A six-degree-of-freedom flight simulation platform

Abstract

The application provides a six-freedom flight simulation platform, which comprises a foundation, a foundation pit arranged in the foundation, a ground cage arranged at the bottom of the foundation pit, three embedded plates fixedly arranged on the ground cage, a driving assembly arranged on each embedded plate, and an upper supporting platform connected to the upper ends of the driving assemblies; a plurality of foundation bolts are fixedly arranged on the embedded plates, and a plurality of nuts are threadedly arranged on each foundation bolt; and the upper supporting platform is used for bearing and connecting a flight vehicle to be detected. In the application, the foundation bolts and the nuts are used to hook the lower ends of the foundation bolts to the ground cage, and then the nuts are screwed on the upper ends of the foundation bolts, so that the embedded plates and the ground cage can be quickly connected and fixed, the foundation bolts are symmetrically distributed on the two sides of the embedded plates, the stress is uniform, the fixation is stable, three nuts are screwed on the foundation bolts, the fixation effect is good, and the nuts will not fall off.

Description

Technical Field

[0001] This invention relates to the field of motion state simulation technology for aircraft and other flight vehicles, and in particular to a six-degree-of-freedom flight simulation platform. Background Technology

[0002] A multi-degree-of-freedom motion platform is a test device used to simulate the motion and turbulence of aircraft and other flying vehicles. A standard multi-degree-of-freedom motion platform is mainly used for heavy-load lifting. By changing multiple degrees of freedom, the equipment or other items on the platform can be moved quickly and flexibly to a suitable position.

[0003] However, when the existing multi-degree-of-freedom motion platform's embedded plate is connected to the ground cage, although bolt connection is used, which has high strength, the structure is not compatible with the ground cage, making the operation more troublesome, and it cannot be installed and fixed quickly, and the stress load is uneven. Summary of the Invention

[0004] The purpose of this invention is to provide a six-degree-of-freedom flight simulation platform to solve the technical problems existing in the prior art.

[0005] To solve the above-mentioned technical problems, the present invention provides a six-degree-of-freedom flight simulation platform, including a foundation, a pit set in the foundation, and a ground cage set at the bottom of the pit. Three pre-embedded plates are fixedly installed on the ground cage, and each pre-embedded plate is provided with a drive component. The upper end of the drive component is connected to an upper support platform.

[0006] Multiple anchor bolts are fixed on the embedded plate, and multiple nuts are threaded onto each anchor bolt;

[0007] The upper support platform is used to support and connect the tested flight vehicle.

[0008] Preferably, the drive assembly includes two lower hinge seats fixed to the embedded plate. The upper ends of the lower hinge seats are rotatably connected to lower hinge components. The upper ends of the lower hinge components are fixedly connected to electric cylinders. The upper ends of the electric cylinders are fixedly connected to upper hinge components. The upper ends of the two upper hinge components are rotatably connected to upper hinge seats. The tops of the two upper hinge seats are fixedly connected to the same connecting plate. The connecting plate is fixedly installed at the bottom of the upper support platform.

[0009] Preferably, the three sets of upper hinge seats are evenly distributed at 120 degrees along a circumference with a diameter of 2600 mm, and the three sets of lower hinge seats are evenly distributed at 120 degrees along a circumference with a diameter of 3200 mm.

[0010] Preferably, the number of anchor bolts is 8, and the model is M30X500, with 3 nuts on each anchor bolt.

[0011] Preferably, the upper support platform is welded from channel steel, and the upper support platform consists of a U-shaped frame and multiple crossbeams fixed to the inner wall of the U-shaped frame. The material of the upper support platform is Q235.

[0012] Preferably, the ground cage is made of HRB335φ16 steel bars.

[0013] Preferably, the depth of the pit is 1200mm.

[0014] Preferably, the cage is Y-shaped.

[0015] Preferably, the upper support platform has an external dimension of 6000 mm. 4130mm.

[0016] Preferably, it also includes a shock-absorbing base plate for vibration reduction, through which the tested flight vehicle is mounted on the support platform.

[0017] Preferably, the shock-absorbing seat plate includes an upper seat plate and a lower seat plate; the upper seat plate is slidably mounted on the lower seat plate along the X-axis direction (i.e., the front-to-back direction); the aircraft being tested is fixedly mounted on the upper seat plate, while the lower seat plate is fixedly connected to the support platform by fasteners.

[0018] Preferably, an oil-gas damping system is provided between the upper seat plate and the lower seat plate. The oil-gas damping system includes: an oil cylinder, an oil reservoir, a first pressure valve, and an oil return pipeline.

[0019] The hydraulic cylinder includes a cylinder body, a piston, and a piston rod; the cylinder body is fixedly connected to the lower seat plate, and the piston rod is fixedly connected to the upper seat plate;

[0020] The rod-side chamber and rodless chamber of the hydraulic cylinder are respectively connected to the oil storage tank through a return oil pipeline, and a first pressure valve is provided on the return oil pipeline.

[0021] Preferably, the return oil pipeline includes a first return oil branch and a second return oil branch;

[0022] The rod chamber is connected to the oil reservoir via a first return oil branch; the rodless chamber is connected to the oil reservoir via a second return oil branch.

[0023] Preferably, it also includes a main return oil line, wherein the first and second return oil branches are connected to one end of the main return oil line, and the other end of the main return oil line is connected to an oil storage tank;

[0024] The first pressure valve is located on the main return oil line.

[0025] By adopting the above technical solution, the present invention has the following beneficial effects:

[0026] 1. In this invention, anchor bolts and nuts are used. The lower end of the anchor bolt is hooked onto the ground cage, and then the nut is screwed onto the upper end of the anchor bolt. This allows for quick connection and fixation of the embedded plate to the ground cage. The anchor bolts are symmetrically distributed on both sides of the embedded plate, resulting in uniform force distribution and stable fixation. Screwing three nuts onto the anchor bolts provides a good fixing effect and prevents them from falling off.

[0027] 2. In this invention, the ground cage is made of HRB335φ16 steel bars, and the intersections are tied with No. 20 iron wire to ensure the structural stability of the ground cage and prevent it from breaking. The upper support platform is made of channel steel welded together. The upper support platform consists of a U-shaped frame and multiple crossbeams fixed to the inner wall of the U-shaped frame. The material of the upper support platform is Q235 steel. Attached Figure Description

[0028] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0029] Figure 1 A front-view stereoscopic structural diagram of the six-degree-of-freedom flight simulation platform provided in Example 1;

[0030] Figure 2 for Figure 1 Enlarged structural diagram at point A;

[0031] Figure 3 A bottom-view three-dimensional structural diagram of the six-degree-of-freedom flight simulation platform provided in Example 1;

[0032] Figure 4 for Figure 1 Enlarged structural diagram at point B;

[0033] Figure 5 A left-side structural diagram of the six-degree-of-freedom flight simulation platform provided in Example 1;

[0034] Figure 6 A front view structural diagram of the six-degree-of-freedom flight simulation platform provided in Example 1;

[0035] Figure 7 A front view of the six-degree-of-freedom flight simulation platform provided in Example 2;

[0036] Figure 8 This is a schematic diagram of the shock-absorbing seat plate structure in Example 2;

[0037] Figure 9 This is a schematic diagram illustrating the working principle of the oil-gas damping system in Example 2;

[0038] Figure 10 This is a schematic diagram illustrating the working principle of the oil-gas damping system in Example 3;

[0039] Figure 11 The diagram shows the working principle of the direct-acting two-position two-way valve in Examples 3 and 4.

[0040] Figure 12 This is a schematic diagram of the working principle of the oil-gas shock absorption system in Example 4.

[0041] Attached reference numerals: 1. Foundation; 2. Ground cage; 3. Embedded plate; 4. Lower hinge seat; 5. Lower hinge component; 6. Electric cylinder; 7. Upper support platform; 8. Connecting plate; 9. Upper hinge seat; 10. Upper hinge component; 11. Anchor bolt; 12. Nut; 13. Foundation pit; 14. Crossbeam;

[0042] 200-Shock absorber seat plate; 210-Lower seat plate; 220-Upper seat plate; 300-Hydraulic cylinder; 310-Cylinder body; 311-Rod chamber; 312-Rodless chamber; 320-Piston rod; 321-Limit baffle; 400-Inertia block; BT-Pump body; DF-One-way valve; F1-First control valve; F2-Second control valve; F3-Third control valve; F4-Fourth control valve; F10-Valve body; F11-Reset spring; F12-Control rod; F13-End plate; F14-One-way damping structure; GZ1-First oil supply branch; GZ2-Second oil supply branch; GZ3-Third oil supply branch; GZ4-Fourth oil supply branch; HZ1-First return oil branch; HZ2-Second return oil branch; X1-First pilot valve; X2-Second pilot valve; YX-Oil reservoir; Y1 - First pressure valve; Y2 - Second pressure valve; ZH - Main return oil line; ZG - Main supply oil line. Detailed Implementation

[0043] The present invention will be further explained below with reference to specific embodiments.

[0044] Example 1

[0045] like Figure 1-6 As shown, this embodiment provides a six-degree-of-freedom flight simulation platform, including a foundation 1, a pit 13 set in the foundation 1, and a cage 2 set at the bottom of the pit 13. Three embedded plates 3 are fixedly installed on the cage 2. Each embedded plate 3 is provided with a drive component. The upper end of the drive component is connected to an upper support platform 7. By activating the drive component, the upper support platform 7 can be driven to move in six degrees of freedom, simulating the spatial motion state of the vehicle on the upper support platform 7.

[0046] Multiple anchor bolts 11 are fixed on the embedded plate 3. Each anchor bolt 11 is threaded with multiple nuts 12. The lower end of the anchor bolt 11 is hooked onto the ground cage 2, and then the nuts 12 are screwed onto the upper end of the anchor bolt 11. This can quickly connect and fix the embedded plate 3 to the ground cage 2. The anchor bolts 11 are symmetrically distributed on both sides of the embedded plate 3, so the force is even and the fixation is stable. Screwing three nuts 12 on the anchor bolt 11 provides a good fixing effect and prevents it from falling off.

[0047] The process of installing the ground cage 2 and the embedded plate 3 is as follows: Clean up the garbage and debris at the bottom of the foundation pit 13, compact the bottom area of ​​the foundation pit 13, then lay a crushed stone cushion layer at the bottom of the ground cage 2 and compact the crushed stone cushion layer. First, temporarily fix the anchor bolts 11 on the embedded plate 3 to the steel ground cage 2 to ensure the horizontal positioning dimensions between the three embedded plates 3. Use a level to adjust and ensure that the embedded plates 3 are level. After the embedded plates 3 are positioned, fix the embedded plates 3 to the ground cage 2 firmly by binding and welding. The anchor bolts 11 that extend beyond the upper surface of the embedded plate 3 need to be wrapped with plastic paper or other materials to prevent cement from entering and damaging the threads. Finally, install the formwork. After fixing the formwork, pour C25 concrete. The concrete must be poured thoroughly and no hollow areas are allowed.

[0048] The drive assembly includes two lower hinge seats 4 fixed on the embedded plate 3. The upper ends of the lower hinge seats 4 are rotatably connected to lower hinge components 5. The upper ends of the lower hinge components 5 are fixedly connected to electric cylinders 6. The upper ends of the electric cylinders 6 are fixedly connected to upper hinge components 10. The upper ends of the two upper hinge components 10 are rotatably connected to upper hinge seats 9. The tops of the two upper hinge seats 9 are fixedly connected to the same connecting plate 8. The connecting plate 8 is fixedly installed at the bottom of the upper support platform 7.

[0049] The corresponding electric cylinder 6 is activated, causing the output end of the electric cylinder 6 to extend, thereby pushing the upper support platform 7, so that the upper support platform 7 can tilt or rise and fall. Different electric cylinders 6 are activated in coordination to achieve different movement postures.

[0050] Three sets of upper hinge seats 9 are evenly distributed at 120 degrees along a circumference with a diameter of 2600mm, and three sets of lower hinge seats 4 are evenly distributed at 120 degrees along a circumference with a diameter of 3200mm. This ensures that the electric cylinder 6 can be driven smoothly, so that the upper support platform 7 can move and the aircraft on the upper support platform 7 can simulate the motion state.

[0051] The number of anchor bolts 11 is 8, and the model is M30X500. Each anchor bolt 11 has 3 nuts 12 to ensure the connection strength between the embedded plate 3 and the foundation 1.

[0052] In order to fully consider the strength and rigidity of the upper platform structure in the design, the upper support platform 7 is made of channel steel welded together. Multiple crossbeams 14 are fixedly connected to the inner wall of the upper support platform 7 at equal intervals. The material of the upper support platform 7 is Q235.

[0053] The ground cage 2 is made of HRB335φ16 steel bars, which have high tensile strength.

[0054] The foundation pit 13 has a depth of 1200mm, which meets the pouring depth requirement. When pouring the ground cage 2, the ground cage 2 is stably connected to the foundation pit 13.

[0055] The ground cage 2 is Y-shaped to ensure stable support and prevent it from tipping over.

[0056] The upper support platform 7 has an external dimension of 6000mm. 4130mm is acceptable, but other sizes can also be used to match the vehicle.

[0057] Example 2

[0058] See Figure 7 As shown, the six-degree-of-freedom flight simulation platform disclosed in this embodiment also includes a shock-absorbing seat plate 200 for vibration reduction. Specifically, the shock-absorbing seat plate 200 is set on the upper support platform 7, and the flight vehicle under test is set on the support platform 7 through the shock-absorbing seat plate 200, so that the load conditions of instruments, equipment and even personnel inside the vehicle under different motion modes can be detected under the shock-absorbing structure.

[0059] See Figure 8 As shown, the shock-absorbing base plate 200 in this embodiment includes an upper base plate 220 and a lower base plate 210; the upper base plate 220 is slidably disposed on the lower base plate 210 along the X-axis direction (i.e., the front-to-back direction). The aircraft under test is fixedly disposed on the upper base plate 220, while the lower base plate 210 is fixedly connected to the support platform 7 by fasteners.

[0060] See Figure 9 As shown, an oil-gas damping system is provided between the upper seat plate 220 and the lower seat plate 210. The oil-gas damping system includes: oil cylinder 300, oil tank YX, first pressure valve Y1, and oil return pipeline.

[0061] The hydraulic cylinder 300 includes a cylinder body 310, a piston, and a piston rod 320; the cylinder body 310 is fixedly connected to the lower seat plate 210, and the piston rod 320 is fixedly connected to the upper seat plate 220.

[0062] The rod chamber 311 and rodless chamber 312 of the hydraulic cylinder 300 are respectively connected to the oil storage tank YX through the oil return pipeline, and a first pressure valve Y1 is provided on the oil return pipeline.

[0063] Preferably, multiple hydraulic cylinders 300 are arranged in a matrix between the upper seat plate 220 and the lower seat plate 210 to ensure uniform force distribution.

[0064] Preferably, the return oil pipeline includes a first return oil branch HZ1 and a second return oil branch HZ2;

[0065] The rod-type chamber 311 is connected to the oil storage tank YX via the first return oil branch HZ1; the rodless chamber 312 is connected to the oil storage tank YX via the second return oil branch HZ2.

[0066] Preferably, it also includes a main return oil line ZH, with the first return oil branch line HZ1 and the second return oil branch line HZ2 connected to one end of the main return oil line ZH, and the other end of the main return oil line ZH connected to the oil storage tank YX.

[0067] The first pressure valve Y1 is installed on the main return oil line ZH.

[0068] Optionally, a first pressure valve Y1 is provided on the first return oil branch HZ1 and the second return oil branch HZ2 respectively, for adjusting and controlling the oil pressure on the oil lines respectively.

[0069] More preferably, one-way valves DF are respectively provided on the first oil return branch HZ1 and the second oil return branch HZ2 to control the oil in the cylinder 300 to flow unidirectionally to the oil storage tank YX.

[0070] Preferably, it also includes a first oil supply branch GZ1, a second oil supply branch GZ2, and a main oil supply line ZG. One end of the first oil supply branch GZ1 is connected to the rod-mounted cavity 311, and the other end is connected to the main oil supply line ZG. One end of the second oil supply branch GZ2 is connected to the rodless cavity 312, and the other end is connected to the main oil supply line ZG.

[0071] A pump body BT is installed on the main oil supply line ZG; a first pilot valve X1 and a second pilot valve X2 are respectively installed on the first oil supply branch line GZ1 and the second oil supply branch line GZ2; the control ports on the first pilot valve X1 and the second pilot valve X2 are respectively connected to the rod chamber 311 and the rodless chamber 312 through the first control oil circuit and the second control oil circuit.

[0072] Preferably, the first oil supply branch GZ1 and the second oil supply branch GZ2 are respectively provided with a one-way valve DF, which is used to control the oil to flow unidirectionally to the rod chamber 311 and the rodless chamber 312.

[0073] Preferably, a second pressure valve Y2 is also provided on the main oil supply line ZG.

[0074] Under impact, when the upper seat plate 220 moves relative to the lower seat plate 210, the upper seat plate 220 drives the piston to move within the cylinder 310 via the piston rod 320. This causes the oil in the rod chamber 311 or rodless chamber 312 to be squeezed. When the pressure exceeds the set pressure of the first pressure valve Y1, the oil in the rod chamber 311 or rodless chamber 312 flows back to the oil storage tank YX through the return oil line. Meanwhile, the oil pressure in the rodless chamber 312 or rod chamber 311 on the opposite side decreases, or even becomes negative pressure. At this time, the pressure in the second control oil circuit or the first control oil circuit decreases, thereby causing the second pilot valve X2 or the first pilot valve X1 to reset under the action of its internal reset spring and the oil circuit to open. The oil in the oil storage tank YX flows into the rodless chamber 312 or rod chamber 311.

[0075] Equivalent to existing spring-based damping methods, the oil-gas damping system disclosed in this application maintains a constant damping force and does not exhibit any rebounding impact during damping.

[0076] Example 3

[0077] See Figure 10 As shown, this embodiment has a basically the same structure as embodiment 2, except that:

[0078] The shock absorption structure disclosed in this embodiment also includes a first control valve F1, a second control valve F2, and an inertial block 400;

[0079] The first control valve F1 and the second control valve F2 are respectively installed on the first return oil branch HZ1 and the second return oil branch HZ2.

[0080] The first control valve F1 and the second control valve F2 are direct-acting two-position two-way valves; refer to Figure 9 As shown, the direct-acting two-position two-way valve includes a valve body F10, a valve core (not shown), a return spring F11, and a control rod F12. The valve core is slidably disposed within the valve body F10. The return spring F11 and the control rod F12 are respectively disposed at both ends of the valve core and are used to control the valve core to switch between two working positions. The two-position two-way valve remains in a normally closed state under the action of the return spring F11. The outer end of the control rod F12 extends out from the valve body F10. By using external force to push the outer end of the control rod F12 to overcome the spring force of the return spring F11, the valve core is pushed inward, and the ports on both sides of the two-position two-way valve are connected (i.e., the two-position two-way valve is in the connected state).

[0081] The inertial block 400 is slidably mounted on the lower seat plate 210 along the X direction; the first control rod F12 on the first control valve F1 and the second control rod F12 on the second control valve F2 are both mounted along the X direction, and the outer ends of the first control rod F12 and the outer ends of the second control rod F12 are respectively mounted at both ends of the moving path of the inertial block 400.

[0082] When suddenly decelerating or accelerating, the inertial block 400 moves relative to the lower seat plate 210 under the action of inertia. When it touches the first control lever F12 or the second control lever F12, the first control valve F1 and the second control valve F2 are opened through the first control lever F12 or the second control lever F12, and the first oil return branch HZ1 or the second oil return branch HZ2 is connected, so that the oil in the rod chamber 311 or the rodless chamber 312 flows back to the oil storage tank YX.

[0083] In this application, the first control valve F1 and the second control valve F2 are in a normally closed (normally open) state, and the oil in the rod chamber 311 and the rodless chamber 312 cannot flow out. This locks the upper seat plate 220 and the lower seat plate 210, preventing relative movement between them and thus preventing people and objects on the shock-absorbing seat plate 200 from shaking, especially preventing patients from getting dizzy.

[0084] Only when there are large speed changes and impacts can the first control valve F1 or the second control valve F2 be opened by the inertial block 400, thereby forming an active damping system.

[0085] More preferably, the direct-acting two-position two-way valve has a one-way damping structure F14 between the control lever F12 and the valve body F10, which is used to control the control lever F12 to slowly reset under the action of the reset spring F11, thereby providing sufficient damping time for the entire oil and gas damping system, that is, ensuring that the oil flows back to the oil storage tank YX within a sufficient time.

[0086] When the inertial block 400 applies a force to the control lever F12, the unidirectional damping structure F14 does no work, thus ensuring that the first control valve F1 or the second control valve F2 responds quickly and is activated. The unidirectional damping structure F14 is a conventional technology and will not be described in detail here.

[0087] More preferably, the control rod F12 of the direct-acting two-position two-way valve is provided with an end plate F13 on its outer end to facilitate the collision of the inertial block 400.

[0088] Furthermore, a spring is provided between the inertia block 400 and the lower seat plate 210 to facilitate the inertia block 400's reset and stay in the middle position between the two end plates F13. The inertia block 400 is preferably a metal block in the form of a cylinder or cuboid.

[0089] Preferably, in this embodiment, the inertial block 400 is provided with a wrench (not shown) extending outward from the lower seat plate 210. The wrench forces the inertial block 400 to actively contact the end plate F13 and the control lever F12, thus manually resetting the oil-gas damping system and the upper seat plate 220. Under normal circumstances, the probability of inertial impact caused by deceleration and acceleration is roughly equal, and the piston in the cylinder 300 moves left and right within its stroke to achieve automatic reset or balance. However, when the number or frequency of inertial impacts caused by acceleration and deceleration differs, the piston may remain at an extreme position, for example, the rod chamber 311 may be compressed to its minimum. In this case, the rod chamber 311 cannot be used for buffering. To solve this problem, the inertial block 400 is moved by a wrench and touches the control rod F12 of the second control valve F2. The oil in the rodless chamber 312 flows back to the oil storage tank YX. At the same time, due to the negative pressure in the rod chamber 311, the first pilot valve X1 is opened and oil is input into the rod chamber 311, thereby realizing the reset of the oil cylinder 300.

[0090] Example 4

[0091] See Figure 12 As shown, this embodiment is basically the same in structure as embodiment 3, except that: this embodiment also includes a third oil supply branch GZ3 and a fourth oil supply branch GZ4. One end of the third oil supply branch GZ3 is connected to the main oil supply branch ZG, and the other end is connected to the rod cavity 311; one end of the fourth oil supply branch GZ4 is connected to the main oil supply branch ZG, and the other end is connected to the rodless cavity 312.

[0092] The third oil supply branch GZ3 and the fourth oil supply branch GZ4 are respectively equipped with a third control valve F3 and a fourth control valve F4. The third control valve F3 and the fourth control valve F4 are direct-acting two-position two-way valves as described in Example 3.

[0093] Specifically, the input end of the third control valve F3 is connected to the main oil supply line ZG, and the output end of the third control valve F3 is connected to the rod chamber 311; the input end of the fourth control valve F4 is connected to the main oil supply line ZG, and the output end of the fourth control valve F4 is connected to the rod chamber 311.

[0094] A limit baffle 321 is provided on the piston rod 320. The third control rod F12 on the third control valve F3 and the fourth control rod F12 on the fourth control valve F4 are arranged along the X direction (the extension and retraction direction of the piston rod 320), and the ends of the third control rod F12 and the fourth control rod F12 are respectively located at both ends of the moving path of the limit baffle 321.

[0095] When the piston rod 320 moves to the first limit position (left limit position), the limit baffle 321 touches the third control rod F12, the third control valve F3 opens, and oil is input into the rod chamber 311. The piston moves towards the rodless chamber 312 under hydraulic action. When the piston rod 320 moves to the second limit position (right limit position), the limit baffle 321 touches the fourth control rod F12, the fourth control valve F4 opens, and oil is input into the rodless chamber 312. The piston moves towards the rod chamber 311 under hydraulic action.

[0096] The one-way damping structure F14 on the third control valve F3 and the fourth control valve F4 controls the reset time of the control lever F12, that is, the time for the oil to be input into the rod chamber 311 and the rodless chamber 312. After the control lever F12 is fully reset under the action of the reset spring F11, the third control valve F3 or the fourth control valve F4 is closed, the oil input stops, and the piston is roughly stationary in the middle of the cylinder 310.

[0097] Compared to Example 3, this example can automatically reset the hydraulic cylinder 300 and the upper seat plate 220, preparing for the next buffering operation. It has a high degree of automation and good active damping effect.

[0098] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A six-degree-of-freedom flight simulation platform, characterized in that, It includes a foundation, a foundation pit set in the foundation, and a ground cage set at the bottom of the foundation pit. Three pre-embedded plates are fixedly installed on the ground cage. Each pre-embedded plate is provided with a driving component. The upper end of the driving components is connected to an upper support platform. Multiple anchor bolts are fixed on the embedded plate, and multiple nuts are threaded onto each anchor bolt; The upper support platform is used to support and connect the tested flight vehicle; It also includes shock-absorbing base plates for vibration reduction, through which the tested aircraft is mounted on the support platform; The shock-absorbing seat plate includes an upper seat plate and a lower seat plate; the upper seat plate is slidably mounted on the lower seat plate along the X-axis direction; the aircraft being tested is fixedly mounted on the upper seat plate, while the lower seat plate is fixedly connected to the support platform by fasteners; An oil-gas damping system is provided between the upper seat plate and the lower seat plate. The oil-gas damping system includes: an oil cylinder, an oil reservoir, a first pressure valve, and an oil return pipeline. The hydraulic cylinder includes a cylinder body, a piston, and a piston rod; the cylinder body is fixedly connected to the lower seat plate, and the piston rod is fixedly connected to the upper seat plate; The rod-side chamber and rodless chamber of the hydraulic cylinder are respectively connected to the oil storage tank through a return oil pipeline, and a first pressure valve is provided on the return oil pipeline; The return oil pipeline includes a first return oil branch and a second return oil branch; The rod chamber is connected to the oil reservoir via a first return oil branch; the rodless chamber is connected to the oil reservoir via a second return oil branch. It also includes a main return oil line, with the first and second return oil branches connected to one end of the main return oil line and the other end of the main return oil line connected to an oil storage tank. The first pressure valve is installed on the main return oil line; It also includes a first oil supply branch, a second oil supply branch, and a main oil supply line. One end of the first oil supply branch is connected to the rod-mounted cavity, and the other end is connected to the main oil supply line. One end of the second oil supply branch is connected to the rodless cavity, and the other end is connected to the main oil supply line. It also includes a first control valve, a second control valve, and an inertial block; The first control valve and the second control valve are respectively installed on the first return oil branch and the second return oil branch. The inertial block can be freely slidably mounted on the lower base plate along the X direction; It also includes a third oil supply branch and a fourth oil supply branch. One end of the third oil supply branch is connected to the main oil supply line, and the other end is connected to the rod-mounted cavity. One end of the fourth oil supply branch is connected to the main oil supply line, and the other end is connected to the rodless cavity.

2. The six-degree-of-freedom flight simulation platform according to claim 1, characterized in that, The drive assembly includes two lower hinge seats fixed to the embedded plate. The upper ends of the lower hinge seats are rotatably connected to lower hinge components. The upper ends of the lower hinge components are fixedly connected to electric cylinders. The upper ends of the electric cylinders are fixedly connected to upper hinge components. The upper ends of the two upper hinge components are rotatably connected to upper hinge seats. The tops of the two upper hinge seats are fixedly connected to the same connecting plate. The connecting plate is fixedly installed at the bottom of the upper support platform.

3. The six-degree-of-freedom flight simulation platform according to claim 2, characterized in that, The three sets of upper hinge seats are evenly distributed at 120-degree intervals along a circumference with a diameter of 2600mm, and the three sets of lower hinge seats are evenly distributed at 120-degree intervals along a circumference with a diameter of 3200mm.

4. The six-degree-of-freedom flight simulation platform according to claim 1, characterized in that, The number of anchor bolts is 8, and the number of nuts on each anchor bolt is 3.

5. The six-degree-of-freedom flight simulation platform according to claim 1, characterized in that, The upper support platform is welded from channel steel and consists of a U-shaped frame and multiple crossbeams fixed to the inner wall of the U-shaped frame.

6. The six-degree-of-freedom flight simulation platform according to claim 1, characterized in that, The cage is Y-shaped.

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