection device, including pedestal, institute
It states pedestal to be fixedly mounted on the ground, the base upper surface centre position is provided with instrument connection, and being equipped with pressure in the pedestal fills
Set, the pressure apparatus by be sleeved in instrument connection sliding part, be located at sliding part in and with sliding part inner surface slide connect
The pressure plare that connects is fixedly connected below pressure plare with pressure plare lower surface and equally distributed pressure sensor and positioned at pressing
The Signal connector being fixedly connected on the right side of force snesor and with centre position below pressure sensor right lateral surface collectively forms, described
Fixing device is equipped with above pressure plare, the fixing device is by being opened in the sliding groove in pressure plare upper surface centre position, being located at and slide
It is fixedly connected with the weight supporting slide that sliding groove is slidably connected, above weight supporting slide and with weight supporting slide upper surface in dynamic slot
Bearing frame, the contact plate being fixedly connected on the right side of the bearing frame and with centre position above bearing frame right lateral surface, positioned at contacting
The load-bearing axle one that is fixedly connected in front of plate and with contact plate front surface, to be sleeved on load-bearing axle one outer and be rotatablely connected with load-bearing axle one
Load-bearing set one, positioned at contact plate rear and the load-bearing axle two that is fixedly connected with contact plate rear surface and be sleeved on outside load-bearing axle two
And the load-bearing set two being rotatablely connected with load-bearing axle two collectively forms, and clamp device, the fastening are equipped with above the fixing device
Device by positioned at load-bearing set one top with load-bearing cover a upper surface be fixedly connected preceding connecting shaft, be sleeved on before connecting shaft outside and
The front connector of preceding connecting shaft rotation connection, is located at load-bearing set two at the mounting hole one for being opened in front connector rear surface centre position
Top and load-bearing cover the rear connecting shaft that two upper surfaces are fixedly connected, are sleeved on outside rear connecting shaft and the rotation connection of rear connecting shaft
Rear connectors, the mounting hole two for being opened in rear connectors front surface centre position, base sheath are mounted in mounting hole two and flexible end cap
Main hydraulic cylinder in mounting hole one, above main hydraulic cylinder be fixedly connected in front of the centre position of main hydraulic cylinder upper surface
Oil inlet pipe and the common structure of flowline that is fixedly connected with main hydraulic cylinder upper surface centre position rear above main hydraulic cylinder
At.
Auxiliary frame is equipped in the fixing device on the right side of bearing frame, auxiliary hydraulic cylinder is equipped on the right side of the auxiliary frame, it is described auxiliary
Hydraulic cylinder extension end is equipped with auxiliary sleeve.
Corner location is equipped with guard column above the pedestal.
Be equipped with air-intake device between the guard column, the air-intake device by be located above pedestal and both ends respectively with protection
Blower rack that column centre position is fixedly connected, the assembling hole for being opened in blower rack centre position and in assembling hole and
The accessory fan that blower rack is fixedly connected collectively forms.
Guard column inner surface centre position is equipped with pneumatics sensor.
The base plate front surface centre position is equipped with liquid crystal display, and control panel is equipped on the right side of the liquid crystal display.
The sliding groove rear is equipped with balancing device, and the balancing device is by being located at sliding groove rear and pressure plare upper surface
The gear bar that is fixedly connected, is sleeved on the balance motor seat being fixedly connected with weight supporting slide rear surface positioned at weight supporting slide rear
Balance motor seat inner equilibrium motor and the driving gear being sleeved on the outside of balance motor output shaft collectively form.
The accessory fan rear is equipped with catch net, and the catch net is fixedly connected with accessory fan outer surface.
The fixed part symmetrical and consistent structure with fixing device is equipped on the right side of the pressure plare upper surface.
Fuel tank is equipped in the pedestal, the main hydraulic cylinder, oil inlet pipe, flowline are connected with auxiliary hydraulic cylinder by oil pipe,
It is electrically connected between the Signal connector, accessory fan, pneumatics sensor, liquid crystal display, control panel and balance motor.
A kind of aeroengine thrust detection device made using technical scheme of the present invention is in horizontal pressure plare
Outside the gravity for bearing aero-engine and bearing frame, while by the downward thrust of aero-engine, relative in the horizontal direction
The case where testing thrust, stress is more stable, and under the monitoring of pneumatics sensor, and air-intake device can adjust aero-engine
Air inlet pressure, test the thrust under different condition, and the pressure sensor at the pressure plare following four corners can be basic
Thrust of the mean allocation from aero-engine.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of aeroengine thrust detection device of the present invention；
Fig. 2 is a kind of vertical view of aeroengine thrust detection device of the present invention；
Fig. 3 is the partial enlarged view of pressure apparatus of the present invention；
Fig. 4 is the partial enlarged view of fixing device of the present invention；
Fig. 5 is the partial enlarged view of balancing device of the present invention；
In figure, 1, pedestal；2, instrument connection；3, pressure apparatus；4, sliding part；5, pressure plare；6, pressure sensor；7, signal connects
Head；8, fixing device；9, sliding groove；10, weight supporting slide；11, bearing frame；12, contact plate；13, load-bearing axle one；14, load-bearing set
One；15, load-bearing axle two；16, load-bearing set two；17, clamp device；18, preceding connecting shaft；19, front connector；20, mounting hole one；
21, rear connecting shaft；22, rear connectors；23, mounting hole two；24, fuel tank；25, main hydraulic cylinder；26, oil inlet pipe；27, flowline；
28, auxiliary frame；29, auxiliary hydraulic cylinder；30, auxiliary sleeve；31, guard column；32, air-intake device；33, blower rack；34, assembling
Hole；35, catch net；36, accessory fan；37, pneumatics sensor；38, liquid crystal display；39, control panel；40, balancing device；
41, gear bar；42, balance motor seat；43, balance motor；44, driving gear.
Specific implementation mode
The present invention is specifically described below in conjunction with the accompanying drawings, as shown in Figs. 1-5, a kind of detection of aeroengine thrust is set
It is standby, including pedestal 1, on the ground, 1 upper surface centre position of the pedestal is provided with instrument connection 2, institute to the fixed installation of the pedestal 1
State and be equipped with pressure apparatus 3 in pedestal 1, the pressure apparatus 3 by be sleeved in instrument connection 2 sliding part 4, be located in sliding part 4
And be slidably connected with 4 inner surface of sliding part pressure plare 5, be fixedly connected with 5 lower surface of pressure plare positioned at 5 lower section of pressure plare and
Equally distributed pressure sensor 6 and positioned at the right side of pressure sensor 6 and with centre position below 6 right lateral surface of pressure sensor
The Signal connector 7 being fixedly connected collectively forms, and 5 top of the pressure plare is equipped with fixing device 8, and the fixing device 8 is by being opened in
The sliding groove 9 in 5 upper surface centre position of pressure plare, the weight supporting slide 10 being slidably connected with sliding groove 9 in sliding groove 9, position
The bearing frame 11 that is fixedly connected above weight supporting slide 10 and with 10 upper surface of weight supporting slide, positioned at 11 right side of bearing frame and with hold
Centre position is fixedly connected above weight frame 11 right lateral surface contact plate 12, be located at 12 front of contact plate and with table before contact plate 12
Load-bearing axle 1 that face is fixedly connected, be sleeved on that load-bearing axle 1 is outer and the load-bearing that be rotatablely connected with load-bearing axle 1 cover 1,
Positioned at 12 rear of contact plate and the load-bearing axle 2 15 that is fixedly connected with 12 rear surface of contact plate and be sleeved on load-bearing axle 2 15 it is outer and
The load-bearing set 2 16 being rotatablely connected with load-bearing axle 2 15 collectively forms, and 8 top of the fixing device is equipped with clamp device 17, institute
Clamp device 17 is stated by covering the preceding connecting shaft 18 being fixedly connected with one 14 upper surfaces of load-bearing set above in the of one 14 positioned at load-bearing, being sleeved on
The front connector 19 of 18 outside of preceding connecting shaft and the rotation connection of preceding connecting shaft 18 is opened in 19 rear surface centre position of front connector
Mounting hole 1, positioned at load-bearing set 2 16 top with load-bearing set 2 16 upper surfaces be fixedly connected rear connecting shaft 21, be sleeved on after
The rear connectors 22 of 21 outside of connecting shaft and the rotation connection of rear connecting shaft 21, the peace for being opened in 22 front surface centre position of rear connectors
Dress hole 2 23, base sheath are mounted in the main hydraulic cylinder 25 that in mounting hole 2 23 and telescopic end is sleeved in mounting hole 1, are located at master
The oil inlet pipe 26 and be located at main hydraulic cylinder 25 that 25 top of hydraulic cylinder and 25 upper surface centre position of main hydraulic cylinder front are fixedly connected
The flowline 27 that top is fixedly connected with 25 upper surface centre position rear of main hydraulic cylinder collectively forms；In the fixing device 8
11 right side of bearing frame is equipped with auxiliary frame 28, and 28 right side of the auxiliary frame is equipped with auxiliary hydraulic cylinder 29,29 telescopic end of auxiliary hydraulic cylinder
Equipped with auxiliary sleeve 30；1 top corner location of the pedestal is equipped with guard column 31；Air-intake device is equipped between the guard column 31
32, the air-intake device 32 is by above pedestal 1 and blower rack that both ends are fixedly connected with 31 centre position of guard column respectively
33, it is opened in the assembling hole 34 in 33 centre position of blower rack and is fixedly connected with blower rack 33 in the assembling hole 34
Accessory fan 36 collectively forms；31 inner surface centre position of the guard column is equipped with pneumatics sensor 37；Table before the pedestal 1
Face centre position is equipped with liquid crystal display 38, and 38 right side of the liquid crystal display is equipped with control panel 39；9 rear of the sliding groove
Equipped with balancing device 40, the balancing device 40 is by the gear bar that is fixedly connected with 5 upper surface of pressure plare positioned at 9 rear of sliding groove
41, the balance motor seat 42 that is fixedly connected with 10 rear surface of weight supporting slide positioned at 10 rear of weight supporting slide is sleeved on balance motor
42 inner equilibrium motor 43 of seat and the driving gear 44 being sleeved on the outside of 43 output shaft of balance motor collectively form；The accessory fan
36 rears are equipped with catch net 35, and the catch net 35 is fixedly connected with 36 outer surface of accessory fan；5 upper surface of the pressure plare
The fixed part that right side is equipped with fixing device 8 is symmetrical and structure is consistent；Fuel tank 24, the main hydraulic pressure are equipped in the pedestal 1
Cylinder 25, oil inlet pipe 26, flowline 27 are connected with auxiliary hydraulic cylinder 29 by oil pipe, the Signal connector 7, accessory fan 36, pneumatics
It is electrically connected between sensor 37, liquid crystal display 38, control panel 39 and balance motor 43.
The characteristics of the present embodiment is that pedestal is fixedly mounted on the ground, and base upper surface centre position is provided with instrument connection,
Be equipped with pressure apparatus in pedestal, pressure apparatus by be sleeved in instrument connection sliding part, be located in sliding part and in sliding part
Pressure plare that side surface is slidably connected is fixedly connected below pressure plare with pressure plare lower surface and equally distributed pressure biography
Sensor and the Signal connector being fixedly connected on the right side of pressure sensor and with centre position below pressure sensor right lateral surface
It collectively forms, is equipped with fixing device above pressure plare, fixing device is by being opened in sliding groove, the position in pressure plare upper surface centre position
In the weight supporting slide being slidably connected with sliding groove in sliding groove, it is located above weight supporting slide and fixes company with weight supporting slide upper surface
The bearing frame that connects, on the right side of bearing frame and be fixedly connected with centre position above bearing frame right lateral surface contact plate, be located at
The load-bearing axle one that is fixedly connected in front of contact plate and with contact plate front surface, to be sleeved on load-bearing axle one outer and rotated with load-bearing axle one
The load-bearing set one of connection positioned at contact plate rear and the load-bearing axle two that is fixedly connected with contact plate rear surface and is sleeved on load-bearing axle
Two load-bearing sets two that are outer and being rotatablely connected with load-bearing axle two collectively form, and clamp device, clamp device are equipped with above fixing device
By connecting outside connecting shaft before covering the preceding connecting shaft being fixedly connected with one upper surface of load-bearing set above in the of one positioned at load-bearing, be sleeved on and before
The front connector of spindle rotation connection, the mounting hole one for being opened in front connector rear surface centre position are located at two top of load-bearing set
Rear connecting shaft that two upper surfaces are fixedly connected is covered with load-bearing, is sleeved on the rear company with the rotation connection of rear connecting shaft outside rear connecting shaft
Fitting, the mounting hole two for being opened in rear connectors front surface centre position, base sheath are in mounting hole two and telescopic end is sleeved on
Main hydraulic cylinder in mounting hole one, above main hydraulic cylinder be fixedly connected in front of the centre position of main hydraulic cylinder upper surface into
Oil pipe and the flowline being fixedly connected with main hydraulic cylinder upper surface centre position rear above main hydraulic cylinder collectively form, place
It is born outside the gravity of aero-engine and bearing frame in horizontal pressure plare, while by the downward thrust of aero-engine, phase
The case where for testing thrust in the horizontal direction, stress is more stable, and under the monitoring of pneumatics sensor, and air-intake device can be with
The air inlet pressure of aero-engine is adjusted, the thrust under different condition, and the pressure at pressure plare following four corners are tested
Force snesor can basic thrust of the mean allocation from aero-engine.
In the present embodiment, before aero-engine is placed into test device, by control panel by pressure sensing
Then the parameter reset of device adjusts position of the fixing device on pressure plare, aero-engine is then placed on two fixations
Device centre position continues to adjust the outer surface that fixing device makes load-bearing set one and load-bearing set two is bonded aero-engine, then
The main hydraulic cylinder in clamp device is opened, so that load-bearing set one and load-bearing set two is held aero-engine outer surface tightly, is then turned on auxiliary
The auxiliary hydraulic cylinder in frame is helped, aero-engine is auxiliarily fixed, then the position of balancing device fine tuning fixing device makes to be located at pressure
Pressure sensor uniform force below plate, the accessory fan being then turned in air-intake device change aero-engine air intake vent
Air pressure, test different condition under thrust magnitude.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solution of the present invention, those skilled in the art
The principle of the present invention is embodied to some variations that some of which part may be made, belongs to the scope of protection of the present invention it
It is interior.
Claims (10)
1. a kind of aeroengine thrust detection device, including pedestal（1）, which is characterized in that the pedestal（1）It is fixedly mounted on
On ground, the pedestal（1）Upper surface centre position is provided with instrument connection（2）, the pedestal（1）It is interior to be equipped with pressure apparatus（3）, institute
State pressure apparatus（3）By being sleeved on instrument connection（2）Interior sliding part（4）, be located at sliding part（4）Interior and and sliding part（4）Inside
The pressure plare that surface is slidably connected（5）, be located at pressure plare（5）Lower section and pressure plare（5）Lower surface is fixedly connected and is uniformly distributed
Pressure sensor（6）With positioned at pressure sensor（6）Right side and and pressure sensor（6）Centre position is solid below right lateral surface
Surely the Signal connector connected（7）It collectively forms, the pressure plare（5）Top is equipped with fixing device（8）, the fixing device（8）
By being opened in pressure plare（5）The sliding groove in upper surface centre position（9）, be located at sliding groove（9）Interior and sliding groove（9）It is slidably connected
Weight supporting slide（10）, be located at weight supporting slide（10）Top and and weight supporting slide（10）The bearing frame that upper surface is fixedly connected（11）、
Positioned at bearing frame（11）Right side and and bearing frame（11）The contact plate that centre position is fixedly connected above right lateral surface（12）, be located at
Contact plate（12）Front and and contact plate（12）The load-bearing axle one that front surface is fixedly connected（13）, be sleeved on load-bearing axle one（13）Outside
And with load-bearing axle one（13）The load-bearing set one of rotation connection（14）, be located at contact plate（12）Rear and and contact plate（12）Rear surface
The load-bearing axle two being fixedly connected（15）Be sleeved on load-bearing axle two（15）It is outer and with load-bearing axle two（15）The load-bearing set of rotation connection
Two（16）It collectively forms, the fixing device（8）Top is equipped with clamp device（17）, the clamp device（17）It is held by being located at
One is covered again（14）Top covers one with load-bearing（14）The preceding connecting shaft that upper surface is fixedly connected（18）, be sleeved on preceding connecting shaft（18）Outside
Portion and preceding connecting shaft（18）The front connector of rotation connection（19）, be opened in front connector（19）The mounting hole in rear surface centre position
One（20）, be located at load-bearing cover two（16）Top covers two with load-bearing（16）The rear connecting shaft that upper surface is fixedly connected（21）, be sleeved on
Connecting shaft afterwards（21）External and rear connecting shaft（21）The rear connectors of rotation connection（22）, be opened in rear connectors（22）In front surface
Between position mounting hole two（23）, base sheath be mounted in mounting hole two（23）Interior and telescopic end is sleeved on mounting hole one（20）Interior master
Hydraulic cylinder（25）, be located at main hydraulic cylinder（25）Top and main hydraulic cylinder（25）The oil inlet being fixedly connected in front of the centre position of upper surface
Pipe（26）With positioned at main hydraulic cylinder（25）Top and main hydraulic cylinder（25）The flowline that upper surface centre position rear is fixedly connected
（27）It collectively forms.
2. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the fixing device
（8）Interior bearing frame（11）Right side is equipped with auxiliary frame（28）, the auxiliary frame（28）Right side is equipped with auxiliary hydraulic cylinder（29）, the auxiliary liquid
Cylinder pressure（29）Telescopic end is equipped with auxiliary sleeve（30）.
3. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the pedestal（1）On
Square corner location is equipped with guard column（31）.
4. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the guard column（31）
Between be equipped with air-intake device（32）, the air-intake device（32）By being located at pedestal（1）Top and both ends respectively with guard column（31）
The blower rack that centre position is fixedly connected（33）, be opened in blower rack（33）The assembling hole in centre position（34）With positioned at wind turbine
Mounting hole（34）Interior and blower rack（33）The accessory fan being fixedly connected（36）It collectively forms.
5. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the guard column（31）
Inner surface centre position is equipped with pneumatics sensor（37）.
6. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the pedestal（1）Before
Surface centre position is equipped with liquid crystal display（38）, the liquid crystal display（38）Right side is equipped with control panel（39）.
7. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the sliding groove（9）
Rear is equipped with balancing device（40）, the balancing device（40）By being located at sliding groove（9）Rear and pressure plare（5）Upper surface is fixed
The gear bar of connection（41）, be located at weight supporting slide（10）Rear and weight supporting slide（10）The balance motor seat that rear surface is fixedly connected
（42）, be sleeved on balance motor seat（42）Inner equilibrium motor（43）Be sleeved on balance motor（43）Driving tooth on the outside of output shaft
Wheel（44）It collectively forms.
8. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the accessory fan
（36）Rear is equipped with catch net（35）, the catch net（35）With accessory fan（36）Outer surface is fixedly connected.
9. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the pressure plare（5）
Upper surface right side is equipped with and fixing device（8）Symmetrical and consistent structure fixed part.
10. a kind of aeroengine thrust detection device according to claim 1, which is characterized in that the pedestal（1）It is interior
Equipped with fuel tank（24）, the main hydraulic cylinder（25）, oil inlet pipe（26）, flowline（27）With auxiliary hydraulic cylinder（29）Connected by oil pipe
It connects, the Signal connector（7）, accessory fan（36）, pneumatics sensor（37）, liquid crystal display（38）, control panel（39）With
Balance motor（43）Between be electrically connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810061045.8A CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810061045.8A CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108362426A true CN108362426A (en) | 2018-08-03 |
| CN108362426B CN108362426B (en) | 2020-06-30 |
Family
ID=63006466
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810061045.8A Active CN108362426B (en) | 2018-01-22 | 2018-01-22 | Aeroengine thrust detection equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108362426B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110702293A (en) * | 2019-11-28 | 2020-01-17 | 北京航天三发高科技有限公司 | Supersonic engine test bed air inlet thrust measuring device and using method |
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|---|---|---|---|---|
| SU1758454A2 (en) * | 1990-10-17 | 1992-08-30 | Конструкторское бюро химического машиностроения | Device for measuring engine thrust force |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102788698A (en) * | 2012-08-13 | 2012-11-21 | 中国航天科技集团公司第四研究院四0一所 | Ground rotation testing device for solid rocket engine |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN103353399A (en) * | 2013-07-03 | 2013-10-16 | 山河智能装备股份有限公司 | Mechanical performance testing table for piston engine |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
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2018
- 2018-01-22 CN CN201810061045.8A patent/CN108362426B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1758454A2 (en) * | 1990-10-17 | 1992-08-30 | Конструкторское бюро химического машиностроения | Device for measuring engine thrust force |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102788698A (en) * | 2012-08-13 | 2012-11-21 | 中国航天科技集团公司第四研究院四0一所 | Ground rotation testing device for solid rocket engine |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103217295A (en) * | 2013-03-28 | 2013-07-24 | 南京航空航天大学 | Ground test rack system of aviation piston engine |
| CN103353399A (en) * | 2013-07-03 | 2013-10-16 | 山河智能装备股份有限公司 | Mechanical performance testing table for piston engine |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110702293A (en) * | 2019-11-28 | 2020-01-17 | 北京航天三发高科技有限公司 | Supersonic engine test bed air inlet thrust measuring device and using method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108362426B (en) | 2020-06-30 |
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