CN108918582A - A kind of hot external pressure test system and method for aircraft cargo tank structure - Google Patents
A kind of hot external pressure test system and method for aircraft cargo tank structure Download PDFInfo
- Publication number
- CN108918582A CN108918582A CN201810727938.1A CN201810727938A CN108918582A CN 108918582 A CN108918582 A CN 108918582A CN 201810727938 A CN201810727938 A CN 201810727938A CN 108918582 A CN108918582 A CN 108918582A
- Authority
- CN
- China
- Prior art keywords
- testpieces
- external pressure
- servo
- tank structure
- cargo tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
Landscapes
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A kind of hot external pressure test system of aircraft cargo tank structure of the present invention, including thermal force loading system, external pressure loading system, axial loading system；Thermal force loading system includes that heater heats testpieces, and outer compressive load loading system includes leather bag, identical as testpieces outer wall shape, is wrapped in testpieces periphery with the shape, controls pressure size by the way that liquid is added into leather bag；Axial loading system includes servo-cylinder, connecting rod, flexural pivot, servo-cylinder is fixed on above testpieces, one connection servo-cylinder of connecting rod, one connection flexural pivot, start servo-cylinder, drive connecting rod toward upper (lower), so that flexural pivot be driven axially to apply axial tension (pressure) toward testpieces direction.It solves the problems, such as that hot external pressure test applies thermal force, axial tensile loads and outer compressive load to testpieces simultaneously, especially applies axial tensile loads while applying thermal force and outer compressive load.
Description
Technical field
The invention belongs to the aircraft grounds simulation test field such as guided missile, rocket more particularly to the hot external pressures of Flight Vehicle Structure
Test, it is intended to realize that the joint of aircraft thermal force, axial load and uniform external load applies.
Background technique
The calorific intensity occurred when structural thermal external pressure test is to solve the problems, such as aircraft flight and grow up a kind ofly
Face modelling technique is using simulated flight device flight environment of vehicle condition as objective, using full size structure as object, to study and examine
The ground experiment for the purpose of thermo-strength of structure, hot rigidity and thermal protective performance is tested, is indispensable one in aircraft development process
A important link.
The hot external pressure test of tradition applies thermal force and uniform external load using high temperature heat conductive oil, needs during test
Entire experimental rig is closed to realize that outer compressive load applies, and the hot external pressure test of tradition has the disadvantage that：1) during actual tests
Often due to poorly sealed and lead to test failure；2) high temperature heat conductive oil has some potential safety problems during the test, and only
Heating temperature is able to achieve at 200 DEG C or so；3) in the hot external pressure test of tradition, axial tensile loads will cause it is poorly sealed and can not
Apply outer compressive load, therefore the hot external pressure test of tradition can not apply axial tensile loads.
Summary of the invention
(1) the technical issues of solving
The present invention solves hot external pressure test and applies thermal force, axial tensile loads and outer compressive load to testpieces simultaneously
Problem, especially applying thermal force and outer compressive load while applies axial tensile loads.
(2) technical solution
A kind of hot external pressure test system of aircraft cargo tank structure, including thermal force loading system, external pressure loading system, axial direction
Loading system；Thermal force loading system includes the heater to testpieces heating；External pressure loading system includes leather bag, with testpieces
Outer wall shape is identical, is wrapped in testpieces periphery, leather bag pressure adjustable with the shape；Axial loading system include servo-cylinder, connecting rod,
Flexural pivot, servo-cylinder are suspended on above testpieces, one connection servo-cylinder of connecting rod, and a connection flexural pivot starts servo-cylinder,
It drives connecting rod to move up and down, correspondingly flexural pivot is driven to apply axial tension or pressure toward testpieces direction.
Further, thermal force loading system further includes temperature sensor, amplifier, computer heating control computer, and temperature passes
Sensor is mounted on testpieces, and temperature sensor, amplifier, computer heating control computer are connected, and temperature sensor signal is through putting
Big device amplified signal passes to computer heating control computer.
Further, the heater is quartzy lamp group, is placed in testpieces, shape is irradiated with testpieces inner wall to examination
Test part；Quartz lamp have it is small in size, power is big, the feature that thermal inertia is small, controllability is good, constitute arbitrary shape heater,
Further, the quartzy lamp group back position fixed reflecting plate.The part heat that reflecting plate radiates quartzy lamp group
It can be reflected back testpieces surface, improve the heating power of quartz lamp.
Further, the leather bag of the external pressure loading system controls pressure size by injecting or flowing out fluid.
Further, on the leather bag of the outer compressive load loading system include inlet and outlet, respectively with water inlet pipe
It is connected with outlet pipe, is filled the water by pressure pump from water inlet pipe and realize that pressure rises, outlet pipe installs valve, water flow outflow is controlled,
Control pressure decline.
Further, the outer compressive load loading system includes leather bag bracket, force snesor, and leather bag wraps up testpieces and places
On leather bag bracket, leather bag bracket is fixed on ground, and force snesor is connect with water pipe, measures pressure.
Further, the one side that the leather bag is contacted with testpieces installs thermal insulation layer.
Further, the axial loading system further includes portal frame, base cross members, force snesor；Testpieces lower end is solid
It is scheduled in lower beam, portal frame forms self-balancing system after connecting with base cross members, servo-cylinder is fixed below portal frame；
The force snesor is mounted on servo-cylinder, and is connected with axial load computer；The flexural pivot includes bulb and upper cover
Plate, connecting rod lower end connecting ball head, bulb are fixed in upper cover plate, are uniformly pressed axially downwards by upper cover plate.
It further, further include measuring system, measuring system includes metering computer, data collection system, measurement sensing
Device, the signal that measurement sensor receives are transferred to metering computer after data collection system acquires.
The present invention also protects a kind of hot external pressure test method of aircraft cargo tank structure, and process is as follows：
A1：Test installation, test adjustment；
A2：It controls heater and applies thermal force, it is ensured that testpieces reaches assigned temperature；
A3：Apply external pressure and axial load simultaneously by leather bag and servo-cylinder.
Working principle：
Thermal force loading system working principle：As the quartzy lamp group of control object, powered by electrical power regulating device,
The radiant heat issued heats up after being absorbed by testpieces, receives temperature change, amplified input meter by feedback transducer
Calculation machine is compared, the control signal after operation and correction adjusting is defeated by electrical power regulating device, and change is added on quartz lamp both ends
Voltage value, to control the size of heat energy.
External pressure loading system by fill the water and control into leather bag water pressure realize external pressure load, leather bag design have into
Water pipe and outlet pipe, are filled the water from water inlet pipe by hand-operating pressure pump and realize that pressure rises, and outlet pipe connecting valve controls water flow stream
Out, pressure decline is realized.
Axial load loading system applies axial load by servo-cylinder.It will be axial by toolings such as cover board and bulbs
Load transmission is to testpieces.Testpieces lower end is fixed on crossbeam by lower cover plate.This test passes through portal frame and base cross members
Form self-balancing system.During test, system realizes automatic adjustment according to given load program, is experienced by dynamometer and is tested
The axial load that part is born, and control operation, deviation are carried out compared with given value as feedback signal input computer
The range variation through servo valve control servo-cylinder is measured, the magnitude of load being added on testpieces is adjusted.
(3) beneficial effects of the present invention：
Present invention test is not required to consider sealing problem, improves success of the test rate, shortens the hot external pressure test preparatory period, improves
Heating efficiency, reduce empirical risk, enable ground level heat external pressure test simulate axial tensile loads and more accurate simulation fly
The flight environment of vehicle of row device provides more accurate data support for the development and design of aircraft.
Thermal force loading system, axial load loading system and outer compressive load loading system of the present invention, which have, to be carried
Lotus application is accurate, success of the test rate is high, the test period is short and the advantages such as empirical risk is low.By verification experimental verification, the present invention is related to
And pilot system can be realized thermal force (room temperature~800 DEG C), axial load (- 100T~100T), outer compressive load (normal pressure~
Application 1MPa), according to heater heating efficiency, the ability that leather bag applies outer compressive load can further expand test capability
Exhibition.The present invention solves the problems, such as that external pressure test can not apply axial tensile loads, and it is thermally conductive to use hot external pressure test must
The history of oil is gone for ever, and reduces the risk of hot external pressure test.
Detailed description of the invention
Fig. 1：The hot external pressure test system construction drawing of aircraft cargo tank structure of the present invention；
Wherein, 1- heater, 2- testpieces, 3- leather bag, 4- servo-cylinder, 5- connecting rod, 6- flexural pivot, 7- thermal insulation layer, the bottom 8-
Portion's crossbeam, 9- portal frame, 10- reflecting plate
Fig. 2：The hot external pressure test system principle schematic diagram of aircraft cargo tank structure of the present invention；
Fig. 3：The hot external pressure test flow chart of aircraft cargo tank structure of the present invention.
Specific embodiment
In addition to embodiment described below, the present invention can also have other embodiments or be implemented in different ways.Therefore,
It should be known that the invention is not limited to it is described in the following description or in the accompanying drawings shown in component structure it is detailed
Situation.
As shown in Figure 1, 2, the hot external pressure test system of a kind of aircraft cargo tank structure, including thermal force loading system, external pressure
Loading system, axial loading system；Thermal force loading system includes the heater 1 heated to testpieces 2；External pressure loading system packet
Leather bag 3 is included, it is identical as 2 wall shapes outside testpieces, it is wrapped in 2 periphery of testpieces, 3 pressure adjustable of leather bag with the shape；Axially loaded system
System includes servo-cylinder 4, connecting rod 5, flexural pivot 6, and servo-cylinder 4 is suspended on 2 top of testpieces, 5 one connection servo-cylinders of connecting rod
4, a connection flexural pivot 6 starts servo-cylinder 4, and connecting rod 5 is driven to move up and down, and correspondingly drives flexural pivot 6 toward 2 side of testpieces
To application axial tension or pressure.
Thermal force loading system further includes temperature sensor, amplifier, computer heating control computer, and temperature sensor is mounted on
On testpieces, temperature sensor, amplifier, computer heating control computer are connected, and temperature sensor signal amplifies through amplifier to be believed
Number pass to computer heating control computer.The present embodiment heater 1 is quartzy lamp group, is placed in testpieces 2, and shape is with inner wall, irradiation
To testpieces.Quartz lamp have it is small in size, power is big, the feature that thermal inertia is small, controllability is good, constitute arbitrary shape heating
Device；It is described in quartzy lamp group back side fixed reflecting plate 10, the partial heat energy that quartzy lamp group radiates is reflected back test by reflecting plate 10
The heating power of quartzy lamp group is improved on part surface.
Include inlet and outlet on the leather bag of the external pressure loading system, be connected respectively with water inlet pipe and outlet pipe,
It is filled the water by pressure pump from water inlet pipe and realizes that pressure rises, outlet pipe installs valve, control water flow outflow, control pressure decline；
External pressure loading system includes leather bag bracket, force snesor, and leather bag package testpieces is placed on leather bag bracket, and leather bag bracket is fixed
On ground, pressure sensor is connect with water pipe, measures pressure；The one side that the leather bag is contacted with testpieces 2 installs thermal insulation layer 7.
The axial loading system further includes portal frame, base cross members 8, portal frame 9, force snesor；2 lower end of testpieces is logical
It crosses lower cover plate to be fixed in base cross members, portal frame 9 and base cross members 8 form self-balancing system, servo after being connected by screw to
Oil cylinder 4 is fixed on 9 lower section of portal frame；The force snesor is mounted on servo-cylinder 4, and is connected with axial load computer
It connects；The flexural pivot 6 includes bulb and upper cover plate, and the 5 lower end connecting ball head of connecting rod, bulb is fixed in upper cover plate, by upper
Cover board uniformly presses axially downwards, and testpieces lower end is fixed in base cross members by lower cover plate.
Measuring system, measuring system include metering computer, data collection system, measurement sensor etc., measurement sensor
The signal received is transferred to metering computer after data collection system acquires.
As shown in figure 3, a kind of hot external pressure test method of aircraft cargo tank structure, process are as follows：
A1：Test installation, test adjustment；
A2：Thermal force is applied using control heater, it is ensured that testpieces reaches assigned temperature；
A3：Apply external pressure and axial load simultaneously by leather bag and servo-cylinder.
Working principle：
Thermal force loading system working principle：As the quartzy lamp group of control object, powered by electrical power regulating device,
The radiant heat issued heats up after being absorbed by testpieces, receives temperature change, amplified input meter by temperature sensor
Calculation machine is compared, the control signal after operation and correction adjusting is defeated by electrical power regulating device, and change is added on quartz lamp both ends
Voltage value, to control the size of heat energy.
External pressure loading system realizes that the load of external pressure, the design of leather bag 3 have by the way that the pressure of water is filled the water and controlled into leather bag 3
Water inlet pipe and outlet pipe, are filled the water from water inlet pipe by hand-operating pressure pump and realize that pressure rises, and outlet pipe connecting valve controls water flow
Pressure decline is realized in outflow.
Axial load loading system applies axial load by servo-cylinder.By upper cover plate and bulb by axial load
It is transferred to testpieces 2, testpieces lower end is fixed in base cross members by lower cover plate.It is formed certainly by portal frame and base cross members
Balance system.During test, system realizes automatic adjustment according to given load program, experiences testpieces by force snesor and holds
The axial load received, and computer is inputted as feedback signal, compared with given value, carry out control operation, departure warp
The range of servo valve control servo-cylinder changes, and adjusts the magnitude of load being added on testpieces.
In conclusion the hot external pressure test system and method for aircraft cargo tank structure disclosed by the invention is not required to consider that sealing is asked
Topic, can be improved success of the test rate, shortens the hot external pressure test preparatory period, improve heating efficiency, reduces empirical risk, makes ground
The hot external pressure test in face can simulate axial tensile loads and the flight environment of vehicle of more accurate simulated flight device, be the design of aircraft
It develops and more accurate data support is provided.
By verification experimental verification, pilot system of the present invention can be realized thermal force (room temperature~800 DEG C), axial load
The application of (- 100T~100T), outer compressive load (normal pressure~1MPa), test capability are applied according to heater heating efficiency, leather bag
Adding the ability of outer compressive load can further expand.Solve the problems, such as that external pressure test can not apply axial tensile loads and reduce
The risk of hot external pressure test.
The present invention is explained in detail above in conjunction with drawings and examples, but the present invention is not limited to above-mentioned implementations
Example, within the knowledge of a person skilled in the art, can also do without departing from the purpose of the present invention
Various change out, the content that is not described in detail can use the prior art in the present invention.
Claims (11)
1. a kind of hot external pressure test system of aircraft cargo tank structure, which is characterized in that loaded including thermal force loading system, external pressure
System, axial loading system；Thermal force loading system includes the heater (1) to testpieces (2) heating；External pressure loading system packet
It includes leather bag (3), it is identical as testpieces (2) outer wall shape, it is wrapped in testpieces (2) periphery, leather bag (3) pressure adjustable with the shape；Axis
It include servo-cylinder (4), connecting rod (5), flexural pivot (6) to loading system, servo-cylinder (4) is suspended on above testpieces (2), connecting rod
(5) connection servo-cylinders (4), a connection flexural pivot (6) start servo-cylinder (4), and connecting rod (5) is driven to move up and down,
Correspondingly flexural pivot (6) is driven to apply axial tension or pressure toward testpieces direction.
2. the hot external pressure test system of aircraft cargo tank structure as described in claim 1, which is characterized in that thermal force loading system
It further include temperature sensor, amplifier, computer heating control computer, temperature sensor is mounted on testpieces, and temperature sensor is put
Big device, computer heating control computer are sequentially connected and connect, and temperature sensor signal passes to computer heating control through amplifier amplifies signals and calculates
Machine.
3. the hot external pressure test system of aircraft cargo tank structure as described in claim 1 or 2 is any, which is characterized in that described to add
Hot device (1) is quartzy lamp group, is placed in testpieces (2), shape is irradiated with testpieces (2) inner wall to testpieces.
4. the hot external pressure test system of aircraft cargo tank structure as claimed in claim 3, which is characterized in that described in quartzy lamp group
Back position installs reflecting plate (10).
5. the hot external pressure test system of aircraft cargo tank structure as described in claim 1 or 2 is any, which is characterized in that described outer
The leather bag (2) of loading system is pressed to control pressure size by injecting or flowing out fluid.
6. the hot external pressure test system of aircraft cargo tank structure as claimed in claim 5, which is characterized in that external pressure load system
Include inlet and outlet on the leather bag (2) of system, be connected respectively with water inlet pipe and outlet pipe, water inlet pipe realizes pressure when filling the water
Rise, outlet pipe installs valve, control water flow outflow, control pressure decline.
7. the hot external pressure test system of aircraft cargo tank structure as claimed in claim 6, which is characterized in that external pressure load system
System further includes leather bag bracket, force snesor, is placed on leather bag bracket by the testpieces (2) that leather bag (3) are wrapped up, the leather bag support
Frame is fixed on ground, and force snesor is connect with water pipe, measures pressure.
8. the hot external pressure test system of aircraft cargo tank structure as described in claim 5 to 7 is any, which is characterized in that the skin
Capsule (3) and the contact surface of testpieces (2) install thermal insulation layer (7).
9. the hot external pressure test system of aircraft cargo tank structure as described in claim 1, which is characterized in that the axially loaded system
System further includes portal frame, base cross members, force snesor, lower cover plate, axial load computer；Portal frame is fixed on base cross members
On, testpieces lower end is fixed on base cross members, and servo-cylinder is hung under portal frame；The force snesor is mounted on servo-cylinder
On, and be connected with axial load computer；The flexural pivot includes bulb and upper cover plate, connecting rod lower end connecting ball head, ball
Head is fixed in upper cover plate, is uniformly pressed by upper cover plate.
10. the hot external pressure test system of aircraft cargo tank structure as described in claim 1, which is characterized in that further include measurement system
System, measuring system includes metering computer, data collection system, measurement sensor, and the signal that measurement sensor receives is through number
After acquiring according to acquisition system, it is transferred to metering computer.
11. a kind of hot external pressure test method of aircraft cargo tank structure, which is characterized in that process is as follows：
A1：Test installation, test adjustment；
A2：Heater applies thermal force, it is ensured that testpieces reaches assigned temperature；
A3：Apply external pressure and axial load simultaneously by leather bag and servo-cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810727938.1A CN108918582A (en) | 2018-07-05 | 2018-07-05 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810727938.1A CN108918582A (en) | 2018-07-05 | 2018-07-05 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108918582A true CN108918582A (en) | 2018-11-30 |
Family
ID=64424106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810727938.1A Pending CN108918582A (en) | 2018-07-05 | 2018-07-05 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108918582A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110361187A (en) * | 2019-08-21 | 2019-10-22 | 合肥工业大学 | A kind of flexible structure test pneumatic load test device |
| CN111397450A (en) * | 2020-04-23 | 2020-07-10 | 中国工程物理研究院总体工程研究所 | Warhead structure high-temperature test device and method for simulating flight heat load |
| CN112213088A (en) * | 2020-09-22 | 2021-01-12 | 上海航天精密机械研究所 | Cabin structure compression-shear coupling load test device |
| CN113504064A (en) * | 2021-07-09 | 2021-10-15 | 哈尔滨工业大学 | Online simulation driven aircraft structure thermodynamic combined test system and method |
| CN114722543A (en) * | 2022-06-09 | 2022-07-08 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN114778168A (en) * | 2022-06-17 | 2022-07-22 | 中国飞机强度研究所 | Method for determining loading stage number of breaking load in spacecraft cabin section ground strength test |
| CN115806058A (en) * | 2023-02-01 | 2023-03-17 | 天津航天瑞莱科技有限公司 | Thermal strength examination test device for aircraft conical cabin section joint |
| WO2024119534A1 (en) * | 2022-12-05 | 2024-06-13 | 浙江天铁实业股份有限公司 | Dynamic load monitoring pad apparatus, device, and load monitoring system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202693430U (en) * | 2012-07-03 | 2013-01-23 | 北京航空航天大学 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
| CN105300670A (en) * | 2014-07-28 | 2016-02-03 | 北京强度环境研究所 | Some part shaft/external pressure joint test load realization device |
| CN106556537A (en) * | 2016-11-21 | 2017-04-05 | 上海航天精密机械研究所 | A kind of special-shaped nacelle external pressure device |
-
2018
- 2018-07-05 CN CN201810727938.1A patent/CN108918582A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202693430U (en) * | 2012-07-03 | 2013-01-23 | 北京航空航天大学 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
| CN105300670A (en) * | 2014-07-28 | 2016-02-03 | 北京强度环境研究所 | Some part shaft/external pressure joint test load realization device |
| CN106556537A (en) * | 2016-11-21 | 2017-04-05 | 上海航天精密机械研究所 | A kind of special-shaped nacelle external pressure device |
Non-Patent Citations (1)
| Title |
|---|
| 张黎 等: "《弹（箭）结构热强度试验顶压式加载方法研究》", 《强度与环境》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110361187A (en) * | 2019-08-21 | 2019-10-22 | 合肥工业大学 | A kind of flexible structure test pneumatic load test device |
| CN111397450A (en) * | 2020-04-23 | 2020-07-10 | 中国工程物理研究院总体工程研究所 | Warhead structure high-temperature test device and method for simulating flight heat load |
| CN112213088A (en) * | 2020-09-22 | 2021-01-12 | 上海航天精密机械研究所 | Cabin structure compression-shear coupling load test device |
| CN113504064A (en) * | 2021-07-09 | 2021-10-15 | 哈尔滨工业大学 | Online simulation driven aircraft structure thermodynamic combined test system and method |
| CN114722543A (en) * | 2022-06-09 | 2022-07-08 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN114722543B (en) * | 2022-06-09 | 2022-08-12 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
| CN114778168A (en) * | 2022-06-17 | 2022-07-22 | 中国飞机强度研究所 | Method for determining loading stage number of breaking load in spacecraft cabin section ground strength test |
| CN114778168B (en) * | 2022-06-17 | 2022-09-02 | 中国飞机强度研究所 | Method for determining loading stage number of breaking load in aerospace plane cabin section ground strength test |
| WO2024119534A1 (en) * | 2022-12-05 | 2024-06-13 | 浙江天铁实业股份有限公司 | Dynamic load monitoring pad apparatus, device, and load monitoring system |
| CN115806058A (en) * | 2023-02-01 | 2023-03-17 | 天津航天瑞莱科技有限公司 | Thermal strength examination test device for aircraft conical cabin section joint |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108918582A (en) | A kind of hot external pressure test system and method for aircraft cargo tank structure | |
| US8413521B2 (en) | Apparatus and method for over-peak loading for creep-rupture testing | |
| CA3090105C (en) | Multi-load-mode frost heave tester for unsaturated soil and method for_testing amount of frost heave | |
| CN108375507A (en) | Quick changeable temperature couples the concrete for hydraulic structure hydraulic fracture device and method under complex stress condition | |
| CN104990795A (en) | A testing apparatus for rock and soil sample accelerated dry-wet cycle under load and test method thereof | |
| KR101866089B1 (en) | The sealing test apparatus using the motor for the wind tunnel testing model | |
| CN112684109A (en) | High-temperature and high-pressure drilling fluid inhibition evaluation device and application method thereof | |
| CN203858160U (en) | Fertilizer caking testing device | |
| CN104849149B (en) | A kind of polymer thermal insulative material at high temperature hydrostatic performance simulation experiment method | |
| CN106950249A (en) | The analysis experimental provision of rock thermal conductivity is tested under a kind of simulation different pressures | |
| CN115655909A (en) | CO (carbon monoxide) 2 Simulation device and method for phase change stratum response in injection process | |
| CN105157975B (en) | The method that ring axial compression displacement deflection is obturaged in control and measurement | |
| CN109883837A (en) | A kind of the Model Pile tester and its test method of controllable soil temperature | |
| CN105651970A (en) | Temperature control soil expansion instrument | |
| CN103489492A (en) | Passive water level testing device and testing method | |
| CN106525567B (en) | Rock aging deformation test system under combined action of continuous water environment and variable temperature | |
| CN110068510B (en) | Concrete thermal stress testing arrangement in conflagration high temperature | |
| CN210514029U (en) | Experimental device for evaluating water lock damage of tight sandstone gas reservoir | |
| CN112229871A (en) | Thermal contact resistance testing device and method | |
| CN112098231A (en) | Large triaxial mechanical test device and test method for simulating freeze-thaw cycle coarse-grained soil | |
| CN108254252A (en) | A kind of device and method for aviation conduit tube component stress corrosion (cracking) test | |
| CN110749499A (en) | Temperature control device and method for single-shaft compression test | |
| CN105628500B (en) | A kind of temperature coefficient test system of rock thermal insulation STRESS VARIATION | |
| CN204731103U (en) | Under a kind of load action, ground sample accelerates the test unit of drying and watering cycle | |
| CN108037019A (en) | A kind of experimental system for the test of composite material mechanical behavior under high temperature |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181130 |