CN106525477B - Folding missile wing simulation loading test device - Google Patents
Folding missile wing simulation loading test device Download PDFInfo
- Publication number
- CN106525477B CN106525477B CN201611192182.2A CN201611192182A CN106525477B CN 106525477 B CN106525477 B CN 106525477B CN 201611192182 A CN201611192182 A CN 201611192182A CN 106525477 B CN106525477 B CN 106525477B
- Authority
- CN
- China
- Prior art keywords
- missile wing
- force
- resistance
- loading
- mounting hole
- 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.)
- Active
Links
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
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/007—Subject matter not provided for in other groups of this subclass by applying a load, e.g. for resistance or wear testing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to the technical field of folding missile wing simulation test equipment, and discloses a folding missile wing simulation loading test device which comprises a total bench, a resistance loading assembly and a lift loading assembly, wherein a resistance driving assembly of the resistance loading assembly applies resistance which is always opposite to the speed direction of a missile wing through a force rod and a follow-up axial missile wing, and a lift driving assembly of the lift loading assembly applies vertical upward force to a lift loading table surface so as to apply lift to the missile wing.
Description
Technical Field
The invention relates to the technical field of folding missile wing simulation test equipment, in particular to a folding missile wing simulation loading test device.
Background
At present, various airborne missiles adopt a foldable missile wing design, so that the requirements of small volume and long-distance attack of the airborne missiles are met simultaneously. Because the loading condition of the missile body in the flying process is complex, and a plurality of influencing factors such as the attitude of the missile body, the air flow direction, the flying height and the flying speed need to be considered, the missile wing unfolding mechanism must be subjected to comprehensive simulation joint unfolding test in the developing process. Meanwhile, in the unfolding process of the folding wing, the missile is required to be unfolded according to the requirement, and certain requirements are also met on the instantaneous angular speed, the angular acceleration and the like of the wing surface in place, so that the impact overload is not too large to cause adverse effects on the missile body, and therefore, the determination of the loading mode of the missile wing has important significance for weapon model development.
The purpose of the simulation test is to measure relevant parameters of the action mechanism after the action mechanism is loaded according to requirements after the action mechanism is subjected to three comprehensive environments of temperature, humidity and vibration. The loading of the loading system of the existing missile wing simulation mechanism mainly simulates the lifting and resistance environments, wherein the simulation values of lifting and resistance are calculated according to blowing data and related parameters, and the test aims at mainly measuring parameters such as the stretching time, the angular velocity and angular acceleration curve and the like of the stretched missile wing.
The existing missile wing mechanism loading resistance mode is basically balance weight spring loading, the simulated load applied by the balance weight forms a certain angle with the real resistance direction due to the loading principle, the angle changes in real time, the balance weight can generate a certain additional load on the missile wing, and the balance weight spring loading is difficult to accurately and effectively simulate the resistance to the reason; for the simulation of the lifting force, the supporting force component of the inclined plane support is basically adopted as the lifting force born by the missile wing mechanism, the supporting force of the missile wing acting on the missile wing is changed due to the change of the distance between the missile wing pressing center and the mesa in the process of opening the missile wing, and the change of the lifting force in the process is simulated, but because the lifting force is the supporting force component, the other supporting force component cannot be eliminated, and the experiment may be caused.
Disclosure of Invention
First, the technical problem to be solved
The invention provides a folding missile wing simulated loading test device which aims at solving the problems that the existing lifting and resistance loading simulated loading is inaccurate and the test is possibly caused.
(II) technical scheme
In order to solve the technical problems, the invention provides a folding missile wing simulated loading test device, which comprises a general bench, a resistance loading assembly and a lift loading assembly, wherein the general bench comprises a horizontal general table top, the resistance loading assembly comprises a force rod and a resistance driving assembly, one end of the force rod is fixed on the general table top, the general table top is also provided with a missile wing fixing assembly at one end for fixing the force rod, the non-unfolding end of the missile wing is fixed by the missile wing fixing assembly, the force rod is consistent with the axial extension direction of the missile wing and a strip-shaped missile wing resistance transmission hole extending along the length direction of the force rod is reserved at the pressing center position of the missile wing, the lower end of the follow-up shaft penetrates through the missile wing to be in sliding connection with the general table top, the upper end of the follow-up shaft is arranged in the missile wing resistance transmission hole, a gap is reserved between the follow-up shaft and the lateral surfaces at the two ends of the length direction of the missile wing resistance transmission hole, and the follow-up shaft is fixedly connected with the missile wing; the force rod rotates synchronously with the missile wing by taking a fixed point of the force rod on the overall table top as a rotating center under the action force of the deployment of the missile wing, and the resistance driving assembly applies resistance which is always opposite to the speed direction of the missile wing through the force rod and the follow-up axial missile wing; the lifting force loading assembly comprises a lifting force loading table surface and a lifting force driving assembly for driving the lifting force loading table surface to move up and down, the lifting force loading table surface is parallel to the missile wing setting plane and is arranged below the missile wing, and the lifting force driving assembly applies vertical upward force to the lifting force loading table surface so as to apply lifting force to the missile wing.
Further, the missile wing fixing assembly comprises a missile wing fixing block, the missile wing fixing block is of a 'type', the lower end of the 'type' of the missile wing fixing block is connected to the overall table top, and the non-unfolding end of the missile wing is clamped below the horizontal section of the 'type' of the missile wing fixing block.
Further, the force bar is fixed on the overall table top through a force bar connecting block, the force bar connecting block is ' shaped ', the lower end of the ' shaped ' of the force bar connecting block is fixedly connected with the overall table top, and the force bar is fixedly connected with the ' shaped horizontal section of the force bar connecting block through a first connecting pin.
Further, a first mounting hole is formed in the horizontal section of the force rod connecting block, a second mounting hole is formed in the force rod corresponding to the first mounting hole, the first connecting pin penetrates through the first mounting hole and the second mounting hole to fix the force rod and the force rod connecting block, and a first deep groove ball bearing is arranged between the first mounting hole and the pin shaft of the second connecting pin and between the first mounting hole and the pin shaft of the first connecting pin.
Further, the resistance driving component is a resistance electric cylinder hinged on the overall table top, the output end of the resistance electric cylinder is connected with the force rod through a second connecting pin, and the force rod pushes the resistance electric cylinder to rotate through the second connecting pin.
Further, the output end of the resistance electric cylinder is provided with a third mounting hole, the force rod is provided with a fourth mounting hole corresponding to the third mounting hole, the second connecting pin penetrates through the third mounting hole and the fourth mounting hole to fixedly connect the force rod with the output end of the resistance electric cylinder, and a second deep groove ball bearing and a thrust bearing are arranged between the third mounting hole and the fourth mounting hole and between the second connecting pin and the pin shaft.
Further, the lower end of the follow-up shaft is in sliding contact with the lifting force loading table top through a universal ball bearing.
Further, the overall bench further comprises a supporting upright post, a side plate and a bottom plate, wherein the bottom plate is arranged in parallel with the overall table top, the side plate is vertically connected between the bottom plate and the overall table top, and the supporting upright post is vertically arranged on the bottom plate and is in supporting connection with the overall table top.
Further, the lift driving assembly is a lift electric cylinder, the lift electric cylinder is fixed on the bottom plate, the output end of the lift electric cylinder is connected with the center of the bottom of the lift loading table top, and a supporting frame is arranged at the bottom of the lift loading table top.
Further, the bottom plate is provided with a lifting screw.
(III) beneficial effects
The technical scheme of the invention has the following advantages: the folding missile wing simulated loading test device provided by the invention can simulate the change of loading resistance in real time, ensures that the acting direction of the resistance is always opposite to the speed direction of the missile wing in the rotating process, directly acts as lifting force for lifting force loading by applying upward force, eliminates the defect that the other component of the supporting force cannot be eliminated in the original method, and simulates aerodynamic force loading more truly and accurately.
In addition to the technical problems, features of the constituent technical solutions and advantages brought by the technical features of the technical solutions described above, other technical features of the present invention and advantages brought by the technical features of the technical solutions, further description will be made with reference to the accompanying drawings.
Drawings
FIG. 1 is a three-dimensional schematic view of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 2 is a schematic front view of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram of the lift loading of a folding missile wing simulated loading test device in accordance with the embodiment of the present invention;
FIG. 4 is a drag loading schematic diagram of a folding missile wing simulated loading test device in accordance with the embodiment of the present invention;
FIG. 5 is a schematic diagram of a force lever of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 6 is a schematic diagram of a connection between a force lever and a resistance electric cylinder of a folding missile wing simulated loading test device in accordance with the embodiment of the present invention;
FIG. 7 is a schematic diagram of a connection form of a force rod and a connection block of a folding missile wing simulation loading test device according to the embodiment of the present invention;
FIG. 8 is a schematic front view of a lift loading table of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 9 is a schematic top view of a lift loading table of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 10 is a schematic front view of a connection block of a folding missile wing simulated loading test device in accordance with the embodiment of the present invention;
FIG. 11 is a schematic top view of a connection block of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention;
FIG. 12 is a flowchart of the operation of a folding missile wing simulated loading test device in accordance with an embodiment of the present invention.
In the figure: 1: a bottom plate; 2: a side plate; 3: a support column; 4: an overall mesa; 5: a resistance cylinder connecting seat; 6: resistance force an electric cylinder; 7: a third screw; 8: a fourth screw; 9: a missile wing fixing block; 10: a force rod connecting block; 11: a thrust ball bearing; 12: a first connecting pin; 13: a first nut; 14: a first deep groove ball bearing; 15: a second nut; 16: a retainer ring; 17: a second connecting pin; 18: a second deep groove ball bearing; 19: a force lever; 20: a support lug seat; 21: a fifth screw; 22: a follower shaft; 23: a universal ball bearing; 24: a lift loading table; 25: a missile wing; 26: a suspension ring screw; 27: a linear bearing; 28: a second screw; 29: a lift electric cylinder; 30: a lifting force electric cylinder connecting seat; 31: a support rod; 32: a support rod connecting seat; 33: first one a screw; 34: a gasket.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Furthermore, in the description of the present invention, unless otherwise indicated, the meaning of "a plurality", "a plurality of groups" means two or more, and the meaning of "a plurality", "a plurality of roots", "a plurality of groups" means one or more.
As shown in fig. 1 and 2, the folding missile wing simulation loading test device provided by the embodiment of the invention comprises an overall bench, a resistance loading assembly and a lift loading assembly.
The overall bench comprises a horizontal overall table top 4, wherein a missile wing fixing component for fixing a missile wing 25 on the overall table top 4 is arranged on the overall table top 4, the missile wing fixing component can be a missile wing fixing block 9, the lower end of the missile wing fixing block 9 is connected to the overall table top, and the non-unfolding end of the missile wing is clamped below the horizontal section of the missile wing fixing block.
The lift loading assembly includes a lift loading platform 24 and a lift drive assembly that drives the lift loading platform to move up and down.
The resistance loading assembly comprises a force rod 19 and a resistance driving assembly, one end of the force rod is also fixed on the overall table surface, the fixed end of the force rod is consistent with the fixed end of the non-unfolding end of the missile wing, the missile wing 25 is coaxially arranged with the force rod 19, the force rod 19 is provided with a strip-shaped missile wing resistance transmission hole extending along the length direction of the force rod 19 at the pressing center position of the missile wing, the missile wing is provided with a follow-up shaft 22 at the pressing center position of the missile wing, the lower end of the follow-up shaft 22 penetrates through the missile wing to be in sliding connection with the overall table surface, the upper end of the follow-up shaft 22 is arranged in the missile wing resistance transmission hole, a gap is reserved between the follow-up shaft and the lateral surfaces of the two ends of the missile wing resistance transmission hole in the length direction, and the follow-up shaft 22 is fixedly connected with the missile wing; the force rod rotates synchronously with the missile wing by taking a fixed point of the force rod on the overall table top as a rotating center under the action of the deployment of the missile wing, and the resistance driving assembly applies resistance which is always opposite to the speed direction of the missile wing through the force rod and the follow-up axial missile wing.
It is understood that the non-deployed end of the missile wing refers to the end of the missile wing which can be fixed all the time, namely the end is the end of the missile wing serving as a deployment center point; a gap is reserved between the follow-up shaft and the side surfaces of the two ends of the missile wing resistance transmission hole in the length direction, namely, the follow-up shaft is arranged in the middle of the missile wing resistance transmission hole, so that the end surfaces of the two ends of the follow-up shaft missile wing resistance transmission hole are not contacted, and the force from the resistance driving assembly is transmitted to the follow-up shaft 22 through the force rod 19 and is only perpendicular to the movement direction of the missile wing, so that the resistance driving assembly applies resistance which is always opposite to the speed direction of the missile wing through the force rod and the follow-up axial missile wing.
In the folding missile wing simulated loading test device of the embodiment, the resistance driving component applies aerodynamic resistance to the missile wing 25 through the force rod 19 in a simulated manner, and the lift driving component applies vertical upward force to the lift loading table 24 so as to apply lift to the missile wing 25. The folding missile wing simulation loading test device can simulate the change of loading resistance in real time, ensures that the resistance direction is always opposite to the movement direction of the missile wing 25, directly acts as lifting force for lifting force loading by applying vertical upward force, eliminates the defect that the other component of the supporting force cannot be eliminated in the original method, and simulates aerodynamic force loading more truly and accurately.
The missile wing 25 is fixedly connected with the force rod 19 coaxially, and preferably, the missile wing 25 can be arranged above or below the force rod 19.
As shown in fig. 1, the overall bench further comprises a bottom plate 1, side plates 2 and a supporting upright post 3, wherein the bottom plate 1 is parallel to the overall table top 4, the side plates 2 are vertically connected between the bottom plate 1 and the overall table top 4 to form a rectangular frame, and the side plates 2 are respectively in threaded connection with the overall table top 4 and the bottom plate 1 through angle irons; the support upright post 3 is I-shaped steel, is connected with the overall table top 4 and the bottom plate 1 through bolts, and supports the overall table top 4; preferably, the bottom plate 1 is provided with a lifting screw 26 on the outer side of the side plate, and the lifting screw 26 can facilitate the whole lifting of the system.
As shown in fig. 2, as an implementation, the lift driving assembly employs a lift electric cylinder 29, and the lift electric cylinder 29 is fixed to the base plate 1 through a lift electric cylinder connection seat 30. The lifting force loading table surface 24 consists of a Q235-A plate, a reinforcing rib is arranged at the bottom, 5 groups of threaded holes are formed in the lower bottom surface, wherein the central threaded group is used for installing a lug seat 20, and the lug seat 20 connects the output end of a lifting force electric cylinder 29 with the lifting force loading table surface 24; the other four sets of threaded bores mount the support structure of the lift loading table 24. Support frame of lift loading table 24 consists of four groups of supporting structures.
The supporting structure consists of a supporting rod 31, a linear bearing 27 sleeved outside the bottom end of the supporting rod and a supporting rod connecting seat 32. The support rod is used for supporting the lifting loading table top, the support rod connecting seat 32 is arranged at the upper end of the support rod, and the support rod 31 is in threaded connection with the lifting loading table top 24 by matching the support rod connecting seat 32 with the first screw 33; the linear bearing 27 is used to prevent the support bar 31 from tilting, and is screwed to the base plate by its bearing connection 32 in cooperation with the second screw 28.
As shown in fig. 2, the end of the force bar 19 near the resistance drive assembly is connected to the overall table top 4, and the force bar 19 can horizontally rotate about its connection position.
As shown in fig. 2, the force bar 19 is preferably fastened to the overall table top 4 by means of a force bar connection block 10. As shown in fig. 9, the force bar connection block 10 is of a "type" and a reinforcing rib is further connected between the transverse mounting seat and the vertical support. The specific structure of the force bar 19 fixed on the overall table top is shown in fig. 1, the lower end of the force bar connecting block 10 is fixedly connected with the overall table top, and the force bar 19 is fixedly connected with the horizontal section of the force bar connecting block 10 through the first connecting pin 12.
As an implementation manner, as shown in fig. 6, a first mounting hole is provided on a horizontal section of the force rod connection block 10, a second mounting hole is provided on the force rod 19 corresponding to the first mounting hole, the first connecting pin 12 passes through the first mounting hole and the second mounting hole to fix the force rod with the fixing block, and a first deep groove ball bearing 14 and a thrust bearing 11 are provided between the first mounting hole and the second mounting hole and between the pin shafts of the first connecting pin. The first nut is shown at 13 which mates with the first connecting pin.
As shown in fig. 2, as a missile wing fixing block 9 matched with the force rod 19, the missile wing fixing block 9 is arranged on one side of the force rod connecting block 10, and a slotted hole is formed in the missile wing fixing block 9, so that the fixing position of the fourth screw 8 can be conveniently adjusted.
The force rod 19 is connected with the force rod connecting block 10 through the first connecting pin 12, so that the force rod 19 is fixed, and the axis when the force rod 19 is connected with the force rod connecting block 10 is required to be ensured to coincide with the rotation central axis of the folding missile wing during installation. Since the force rod connection block 10 is of a fixed design, the missile wing fixing block 9 is also of a fixed structure fixed on the overall table top 4, and the connecting axis of the missile wing 25 is fixed, so that the rotation center of the force rod 19 and the rotation center of the missile wing are always coaxial for any product form only by arranging the hole of the force rod connection block 10 on the installation axis of the missile wing. The deep groove ball bearing 14 is arranged between the force rod and the first connecting pin 12, so that the first connecting pin 12 can rotate along with the resistance electric cylinder, the thrust ball bearing 11 is arranged between the force rod 19 and the first connecting pin 12, and the thrust ball bearing can be tightly pressed by the gasket 34, thereby preventing the first connecting pin 12 from moving up and down and meeting the relative movement between the force rod 19 and the force rod connecting block 10.
The resistance driving component is a resistance electric cylinder 6 hinged on the overall table top 4 through a resistance cylinder connecting seat 5 and a third screw 7, the output end of the resistance electric cylinder 6 is connected with a force rod 19 through a second connecting pin 17, and the force rod 19 synchronously rotates with the resistance electric cylinder 6 through the second connecting pin 17.
The force rod 19 is connected with the resistance electric cylinder 6 through the second connecting pin 17, and the resistance electric cylinder 6 applies a force to the force rod 19 through the second connecting pin 17.
As a preferable mode of connecting the force rod 19 with the resistance electric cylinder 6, as shown in fig. 6, a third mounting hole is provided at the output end of the resistance electric cylinder 6, a fourth mounting hole is provided corresponding to the third mounting hole in the force rod 19, the second connecting pin 17 passes through the third mounting hole and the fourth mounting hole to fixedly connect the force rod with the output end of the resistance electric cylinder, and a second deep groove ball bearing 18 is respectively provided between the third mounting hole and the pin shaft of the fourth mounting hole and between the second connecting pin 17. Wherein, the third mounting hole and the fourth mounting hole are both structures with clamping grooves at one ends, and one end of the second deep groove ball bearing 18 is clamped in the clamping grooves and the other end is tightly pressed by the check ring 16. Reference numeral 15 in the drawing denotes a second nut which cooperates with the second connecting pin 17.
The second deep groove ball bearing 18 is arranged between the force rod 19 and the second connecting pin 17 and is tightly pressed by the check ring 16, so that the second connecting pin can be prevented from moving up and down, and the second deep groove ball bearing 18 is also arranged between the resistance electric cylinder 6 and the second connecting pin 17 and is tightly pressed by the check ring, so that the lateral resistance effect can be enhanced.
As a preferred mode, the force rod 19 is provided with a slotted hole for connecting with the pressing center position of different test pieces (folding missile wings) and reducing weight.
As shown in fig. 2, the lower end of the follower shaft 22 of the present embodiment is fixedly connected with a universal ball bearing 23 by a fifth bolt, the universal ball bearing 23 is capable of contacting and sliding with the lift loading platform 24 through the force bar 19 and the missile wing 25.
The folding missile wing 25 of test piece is connected with the force rod 19 and the lifting force loading table 24 through the follow-up shaft 22, the follow-up shaft 22 is arranged at the test piece pressing center so as to ensure that the simulated aerodynamic force applied by the loading system always acts at the missile wing pressing center, the tail end of the follow-up shaft 22 is provided with the universal ball bearing 23, the condition that the missile wing 25 always contacts with the lifting force loading table 24 in the rotating unfolding process is ensured, and a force sensor can be arranged at the joint of the follow-up shaft 22 and the test piece 25 to respectively monitor the lifting force and the resistance value applied in the test process in real time.
The working principle of the folding missile wing simulation loading test device of the embodiment is as follows:
the lifting force loading principle is shown in fig. 3, after the electric cylinder and the linear bearing are reasonably arranged, the table top realizes translation, and the thrust of the electric cylinder is consistent with the lifting force. During test, firstly, the electric lift cylinder 29 is started, the electric lift cylinder push rod is connected with the lift loading table 24 through the lift cylinder connecting seat 20, translation of the lift loading table is achieved by changing the elongation of the electric lift cylinder rod until the lift loading table 24 is contacted with the universal ball bearing 23, the lift sensor displays an initial value, the initial value is cleared when the test starts, the electric lift cylinder 29 is continuously controlled to achieve loading, the lift loading table 24 acts on the pressing center of the folding missile wing test product 25 through the universal ball bearing 23 and the follow-up shaft 22, the actual loading value is fed back by comparing the target lift loading value with the sensor, and accordingly real-time correction is carried out on the actual loading, and simulated lift loading is completed.
The principle of resistance loading is shown in fig. 4, an x-y two-dimensional coordinate system is established by using the rotation center of the missile wing, namely the position of the first pin shaft 12 as a center point in fig. 3, wherein a point A in fig. 3 represents a point where the resistance electric cylinder is hinged on the overall table, a point B is a connection point of the first pin shaft 12, namely the force rod connecting block, and the force rod, a point C, D is respectively different positions of the second pin shaft 17, namely the fixed point of the resistance electric cylinder and the force rod, in the process of rotating the force rod, when beta, the missile wing rotates to the position, the included angle between the missile wing axis and the output force F of the resistance electric cylinder is formed, and when theta is the missile wing rotates to the position, the included angle between the missile wing axis and the x axis is formed. The direction of the output force F of the resistance electric cylinder is always along the direction of the cylinder rod.
x 0 The length of the cylinder rod when the second pin shaft 17 moves to the point D; l represents the distance of the hinge point of the resistance cylinder from the first pin 12, R represents the distance of the first pin 12 from the second connecting pin 17, and R represents the distance of the follower shaft 22 from the first pin 12.
The resistance electric cylinder 6 applies a force to the force rod 19 through the connecting pin 12, the force rod 19 transmits the force applied by the resistance electric cylinder 6 to the test piece folding missile wing 25 through the follower shaft 22, the resistance applied in the process of opening the missile wing is simulated, and the applied resistance is always vertical to the folded missile wing, so that the real situation is met.
F D ·R-F 0 ·r＝Jα
F 0 ＝F sinβ
Since α (angular acceleration during rotation of the missile wing) is unknown, it is assumed that jα=0, it is possible to obtain
The output force F curve of the electric cylinder can be obtained by setting the target resistance load FD, the resistance electric cylinder 6 is controlled to be loaded before the test starts until the follow-up shaft 22 is contacted with the force rod 19, the resistance sensor displays an initial value, the initial value is cleared when the test starts, the resistance electric cylinder 6 is continuously controlled to be loaded, and the target resistance load is corrected in real time according to the feedback value of the resistance sensor at the position of the pressing center, so that the purpose of loading resistance at the position of the pressing center is achieved. The weight of the force rod in the structural design is as light as possible, so that the moment of inertia J is smaller, and the difference between the calculated initial electric cylinder output force F curve and the true value is reduced.
The use process of the simulated loading test device for the folding missile wing of the embodiment is shown in fig. 12.
To sum up, the simulation loading test device for the folding missile wing of the embodiment has the following advantages: the loading test bed has certain universality, a universal interface for installing the folding wing mechanism is arranged, and different types of folding wings can share one set of test bed; the whole unfolding process of the folding missile wing mechanism can be realized, resistance and lifting load can be applied to two missile wings according to the angle change rule of the missile wings, and each missile wing can realize different load loading which is an independent control channel; by adopting the novel loading principle, the change of loading resistance can be simulated in real time, the resistance direction is always vertical to the speed direction, a novel loading method is adopted for lift loading simulation to eliminate the defect that the other component of the supporting force in the original method cannot be eliminated, and aerodynamic loading is simulated more truly and accurately; the loading precision is high, the response speed is high, and the additional mass in the loading process is small.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A folding missile wing simulation loading test device is characterized in that: the device comprises a general bench, a resistance loading assembly and a lift loading assembly;
the global stage includes a horizontal global table top;
the resistance loading assembly comprises a force rod and a resistance driving assembly, one end of the force rod is fixed on the overall table top, the overall table top is also provided with a missile wing fixing assembly at one end for fixing the force rod, the non-unfolding end of the missile wing is fixed through the missile wing fixing assembly, the force rod is consistent with the axial extension direction of the missile wing, a long-strip missile wing resistance transmission hole extending along the length direction of the force rod is reserved at the pressing center position of the missile wing, the missile wing is provided with a follow-up shaft at the pressing center position of the missile wing, the lower end of the follow-up shaft penetrates through the missile wing and is in sliding connection with the overall table top, the upper end of the follow-up shaft is arranged in the missile wing resistance transmission hole, a gap is reserved between the follow-up shaft and the lateral surfaces at the two ends of the length direction of the missile wing resistance transmission hole, and the follow-up shaft is fixedly connected with the missile wing; the force rod rotates synchronously with the missile wing by taking a fixed point of the force rod on the overall table top as a rotating center under the action force of the deployment of the missile wing, and the resistance driving assembly applies resistance which is always opposite to the speed direction of the missile wing through the force rod and the follow-up axial missile wing;
the lifting force loading assembly comprises a lifting force loading table surface and a lifting force driving assembly for driving the lifting force loading table surface to move up and down, the lifting force loading table surface is parallel to the missile wing setting plane and is arranged below the missile wing, and the lifting force driving assembly applies vertical upward force to the lifting force loading table surface so as to apply lifting force to the missile wing.
2. The folding missile wing simulated loading test device according to claim 1, wherein: the missile wing fixing assembly comprises a missile wing fixing block, the missile wing fixing block is of a shape, the lower end of the shape of the missile wing fixing block is connected to the overall table top, and the non-unfolding end of the missile wing is clamped below the horizontal section of the shape of the missile wing fixing block.
3. The folding missile wing simulated loading test device according to claim 2, wherein: the force rod is fixed on the overall table top through a force rod connecting block, the force rod connecting block is of a ' shape ', the lower end of the force rod connecting block is fixedly connected with the overall table top, and the force rod is fixedly connected with the horizontal section of the ' shape of the force rod connecting block through a first connecting pin.
4. A folding missile wing simulated loading test device according to claim 3, wherein: the horizontal segment of power pole connecting block is provided with first mounting hole, correspond on the power pole first mounting hole is provided with the second mounting hole, first connecting pin passes first mounting hole, second mounting hole will the power pole with the power pole connecting block is fixed, first mounting hole with in the second mounting hole with be provided with first deep groove ball bearing between the round pin axle of first connecting pin respectively.
5. The folding missile wing simulated loading test device according to claim 1, wherein: the resistance driving component is a resistance electric cylinder hinged on the overall table top, the output end of the resistance electric cylinder is connected with the force rod through a second connecting pin, and the force rod pushes the resistance electric cylinder to rotate through the second connecting pin.
6. The folding missile wing simulated loading test device according to claim 5, wherein: the output end of the resistance electric cylinder is provided with a third mounting hole, the force rod is provided with a fourth mounting hole corresponding to the third mounting hole, the second connecting pin penetrates through the third mounting hole and the fourth mounting hole to fixedly connect the force rod with the output end of the resistance electric cylinder, and a second deep groove ball bearing and a thrust bearing are arranged between the third mounting hole and the second connecting pin shaft in the fourth mounting hole.
7. The folding missile wing simulated loading test device according to claim 1, wherein: the lower end of the follow-up shaft is in sliding contact with the lifting force loading table surface through a universal ball bearing.
8. The folding missile wing simulated loading test device according to any one of claims 1-7, wherein: the overall bench further comprises a supporting upright post, a side plate and a bottom plate, wherein the bottom plate is arranged in parallel with the overall table top, the side plate is vertically connected between the bottom plate and the overall table top, and the supporting upright post is vertically arranged on the bottom plate and is in supporting connection with the overall table top.
9. The folding missile wing simulated loading test device according to claim 8, wherein: the lifting force driving assembly is a lifting force electric cylinder, the lifting force electric cylinder is fixed on the bottom plate, the output end of the lifting force electric cylinder is connected with the center of the bottom of the lifting force loading table top, and a supporting frame is arranged at the bottom of the lifting force loading table top.
10. The folding missile wing simulated loading test device according to claim 8, wherein: and the bottom plate is provided with a suspension ring screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611192182.2A CN106525477B (en) | 2016-12-21 | 2016-12-21 | Folding missile wing simulation loading test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611192182.2A CN106525477B (en) | 2016-12-21 | 2016-12-21 | Folding missile wing simulation loading test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106525477A CN106525477A (en) | 2017-03-22 |
| CN106525477B true CN106525477B (en) | 2023-08-29 |
Family
ID=58340258
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611192182.2A Active CN106525477B (en) | 2016-12-21 | 2016-12-21 | Folding missile wing simulation loading test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106525477B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107264836B (en) * | 2017-07-28 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door large-range follow-up loading test device and test method |
| EP3492370B1 (en) * | 2017-11-17 | 2020-07-15 | Airbus Operations GmbH | Method for testing operation of an arresting unit for locking a foldable wing tip portion in an extended position |
| CN110954395B (en) * | 2019-11-12 | 2022-08-30 | 航天时代飞鸿技术有限公司 | Elastic loading device and method for folding missile wing performance test |
| CN113044241B (en) * | 2019-12-27 | 2022-12-23 | 北京理工大学 | Gear rack unfolding wing experiment platform and experiment method adopting same |
| CN111256966A (en) * | 2020-01-22 | 2020-06-09 | 武汉船用机械有限责任公司 | Loading test device of shark pincers |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4759736A (en) * | 1986-02-11 | 1988-07-26 | Off The Ground Models, Inc. | Folding wing glider |
| CN104457443A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Up-down loading device for stacked folding wings |
| CN204286756U (en) * | 2014-07-25 | 2015-04-22 | 中国航天科工集团第六研究院四十一所 | A kind of missile wing aerodynamic loading analog loading test device |
| CN106507937B (en) * | 2013-07-08 | 2015-05-20 | 浙江理工大学 | A kind of folding wings development mechanism ground simulation test device |
| CN206258268U (en) * | 2016-12-21 | 2017-06-16 | 北京强度环境研究所 | A kind of folding wing analog loading test device |
-
2016
- 2016-12-21 CN CN201611192182.2A patent/CN106525477B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4759736A (en) * | 1986-02-11 | 1988-07-26 | Off The Ground Models, Inc. | Folding wing glider |
| CN106507937B (en) * | 2013-07-08 | 2015-05-20 | 浙江理工大学 | A kind of folding wings development mechanism ground simulation test device |
| CN204286756U (en) * | 2014-07-25 | 2015-04-22 | 中国航天科工集团第六研究院四十一所 | A kind of missile wing aerodynamic loading analog loading test device |
| CN104457443A (en) * | 2014-11-24 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Up-down loading device for stacked folding wings |
| CN206258268U (en) * | 2016-12-21 | 2017-06-16 | 北京强度环境研究所 | A kind of folding wing analog loading test device |
Non-Patent Citations (1)
| Title |
|---|
| 一种新型弹翼加载试验方法研究;靳向往 等;《机械工程师》(第2期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106525477A (en) | 2017-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106525477B (en) | Folding missile wing simulation loading test device | |
| CN101726401B (en) | Scale measuring device for pitching dynamic derivative experiment | |
| CN103979106B (en) | The rotary wind type unmanned plane of a kind of automatic adjustment center of gravity and method of adjustment | |
| CN112224447B (en) | Device and method for measuring gravity center of unmanned aerial vehicle and matching thrust line | |
| CN108645566B (en) | Bullet arrow mass center moment of inertia testboard | |
| CN107247839B (en) | Design method of low-speed wind tunnel virtual flight test airplane model | |
| CN106828972B (en) | A kind of aircraft rudder surface drive ram performance testing device | |
| CN107867414B (en) | Twelve-degree-of-freedom spacecraft simulator docking performance test device | |
| CN106769013A (en) | A kind of loading inertia test apparatus of motor-driven cylinder | |
| CN110745256B (en) | Moment balance test bed for short-distance/vertical take-off and landing aircraft | |
| CN206258268U (en) | A kind of folding wing analog loading test device | |
| CN208588502U (en) | A kind of bullet arrow quality center of mass rotary inertia testboard | |
| CN106425450A (en) | Automatic assembly equipment with wheel type locating combined with space motion posture adjusting | |
| CN113895649A (en) | Ground test system and method for rotor type unmanned aerial vehicle flight dynamics modeling | |
| CN111044221B (en) | Three-dimensional inertia testboard adjusting device of unmanned aerial vehicle | |
| CN103434656B (en) | Rigidity simulator with variable rigidity | |
| CN114166496B (en) | Tilt rotor wing test device | |
| CN110001328B (en) | Spacecraft simulation device | |
| JPH08313388A (en) | Wind tunnel test device | |
| CN101281010A (en) | Test platform for movable spherical robot | |
| CN206813342U (en) | Dynamic equilibrium machinery arm | |
| CN109813521A (en) | A kind of plant protection drone wind field detection device | |
| CN115508038A (en) | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion | |
| CN210375704U (en) | Aeroengine test bench | |
| CN107902106A (en) | Unmanned apparatus test device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |