Rocket anti-toppling device for whole-rocket modal test

Abstract

The invention belongs to the technical field of automatic control, and particularly relates to a whole-rocket modal test rocket anti-toppling device which comprises a bearing ring fixed at the bottom of a rocket; the multiple bottom lifting devices are provided with pressure sensors, and the bottom lifting devices are in lap joint with the bottom face of the bearing ring and used for supporting a rocket; the tops of the steel wire ropes are connected with the tower crane mechanism, and the bottoms of the steel wire ropes are circumferentially connected to the bearing ring; the tower columns are arranged on the ground around the rocket; the two ends of each state wrapping belt are connected to the same position of the tower column, and the middle of each state wrapping belt wraps the outer cylindrical surface of the rocket; the state rings are arranged outside the rocket at equal intervals in a sleeving mode and fixed to the tower column through state ring supporting beams; wherein the steel wire rope is provided with a low-rigidity spring system, the low-rigidity spring system is provided with a displacement sensor for detecting the spring deformation amount of the low-rigidity spring system, and the device and the method are used for judging rocket toppling and preventing rocket toppling.

Description

Technical Field

[0001] The present application belongs to the field of automatic control technology, and in particular relates to a rocket anti-dumping device for a full-arrow modal test. Background Art

[0002] In the full-arrow modal test of the rocket, the rocket is in a "free-free" vertical suspension state, simulating the flight state of the rocket launch in different seconds. Because the rocket is a slender structure with a high center of mass and a large mass, and the rocket is in a vertical suspension state, the rocket is prone to overturning, causing damage to the rocket, affecting the test progress of the full-arrow resonant modal test and subsequent tests. The commonly used method to prevent the rocket from overturning is to directly use a sling to provide lateral tension to the rocket. This method cannot detect the initial state of the rocket overturning in time, and it is difficult to prevent the continued development of the initial overturning state of the rocket. Therefore, in order to further ensure the safety and controllability of the rocket test state, it is necessary to develop a set of anti-dumping devices dedicated to the full-arrow modal test. Summary of the invention

[0003] In order to solve the above problems, the present application provides a rocket anti-dumping device for full-arrow modal test, comprising:

[0004] The carrying ring is fixed to the bottom of the rocket;

[0005] a plurality of bottom lifting devices, equipped with pressure sensors, the bottom lifting devices overlap the bottom surface of the carrying ring and are used to support the rocket;

[0006] A plurality of steel wire ropes, connected to the tower crane mechanism at the top and circumferentially connected to the bearing ring at the bottom, are used to lift the rocket;

[0007] A plurality of towers are set on the ground around the rocket;

[0008] A plurality of state wrapping belts are arranged along the circumference of the rocket, with both ends of each state wrapping belt connected to the same position of the tower column, and the middle part enveloping the outer surface of the rocket;

[0009] The state rings are equidistantly mounted outside the rocket and fixed to the tower column through the state ring support beams; wherein a low-rigidity spring system is arranged on the steel wire rope, and a displacement sensor for detecting the spring deformation of the low-rigidity spring system is arranged on the low-rigidity spring system.

[0010] Preferably, an annular sponge is provided on the inner wall surface of the status ring to reduce damage to the rocket body caused by the rocket tilting and colliding with the status ring.

[0011] Preferably, the bearing ring has a bearing ring ear piece with a double-ear structure, and the bearing ring ear piece is installed with a load-bearing shaft, and the load-bearing shaft is connected to the rope ring at the bottom end of the wire rope.

[0012] Preferably, when the lifting device lifts the rocket by means of a steel wire rope, when the monitoring value of the displacement sensor fluctuates within a preset range, it is determined that the rocket is not tilted or has no tendency to tilt.

[0013] Preferably, when the lifting device lifts the rocket by means of a steel wire rope, when the test values ​​of the pressure sensor are the same within an error range, it is determined that the rocket is not tilted or has no tendency to tilt.

[0014] Preferably, a tightening device is provided on the state bag, and the tilt direction of the rocket is determined according to the test value of the pressure sensor and / or the monitoring value of the displacement sensor, and the tightening device tightens the state bag in the opposite direction according to the tilt direction of the rocket.

[0015] Preferably, the status bands have at least three strips.

[0016] Preferably, the state bag is set at a position of one-half the height of the rocket.

[0017] Advantages of this application include:

[0018] (1) The present invention can effectively monitor the test state of the rocket in each test phase, ensuring that the rocket is in a good vertical test state throughout the test phase;

[0019] (2) The present invention can effectively prevent the rocket from tilting;

[0020] (3) When the rocket tilts, the present invention can promptly prevent the further development of the rocket tilt state, thereby ensuring the safety of the test piece of the test rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the rocket suspension;

[0022] Figure 2 It is a schematic diagram of the load-bearing system;

[0023] Figure 3 is a schematic diagram of the state loop;

[0024] Figure 4 It is a schematic diagram of the state packet distribution;

[0025] Figure 5 is a schematic diagram of a low-rigidity spring system;

[0026] Figure 6 This is a schematic diagram of the displacement sensor installation. DETAILED DESCRIPTION

[0027] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0028] The following is a further detailed description of a rocket anti-dumping device and method for full-arrow modal test of the present invention in conjunction with the accompanying drawings and specific embodiments:

[0029] In the above-mentioned rocket anti-dumping device for full-arrow modal test, the device comprises a state monitoring system and a state maintaining system; Figure 1-Figure 6 As shown;

[0030] The state monitoring system is mainly composed of a pressure sensor 4, a displacement sensor 12, and a bottom lifting device 3. The state monitoring system mainly monitors the current suspension state of the rocket and judges the suspension level of the rocket.

[0031] The state-maintaining system is composed of a load-bearing ring 1, a load-bearing ring ear piece 5, a lower load-bearing wire rope 6, a low-rigidity spring system 13, a state bag 14, a state ring 8, an annular sponge 7, a state ring support beam 9, a tower column 10, etc. The state-maintaining system is mainly used to maintain the suspended state of the rocket and provide corrective protection measures for the weak tilt of the rocket to prevent the rocket from overturning.

[0032] The bottom lifting device 3 is fixed to the foundation by anchor bolts, and the pressure sensor 4 is installed on the top of the bottom lifting device 3. There are four groups of the bottom lifting device 3 and the pressure sensors 4, which are evenly distributed on the foundation, bear the pressure applied by the bearing ring 1, and monitor the pressure applied to the bottom lifting device by the bearing ring 1 at four monitoring points.

[0033] The rocket is mounted on the bearing ring 1 through four evenly distributed arrow feet 2, and the arrow feet 2 are fixed to the bearing ring 1 by bolts. The four bearing ring ear pieces 5 are evenly distributed and mounted on the bearing ring 1 by bolts, and the bearing ring ear pieces 5 are divided into a left bearing ring ear piece and a right bearing ring ear piece. The shaft holes on the left bearing ring ear piece and the right bearing ring ear piece are equipped with a load-bearing shaft, and the load-bearing shaft passes through the rope ring at the lower end of the lower bearing wire rope 6 to bear the tension of the lower bearing wire rope 6. The rope ring at the upper end of the lower bearing wire rope 6 is installed on the lower lifting ring 16 of the low-rigidity spring system 13, and the rope ring at the lower end of the upper bearing wire rope 11 is installed on the upper lifting ring 15 of the low-rigidity spring system 13. The upper bearing wire rope 11 is installed on the tower top lifting mechanism through the rope ring at the upper end. The displacement sensor 12 is installed inside the low-rigidity spring system 13 by bolts. The displacement sensor 12 will monitor the spring deformation of the low-rigidity spring system 13, so as to obtain the change value of the tension applied to the low-rigidity spring system 13, which is used to judge the suspension state of the rocket.

[0034] The state wrapping belt 14 surrounds the rocket, and the two ends are fixed on the vibration tower column. There are three state wrapping belts 14, and their distribution is shown in the figure. The state wrapping belt is installed at half the height of the rocket. The state wrapping belt should not be too tight, so as to affect the "free-free" state of the rocket.

[0035] An annular sponge 7 is pasted on the inner side of the state ring 8, and the inner side of the annular sponge is about 10 cm away from the arrow body. The annular sponge can avoid hard contact between the arrow body and the state ring, thereby reducing damage to the arrow body caused by possible collision. The state ring 8 is spliced ​​by two half rings, and the splicing is connected by bolts. The outer side of the state ring 8 is connected to the state ring support beam 9 by bolts, and the other end of the state ring support beam 9 is connected to the tower column by bolts. There are 3 turntable ring support beams in total, and they are evenly distributed on the outer side of the state ring 8.

[0036] In an optional implementation, a tightening device is provided on the state bag (14), and the tilting direction of the rocket is determined according to the test value of the pressure sensor (4) and / or the monitoring value of the displacement sensor. The tightening device tightens the state bag (14) in the opposite direction according to the tilting direction of the rocket to correct the posture of the rocket and prevent it from tipping over.

[0037] In the above-mentioned device and method for preventing a rocket from tipping over during a full-rocket modal test, the test state of the rocket is ensured by the following points:

[0038] (i) When the rocket is in the suspended test state, the displacement sensor 12 on the low-rigidity spring system 13 will monitor the tension change state of the load-bearing wire rope. Under normal conditions, the displacement sensor monitoring value should fluctuate within a small range;

[0039] (ii) When the carrying ring 1 falls on the bottom lifting device 3, the test values ​​of the pressure sensors 4 on the four bottom lifting devices 3 should be the same within the error and maintain a stable value within the error. When the rocket is suspended by the load-bearing steel wire 6, the change of the test value of the pressure sensor 4 is monitored. The test value of the pressure sensor 4 should change slowly and synchronously until the rocket is completely lifted and the test value of the pressure sensor 4 is zero;

[0040] (iii) The rocket is in the embrace of the state bag. When the rocket tilts slightly, the state bag 14 will hold the rocket to prevent the rocket from further tilting.

[0041] (iv) When the rocket tilts further, the state ring 8 at the outer periphery of the rocket will contact the rocket body, preventing the rocket from tilting further. The rocket should be at the center of the state ring 8 in any state.

[0042] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A rocket anti-dumping device for full-rocket modal test, characterized in that: include: A carrying ring (1), fixed to the bottom of the rocket; A plurality of bottom lifting devices (3) are provided with pressure sensors (4), the bottom lifting devices (3) being overlapped with the bottom surface of the carrying ring (1) for supporting the rocket; A plurality of steel wire ropes, the top of which is connected to the tower crane mechanism and the bottom of which is circumferentially connected to the bearing ring (1), for hoisting the rocket; A plurality of tower columns (10) are arranged on the ground around the rocket; A plurality of state wrapping belts (14) are arranged along the circumference of the rocket, with both ends of each state wrapping belt (14) connected to the same position of the tower column (10), and the middle portion of each state wrapping belt (14) enclosing the outer surface of the rocket; The state ring (8) is sleeved outside the rocket at equal intervals and fixed on the tower column (10) through the state ring support beam (9); wherein a low-rigidity spring system (13) is arranged on the steel wire rope, and a displacement sensor (12) for detecting the spring deformation of the low-rigidity spring system (13) is arranged on the low-rigidity spring system (13).

2. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: An annular sponge (7) is arranged on the inner wall surface of the state ring (8) to reduce the damage to the rocket body caused by the rocket tilting and colliding with the state ring (8).

3. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: The bearing ring (1) is provided with a bearing ring ear piece (5) with a double ear structure, and the bearing ring ear piece (5) is installed with a load-bearing shaft, and the load-bearing shaft is connected to the rope ring at the bottom end of the steel wire rope.

4. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: When the lifting device lifts the rocket through the wire rope, when the monitoring value of the displacement sensor fluctuates within the preset range, it is determined that the rocket is not tilted or has no tendency to tilt.

5. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: When the lifting device lifts the rocket by means of the steel wire rope, if the test values ​​of the pressure sensor (4) are the same within the error range, it is determined that the rocket is not tilted or has no tendency to tilt.

6. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: A tightening device is provided on the state bag (14), and the tilting direction of the rocket is determined according to the test value of the pressure sensor (4) and / or the monitoring value of the displacement sensor. The tightening device tightens the state bag (14) in the opposite direction according to the tilting direction of the rocket.

7. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: The state wrapping belt (14) has at least three strips.

8. The rocket anti-dumping device for full-arrow modal test according to claim 1, characterized in that: The state bag belt (14) is arranged at a position of one-half of the rocket height.

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