CN117030292A - Shock-falling testing device for aerocar - Google Patents
Shock-falling testing device for aerocar Download PDFInfo
- Publication number
- CN117030292A CN117030292A CN202311287292.7A CN202311287292A CN117030292A CN 117030292 A CN117030292 A CN 117030292A CN 202311287292 A CN202311287292 A CN 202311287292A CN 117030292 A CN117030292 A CN 117030292A
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- aerocar
- lifting
- base
- release mechanism
- mounting
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- 238000012360 testing method Methods 0.000 title claims abstract description 63
- 230000003028 elevating effect Effects 0.000 claims abstract description 29
- 230000035939 shock Effects 0.000 claims abstract description 22
- 210000000078 claw Anatomy 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 2
- 239000000725 suspension Substances 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 4
- 238000005259 measurement Methods 0.000 abstract description 2
- 230000036544 posture Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M17/00—Testing of vehicles
- G01M17/007—Wheeled or endless-tracked vehicles
- G01M17/0078—Shock-testing of vehicles
Abstract
The invention relates to the technical field of a falling shock testing device, and discloses a falling shock testing device for a flying car, which comprises the following components: the device comprises a main body frame, a guide balance mechanism, a lifting mechanism, a latch hook release mechanism and a force measuring mechanism; the device is connected elevating platform and the cooperation of hoisting point on the aerocar through the lifting rope, and set up to detachable connection between lifting rope and elevating platform, therefore can adjust the gesture of aerocar through the length difference between the many lifting ropes of adjustment, and after the elevating platform is released to latch hook release mechanism, the elevating platform slides along the guide rail, the aerocar removes along with the elevating platform, the in-process gesture that falls at the aerocar also can not change, can accomplish the shock test that falls of aerocar at different whereabouts gesture after the aerocar strikes force measuring mechanism, in order to gather the deformation data that aerocar lands, in addition, the device can also adjust the measurement height of aerocar through elevating mechanism, further richen experimental data.
Description
Technical Field
The invention relates to the technical field of a landing vibration testing device, in particular to a landing vibration testing device for a flying automobile.
Background
At present, the shock test of the aerocar is an important test item for verifying the structural strength and safety of an airplane body, and the conventional shock test device can test the impact force of the aerocar in a falling state, but can not simulate the falling gesture of the aerocar.
Disclosure of Invention
The purpose of the invention is that: the utility model provides a fall and shake testing arrangement for aerocar can accomplish the fall and shake test of the different whereabouts postures of aerocar to gather the load change condition that aerocar lands.
In order to achieve the above object, the present invention provides a shock test device for a flying car, in which a plurality of hanging points are provided on an outer circumferential side surface of the flying car, the shock test device for a flying car comprising: the device comprises a main body frame, a guide balance mechanism, a lifting mechanism, a latch hook release mechanism and a force measuring mechanism; the main body frame comprises a base and a bracket arranged on the base, wherein the bracket and the base are enclosed together to form a test space, and a guide rail extending along a first direction is arranged on the inner side of the bracket; the guide balance mechanism is positioned in the test space and comprises a lifting platform and a plurality of lifting ropes, the lifting platform is connected to the guide rail in a sliding manner, and the lifting ropes are detachably arranged on the bottom surface of the lifting platform and are respectively arranged in one-to-one correspondence with the lifting points; the lifting mechanism is arranged at the top of the bracket; the lock hook release mechanism is positioned in the test space, one end of the lock hook release mechanism is connected with the lifting mechanism, the other end of the lock hook release mechanism is disconnected with the top of the lifting platform, and the lifting mechanism is used for controlling the lock hook release mechanism to move along the first direction; the force measuring mechanism is located in the test space and mounted on the top surface of the base and used for measuring the landing load of the aerocar.
Optionally, the support includes mounting panel and two support units that set up along the second direction corresponds, the support unit is the door type, including supporting beam and two support columns, the bottom of support column is installed on the base, the guide rail sets up the inboard of support column, the both ends of supporting beam respectively with two the top of support column is connected, the both sides of mounting panel respectively with two the supporting beam is connected, elevating system installs on the mounting panel, two support unit with the base encloses jointly and closes and form test space.
Optionally, the support still includes fixing bolt be equipped with a plurality of mounting grooves that set up along the third direction interval on the top surface of base, the mounting groove is followed the second direction extend and run through in the base, the bottom surface of support column is equipped with the fixture block, the fixture block joint in the mounting groove still is provided with a plurality of first locating holes between arbitrary adjacent two between the mounting groove, a plurality of first locating holes are followed the second direction interval sets up, the bottom of support column is equipped with protruding edge, be equipped with the second locating hole on the protruding edge, fixing bolt passes the second locating hole extremely first locating hole, so that the support column is fixed on the base.
Optionally, the mounting panel includes plate body and a plurality of bearing unit, offer on the plate body a plurality of edges the spout that the second direction extends, a plurality of the spout is followed the third direction interval sets up, a plurality of the bearing unit sets up respectively in a plurality of the spout, the bearing unit includes first roof beam, second roof beam, first installed part and second installed part, be equipped with a plurality of edges on the spout the mounting hole that the second direction interval set up, first roof beam sliding connection in the spout, and one end and one of them a supporting beam can dismantle and be connected, and the other end passes through first installed part and one of them the mounting hole can dismantle and be connected.
Optionally, the elevating platform includes main part and extension, the extension is installed the side of main part, and towards the guide rail sets up the extension is adjacent one side of guide rail is provided with the pulley, pulley sliding connection in the guide rail, many the lifting rope demountable installation in the bottom surface of main part.
Optionally, the device further comprises a limiting device, the limiting device comprises a first driving hydraulic cylinder, a rotating wheel and a limiting rope, the first driving hydraulic cylinder is installed at the top of the support, the rotating wheel is installed at the output end of the first driving hydraulic cylinder, the first driving hydraulic cylinder is used for driving the rotating wheel to move in the first direction, one end of the limiting rope is connected with the top surface of the lifting platform, the other end of the limiting rope passes through the top end of the rotating wheel and then is connected with the top surface of the lifting platform, and the limiting rope can be switched between a loose state and a tight state along with the movement of the rotating wheel in the first direction.
Optionally, still be provided with mechanical limit baffle on the guide rail, mechanical limit baffle is used for the restriction the gliding scope of elevating platform prevents stop device's spacing rope inefficacy and then damages experimental aerocar.
Optionally, elevating system includes lead screw motor, lead screw and connecting plate, the lead screw motor is installed the top of support, the lead screw is followed first direction extends, and with lead screw motor transmission is connected, the lead screw motor is used for the drive the lead screw is followed first direction removes, the connecting plate is located test space's inside, and install the lead screw orientation the one end of base, latch hook release mechanism installs on the connecting plate orientation one side of base.
Optionally, the lifting mechanism further includes a second driving hydraulic cylinder, where the second driving hydraulic cylinder is disposed between the latch hook release mechanism and the connecting plate, and is used to drive the latch hook release mechanism to move along the first direction.
Optionally, the latch hook release mechanism includes actuating cylinder and jack catch, still be equipped with the mounting on the top surface of elevating platform, actuating cylinder installs elevating system is last, the jack catch is installed actuating cylinder's output, actuating cylinder is used for controlling opening and closure of jack catch, the jack catch with the mounting can be disconnected.
Compared with the prior art, the earthquake drop testing device for the aerocar has the beneficial effects that: the device is connected elevating platform and the cooperation of hoisting point on the aerocar through the lifting rope, and set up to detachable connection between lifting rope and elevating platform, therefore can adjust the gesture of aerocar through the length difference between the many lifting ropes of adjustment, and after the elevating platform is released to latch hook release mechanism, the elevating platform slides along the guide rail, the aerocar removes along with the elevating platform, the in-process gesture that falls at the aerocar also can not change, can accomplish the shock test that falls of aerocar at different whereabouts gesture after the aerocar strikes force measuring mechanism, with load and deformation data that gathers the aerocar landing, in addition, the device can also adjust the measuring height of aerocar according to test demand through elevating mechanism, further richen experimental data.
Drawings
FIG. 1 is a schematic main structure of a shock test device for a flying car according to an embodiment of the present invention;
FIG. 2 is an enlarged view of the landing test apparatus for a flying car according to an embodiment of the present invention at A in FIG. 1;
FIG. 3 is an enlarged view at B in FIG. 1 of the shock test device for a flying car according to an embodiment of the present invention;
FIG. 4 is an enlarged view of FIG. 1 of the shock test device for a flying car according to an embodiment of the present invention;
FIG. 5 is a schematic main body structure of the main body frame of the shock test device for a flying car according to the embodiment of the present invention;
FIG. 6 is a schematic diagram of the main structure of the guide balance mechanism of the shock test device for a flying car according to the embodiment of the present invention;
FIG. 7 is a schematic diagram of a main structure of the latch hook release mechanism of the shock test device for a flying car according to an embodiment of the present invention;
FIG. 8 is a schematic view of the shock test apparatus for a flying car as it impacts the load cell of an embodiment of the present invention.
In the figure, 1, a flying car; 11. a hanging point; 2. a main body frame; 21. a base; 211. a mounting groove; 22. a bracket; 221. a mounting plate; 2211. a plate body; 22111. a chute; 2212. a load bearing unit; 22121. a first beam; 22122. a second beam; 222. a supporting unit; 2221. a support beam; 2222. a support column; 22221. a guide rail; 22222. a convex edge; 22223. a mechanical limit baffle; 223. a fixing bolt; 23. a test space; 3. a guide balance mechanism; 31. a lifting table; 311. a main body portion; 312. an extension; 313. a pulley; 314. a fixing member; 32. a hanging rope; 4. a lifting mechanism; 41. a lead screw motor; 42. a screw rod; 43. a connecting plate; 44. a second driving hydraulic cylinder; 5. a latch hook release mechanism; 51. a driving cylinder; 52. a claw; 6. a force measuring mechanism; 7. a limiting device; 71. a first driving hydraulic cylinder; 72. a rotating wheel; 73. a limit rope; x, a first direction; y, second direction; z, third direction.
Detailed Description
The following describes in further detail the embodiments of the present invention with reference to the drawings and examples. The following examples are illustrative of the invention and are not intended to limit the scope of the invention.
In the description of the present invention, it should be understood that the terms "upper," "top," "bottom," "inner," "outer," and the like as used herein are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
As shown in fig. 1, in a shock test device for a aerocar 1 according to a preferred embodiment of the present invention, a plurality of hanging points 11 are provided on an outer peripheral side surface of the aerocar 1, and the shock test device for the aerocar 1 includes: the device comprises a main body frame 2, a guide balance mechanism 3, a lifting mechanism 4, a latch hook release mechanism 5 and a force measuring mechanism 6; the main body frame 2 includes a base 21 and a bracket 22 mounted on the base 21, the bracket 22 and the base 21 enclosing together to form a test space 23, and a guide rail 22221 extending in a first direction X is provided inside the bracket 22; the guide balance mechanism 3 is positioned in the test space 23, the guide balance mechanism 3 comprises a lifting table 31 and a plurality of lifting ropes 32, the lifting table 31 is slidably connected to the guide rail 22221, and the lifting ropes 32 are detachably arranged on the bottom surface of the lifting table 31 and are respectively arranged in one-to-one correspondence with the lifting points 11; the lifting mechanism 4 is arranged on the top of the bracket 22; the lock hook release mechanism 5 is located in the test space 23, one end of the lock hook release mechanism 5 is connected to the lifting mechanism 4, the other end of the lock hook release mechanism is disconnected with the top of the lifting table 31, and the lifting mechanism 4 is used for controlling the lock hook release mechanism 5 to move along the first direction X; the load cell 6 is located inside the test space 23 and is mounted on the top surface of the base 21 for measuring the landing load of the aerocar 1.
Based on the above scheme, the device is through lifting rope 32 connection elevating platform 31 and the cooperation of the hoisting point 11 on the aerocar 1, and set up to detachable connection with between lifting rope 32 and elevating platform 31, the hoisting point 11, consequently can adjust the gesture of aerocar 1 through the length difference between adjusting many lifting ropes 32, and after latch hook release mechanism 5 releases elevating platform 31, elevating platform 31 slides along guide rail 22221, aerocar 1 moves along with elevating platform 31, the in-process gesture of 1 whereabouts also can not change, can accomplish the shock test of 1 in the whereabouts gesture of different of aerocar after aerocar 1 strikes dynamometry mechanism 6, in order to gather the load and the deformation data that aerocar 1 lands, in addition, the device can also adjust the measurement height of aerocar 1 through elevating mechanism 4 according to experimental demand, further enrich experimental data.
Wherein the mounting position of the load cell 6 is determined according to the landing position of the tyre or skid of the aerocar 1.
As shown in fig. 5, for convenience in use, the support 22 includes a mounting plate 221 and two support units 222 that set up along the second direction Y correspondingly, the support units 222 are door-shaped, including a support beam 2221 and two support columns 2222, the bottom of support column 2222 is installed on base 21, guide rail 22221 sets up in the inboard of support column 2222, the both ends of support beam 2221 are connected with the top of two support columns 2222 respectively, the both sides of mounting plate 221 are connected in two support beams 2221 respectively, elevating system 4 installs on mounting plate 221, two support units 222 and base 21 enclose jointly and form test space 23, the specification of mounting plate 221 and two support units 222 can be changed according to the size specification of aerocar 1, in order to strengthen the suitability of this device.
As shown in fig. 2, in order to facilitate the adjustment of the position of the support column 2222 or the replacement of the specification of the support column 2222, the support 22 further includes a fixing bolt 223, a plurality of mounting grooves 211 are formed on the top surface of the base 21 and are arranged at intervals along the third direction Z, the mounting grooves 211 extend along the second direction Y and penetrate through the base 21, a clamping block (not shown in the drawing) is arranged on the bottom surface of the support column 2222, the clamping block is clamped in the mounting grooves 211, a plurality of first positioning holes (not shown in the drawing) are further formed between any two adjacent mounting grooves 211, the plurality of first positioning holes are arranged at intervals along the second direction Y, a convex edge 22222 is arranged at the bottom of the support column 2222, a second positioning hole (not shown in the drawing) is formed on the convex edge 22222, and the fixing bolt 223 penetrates through the second positioning holes to the first positioning holes so as to fix the support column 2222 on the base 21, and thus the quick adjustment of the position of the support column 2222 or the quick replacement of the specification of the support column 2222 can be realized.
As shown in fig. 3, in the present embodiment, in order to avoid the fixture block from being separated from the mounting groove 211, the mounting groove 211 is T-shaped, and the shape of the fixture block is adapted to the shape of the mounting groove 211.
As shown in fig. 1 and 5, in order to adjust the specification of the mounting plate 221 to adapt to the aerocar 1 with different specifications, the mounting plate 221 includes a plate body 2211 and a plurality of bearing units 2212, a plurality of sliding grooves 22111 extending along the second direction Y are formed on the plate body 2211, the sliding grooves 22111 are arranged at intervals along the third direction Z, the bearing units 2212 are respectively arranged in the sliding grooves 22111, the bearing units 2212 include a first beam 22121, a second beam 22122, a first mounting member (not shown in the drawing) and a second mounting member (not shown in the drawing), a plurality of mounting holes (not shown in the drawing) are formed in the sliding grooves 22111 and are arranged at intervals along the second direction Y, the first beam 22121 is slidably connected to the sliding grooves 22111, one end of the first beam 2211 is detachably connected to one of the bearing units, and the other end of the first beam 2212 is detachably connected to one of the mounting holes through the first mounting member.
As shown in fig. 6, in order to ensure balance of the lifting platform 31, the lifting platform 31 includes a main body 311 and an extension 312, the extension 312 is mounted on a side surface of the main body 311 and is disposed towards the guide rail 22221, a pulley 313 is disposed on a side of the extension 312 adjacent to the guide rail 22221, the pulley 313 is slidably connected to the guide rail 22221, and a plurality of lifting ropes 32 are detachably mounted on a bottom surface of the main body 311, so that the sliding connection between the lifting platform 31 and the guide rail 22221 is more stable by providing the pulley 313.
As shown in fig. 6, in this embodiment, in order to further improve the stability of the lifting platform 31, a connecting portion is further provided at an end of the extending portion 312 adjacent to the guide rail 22221, the connecting portion is V-shaped, both sides of the support column 2222 located in the test space 23 are provided with the guide rail 22221, and both sides of the connecting portion facing the guide rail 22221 are provided with pulleys 313, so as to further improve the stability of the lifting platform 31.
As shown in fig. 4, in order to prevent the lifting platform 31 from falling off the guide rail 22221 and being crashed on the aerocar 1, the device further comprises a limiting device 7, wherein the limiting device 7 comprises a first driving hydraulic cylinder 71, a rotating wheel 72 and a limiting rope 73, the first driving hydraulic cylinder 71 is arranged at the top of the bracket 22, the rotating wheel 72 is arranged at the output end of the first driving hydraulic cylinder 71, the first driving hydraulic cylinder 71 is used for driving the rotating wheel 72 to move in a first direction X, one end of the limiting rope 73 is connected with the top surface of the lifting platform 31, the other end of the limiting rope 73 is connected with the top surface of the lifting platform 31 after passing through the top end of the rotating wheel 72, and the limiting length of the limiting rope 73 is adjusted through the movement of the rotating wheel 72 in the first direction X;
as shown in fig. 1 and 8, the limiting rope 73 operates as follows: when the lifting mechanism 4 lifts and releases the lifting table 31, the limiting ropes 73 are in a loose state; when the aerocar 1 impacts the force measuring mechanism 6, the lifting rope 32 is in a loose state, and the limiting rope 73 is converted into a tight state so as to lift the lifting table 31, so that the lifting table 31 is prevented from being crashed on the aerocar 1.
As shown in fig. 5, in order to prevent the lifting platform 31 from falling off the guide rail 22221 and being hit on the aerocar 1, the guide rail 22221 is further provided with a mechanical limit stop 22223, and the mechanical limit stop 22223 is used for limiting the sliding range of the lifting platform 31.
As shown in fig. 4, in order to facilitate adjustment of the test height of the flying car 1, the elevating mechanism 4 includes a screw motor 41, a screw 42 and a connection plate 43, the screw motor 41 is mounted on the top of the bracket 22, the screw 42 extends along a first direction X and is in driving connection with the screw motor 41, the screw motor 41 is used for driving the screw 42 to move along the first direction X, the connection plate 43 is located inside the test space 23 and is mounted at one end of the screw 42 facing the base 21, and the latch hook release mechanism 5 is mounted on the connection plate 43 at one side facing the base 21.
As shown in fig. 4, in order to facilitate adjustment of the test height of the flying car 1, the lifting mechanism 4 further comprises a second driving hydraulic cylinder 44, the second driving hydraulic cylinder 44 being arranged between the latch hook release mechanism 5 and the connection plate 43 for driving the latch hook release mechanism 5 to move in the first direction X.
As shown in fig. 7, in order to facilitate control of release of the flying car 1, the latch hook release mechanism 5 includes a driving cylinder 51 and a claw 52, a fixing member 314 is further provided on the top surface of the elevating platform 31, the driving cylinder 51 is mounted on the elevating mechanism 4, the claw 52 is mounted at an output end of the driving cylinder 51, the driving cylinder 51 is used for controlling opening and closing of the claw 52, and the claw 52 is disconnectable from the fixing member 314.
The fixing element 314 may be a pin in this embodiment, and the claw 52 may be engaged with the pin.
In summary, the embodiment of the invention provides a device for testing the landing of a aerocar, which is characterized in that a lifting table 31 is connected with a lifting point 11 on the aerocar 1 through a lifting rope 32, and the lifting rope 32 is detachably connected with the lifting table 31 and the lifting point 11, so that the posture of the aerocar 1 can be adjusted through adjusting the length difference among a plurality of lifting ropes 32, when a lock hook release mechanism 5 releases the lifting table 31, the lifting table 31 slides along a guide rail 22221, the aerocar 1 moves along with the lifting table 31, the posture of the aerocar 1 is not changed in the falling process of the aerocar 1, and the landing test of the aerocar 1 in different falling postures can be completed after the aerocar 1 impacts a force measuring mechanism 6 so as to acquire the landing load change condition of the aerocar 1.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and substitutions can be made by those skilled in the art without departing from the technical principles of the present invention, and these modifications and substitutions should also be considered as being within the scope of the present invention.
Claims (10)
1. A fall and shake testing arrangement for aerocar be provided with a plurality of hoisting points in aerocar's periphery side, its characterized in that includes: the device comprises a main body frame, a guide balance mechanism, a lifting mechanism, a latch hook release mechanism and a force measuring mechanism;
the main body frame comprises a base and a bracket arranged on the base, wherein the bracket and the base are enclosed together to form a test space, and a guide rail extending along a first direction is arranged on the inner side of the bracket;
the guide balance mechanism is positioned in the test space and comprises a lifting platform and a plurality of lifting ropes, the lifting platform is connected to the guide rail in a sliding manner, and the lifting ropes are detachably arranged on the bottom surface of the lifting platform and are respectively arranged in one-to-one correspondence with the lifting points;
the lifting mechanism is arranged at the top of the bracket;
the lock hook release mechanism is positioned in the test space, one end of the lock hook release mechanism is connected with the lifting mechanism, the other end of the lock hook release mechanism is disconnected with the top of the lifting platform, and the lifting mechanism is used for controlling the lock hook release mechanism to move along the first direction;
the force measuring mechanism is located in the test space and mounted on the top surface of the base and used for measuring the landing load of the aerocar.
2. The landing testing device for a flying automobile according to claim 1, wherein the bracket comprises a mounting plate and two supporting units which are correspondingly arranged along the second direction, the supporting units are door-shaped and comprise a supporting beam and two supporting columns, the bottoms of the supporting columns are arranged on the base, the guide rails are arranged on the inner sides of the supporting columns, two ends of the supporting beam are respectively connected with the tops of the two supporting columns, two sides of the mounting plate are respectively connected with the two supporting beams, the lifting mechanism is arranged on the mounting plate, and the mounting plate, the two supporting units and the base jointly enclose to form the testing space.
3. The device for the falling shock test of a flying car according to claim 2, wherein the bracket further comprises a fixing bolt, a plurality of mounting grooves are formed in the top surface of the base at intervals along a third direction, the mounting grooves extend along the second direction and penetrate through the base, a clamping block is arranged on the bottom surface of the supporting column, the clamping block is clamped in the mounting grooves, a plurality of first positioning holes are further formed in the base at positions between any two adjacent mounting grooves, the first positioning holes are arranged at intervals along the second direction, a convex edge is arranged at the bottom of the supporting column, a second positioning hole is formed in the convex edge, and the fixing bolt penetrates through the second positioning holes to the first positioning holes so as to fix the supporting column on the base.
4. The device for testing the landing vibration of a flying car according to claim 3, wherein the mounting plate comprises a plate body and a plurality of bearing units, a plurality of sliding grooves extending along the second direction are formed in the plate body, a plurality of sliding grooves are formed in the third direction at intervals, a plurality of bearing units are respectively arranged in the sliding grooves, the bearing units comprise a first beam, a second beam, a first mounting piece and a second mounting piece, a plurality of mounting holes are formed in the sliding grooves at intervals along the second direction, the first beam is slidably connected to the sliding grooves, one end of the first beam is detachably connected with one of the supporting beams, and the other end of the first beam is detachably connected with one of the mounting holes through the first mounting piece.
5. The landing testing apparatus for a flying car of claim 1, wherein the elevating platform comprises a main body portion and an extension portion, the extension portion is installed at a side surface of the main body portion and is disposed toward the guide rail, a pulley is disposed at a side of the extension portion adjacent to the guide rail, the pulley is slidably connected to the guide rail, and the plurality of suspension ropes are detachably installed at a bottom surface of the main body portion.
6. The landing testing device for a flying car according to claim 1, further comprising a limiting device, wherein the limiting device comprises a first driving hydraulic cylinder, a rotating wheel and a limiting rope, the first driving hydraulic cylinder is mounted at the top of the support, the rotating wheel is mounted at the output end of the first driving hydraulic cylinder, the first driving hydraulic cylinder is used for driving the rotating wheel to move in the first direction, one end of the limiting rope is connected with the top surface of the lifting platform, the other end of the limiting rope passes through the top end of the rotating wheel and then is connected with the top surface of the lifting platform, and the limiting rope can be switched between a loose state and a tight state along with the movement of the rotating wheel in the first direction.
7. The shock test device for a flying car according to claim 1, wherein the guide rail is further provided with a mechanical limit baffle for limiting a sliding range of the lifting platform.
8. The drop test device for a flying car according to claim 1, wherein the lifting mechanism comprises a screw motor, a screw rod and a connecting plate, the screw rod motor is mounted at the top of the bracket, the screw rod extends along the first direction and is in transmission connection with the screw rod motor, the screw rod motor is used for driving the screw rod to move along the first direction, the connecting plate is located in the test space and is mounted at one end of the screw rod facing the base, and the latch hook release mechanism is mounted on the connecting plate facing one side of the base.
9. The shock test device for a flying car of claim 8, wherein the lift mechanism further comprises a second drive cylinder disposed between the shackle release mechanism and the connecting plate for driving the shackle release mechanism to move in the first direction.
10. The shock test device for a flying car according to claim 1, wherein the latch hook release mechanism comprises a driving cylinder and a claw, a fixing piece is further arranged on the top surface of the lifting platform, the driving cylinder is installed on the lifting mechanism, the claw is installed at the output end of the driving cylinder, the driving cylinder is used for controlling opening and closing of the claw, and the claw is disconnected with the fixing piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311287292.7A CN117030292A (en) | 2023-10-08 | 2023-10-08 | Shock-falling testing device for aerocar |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311287292.7A CN117030292A (en) | 2023-10-08 | 2023-10-08 | Shock-falling testing device for aerocar |
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| CN117030292A true CN117030292A (en) | 2023-11-10 |
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| CN202311287292.7A Pending CN117030292A (en) | 2023-10-08 | 2023-10-08 | Shock-falling testing device for aerocar |
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