CN111762337A - Loading method and loading device for fatigue test of aircraft engine frame - Google Patents
Loading method and loading device for fatigue test of aircraft engine frame Download PDFInfo
- Publication number
- CN111762337A CN111762337A CN202010644399.2A CN202010644399A CN111762337A CN 111762337 A CN111762337 A CN 111762337A CN 202010644399 A CN202010644399 A CN 202010644399A CN 111762337 A CN111762337 A CN 111762337A
- Authority
- CN
- China
- Prior art keywords
- loading
- main beam
- loading device
- frame
- lower main
- 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
- 238000011068 loading method Methods 0.000 title claims abstract description 148
- 238000009661 fatigue test Methods 0.000 title claims abstract description 29
- 230000005484 gravity Effects 0.000 claims abstract description 18
- 238000005452 bending Methods 0.000 claims description 25
- QNRATNLHPGXHMA-XZHTYLCXSA-N (r)-(6-ethoxyquinolin-4-yl)-[(2s,4s,5r)-5-ethyl-1-azabicyclo[2.2.2]octan-2-yl]methanol;hydrochloride Chemical compound Cl.C([C@H]([C@H](C1)CC)C2)CN1[C@@H]2[C@H](O)C1=CC=NC2=CC=C(OCC)C=C21 QNRATNLHPGXHMA-XZHTYLCXSA-N 0.000 claims description 3
- 229910003460 diamond Inorganic materials 0.000 claims description 2
- 239000010432 diamond Substances 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 229910000797 Ultra-high-strength steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A loading method and a loading device for an aircraft engine frame fatigue test are disclosed, wherein a truss structure of the loading device is provided with a plurality of hoisting points which respectively simulate the connection of an aircraft engine and an engine frame; the loading device meets the real gravity center position of the engine, simulates the real connection relation between the engine and the engine frame, more accurately simulates the loading condition of the engine frame in the flying process of the airplane, and effectively improves the reliability and the authenticity of a test result.
Description
Technical Field
The patent relates to the field of airplane design, further relates to an engine mount fatigue test technology, and particularly discloses an airplane engine mount fatigue test loading method and loading device.
Background
The aircraft flies and is powered by an engine which is connected with the aircraft by an engine frame. The engine mount is an important bearing component of the airplane and bears complex load in the use process. The engine frame generally adopts ultra-high strength steel, and this kind of material breach sensitivity is high, and the crack detectable rate is low, and crack propagation rate is fast, in order to guarantee aircraft security and reliability, discovers the tired weak link of engine frame and the position that probably ftractures in early stage, need carry out engine frame fatigue test, consequently need design engine frame fatigue test loading device.
During the takeoff, climbing, flat flying, gliding and landing taxiing of the airplane, the engine frame can bear course load, vertical load, lateral load, course bending moment, vertical bending moment and lateral bending moment due to the change of the thrust of the engine and the change of the vibration environment in the air.
At present, the widely used engine frame fatigue test device is mostly an integrated rigid square box, the gravity center is inconsistent with the gravity center of the engine, the actual weight of the engine is larger, the change of the gravity center position can influence the load, according to the fatigue strength theory, the load is deviated by 15 percent, the fatigue life can be deviated by 1 time, the widely used engine frame fatigue test device applies the concentrated force of the course load, the vertical load and the lateral load during the fatigue test, only the course load, the main elements of the vertical load and the lateral load are considered, the course bending moment, the secondary elements of the vertical bending moment and the lateral bending moment are ignored, and the loading load of the fatigue test is not comprehensive.
Disclosure of Invention
In order to overcome the defects in the prior art and meet the requirements of airplane research and development, the application aims to provide a loading method and a loading device for an airplane engine frame fatigue test.
A loading method for an aircraft engine frame fatigue test is characterized by comprising the following steps: 1) the loading device is provided with a truss structure, the gravity center of the loading device is consistent with that of the engine, and the connection mode of the loading device and the engine frame simulates the connection mode of the aircraft engine and the engine frame; 2) a plurality of hoisting points are arranged on a truss structure of the loading device and respectively simulate the connection between an aircraft engine and an engine frame; 3) the loading device comprises a loading device, a truss structure, a plurality of course loading supports, a plurality of vertical loading supports and a lateral loading support, wherein the plurality of course loading supports, the plurality of vertical loading supports and the lateral loading support are arranged on the truss structure of the loading device, course load and vertical bending moment are applied to the loading device through the course loading supports, vertical load and lateral bending moment are applied to the loading device through the vertical loading supports, and lateral load and course bending moment are applied to the loading device through the lateral loading supports, and are respectively used for simulating the loading condition of the engine frame in.
The application also provides a loading device for the fatigue test of the aircraft engine frame, which is characterized in that the body of the loading device is of a truss structure, the gravity center of the loading device is consistent with that of an engine, the connection mode of the loading device and the engine frame simulates the connection mode of the aircraft engine and the engine frame, the truss structure of the loading device comprises an upper main beam and a lower main beam, the upper main beam and the lower main beam are connected through a front longitudinal beam, a middle longitudinal beam and a rear longitudinal beam, a transverse lower middle beam perpendicular to the lower main beam and the middle longitudinal beam is arranged in the middle of the lower main beam, the center of the lower middle beam and the axle center of the middle longitudinal beam are coaxial with the gravity center of the loading device, a rhombic front supporting frame is formed at the front ends of the upper main beam and the lower main beam and on two sides of the front longitudinal beam through four supporting beams, a triangular middle supporting frame is formed at the middle part of the upper main, the two ends of the lower middle beam are respectively connected with the front end of the lower main beam and the rear end of the lower main beam through inclined beams, and the front supporting frame and the middle supporting frame are respectively connected through inclined beams; the top of the center of the front support frame is provided with a front lifting point of a loading device, the tops of the two side ends of the front support frame are respectively provided with a side lifting point of the loading device, and the top of the rear longitudinal beam is provided with a rear lifting point of the loading device at the rear end of the upper main beam; a course loading support is arranged at the front end of the lower main beam on the front support frame, and a course loading support is respectively arranged at the front sides of the end heads at the two sides of the lower middle beam on the middle support frame; three vertical loading supports are arranged at the lower end of the middle part of the lower main beam along the axis of the lower main beam, wherein the middle vertical loading support is coaxial with the center of gravity of the middle longitudinal beam and the loading device; and a lateral loading support is arranged on one side of the middle support frame and on the outer side of the end head of the lower middle beam.
When the fatigue test of the aircraft engine frame is carried out, the engine frame is fixed at first, and then the engine frame is connected with an engine mounting interface on the engine frame through a front lifting point, a rear lifting point and a side lifting point of a loading device. And then, a course load, a vertical bending moment, a vertical load, a lateral bending moment, a lateral load and a course bending moment are applied to the lateral loading support, the course loading support and the vertical loading support of the loading device through the loading actuating cylinders respectively, and the load is controlled by using a plurality of loading actuating cylinders in a combined manner so as to simulate various stress conditions of the engine frame.
The beneficial effect of this application is: 1) the test loading device is connected with the engine frame in the same connection mode of the engine and the engine frame, and the fatigue test constraint condition is the same as the real constraint condition of the airplane; 2) the gravity center of the test loading device is consistent with that of the engine, so that the influence of the change of the gravity center of the engine on the fatigue test load is avoided, and the test effect is more real; 3) the test loading device can apply load and bending moment in the course, the vertical direction and the lateral direction, can simulate simple and complex stress conditions, and ensures that the test effect is more comprehensive.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic side view of a loading device for a fatigue test of an aircraft engine mount.
Fig. 2 is a left side view structural schematic diagram of the fatigue test loading device for the aircraft engine mount.
FIG. 3 is a schematic top view of the loading device for the fatigue test of the aircraft engine mount.
The numbering in the figures illustrates: the device comprises an upper main beam 1, a lower main beam 2, a front longitudinal beam 3, a middle longitudinal beam 4, a rear longitudinal beam 5, a middle lower beam 6, a supporting beam 7, an oblique beam 8, a front hoisting point 9, a rear hoisting point 10, a side hoisting point 11, a course loading support 12, a lateral loading support 13 and a vertical loading support 14.
Detailed Description
Referring to the attached drawings, the loading device for the fatigue test of the aircraft engine frame is connected with the aircraft engine frame and used for simulating the fatigue load of the aircraft engine on the engine frame, the body of the loading device is of a truss structure, the gravity center of the loading device is consistent with that of the engine, the connection mode of the loading device and the engine frame simulates the connection mode of the aircraft engine and the engine frame, the truss structure of the loading device comprises an upper main beam 1 and a lower main beam 2, the upper main beam 1 and the lower main beam 2 are parallel to each other, the upper main beam 1 and the lower main beam 2 are connected through a front longitudinal beam 3, a middle longitudinal beam 4 and a rear longitudinal beam 5, a transverse middle lower beam 6 perpendicular to the lower main beam 2 and the middle longitudinal beam 4 is arranged in the middle of the lower main beam 2, and the center of the middle longitudinal beam 6 and the center of the middle longitudinal beam 4. A rhombic front support frame is formed at the front ends of an upper main beam 1 and a lower main beam 2 and on two sides of a front longitudinal beam 3 through four support beams 7, a triangular middle support frame is formed at the middle part of the upper main beam 1 and on two sides of a middle longitudinal beam 4 by respectively connecting one support beam 7 with two ends of a lower middle beam 6, the front support frame and the middle support frame are perpendicular to the upper main beam 1 and the lower main beam 2, two ends of the lower middle beam 6 are respectively connected with the front end of the lower main beam 2 and the rear end of the lower main beam 2 through oblique beams 8, and the oblique beams 8 are respectively connected between the front support frame and the middle support frame; on the front support frame, the top end of the front longitudinal beam 3 is provided with a front lifting point 9 of a loading device, the top end parts of the support beams on the two sides of the front support frame are respectively provided with a side lifting point 11 of the loading device, the top of the rear longitudinal beam 5 is provided with a rear lifting point 10 of the loading device at the rear end of the upper main beam 1, and the front lifting point 9, the rear lifting point 10 and the two side lifting points 11 respectively simulate the connection of an aircraft engine and an engine frame.
On the front supporting frame, the front end of the lower main beam 2 is provided with a course loading support 12, and on the middle supporting frame, the front sides of the end heads on the two sides of the lower middle beam 6 are respectively provided with a course loading support 12; and applying a heading load and a vertical bending moment to the loading device through the three heading loading supports 12. Three vertical loading supports 14 are arranged at the lower end of the middle part of the lower main beam 2 along the axis of the lower main beam, wherein the middle vertical loading support 14 is coaxial with the center of gravity of the middle longitudinal beam 4 and the loading device; vertical loads and lateral bending moments are applied to the loading device through the three vertical loading supports 14. And a lateral loading support 13 is arranged on one side of the middle support frame and on the outer side of the end head of the lower middle beam 6, and lateral loads and heading bending moments are applied to the loading device through the lateral loading support. The loading device is applied with the course load and the vertical bending moment, and the vertical load and the lateral bending moment as well as the lateral load and the course bending moment are applied, so that the loading condition of the engine frame in the flight process of the airplane is fully simulated, the load borne by the engine frame is ensured to be consistent with the actual condition, and the reliability and the authenticity of the test result are improved.
In implementation, the upper main beam is formed by oppositely welding two channel steels, the rear part of each channel steel is provided with a rectangular notch, the front end part of the upper main beam is welded with a front plugging plate, the lower main beam is positioned right below the upper main beam and is respectively welded with the front part, the middle part and the rear part of the upper main beam through a front longitudinal beam, a middle longitudinal beam and a rear longitudinal beam; the supporting beams of the front supporting frame are four square tubes and are arranged in a diamond shape, the inner sides of the two square tubes at the upper part are welded on the two sides of the front part of the upper main beam, the inner sides of the two square tubes at the lower part are welded on the two sides of the front part of the lower main beam, and the outer sides of the two square tubes arranged at the same side are welded together; the lower middle beam 6 comprises two square tubes which are welded on the left side and the right side of the lower main beam 2 respectively and located at the welding position of the middle longitudinal beam 4, the supporting beams of the middle supporting frame are two square tubes which are located on the two sides of the middle longitudinal beam respectively, the upper ends of the square tubes are connected with the middle side of the upper main beam, and the lower ends of the square tubes are connected with the outer side end of the lower middle beam 6 to form a triangular structure.
When the fatigue test of the airplane engine frame is carried out, the engine frame is fixed at first, and then the engine frame is connected with an engine mounting interface on the engine frame through a front lifting point 9, a rear lifting point 10 and a side lifting point 11 of a loading device. And then a course load, a vertical bending moment, a vertical load, a lateral bending moment, a lateral load and a course bending moment are respectively applied to a course loading support 12, a vertical loading support and a lateral loading support 14 of the loading device through the loading actuating cylinders, and the load is controlled by using a plurality of loading actuating cylinders in a combined manner so as to simulate various stress conditions of the engine frame.
Claims (7)
1. A loading method for an aircraft engine frame fatigue test is characterized by comprising the following steps: 1) the loading device is provided with a truss structure, the gravity center of the loading device is consistent with that of the engine, and the connection mode of the loading device and the engine frame simulates the connection mode of the aircraft engine and the engine frame; 2) a plurality of hoisting points are arranged on a truss structure of the loading device and respectively simulate the connection between an aircraft engine and an engine frame; 3) the loading device comprises a loading device, a truss structure, a plurality of course loading supports, a plurality of vertical loading supports and a lateral loading support, wherein the plurality of course loading supports, the plurality of vertical loading supports and the lateral loading support are arranged on the truss structure of the loading device, course load and vertical bending moment are applied to the loading device through the course loading supports, vertical load and lateral bending moment are applied to the loading device through the vertical loading supports, and lateral load and course bending moment are applied to the loading device through the lateral loading supports, and are respectively used for simulating the loading condition of the engine frame in.
2. The loading method for the fatigue test of the engine mount of the airplane as claimed in claim 1, wherein the truss structure of the loading device comprises an upper main beam and a lower main beam, the upper main beam and the lower main beam are connected through a front longitudinal beam, a middle longitudinal beam and a rear longitudinal beam, a transverse lower middle beam vertical to the lower main beam and the middle longitudinal beam is arranged in the middle of the lower main beam, the center of the lower middle beam and the axle center of the middle longitudinal beam are coaxial with the gravity center of the loading device, a rhombic front supporting frame is formed at the front ends of the upper main beam and the lower main beam and at the two sides of the front longitudinal beam through four supporting beams, a supporting beam is respectively arranged at the two sides of the middle longitudinal beam in the middle of the upper main beam to form a triangular middle supporting frame with the two ends of the lower middle beam connected, the two ends of the lower middle beam are respectively connected with the front end of the lower main beam and the rear end of the lower main beam through oblique beams, and the front supporting frame and the middle supporting frame are respectively connected through the oblique beams.
3. An aircraft engine mount fatigue test loading method according to claim 1 or 2, wherein a front lifting point of the loading device is provided at the top of the center of the front support frame, side lifting points of the loading device are provided at the tops of both side ends of the front support frame, respectively, and a rear lifting point of the loading device is provided at the top of the rear longitudinal beam at the rear end of the upper main beam.
4. An aircraft engine mount fatigue test loading method according to claim 1 or 2, wherein a heading loading support is provided at the front end of the lower main beam on the front support frame, and a heading loading support is provided at each of the front sides of the ends of the lower middle beam on both sides on the middle support frame.
5. An aircraft engine mount fatigue test loading method according to claim 1 or 2, wherein three vertical loading supports are arranged at the lower end of the middle part of the lower main beam along the axis of the lower main beam, wherein the middle vertical loading support is coaxial with the center of gravity of the middle longitudinal beam and the loading device.
6. An aircraft engine mount fatigue test loading method as defined in claim 1 or 2, wherein a lateral loading support is provided on one side of the center support frame and outside the lower center sill end.
7. A loading device for an aircraft engine frame fatigue test is characterized in that a body of the loading device is of a truss structure, the gravity center of the loading device is consistent with that of an engine, the connection mode of the loading device and an engine frame simulates the connection mode of the aircraft engine and the engine frame, the truss structure of the loading device comprises an upper main beam and a lower main beam, the upper main beam and the lower main beam are connected through a front longitudinal beam, a middle longitudinal beam and a rear longitudinal beam, a transverse middle longitudinal beam perpendicular to the lower main beam and the middle longitudinal beam is arranged in the middle of the lower main beam, the center of the lower middle longitudinal beam and the axis of the middle longitudinal beam are coaxial with the gravity center of the loading device, a diamond front supporting frame is formed at the front ends of the upper main beam and the lower main beam and at the two sides of the front longitudinal beam through four supporting beams, a supporting beam is respectively arranged in the middle of the upper main beam and at the two, the two ends of the lower middle beam are respectively connected with the front end of the lower main beam and the rear end of the lower main beam through inclined beams, and the front supporting frame and the middle supporting frame are respectively connected through inclined beams; the top of the center of the front support frame is provided with a front lifting point of a loading device, the tops of the two side ends of the front support frame are respectively provided with a side lifting point of the loading device, and the top of the rear longitudinal beam is provided with a rear lifting point of the loading device at the rear end of the upper main beam; a course loading support is arranged at the front end of the lower main beam on the front support frame, and a course loading support is respectively arranged at the front sides of the end heads at the two sides of the lower middle beam on the middle support frame; three vertical loading supports are arranged at the lower end of the middle part of the lower main beam along the axis of the lower main beam, wherein the middle vertical loading support is coaxial with the center of gravity of the middle longitudinal beam and the loading device; and a lateral loading support is arranged on one side of the middle support frame and on the outer side of the end head of the lower middle beam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010644399.2A CN111762337A (en) | 2020-07-06 | 2020-07-06 | Loading method and loading device for fatigue test of aircraft engine frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010644399.2A CN111762337A (en) | 2020-07-06 | 2020-07-06 | Loading method and loading device for fatigue test of aircraft engine frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111762337A true CN111762337A (en) | 2020-10-13 |
Family
ID=72723924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010644399.2A Pending CN111762337A (en) | 2020-07-06 | 2020-07-06 | Loading method and loading device for fatigue test of aircraft engine frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111762337A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461525A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Unmanned helicopter engine mounting bracket test device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160039527A1 (en) * | 2014-08-08 | 2016-02-11 | Mitsubishi Aircraft Corporation | Aircraft and method for mounting device to be installed outside aircraft onto airframe |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| US10053238B1 (en) * | 2017-02-21 | 2018-08-21 | The Boeing Company | Fixture, system, and method for testing loads in a flexible aerodynamic member |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN110595750A (en) * | 2019-09-19 | 2019-12-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Loading device for wing hanging joint |
| CN111003200A (en) * | 2019-11-20 | 2020-04-14 | 中国飞机强度研究所 | Fatigue test device for outer front flap and joint test piece |
-
2020
- 2020-07-06 CN CN202010644399.2A patent/CN111762337A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160039527A1 (en) * | 2014-08-08 | 2016-02-11 | Mitsubishi Aircraft Corporation | Aircraft and method for mounting device to be installed outside aircraft onto airframe |
| US10053238B1 (en) * | 2017-02-21 | 2018-08-21 | The Boeing Company | Fixture, system, and method for testing loads in a flexible aerodynamic member |
| CN107651216A (en) * | 2017-10-23 | 2018-02-02 | 重庆通用航空产业集团有限公司 | Engine loading device and method applied to single-shot fixed wing aircraft slow test |
| CN108528758A (en) * | 2018-05-04 | 2018-09-14 | 中电科芜湖钻石飞机制造有限公司 | General-purpose aircraft mechanical property testing system |
| CN110595750A (en) * | 2019-09-19 | 2019-12-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Loading device for wing hanging joint |
| CN111003200A (en) * | 2019-11-20 | 2020-04-14 | 中国飞机强度研究所 | Fatigue test device for outer front flap and joint test piece |
Non-Patent Citations (2)
| Title |
|---|
| 付友波等: "机翼吊挂结构设计技术研究", 《现代制造技术与装备》, no. 04, 15 April 2020 (2020-04-15), pages 97 - 99 * |
| 霍文辉等: "安装框架地面标定方法研究", 《科技与创新》, no. 01, 5 January 2020 (2020-01-05), pages 88 - 89 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461525A (en) * | 2020-11-20 | 2021-03-09 | 中国直升机设计研究所 | Unmanned helicopter engine mounting bracket test device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108238282B (en) | Central wing box test equipment | |
| CN101726401B (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN103376193A (en) | System and method for ground vibration testing and weight and balance measurement | |
| CN207570942U (en) | A kind of tail undercarriage damper leg erection joint fatigue experimental device | |
| CN108528758B (en) | Universal aircraft mechanical property test system | |
| CN105716888A (en) | Aerofoil box segment test device and method | |
| CN202485908U (en) | Engine loading simulated sample for static test of airplane | |
| CN111762337A (en) | Loading method and loading device for fatigue test of aircraft engine frame | |
| CN106996873A (en) | A kind of heavy vehicle frame road imitation tester | |
| CN103630346B (en) | The emergent dialysis pin testing stand of a kind of undercarriage and test method thereof | |
| CN113740181A (en) | Wing oil tank wall plate impact test system and test method thereof | |
| CN103593515B (en) | A kind of load design method of pylon of aircraft | |
| CN210071501U (en) | Fatigue test device for main landing gear beam of airplane | |
| CN106769543A (en) | A kind of composite material spar docking structure shearing performance test devices and methods therefor | |
| CN114295401B (en) | Truss structure loading device and method for static test of spacecraft cabin propulsion module | |
| CN110228603B (en) | Static test end frame for simulating aircraft air state | |
| CN217673291U (en) | Aircraft pod static test loading device | |
| CN210014888U (en) | Whole-airplane strength and modal test frame device of fixed-wing airplane | |
| CN114056537B (en) | Main bearing structure of fuselage in unmanned high-speed helicopter | |
| CN222663780U (en) | Aircraft rudder surface test device | |
| CN217945557U (en) | Flight control semi-physical simulation test bed | |
| CN115950315B (en) | A double-track rocket sled aerodynamic shape structure suitable for hypersonic speed | |
| CN203601581U (en) | Loading test assembly | |
| CN117602099A (en) | Device and method for testing typical connection structure of vertical stabilizer and fuselage | |
| CN204964176U (en) | Aircraft accessory drive casing analogue means |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20201013 |
|
| WD01 | Invention patent application deemed withdrawn after publication |