CN211527791U - Small and medium-sized fixed wing static test device - Google Patents
Small and medium-sized fixed wing static test device Download PDFInfo
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- CN211527791U CN211527791U CN201921956452.1U CN201921956452U CN211527791U CN 211527791 U CN211527791 U CN 211527791U CN 201921956452 U CN201921956452 U CN 201921956452U CN 211527791 U CN211527791 U CN 211527791U
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Abstract
The utility model discloses a middle-size and small-size fixed wing static test device, including braced system and loading system, braced system includes the bearing plate, bearing plate perpendicular to level ground is fixed, is provided with the multiunit mounting hole on the bearing plate, be used for installing the wing, loading system includes braced frame, elevating system, load roof beam, couple, load, braced frame can freely remove on the level ground, and elevating system fixes on braced frame, and load roof beam hangs on braced frame with the help of elevating system liftable, and load roof beam is provided with the slide rail, and a plurality of couples are respectively in order to follow the gliding mode of slide rail is hung in the below of load roof beam, and load can hang on the couple through the cotton rope. The utility model discloses the device has area little, advantages such as size is adjustable, adaptable not unidimensional big or small wing. The device is convenient to assemble, transport and store, and can be automatically unloaded when the structure is damaged in the test process through the lifting adjustable loading device, so that the damaged part is prevented from being continuously expanded.
Description
Technical Field
The utility model relates to an aeronautical technical field especially relates to an unmanned aerial vehicle draw gear who connects main undercarriage.
Background
The structural static test is an important component in the structural design of the aircraft, for structures with complex geometric shapes and working environments such as wings, only results after conditions are simplified can be obtained only by means of computer-aided modeling technology and finite element analysis, the structural static test is still needed for verification, and the strength performance and the bearing capacity of the structure are obtained through performance observation (strength, rigidity and stability) and result parameter analysis (stress, strain, displacement and the like) after the structure is loaded, so that the structural strength design is completed.
Wings, which are the main lift providing components of an aircraft, are important load bearing components and therefore have been the focus of strength design. In recent years, with the improvement of the technical level, means and methods of structural static tests are continuously improved, a heavy object is loaded to an electric mechanical booster or a hydraulic actuator cylinder and a jack, then a lever system capable of realizing multi-point coordination is used for loading, then an electric hydraulic servo system is loaded, the large-scale development is gradually carried out, higher requirements are provided for the field environment and the test equipment of the tests, and the design is mature. However, for small and medium-sized aircrafts, the complex test conditions more suitable for large airplanes are not completely suitable, test sites and facilities need special building requirements, test equipment is complex, test cost is high, and test period is long.
The small and medium-sized aircraft is relatively simple in loaded and small in structural size, but has more complex and abrupt appearance, so that a static test device more suitable for the small and medium-sized aircraft needs to be designed, and a special test field is not needed; the supporting device can be repeatedly used for multiple times so as to avoid wasting resources; the loading system is simplified as much as possible, higher requirements are put forward on the basis of the traditional loading mode, and the automatic unloading can be realized when the structure is damaged so as to avoid the continuous expansion of the damaged part; the test steps are simple, and the economic cost and the labor cost of the test are effectively controlled.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: the existing middle-size and small-size wing loading mode cannot avoid constraint on a wing skin, particularly when the skin is made of a composite material, the surface of the skin is easily damaged, and manpower and material resources are consumed in the traditional heavy loading mode. The utility model provides a do not harm wing covering, the test piece installation is swift convenient, and the load is applyed simply accurately, does not have the static test loading device that special place required, and its corollary equipment can repeat repetitious usage, and it is simple and convenient to draw materials, has greatly saved experimental manpower and materials.
The technical scheme of the utility model is that: a set of static test loading device suitable for small and medium-sized fixed wing aircrafts is effective on straight wings, small-sweep-angle swept wings and slightly large-sweep-angle swept wings. The test system mainly comprises a mechanical device part and a test instrument part, wherein the mechanical device part comprises a support system, a loading system and an object to be tested, and the test instrument part comprises a displacement tester and a strain tester. The utility model discloses mainly carry out technological improvement and innovation in support system and loading system part.
The utility model discloses a middle-size and small-size fixed wing static test device includes braced system and loading system, braced system includes the bearing plate, the bearing plate is perpendicular to the level ground and fixes, be provided with the multiunit mounting hole on the bearing plate for install the wing, loading system includes braced frame, elevating system, load roof beam, couple, load, braced frame can freely move on the level ground, elevating system fixes on braced frame, the load roof beam with the help of elevating system liftable hang on braced frame, the load roof beam is provided with the slide rail, a plurality of the couple hang in the below of load roof beam in the mode that can slide along the slide rail respectively, the load can hang on the couple through the cotton rope, when testing, with the wing fixed mounting after on the bearing plate, moving the support frame to enable the load beam to be positioned above the wing, sliding the hook to adjust the distribution of the loading points in the wingspan direction, enabling a plurality of loads hung on the hook to be correspondingly positioned right above a plurality of loading points on the wing by means of a lifting mechanism, starting the lifting mechanism to enable the load beam to descend until all the loads are seated on each loading point, and enabling the rope not to be stressed on the hook.
Preferably, the bearing plate is fixed on the hollow square beam group, the hollow square beam group is fixed on the horizontal ground through foundation bolts, and the foundation bolts are embedded in the concrete.
Preferably, the support frame forms a cuboid door-opening type frame through 4 longitudinal beams and 6 cross beams, lower reinforcing cross beams are respectively arranged on two sides of the support frame, and bases with rotating wheels are respectively installed at the lower ends of the 4 longitudinal beams.
Preferably, the 4 longitudinal beams are equally divided into two sections, the upper sections of the longitudinal beams are inserted into the lower sections of the longitudinal beams and can be locked by screws to form a lifting structure, the height of the lifting structure can be adjusted, and the two lower reinforcing cross beams are arranged on the lower sections of the longitudinal beams at equal height.
Preferably elevating system includes crank mechanism, assembly pulley and wire rope, is lieing in two of one side the upper segment of longeron corresponds human high department and installs a crank mechanism respectively, has a fixed pulley that is used for turning to at each fixed mounting of the upper end of these two longerons, is lieing in two at door opening type frame both ends top be provided with the slide rail on the crossbeam respectively, two movable pulley installs on the slide rail of two crossbeams with slidable mode respectively to can lock and die at optional position, distribute along wing chordwise position with the adjustment loading point, two wire rope's one end corresponds separately and connects on crank mechanism, via fixed pulley and movable pulley that correspond separately respectively, the other end is connected respectively the both ends of load beam will the load beam is hung in braced frame's door opening.
Preferably, the load is a water bag, and volume scales are arranged on the surface of the water bag and used for adjusting the water quantity.
Preferably, the hollow square beam set is formed by welding and connecting hollow square beams, and the bearing plate is welded on the hollow square beam set.
Preferably, the anchor bolt material is Q235.
Preferably, the cross beams at the top are connected by rivet type connecting pins.
Preferably, the longitudinal beams and the cross beams are made of aluminum alloy sections
The utility model has the advantages that:
1. the utility model provides a brand-new static test mode of heavy object loading mainly is applicable to middle-size and small-size stationary vane structure, and the alignment wing all has stronger adaptability with sweepback wing. The loading system has small occupied area, simple processing and manufacturing, low cost and adjustable size, and can adapt to wings of different sizes by changing the length, the width and the height of the supporting beam. And the loading system is mainly made of sectional materials, is of a detachable structure and is convenient to assemble, transport and store.
2. The utility model discloses have convenient loading uninstallation system, through waveing the handle when the loading, make and hang the load roof beam level decline that has the load, water bag and wing surface contact make the load the wing surface simultaneously, need load the fixed heavy object of point one by one when being different from the loading of traditional heavy object, make the loading load more accurate, efficiency is higher, and has greatly saved the manpower. When the structure is damaged, the load beam is lifted, the heavy object is lifted, the load is quickly unloaded, and the structure is prevented from being damaged more greatly.
3. The couple of hanging the heavy object receives length restriction, and in the test process, when the structure of being examined takes place great bending failure, the water bag will be with wing structure autosegregation, avoids crushing the continuation of structure.
4. The water bag is selected for use to the heavy object, and convenient for obtaining materials compares other kind heavy objects, and the scale of water bag makes when adjusting load more convenient through changing the volume, saves the cost.
5. The utility model discloses the device need not be changed wing structure, avoids retraining the heavy object on the wing covering during the loading, can not destroy the covering, is applicable to the combined material wing.
Drawings
Fig. 1 is an overall indication diagram of the testing device of the present invention, which includes the loading of the heavy water bag on the wing.
Fig. 2 is a schematic diagram of the support system of the present invention.
Fig. 3 is the structure assembly diagram of the lifting loading device of the present invention.
Fig. 4 is a structure view of the pulley of the present invention.
Fig. 5 is a schematic view of the rocking handle of the present invention.
The symbols in the figures are labeled as follows:
1-bearing plate, 2-hollow square beam group, 3-ground, 4-foundation bolt, 5-wing, 6-longitudinal supporting beam, 7-transverse supporting beam, 8-base with runner, 9-reinforcing beam, 10-pulley block, 11-crank mechanism, 12-steel wire rope, 13-load beam, 14-hook and 15-water bag load.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.
Referring to the schematic structural diagrams of the testing device shown in fig. 1, fig. 2 and fig. 3, the testing device of the present invention mainly comprises a supporting system and a loading system. A sweepback wing with a wingspan of five meters is selected as a tested piece.
The main structure of the support system is a support structure composed of a bearing plate 1 and a hollow square beam group 2, and specifically referring to the structural schematic diagram of fig. 3, a plurality of groups of mounting holes are punched on the bearing plate 1 and used for mounting wing structures with different structural forms and sizes. Hollow square beam group 2 is through welding each other hollow square tubular beam and is constituteed, also welded connection with bearing plate 1, and whole braced system leans on rag bolt 4 to fix on level ground 3, and rag bolt 4 material is Q235, can provide sufficient holding power for wing 5 loading, and whole structure processing is convenient, and is with low costs, and it is less to installation site environment requirement, does not need special load hall and load ceiling, shortens test period.
The utility model discloses a loading system that another key innovation object is liftable adjustable, and fig. 4 is loading schematic diagram. The loading system comprises a longitudinal supporting beam 6, a transverse supporting beam 7, a base 8 with a rotating wheel, a reinforcing beam 9, a pulley block 10, a hand crank mechanism 11, a steel wire rope 12, a load beam 13, a hook 14, a water bag load 15 and the like.
The four longitudinal supporting beams 6 and the six transverse supporting beams 7 form an integral frame of the loading system, the integral frame is made of aluminum alloy sections, the upper portion of each longitudinal supporting beam 6 is of a height-adjustable inserting structure, and the upper portions of the longitudinal supporting beams extend out to be suitable for the height and are locked by screws. The base 8 with the rotating wheels is also made of aluminum alloy, and the loading structure is convenient to move and mount through the rotating wheels. The lower reinforcing beam 9 is mainly used for supporting a reinforcing structure, the transverse supporting beams 7 at the top parts of two ends are used for connecting the load beam 13, and the bottom of the transverse beam is provided with a sliding rail, so that a pulley arranged on the sliding rail can move along the sliding rail and be locked. The top beam is connected by rivet type pins.
The pulley block 10 is installed on the transverse supporting beam 7 and the longitudinal supporting beam 6, the pulley on the cross beam can move along the slide rail in the wing chord direction, the loading point of the chord direction position is adjusted, the pulley on the longitudinal beam is fixed in position and is connected to the longitudinal beam through a bolt, and the bolt is a standard component.
The load beam 13 is connected by a steel wire rope 12, the steel wire rope is wound and unwound by the crank mechanism 11 through being connected with the pulley block 10, and the load beam 13 does lifting motion, so that rapid loading and unloading are realized.
The lower part of the load beam is provided with a slide rail, and hooks 14 with rollers are distributed along the load beam and used for hanging a water bag 15. The distribution of the loading points at the spanwise position of the machine is adjusted by adjusting the distribution of the hooks 14 on the slide rails.
The scales of the water bag are used for controlling the water adding amount, so that the weight can be conveniently adjusted according to the loading requirement.
The utility model discloses a choose for use the heavy object loading, loading mode simple accurate. Hanging a heavy object (a water bag) on a load beam 13 through a hook 14, adjusting the position of the water bag according to the distribution of a loading point along the unfolding direction, shaking a handle 11, driving the load beam 13 to descend by a steel wire rope 12 until the wing completely bears the heavy object, and starting test measurement; if the structure is damaged, the loaded object is limited by the length of the hanging rope and can be separated from the surface of the wing, loading is stopped, meanwhile, the handle 11 is shaken, the load beam 13 is lifted, unloading is carried out rapidly, and the purpose of protecting the structure from further damage is achieved.
The test device is characterized in that:
1. the bearing plate of the support system is supported by the hollow square beam group which is connected by welding, and a plurality of groups of mounting holes are arranged on the bearing plate, so that the support system is suitable for wing structures with different sizes and heights.
2. The transverse supporting structure and the longitudinal supporting structure of the loading system are aluminum alloy sections, so that the supporting strength requirement is met, the weight is reduced, and the loading system is convenient to disassemble and carry.
3. The upper structure of the supporting beam is of a lifting structure, the height is adjusted, the supporting beam is locked by screws and can be detached independently, and the supporting beam is convenient to store.
4. The load is hung on the load beam through the hook and can move along the direction of the cross beam, and the distribution of the load points in the span direction of the airplane is adjusted. The load beam is connected with the pulley by a steel wire rope, the pulley can move along the supporting beam to change the direction of the lower load beam, so that the distribution of loading points along the chord direction of the wing is adjusted, and the loading system can be simultaneously used for straight wing structures and swept wing structures.
5. The load beam ascends and descends through a steel wire rope, a pulley block and a rocking handle mechanism 11, as shown in fig. 5, loading and unloading are conveniently achieved, the method is different from a traditional weight loading mode, when the structure is damaged, a weight can be quickly separated from the wing structure, and larger structural damage is avoided.
6. The weight is a water bag, and volume scales are arranged on the surface of the water bag, so that the water quantity is conveniently adjusted, and the load is changed.
The details of the present invention not described in detail in the specification are well known to those skilled in the art.
Claims (10)
1. A middle and small fixed wing static test device is characterized in that: the airplane wing loading system comprises a supporting system and a loading system, wherein the supporting system comprises a bearing plate, the bearing plate is perpendicular to the horizontal ground and is fixed, a plurality of groups of mounting holes are formed in the bearing plate and used for mounting wings, the loading system comprises a supporting frame, a lifting mechanism, a load beam, hooks and a load, the supporting frame can freely move on the horizontal ground, the lifting mechanism is fixed on the supporting frame, the load beam is hoisted and hung on the supporting frame by virtue of the lifting mechanism, the load beam is provided with a slide rail, the hooks are respectively hung below the load beam in a sliding manner along the slide rail, the load can be hung on the hooks through ropes, when a test is carried out, after the wings are fixedly mounted on the bearing plate, the supporting frame is moved to enable the load beam to be located above the wings, and sliding the hook to adjust the distribution of the loading points in the span direction of the airplane, enabling a plurality of loads hung on the hook to be correspondingly positioned right above a plurality of loading points on the wing by virtue of the lifting mechanism, and starting the lifting mechanism to enable the load beam to descend until all the loads are seated on each loading point, wherein the rope is not stressed on the hook.
2. The small and medium-sized fixed wing static test device according to claim 1, characterized in that: the bearing plate is fixed on the hollow square beam group, the hollow square beam group is fixed on the horizontal ground through foundation bolts, and the foundation bolts are embedded in the concrete.
3. The small and medium-sized fixed wing static test device according to claim 1, characterized in that: the support frame forms a cuboid door-opening type frame through 4 longitudinal beams and 6 cross beams, lower reinforcing cross beams are arranged on two sides of the support frame respectively, and the lower ends of the 4 longitudinal beams are provided with bases with rotating wheels respectively.
4. The small and medium-sized fixed wing static test device according to claim 3, characterized in that: the 4 longitudinal beams are equally divided into two sections, the upper sections of the two longitudinal beams are inserted into the lower sections of the two longitudinal beams and can be locked by screws to form a lifting structure, the height of the lifting structure can be adjusted, and the two lower reinforcing cross beams are arranged on the lower sections of the longitudinal beams at equal height.
5. The small and medium-sized fixed wing static test device according to claim 4, characterized in that: elevating system includes crank mechanism, assembly pulley and wire rope, is lieing in two of one side the upper segment of longeron corresponds human high department and installs a crank mechanism respectively, has a fixed pulley that is used for turning to at each fixed mounting of the upper end of these two longerons, is lieing in two at door opening type frame both ends top be provided with the slide rail on the crossbeam respectively, and two movable pulleys install on the slide rail of two crossbeams with the slidable mode respectively to can lock and die at optional position, distribute along wing chordwise position to the adjustment loading point, two wire rope's one end corresponds separately and connects on crank mechanism, respectively via fixed pulley and movable pulley that correspond separately, the other end is connected respectively the both ends of load beam will the load beam is hung in braced frame's door opening.
6. The small and medium-sized fixed wing static test device according to claim 1, characterized in that: the load adopts a water bag, and volume scales are arranged on the surface of the water bag and used for adjusting the water quantity.
7. The small and medium-sized fixed wing static test device according to claim 2, characterized in that: the hollow square beam set is formed by welding and connecting hollow square tubular beams, and the bearing plate is welded on the hollow square beam set.
8. The small and medium-sized fixed wing static test device according to claim 2, characterized in that: the anchor bolt is made of Q235.
9. The small and medium-sized fixed wing static test device according to claim 5, characterized in that: the crossbeam at the top is connected by adopting rivet type connecting pins.
10. The small and medium-sized fixed wing static test device according to claim 9, characterized in that: the longitudinal beams and the cross beams are made of aluminum alloy sections.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921956452.1U CN211527791U (en) | 2019-11-13 | 2019-11-13 | Small and medium-sized fixed wing static test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921956452.1U CN211527791U (en) | 2019-11-13 | 2019-11-13 | Small and medium-sized fixed wing static test device |
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| CN211527791U true CN211527791U (en) | 2020-09-18 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN112539911A (en) * | 2020-12-03 | 2021-03-23 | 北京强度环境研究所 | Load applying-unhooking test device in wing body thermal separation process |
| CN112722325A (en) * | 2021-02-26 | 2021-04-30 | 芜湖创联航空科技有限公司 | Static test device and method for fixed-wing unmanned aerial vehicle body |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
| CN114476147A (en) * | 2021-12-31 | 2022-05-13 | 北京空间机电研究所 | Spacecraft cabin multi-point hoisting static test loading device and method |
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2019
- 2019-11-13 CN CN201921956452.1U patent/CN211527791U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| CN112539911A (en) * | 2020-12-03 | 2021-03-23 | 北京强度环境研究所 | Load applying-unhooking test device in wing body thermal separation process |
| CN112539911B (en) * | 2020-12-03 | 2023-03-10 | 北京强度环境研究所 | Load applying-unhooking test device in wing body thermal separation process |
| CN112722325A (en) * | 2021-02-26 | 2021-04-30 | 芜湖创联航空科技有限公司 | Static test device and method for fixed-wing unmanned aerial vehicle body |
| CN112722325B (en) * | 2021-02-26 | 2022-07-29 | 芜湖创联航空装备产业研究院有限公司 | Static test device and method for fixed-wing unmanned aerial vehicle body |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
| CN113335560B (en) * | 2021-06-04 | 2024-01-30 | 中国飞机强度研究所 | Complex load box section or barrel section test device and method |
| CN114476147A (en) * | 2021-12-31 | 2022-05-13 | 北京空间机电研究所 | Spacecraft cabin multi-point hoisting static test loading device and method |
| CN114476147B (en) * | 2021-12-31 | 2022-11-01 | 北京空间机电研究所 | Spacecraft cabin multi-point hoisting static test loading device and method |
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