CN110595755A - Main landing gear loading test device with single wheel and inclined angle - Google Patents
Main landing gear loading test device with single wheel and inclined angle Download PDFInfo
- Publication number
- CN110595755A CN110595755A CN201910937663.9A CN201910937663A CN110595755A CN 110595755 A CN110595755 A CN 110595755A CN 201910937663 A CN201910937663 A CN 201910937663A CN 110595755 A CN110595755 A CN 110595755A
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- wheel
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a single-wheel main landing gear loading test device with an inclination angle, which comprises a left-side wheel dummy member (1) and a vertical loading joint (3), the right wheel dummy part (2) is sequentially arranged on an axle (0-1) of the main landing gear, the left wheel dummy part and the right wheel dummy part are fixed together and locked along the axial direction, the distance from a mounting hole (2-2) on the left wheel dummy part and a mounting hole (2-1) on the right wheel dummy part to an axle center hole (2-1) is equal to the distance from a tire touch point to the axle, a polished rod (6-1) of an outward extending fork lug (6) penetrates through the mounting hole (2-2), a course loading joint (5) is fixed on the polished rod (6-1), a lateral loading joint (4) is connected with the wheel dummy part through a lug piece (6-2) of the outward extending fork lug, and the right wheel dummy part is connected with a brake disc (0-4) of. The loading test device can simulate the structure and the loaded characteristics of the airplane wheel more truly and accurately, simplifies the design of a three-way loading structure, is simple and practical, and is mutually coordinated and non-interfered in loading in three directions.
Description
Technical Field
The invention belongs to the helicopter main undercarriage fatigue test technology, and relates to a main undercarriage loading test device with a single wheel with an inclination angle.
Background
Landing gear is a key hydraulic component on a helicopter and is subjected to large loads during landing and taxiing of the helicopter. Each flight of the helicopter is subjected to a process of periodically changing load action from take-off to landing, and the strength and the flight safety of the helicopter are directly influenced by the performance of the helicopter. Therefore, the stress state in flight needs to be simulated during the fatigue test, and the three-way load is applied to the main landing gear.
This type of main landing gear is fitted with a tyre which is inclined at an angle to the vertical and the three load points are concentrated at one place (the tyre touchdown point) during the test. For the landing gear with special structure and complicated stress condition, the prior loading design method cannot be used for reference.
Disclosure of Invention
In view of the above situation in the prior art, the invention aims to provide a main landing gear loading test device with a single wheel with an inclination angle, which is used for a main landing gear fatigue test, has a stable structure and reliable performance, and can well meet the test requirements.
The above object of the present invention is achieved by the following technical solutions:
a loading test device for a main landing gear with a single wheel having an inclination angle comprises a left dummy wheel component, a right dummy wheel component, a vertical loading joint, a lateral loading joint, a course loading joint and an outward extending fork lug, wherein the left dummy wheel component, the vertical loading joint and the right dummy wheel component are sequentially arranged on a wheel shaft of the main landing gear, the left dummy wheel component and the right dummy wheel component are fixed together and axially locked, the left dummy wheel component and the right dummy wheel component are respectively provided with a mounting hole, the distance from the mounting hole to the center of the wheel shaft is equal to the distance from a tire touch point to the wheel shaft, a polished rod of an outward extending fork lug penetrates through the mounting holes of the left dummy wheel component and the right dummy wheel component, the outward extending fork lug is fixed on the dummy airplane wheel component, the course loading joint is fixed on a polished rod of the outward extending fork lug, the lateral loading joint is connected with the dummy airplane wheel component through the lug piece of the outward extending fork lug, and the dummy airplane wheel component on the right side is connected with a brake disc of the undercarriage.
The vertical loading joint is used for applying vertical load and comprises a left shoulder bush, a right shoulder bush, a joint bearing and a loading handle, wherein the joint bearing is arranged in a hole of the loading handle, and the left shoulder bush and the right shoulder bush are inlaid on two sides of an inner hole of the joint bearing through an assembling relation. Additionally, the location of the load point of the vertical load joint on the axle is determined by the width of the left and right shoulder bushings of the vertical load joint. The left dummy wheel component and the right dummy wheel component are fixed together through a locking nut, a fixed long bushing and a fixed bolt. The course loading joint is fixed on the polish rod of the outward extending fork lug through two short bushings. The dummy wheel is axially locked by a bush and a lock nut on the landing gear.
The main undercarriage loading test device with the single wheel having the inclination angle can simulate the structure and the loaded characteristics of the wheel more truly and accurately, simplifies the design of a three-way loading structure, is simple and practical, and is free from mutual interference and coordination of loading in three directions.
Drawings
FIG. 1 is a schematic three-way loading of a main landing gear with a single wheel having an inclination angle;
FIG. 2 is a cross-sectional view showing the structure of the main landing gear load test apparatus for a single wheel with inclination angle of the present invention;
FIG. 3 is an isometric view showing the configuration of the main landing gear load test apparatus of the present invention with a single wheel having an angle of inclination;
FIG. 4 is a front (left) and side (right) view schematically illustrating the structure of a main landing gear with a single wheel having an inclination angle;
FIG. 5 is a block diagram showing a vertical load joint;
FIG. 6 is a cross-sectional view of a vertical load joint;
FIG. 7 is a block diagram of the right side wheel dummy;
FIG. 8 is a schematic view of an outrigger ear configuration.
Detailed Description
The main landing gear loading test device for single-wheel belt inclination angle of the invention is clearly and completely described in connection with the embodiment of the invention by referring to the attached drawings.
FIG. 1 is a schematic three-way loading diagram of a main landing gear with a single wheel having an inclination angle. As shown, the tire is inclined at an angle to the vertical and the three load points are concentrated at one location (tire touchdown point) during the test. For the landing gear with special structure and complicated stress condition, the prior loading design method cannot be used for reference.
Fig. 2 and 3 show the structure of the main landing gear loading test device with inclination angle of single wheel of the invention. As shown in the figure, the single-wheel main landing gear loading test device with the inclination angle comprises a left dummy wheel component 1, a right dummy wheel component 2, a vertical loading joint 3, a lateral loading joint 4, a course loading joint 5 and an outward extending fork lug 6. The left dummy wheel assembly 1, the vertical loading joint 3 and the right dummy wheel assembly 2 are sequentially arranged on an axle 0-1 of the main undercarriage and are arranged in the undercarriage through the matching relation of cylindrical surfaces of the axles, and the positions of the left dummy wheel assembly 1 and the right dummy wheel assembly 3 on the axles completely simulate the positions of two rolling bearings on wheels. The left dummy wheel and the right dummy wheel are fixed together by a locking nut 7, a fixed long bush 8 and a fixed bolt 9 to form an assembly similar to the wheel of the main landing gear. The dummy wheel is locked in the direction of the wheel axle by using a bush 0-2 and a lock nut 0-3 (see figure 4) on the landing gear, so that the axial movement of the dummy wheel is restrained.
The vertical loading joint 3 is a joint for applying vertical load and consists of a left shoulder bush 3-1, a right shoulder bush 3-2, a joint bearing 3-3 and a loading handle 3-4, wherein the joint bearing 3-3 is arranged in a hole of the loading handle 3-4, and the left shoulder bush 3-1 and the right shoulder bush 3-2 are inlaid on two sides of an inner hole of the joint bearing through an assembling relation (see figures 5 and 6). The loading point of the vertical load is a tire touch point (as shown in figure 1), the loading points of the three loads are concentrated in one place, the clamps are easy to interfere with each other, and in order to simplify the mechanism, the vertical load is translated upwards to the wheel shaft along the stress direction. The location of the load point on the axle is matched by the width of the shouldered bushings 3-1, 3-2 of the vertical load joint. The joint bearing 3-3 can flexibly rotate, automatically adapt to the angle between the load direction and the wheel shaft, and eliminate the influence of the change of an included angle caused by the inclination of the wheel shaft.
Figure 7 is a block diagram of the right side wheel dummy. The distance between the contact point of the tire and the wheel axle is set to be L, the right wheel dummy is provided with a mounting hole 2-2, the distance between the hole 2-2 and the hole 2-1 is equal to the distance L, and the left wheel dummy is also provided with a similar hole, so that the actual distance L between the loading point of the course and the lateral load and the wheel axle is truly simulated. (ii) a
FIG. 8 is a schematic view of an outrigger ear configuration. As shown in fig. 8, the polish rod 6-1 of the outrigger 6 passes through the mounting holes 2-2 of the left and right dummy airplane members, and the outrigger 6 is fixed on the dummy airplane member through the mounting holes 2-2 of the left and right dummy airplane members. Then the course loading joint 5 is fixed on the polished rod 6-1 of the outward extending fork lug through two short bushings 10, and the lateral loading joint 4 is connected with the dummy wheel through the lug 6-2 of the outward extending fork lug, so that the course and lateral loading mechanism is set. The lateral loading joint 4 and the course loading joint 5 are in threaded connection with the loading actuator, and the load of the actuator is transmitted.
Finally, 6 threaded holes 2-3 are formed in a flange plate of the wheel dummy piece on the right side, and the wheel dummy piece can be prevented from rotating around a wheel shaft when being loaded by connecting the wheel anti-rotation bolt 11 with a brake disc 0-4 (see figure 4) of the undercarriage.
In the test process, load is applied through the actuator and the sensor, and the load is respectively transmitted to the main undercarriage through the three loading joints. Through the test device, three-way loads can be loaded, and the structure is stable, the mutual noninterference and the loading central points are consistent.
Due to the structure, the main undercarriage loading test device with the single wheel having the inclination angle can accurately simulate boundary conditions, is flexible in mechanism, stable in loading and good in test environment, the total test error can be controlled within 3%, and when the loading device loads the undercarriage, stable loading, balanced stress, coordinated in structure and better in data of the wheels can be realized.
Claims (8)
1. A main landing gear loading test device with a single wheel having an inclination angle comprises a left wheel dummy member (1), a right wheel dummy member (2), a vertical loading joint (3), a lateral loading joint (4), a course loading joint (5) and an outward extending fork lug (6), wherein the left wheel dummy member (1), the vertical loading joint (3) and the right wheel dummy member (2) are sequentially arranged on a wheel shaft (0-1) of the main landing gear, the left and right wheel dummy members are fixed together and axially locked, mounting holes (2-2) are respectively arranged on the left and right wheel dummy members, the distance from the mounting holes (2-2) to a central hole (2-1) of the wheel shaft is equal to the distance from a ground contact point of a tire to the wheel shaft, a polished rod (6-1) of the outward extending fork lug (6) penetrates through the mounting holes (2-2) of the left and right wheel dummy members, the overhanging fork lug (6) is fixed on the dummy wheel component, the course loading joint (5) is fixed on a polished rod (6-1) of the overhanging fork lug, the lateral loading joint (4) is connected with the dummy wheel component through a lug piece (6-2) of the overhanging fork lug, and the dummy wheel component on the right side is connected with a brake disc (0-4) of the undercarriage.
2. The load test device according to claim 1, wherein the vertical load joint (3) is composed of a left shoulder bush (3-1), a right shoulder bush (3-2), a knuckle bearing (3-3) and a load handle (3-4), the knuckle bearing (3-3) is installed in a hole of the load handle (3-4), and the left and right shoulder bushes (3-1, 3-2) are embedded on two sides of an inner hole of the knuckle bearing (3-3) through an assembling relation.
3. The load test apparatus according to claim 2, wherein the location of the load point of the vertical load joint (3) on the axle is determined by the width of the right and left shoulder bushings (3-1, 3-2) of the vertical load joint.
4. The loading test device according to claim 1, wherein the left and right dummy wheel assemblies are fixed together by a lock nut (7), a fixed long bush (8) and a fixed bolt (9).
5. The load test apparatus according to claim 1, wherein the heading load joint (5) is fixed to the polished rod (6-1) of the outrigger lug by two short bushings (10).
6. The loading test rig according to claim 1, wherein the dummy wheel is axially locked by means of a bushing (0-2) on the landing gear and a lock nut (0-3).
7. A loading test apparatus according to claim 1, wherein the flange of the right dummy wheel is connected to the brake discs (0-4) of the landing gear by means of wheel rotation preventing bolts (11).
8. The loading test device according to claim 1, wherein the dummy wheel is axially locked by a bushing (0-2) and a lock nut (0-3) on the undercarriage, and the flange of the dummy wheel on the right side is connected with a brake disc (0-4) of the undercarriage by a wheel rotation preventing bolt (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910937663.9A CN110595755B (en) | 2019-09-29 | 2019-09-29 | Main landing gear loading test device with single wheel and inclined angle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910937663.9A CN110595755B (en) | 2019-09-29 | 2019-09-29 | Main landing gear loading test device with single wheel and inclined angle |
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| Publication Number | Publication Date |
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| CN110595755A true CN110595755A (en) | 2019-12-20 |
| CN110595755B CN110595755B (en) | 2021-07-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910937663.9A Active CN110595755B (en) | 2019-09-29 | 2019-09-29 | Main landing gear loading test device with single wheel and inclined angle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
| CN112461515A (en) * | 2020-10-30 | 2021-03-09 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN113212795A (en) * | 2021-06-04 | 2021-08-06 | 中国飞机强度研究所 | Loading false wheel for undercarriage strength test |
| CN114919773A (en) * | 2022-06-10 | 2022-08-19 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage loading device and loading method based on moment balance |
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| CN104773306A (en) * | 2015-04-07 | 2015-07-15 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| CN205819590U (en) * | 2016-07-01 | 2016-12-21 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test main landing gear loading simulation part |
| CN106240841A (en) * | 2016-07-07 | 2016-12-21 | 中国飞机强度研究所 | A kind of gear test charger |
| CN109533386A (en) * | 2018-11-13 | 2019-03-29 | 中国直升机设计研究所 | Connection structure strength test device on a kind of undercarriage machine |
| CN209027777U (en) * | 2018-11-15 | 2019-06-25 | 中国直升机设计研究所 | A kind of nose-gear two-wheel biaxial loadings device |
| CN209023161U (en) * | 2018-09-25 | 2019-06-25 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test nose-gear loaded member |
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2019
- 2019-09-29 CN CN201910937663.9A patent/CN110595755B/en active Active
Patent Citations (6)
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| CN104773306A (en) * | 2015-04-07 | 2015-07-15 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| CN205819590U (en) * | 2016-07-01 | 2016-12-21 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test main landing gear loading simulation part |
| CN106240841A (en) * | 2016-07-07 | 2016-12-21 | 中国飞机强度研究所 | A kind of gear test charger |
| CN209023161U (en) * | 2018-09-25 | 2019-06-25 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test nose-gear loaded member |
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| CN209027777U (en) * | 2018-11-15 | 2019-06-25 | 中国直升机设计研究所 | A kind of nose-gear two-wheel biaxial loadings device |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
| CN112461515A (en) * | 2020-10-30 | 2021-03-09 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN112461515B (en) * | 2020-10-30 | 2022-07-01 | 中国直升机设计研究所 | Helicopter undercarriage loading device |
| CN113212795A (en) * | 2021-06-04 | 2021-08-06 | 中国飞机强度研究所 | Loading false wheel for undercarriage strength test |
| CN113212795B (en) * | 2021-06-04 | 2024-04-09 | 中国飞机强度研究所 | Landing gear strength test loading false wheel |
| CN114919773A (en) * | 2022-06-10 | 2022-08-19 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage loading device and loading method based on moment balance |
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| Publication number | Publication date |
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| CN110595755B (en) | 2021-07-23 |
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